Bibliographies |  |
ADA511680
Advanced Systems and Concepts Joint Capability Technology Demonstrations. ISR Task Force II
Descriptive Note: Briefing charts
Personal Author(s): Loxterkamp, Ed
Report Date: 09 Jun 2009
Media Count: 16 Page(s)
Descriptors: (U) *AIRSHIPS, *SURVEILLANCE DRONES, MILITARY REQUIREMENTS, TASK FORCES
Identifiers: (U) ISR (INTELLIGENCE SURVEILLANCE RECONNAISSANCE) TASK FORCE, LEMV(LONG ENDURANCE MULTI-INT VEHICLE), CONDOR(HIGH ALTITUDE VEHICLES), JROCM 133-08, PERSISTENT SURVEILLANCE, BRIEFING CHARTS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) SECDEF created the ISR Task Force in April 2008 to assess and propose options for maximizing and optimizing currently deployed ISR capability. This briefing examines the organization structure of the ISR TF and its work. Among the projects examined is the Long Endurance Multi-INT Vehicle (LEMV)
ADA505728
Pressurized Structure Technology for UAVS
Descriptive Note: Conference paper
Personal Author(s): Edge, H, Nixon; M, Janas; A, Ross; W, Collins, J
Report Date: Dec 2008
Media Count: 10 Page(s)
Descriptors: (U) *URBAN AREAS, *DEFICIENCIES, *SURVEILLANCE DRONES, *AIRSHIPS, AERODYNAMIC CHARACTERISTICS, HELIUM, TRADE OFF ANALYSIS, DESIGN CRITERIA, STEALTH TECHNOLOGY, AIRCRAFT NOISE, ENERGY MANAGEMENT, HIGH PRESSURE, CONTROL SYSTEMS, SYMPOSIA, REQUIREMENTS, MANEUVERABILITY
Identifiers: (U) UAV(UNMANNED AERIAL VEHICLES), TIME ALOFT, VERTICAL TAKEOFF, PSB(PRESSURIZED STRUCTURE-BASED) TECHNOLOGY
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) There is a critical need to improve the performance and utility of unmanned aerial vehicles (UAVs). Several areas of UAV performance need to be improved for the next generation of UAVS to be used successfully in expanded future combat roles. For example current time aloft is only on the order of an hour or two for electric-powered UAVs. The current generation of UAVs lacks vertical takeoff and landing (VTOL) capability and precision slow-speed maneuverability required for urban navigation and targeting. In addition, the UAVs are not capable of stealth, and are easily spotted and/or heard. These deficiencies are related mostly to the airframe and method of propulsion. Most fielded UAVs are currently based on fixed-wing or rotor-craft airframes and thus are constrained to their flight characteristics. UAV propulsion using ducted fans may also be fielded. In general, these vehicles require the motors, electrical or internal combustion to be running at high speed to keep the UAV aloft. This requires a substantial amount of energy and generates noise at excessive levels. One way to address the deficiencies of the UAVs just listed is to employ lighter-than-air or pressurized structure-based (PSB) technology. Basically, the UAV will be built such that a considerable percentage of its weight is supported by or constructed from inflatable structures containing air or helium. PSB technology will reduce the amount of energy required to keep the UAV aloft thus allowing the use of smaller, slower, and quieter motors. An airframe near neutral buoyancy will allow much slower flight speeds and increased maneuverability while expending little power. PSB airframes used in conjunction with technologies such as solar cells may be able to stay aloft for extended periods of time.
ADA483334
Hybrid Airship Multi-Role (HAMR) Anti-Submarine Warfare (ASW) Mission Capability
Descriptive Note: Technical rept.
Personal Author(s): Agpaoa, Roy; Cawley, Matthew, Cossey; Chad, Galvan; Jose, Giang; Alan, Hanchinamani, Joseph, Ikeda, Jeffrey; Kenney, John; Magnusson, Lance; Martinez, Christopher
Report Date: 20 Jun 2008
Media Count: 196 Page(s)
Descriptors: (U) *AIRSHIPS, *DETECTORS, LIFE CYCLE COSTS, ANTISUBMARINE WARFARE, SYSTEMS ENGINEERING, SIMULATION, MISSIONS
Identifiers: (U) HAMR(HYBRID AIRSHIP MULTI-ROLE), NSS(NAVAL SYSTEMS SIMULATION), HYBRID AIRSHIP, UNMANNED ASW SENSORS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The Hybrid Airship Multi-Role (HAMR) Anti-Submarine Warfare (ASW) Mission Module project applies established systems engineering principles and processes to the design of an ASW payload module that examines the capability of the HAMR to perform persistent ASW mission support. Critical system functions and objectives are identified and are assigned appropriate quantitative metrics. Additionally, three alternative architectures are generated and evaluated using the appropriate metrics based on results from modeling using Naval Systems Simulation (NSS). Manning is considered as a key stakeholder parameter and is included as an evaluation concern. The alternatives are also compared through the examination of life cycle costs. The recommendation to the stakeholders based on the research and results is an unmanned ASW sensor platform that uses other ASW assets for prosecution.
ADA521082
WSTIAC Quarterly, Volume 7, Number 3 - High Altitude Airship: Leading the Way for Stratospheric Defense Systems
Descriptive Note: Journal
Personal Author(s): Gibbs, Mark,;Waston, Charles; Peltier, Ashle;, Truax, Corey; Kruzel, John
Report Date: 01 Aug 2007
Media Count: 17 Page(s)
Descriptors: (U) *AIRSHIPS, *AIR DEFENSE, THEATER LEVEL OPERATIONS, OPERATIONAL READINESS, WEAPON SYSTEMS, HIGH ALTITUDE, TELECOMMUNICATIONS, COURSES(EDUCATION), MINE RESISTANT VEHICLES, COUNTERTERRORISM, SPACE MISSIONS, RECONNAISSANCE AIRCRAFT, STRATOSPHERE, AMPHIBIOUS ASSAULT SHIPS, AIR INTELLIGENCE, HOMELAND SECURITY, COMMAND CONTROL COMMUNICATIONS, AERIAL RECONNAISSANCE, SURVEILLANCE
Identifiers: (U) *STRATOSPHERIC DEFENSE SYSTEMS, WSTIAC(WEAPON SYSTEMS TECHNOLOGY INFORMATION ANALYSIS), WSTIAC COLLECTION, AERIAL SURVEILLANCE, ISR(INTELLIGENCE SURVEILLANCE RECONNAISSANCE), PERSISTENCE, GLOBAL WAR ON TERRORISM, RQ-4 AIRCRAFT, GLOBAL HAWK PROGRAM, MRAP(MINE RESISTANT AMBUSH PROTECTED)
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) This issue of the WSTIAC Quarterly features an article on the High Altitude Airship. Also included are recent news items related to weapon systems technology, the WSTIAC Calendar of Events and an introduction to the new WSTIAC Director. Details on several Training Courses sponsored by WSTIAC are also included in this issue. Contents of in the News: Beale Global Hawk Deploys For First Time, Essex Demonstrates Sustained Mission Readiness, and Gates Urges Faster Production of Mine Resistant Ambush Protected Vehicles.
ADA505388
New Again: Innovative Missions for 21st Century American Airships
Descriptive Note: Master's thesis
Personal Author(s): Bilko, Daniel T
Report Date: Jan 2007
Media Count: 29 Page(s)
Descriptors: (U) *AIRSHIPS, *AIRLIFT OPERATIONS, MILITARY OPERATIONS, THEATER LEVEL OPERATIONS, DETECTORS, DEFENSE SYSTEMS, PRODUCTION, PATROLLING, THESES, PROPULSION SYSTEMS, INTEGRATION, GAIN, LAUNCHING, OCEANS, RECONNAISSANCE, STRUCTURAL ENGINEERING, AVIONICS, GUIDED MISSILES
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Airships have great potential to support 21st Century American military operations in a wide variety of missions. The US should embrace airships and take the necessary steps to ensure its armed forces gain the greatest advantage from these unique platforms. Recent improvements in structural technology, propulsion systems, avionics, and sensors have greatly increased the performance of airships. Airships can be used to perform an expanding list of missions, including: intelligence, surveillance, and reconnaissance (ISR); airlift; communications replay; maritime patrol; theater ballistic missiles defense; and space launch. However, lack of both focus and funding is currently hampering the development, production, and integration of airships into America's 21st Century arsenal. Recent advances in airships performance, in conjunction with ongoing research and development, point to a bright future for airships in support of future US military operations. America must take the necessary steps now to gain the greatest benefits from the unique capabilities of tomorrow's airships.
ADA520366
Potential Military Use of Airships and Aerostats
Descriptive Note: Congressional rept.
Personal Author(s): Bolkcom, Christopher
Report Date: 01 Sep 2006
Media Count: 7 Page(s)
Descriptors: (U) *ANTISUBMARINE WARFARE, *AIRSHIPS, *MILITARY INTELLIGENCE, *AEROSPACE SYSTEMS, HISTORY, PROTECTION, STANDARDS, CONFLICT, HELIUM, MILITARY PLANNING, FIXED WING AIRCRAFT, SURVEILLANCE, ASIA, URBAN AREAS, TETHERING, HELICOPTERS, BATTLEFIELDS, AIR FORCE, HOMELAND SECURITY, EUROPE
Identifiers: (U) MILITARY SURVEILLANCE
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Airships and aerostats have been used historically for military surveillance and antisubmarine warfare. Unlike fixed-wing aircraft or helicopters, aerostats and airships are lighter-than-air (LTA); typically using helium to stay aloft. Airships are traditionally manned, and use engines to fly. Aerostats are tethered to the ground, by a cable that also provides power. As many as 32 companies are involved in the design or manufacture of more than 100 commercially available airships and aerostats in Europe, Asia, and North America. The Navy disbanded its last airship unit in1962, and since then, military use of lighter-than-air platforms has been limited to Air Force custodianship of a dozen aerostats. However, a number of developments have combined to draw increased attention toward LTA platforms. First, U.S. aerospace dominance in military conflicts since 1991 has been overwhelming, making threats to LTA platforms appear to be very low by historical standards. Second, the military's demand for persistent surveillance, a function for which aerostats appear to be well suited, is growing. Network-centric warfare approaches, increased emphasis on homeland security, and growing force protection demands in urban environments all call for dominant battlespace awareness.
ADA460177
Near Space: Should Air Force Space Command Take Control of Its Shore? (Maxwell Paper, Number 38)
Descriptive Note: Monograph
Personal Author(s): Hall, Kurt D
Report Date: Sep 2006
Media Count: 39 Page(s)
Descriptors: (U) *SPACE DEFENSE, *SPACE SURVEILLANCE, BALLOONS, AIRSHIPS, MILITARY INTELLIGENCE, SPACE COMMUNICATIONS
Identifiers: (U) *NEAR SPACE, BLOS(BEYOND LINE-OF-SIGHT), ORS(OPERATIONALLY RESPONSIVE SPACE), JWS(JOINT WARFIGHTING SPACE), ISR(INTELLIGENCE-SURVEILLANCE-RECONNAISSANCE)
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) One lesson the DOD realized from recent conflicts, as well as humanitarian and relief operations, involves significant shortfalls in command, control, communications, computers, intelligence, surveillance, and reconnaissance (C4ISR), the enabling mission area that supports joint operations across the range of military operations. These shortfalls include tactical beyond-line-of-sight (BLOS) communications on the move, persistent ISR, red-force tracking, change detection, detection of mines and improvised explosive devices, and all-weather imaging. To correct these shortfalls, Gen John P. Jumper, the former Air Force chief of staff, tasked Air Force Space Command (AFSPC) with the responsibility of developing, fielding, and executing tactical and operationally responsive space (ORS) capabilities near and through space. Although it has expertise in providing capabilities through and in space, AFSPC possesses no such skills in near space-the portion of Earth's atmosphere above internationally controlled airspace (65,000 feet) and below the recognized limit of orbital space (60 miles). Thus, AFSPC created the Joint Warfighting Space (JWS) initiative, which focuses on near space due to the claim of achieving space-like capabilities at a lower cost and providing them directly to tactical commanders. AFSPC claims that future near-space systems will have BLOS communications and ISR persistence measured in days, weeks, and months, greatly exceeding the capabilities of long-endurance vehicles such as unmanned aerial vehicles (UAV). These systems will look like neither satellites nor launch vehicles but more like balloons and blimps. The United States has had experience with the latter two since the 1930s-but at aircraft altitudes. Accordingly, the JWS team galvanized universities and commercial companies to improve current near-space capabilities, and recent experiments with balloons and tactical radios for BLOS communicailons show promise.
ADA461633
Lighter-Than-Air Systems for Future Naval Missions
Descriptive Note: Group study, Mar 2005-Mar 2006
Personal Author(s): Bowes, W C; Engelland, J; Fernandez, F L; Fratarangelo, P; Kohn, Jr , E R; Lister, M J, Neal; W A, Polmar; N, Rumpf; R L, Smith, T B
Report Date: Apr 2006
Media Count: 110 Page(s)
Descriptors: (U) *NAVAL AIRCRAFT, *AIRSHIPS, AERIAL RECONNAISSANCE, CARGO, RELAYS, HOMELAND DEFENSE, HARBOR DEFENSE SYSTEMS, PORTS(FACILITIES), SURVEILLANCE, AIRLIFT OPERATIONS
Identifiers: (U) *LTA(LIGHTER-THAN-AIR), COMMUNICATIONS RELAYS, CARGO TRANSFER, BORDER CONTROL, PORT SECURITY, HARBOR SECURITY, ISR(INTELLIGENCE-SURVEILLANCE-RECONNAISSANCE)
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The Panel concluded that several Lighter-Than-Air (LTA) vehicles now available could provide the endurance and station-keeping needed for persistent ISR, communications relay, and electronic warfare. These vehicles can provide a desired long range communication relay for the Marine Corps and can perform port and harbor security missions at low costs. LTA vehicles offer the potential to provide an enhanced capability for high-altitude (greater than 60,000 feet) communications and surveillance at significantly lower cost than current heavier-than-air vehicles. LTA vehicles also could provide the capability to lift and deliver more than 500 tons of material or personnel to an operational area. While this capability does not exist today, with significant technology development, LTA vehicles could carry out these missions.
ADA446699
Performance Capability of a Damaged Lighter-Than-Air Vehicle Operating in the Near Space Regime
Descriptive Note: Master's thesis
Personal Author(s): Vogt, Jr, Charles W
Report Date: Mar 2006
Media Count: 93 Page(s)
Descriptors: (U) *AIRSHIPS, SURVIVABILITY, OVERPRESSURE, THESES, GASES, HIGH ALTITUDE, ENVELOPE(SPACE), HULLS(STRUCTURES)
Identifiers: (U) DEPRESSURIZATION, LIGHTER-THAN-AIR
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) This study investigates the ability of a high-altitude airship to maintain lift following the compromise of its lifting gas envelope. Accepted engineering principles are applied to develop a model that provides comparative analyses for airship depressurization alternatives following hull compromise. Specifically, maintaining lifting gas envelope overpressure to provide controllability in wind currents while sacrificing some buoyancy is compared with allowing envelope depressurization to occur with the goal of maintaining greater buoyancy as long as possible. The model provides insights to alternatives for recovering a damaged vehicle and its payload. In particular, the analysis demonstrates that maintaining the ability to navigate while forfeiting buoyancy can provide additional down-range maneuver capability. In some cases preserving the airship's hull overpressure for some period of time following compromise, vice allowing a slow depressurization to atmospheric equilibrium, extends the distance a damaged airship can sustain controlled navigation as much as eighty percent. However, the airship will forfeit nearly twenty percent of the altitude it would otherwise preserve by not forcing a constant hull overpressure.
ADA449841
Guidance, Navigation and Control of High-Altitude Airships
Personal Author(s): Mueller, Joseph
Report Date: Jan 2006
Media Count: 10 Page(s)
Descriptors: (U) *NAVIGATION, *SOLAR ENERGY, *GUIDANCE, *AIRSHIPS, *HIGH ALTITUDE, MILITARY FORCES(UNITED STATES), HIGH COSTS, MILITARY EQUIPMENT, LAUNCHING, AIR TRAFFIC, HIGH SENSITIVITY, RADIO RELAY STATIONS, STRATOSPHERE, UPLINKS, SURVEILLANCE, LIGHTWEIGHT, STATIONARY, SOLAR CELLS, PATROLLING, WIND, THIN FILMS
Identifiers: (U) *HIGH ALTITUDE AIRSHIPS, LIGHTWEIGHT MATERIALS, HAA(HIGH ALTITUDE AIRSHIP), SBIR REPORTS, SBIR(SMALL BUSINESS INNOVATION RESEARCH)
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Recent developments in lightweight materials and renewable energy technologies have sparked a renewed interest in an old concept. Airships have been flying since 1852, and have been serving the U.S. military since 1908. Since their inception, they have been used for sightseeing, civilian and military transport, and most recently, advertising. However, the potential of these lighter-than-air vehicles has not yet been fully tapped. With recent advances in ultra-lightweight fabrics, composites, and thin-film solar cells, airships can now reach the stratosphere and sustain powered flight using only solar energy. This concept of a high altitude airship (HAA) represents a new service platform that compliments, and in many ways, outperforms satellites. Flying in the calmest region of the atmosphere, above all cloud cover and all regulated air traffic, the HAA is designed to station-keep at an altitude range of 65-70 km, or 19-21 thousand feet. Unlike satellites, airships can maintain any geostationary position; their close-proximity offers improved uplink capability; they are serviceable and easily re-stationed; and they do not carry the burden of high launch costs. Some broad examples of the potential applications include data relay stations for the military and telecommunication industry, mobile observatories for weather and scientific study, and surveillance platforms for activities such as border patrol, disaster relief, and private security. While the potential benefits of the HAA concept are clear, it does remain a concept. To advance from the design stage to an operational platform, the HAA must demonstrate reliable, controlled flight for days, weeks, and eventually months at a time. The unique dynamics of the HAA vehicle make this a challenging task, with widely varying mass properties, significant effects from added mass and inertia, and high sensitivity to wind.
ADA463564
Lowering the High Ground: Using Near-Space Vehicles for Persistent C3ISR
Descriptive Note: Research paper
Personal Author(s): Knoedler, Andrew J
Report Date: Nov 2005
Media Count: 33 Page(s)
Descriptors: (U) *HIGH ALTITUDE, *AIRSHIPS, COMMAND CONTROL COMMUNICATIONS, SURVEILLANCE, SENSOR FUSION, MULTISENSORS, RECONNAISSANCE, INTELLIGENCE
Identifiers: (U) C3ISR(COMMAND CONTROL COMMUNICATION INTELLIGENCE SURVEILLANCE RECONNAISSANCE), NEAR SPACE
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Department of Defense (DOD), military service, and industry leaders have focused on increasing command, control, communications, intelligence, surveillance, and reconnaissance (C3ISR) persistence. As of today, the air and space platforms do not provide persistent C3ISR. Platforms exploiting near space will be part of an integrated solution to increase persistent C3ISR. This paper covers the capabilities and limitations of current C3ISR platforms supporting battlespace awareness. After identifying the deficiencies, the essay then explores the various platform and payload combinations that can reach the near space altitudes of 20 to 150 kilometers (km). Finally, the paper concludes with a comparison of capabilities and concepts of operations (CONOPS) for several near-space vehicle (NSV) constellations.
ADA444479
Lighter-Than-Air Systems for Future Naval Missions
Descriptive Note: Briefing charts
Report Date: 04 Oct 2005
Media Count: 52 Page(s)
Descriptors: (U) *NAVY, *MISSIONS, *AIRSHIPS, *BALLOONS, DEPLOYMENT, DETECTORS, HIGH ALTITUDE, COSTS, SURVIVABILITY
Identifiers: (U) LTA(LIGHTER-THAN-AIR), LIGHTER THAN AIR VEHICLES, LIMITATIONS, AEROSTATS, HEAVY LIFT, BRIEFING CHARTS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Outline of presentation: Panel Membership; Terms of Reference; Categories of LTA Vehicles; Executive Summary; Study Flow; Briefings Received; LTA vehicles and characteristics; Missions; LTA Categories vs Missions Matrix; Study Findings- Aerostat and Low Altitude Airship, High Altitude Airship, Heavy-Lift Hybrid Airship; Conclusions; Summary Recommendations.
ADA445196
Off-The-Shelf and Free Software Technologies for Spacecraft Control & Command: An Example, Balloon-Borne Stabilised Gondolas
Personal Author(s): Laurens, Andre
Report Date: 13 Jul 2005
Media Count: 17 Page(s)
Descriptors: (U) *ATTITUDE CONTROL SYSTEMS, *OFF THE SHELF EQUIPMENT, *ARTIFICIAL SATELLITES, *BALLOONS, *GONDOLAS, *ADA PROGRAMMING LANGUAGE, *COMMAND AND CONTROL SYSTEMS, MEASUREMENT, REAL TIME, GROUND BASED, ASTROPHYSICS, SPACE MISSIONS, SPACECRAFT
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Balloons are low-cost, short development time space vehicles for science missions and technology in-flight experiments that need out-of-atmosphere or in-situ measurements, thus being complementary to the satellite. CNES stabilised gondolas are versatile space platforms used to fly science instruments mainly for aeronomy and astrophysics that need stabilisation and pointing capabilities, analogous to satellite attitude control subsystems. In order to increase gondola flexibility to new missions, promoted control & command technologies are those of industrial computers, ground networks, free software and, over all, Ada language, for they are open, standard, powerful, low-cost and longlasting solutions. After a brief description of domain-oriented characteristics of stabilised gondola control & command, this paper introduces the various technologies and main design principles proposed to meet system-level goals. Then focus is put on on-board architectures (Ada95 real-time distributed applications), and describes the prototyping work and preliminary development done to ensure feasibility. The paper then discusses the applicability of such solutions to global, ground-toboard, distributed control & command applications, through an IP-based telemetry & telecommand link, such as the one under development in CNES for balloon systems. As a conclusion, this paper shows how adoption of the above technologies for other space programs such as satellite platforms and payloads may change design, development costs, duration and organisation, as well as it may open new ways in ground-to-board communication and spacecraft operation.
ADA437046
The Lifeblood of Seabasing: Sustainment Through Rapid Strategic Airlift
Descriptive Note: Master's thesis
Personal Author(s): Magness, Matthew T
Report Date: 17 Jun 2005
Media Count: 110 Page(s)
Descriptors: (U) *MILITARY AIRCRAFT, *AIRLIFT OPERATIONS, *SEA BASED, LITERATURE SURVEYS, SEAPLANES, THESES, TRANSPORT
Identifiers: (U) *SEABASING, *SUSTAINMENT, LTA(LIGHTER-THAN-AIR), WIG(WING-IN-GROUND), ADVANCED THEATER TRANSPORT, GRID ANALYSIS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The future of Seabasing rests with the capability to rapidly re-supply and sustain forces from strategic distances. Sealift presents one way of accomplishing this sustainment; however, it is slow. The solution for rapid long-range sustainment of a Seabase must come in the form of aircraft capable of lifting massive weights over vast distances and delivering them directly to the structure. This thesis explores the primary research question: What are the long-range, heavy lift aircraft programs that could sustain Seabasing? The question is explored by using the Wisconsin 7-Step Problem-Solving Strategy: state the problem, determine the solution criteria, gather needed information, generate potential solutions, compare solutions and problem, select the solution, and prepare communications. Four concepts were identified (Lighter-than-Air, Wing-in-Ground, Advanced Theater Transport, and Seaplanes) as having the capabilities to support Seabasing. Due to the many factors associated with determining the best solution, a technique of performing a grid analysis with weighted criteria is used. The results indicate that the best types of aircraft suited to sustain a Seabase are ones that are large, joint in development and operation, can be utilized outside standard military applications, and are capable of carrying massive payloads great distances.
ADA467685
Potential Military Use of Airships and Aerostats
Descriptive Note: Congressional rept.
Personal Author(s): Bolkcom, Christopher
Report Date: 09 May 2005
Media Count: 7 Page(s)
Descriptors: (U) *AIRSHIPS, *AEROSTATICS, MILITARY INTELLIGENCE, DEPARTMENT OF DEFENSE, HOMELAND SECURITY, TETHERING, MILITARY PLANNING, SEARCH RADAR
Identifiers: (U) AEROSTATS, LTA(LIGHTER-THAN-AIR), TARS(TETHERED AEROSTAT RADAR SYSTEM)
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The Department of Defense (DOD) has a history of using lighter-than-air (LTA) platforms. Aerostats have recently been fielded to protect U.S. troops in the field. Contemporary interest is growing in using airships for numerous missions. This report examines the various concepts being considered and describes the issues for Congress.
ADA437762
Technical Feasibility of Loitering Lighter-Than-Air Near-Space Maneuvering Vehicles
Descriptive Note: Master's thesis
Personal Author(s): Moomey, Eric R
Report Date: Mar 2005
Media Count: 98 Page(s)
Descriptors: (U) *AIRSHIPS, GUIDED MISSILES, ORBITS, DENSITY, MANEUVERABILITY, PAYLOAD, PARAMETRIC ANALYSIS, LOW COSTS, MONITORING, THESES, FEASIBILITY STUDIES, NAVIGATION, PLATFORMS, COEFFICIENTS, PRECISION, ARTIFICIAL SATELLITES, HIGH ALTITUDE, COMMUNICATION AND RADIO SYSTEMS, STATIONKEEPING, RELAYS, WARNING SYSTEMS, EARTH ATMOSPHERE, BUOYANCY, POWER, EARTH SURFACE, DRAG, FUEL CELLS, WEAPON DELIVERY, ENVELOPE(SPACE), SPACE COMMUNICATIONS
Identifiers: (U) *LIGHTER THAN AIR VEHICLES
Distribution Statement:
Approved for public release; distribution is unlimited.
Abstract: (U) The near-space region of earth's atmosphere above 20 kilometers altitude is greatly underutilized. Lighter-than-air maneuvering vehicles, or airships, using the principle of buoyancy can take advantage of this region to become potential platforms for precision navigation, environmental monitoring, communication relays, missile warning, surveillance, and weapon delivery. These vehicles purportedly provide persistent coverage over large areas of the earth's surface at substantially lower costs than orbiting satellites. This study investigated the technical requirements to loiter an operational payload within this high altitude region using a lighter-than-air maneuvering platform. A parametric analysis was conducted to identify the critical technologies needed to achieve operational payload, power, altitude, and stationkeeping requirements. The research concluded feasibility of stationkeeping a 1000 kg payload in lower near-space (20-25 km) using current airship technologies. Solar powered electric propellers provided the best overall near-space loiter capability for missions beyond 30 days. Additional loiter capability can be attained for shorter missions using fuel cell technologies. Technology improvements in the airship's drag coefficient, envelope fabric density, and payload mass and power requirements are required to attain altitudes beyond 25 km.
ADA440454
High-Altitude Airships for the Future Force Army
Descriptive Note: Technical rept.
Personal Author(s): Jamison, Lewis; Sommer, Geoffrey S; Porche, III, Isaac R
Report Date: Jan 2005
Media Count: 66 Page(s)
Descriptors: (U) *LIMITATIONS, *COMMUNICATIONS NETWORKS, *SURVEILLANCE, *AIRSHIPS, *HIGH ALTITUDE, *RISK ANALYSIS, LINE OF SIGHT, PAYLOAD, WEATHER, LIGHTWEIGHT, ARMY, WIRELESS LINKS, COST REDUCTION, LOITERING, BENEFITS, DRONES, MILITARY APPLICATIONS, UNMANNED, SOLAR ENERGY, VULNERABILITY, LONG RANGE(TIME)
Identifiers: (U) *HAAS(HIGH-ALTITUDE AIRSHIPS), LTA(LIGHTER-THAN-AIR), LPI(LOW PROBABILITY OF INTERCEPT), HALE(HIGH ALTITUDE LONG ENDURANCE), HALL(HIGH ALTITUDE LONG LOITER), NETWORK CENTRIC WARFARE, MANEUVERING AIRSHIPS, DIRIGIBLES, BLIMPS, ZEPPELINS, COMMERCIAL APPLICATIONS, UAV(UNMANNED AERIAL VEHICLES)
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Across the services, there is an increasing demand for overhead communications capacity. For the U.S. Army, this is a result of its transition to a new force structure that will be knowledge-based and network-centric. Future forces may be more dispersed. Extending their range of communication will be key. Messages will have to be relayed through a multilayered network of terrestrial-, air-, and space-based retransmission nodes. Currently, satellite communications (SATCOM) is being relied on to connect distant units. However, the exclusive use of military or commercial SATCOM may not be available to meet all of the Army's connectivity needs, and high-altitude airships (HAAs) are being considered as an optional surrogate, which could be even more cost-effective if proved technically feasible. New, lighter-than-air (LTA) vehicles that operate at very high altitudes have an obvious attraction for planners of surveillance and communication missions; the ability to see to a more distant horizon results in greatly expanded surveillance volumes (assuming that appropriately powerful sensors are carried onboard). Low probability of intercept (LPI) direct line-of-sight communications will also increase their reach. In recent years, increased emphasis has been placed on systems that can provide extended surveillance and communications support at such high altitudes. These are generically known as High Altitude Long Endurance (HALE) systems or High Altitude Long Loiter (HALL) systems. The Global Hawk unmanned aerial vehicle (UAV) was perhaps the first of these systems to achieve operational success. Flight at high altitude (say, over 60,000 feet) for extended periods (for a matter of days or more) is an extreme technical challenge for fixed-wing aircraft. The purpose of this report is to inform the U.S. Army about the usefulness and limitations of airships in roles of supporting communications and surveillance functions in theater battlespace.
ADA432916
Acoustic Detection from Aerial Balloon Platform
Descriptive Note: Conference paper
Personal Author(s): Reiff, C; Pham, T; Scanlon, M; Noble, J; Van Landuyt, A; Petek, J; Ratches, J
Report Date: Dec 2004
Media Count: 9 Page(s)
Descriptors: (U) *ACOUSTIC DETECTION, *DRONES, *FLYING PLATFORMS, *BALLOONS, SYMPOSIA, ROBOTICS, FIELD TESTS, WAVE PROPAGATION, GROUND VEHICLES, AUTONOMOUS NAVIGATION, COMPUTER NETWORKS, SPECTROGRAPHS, AEROSTATICS
Identifiers: (U) COMPONENT REPORTS, FCS(FUTURE COMBAT SYSTEMS), UAV(UNMANNED AERIAL VEHICLES), NSFFF(NETWORKED SENSORS FOR THE FUTURE FORCE)
Distribution Statement: Approved for public release; distribution is unlimited., Availability: This document is not available from DTIC in microfiche.
Abstract: (U) The US Army Research Laboratory (ARL) and US Army Night Vision and Electronic Sensors Directorate (NVESD) are leading the research and development in autonomous sensing and sensor networks for the Networked Sensors for the Future Force (NSfFF) and Future Combat System (FCS). With the emphasis being shifted to lighter and more mobile forces, ARL and NVESD have been collaborating and exploring various mobile platforms such as robotic vehicles and aerial platforms such as unmanned aerial vehicles (UAVs) and balloons. Our most immediate collaboration focuses on the use of acoustic sensors on small balloons and/or aerostats at several elevations and on the ground with the primary goals of: (i) investigate the acoustic sensing and detection ranges; (ii) acoustically cue IR imagers and/or video cameras; and (iii) explore the networking of elevated sensors and ground sensors for NSfFF. In this paper, we only focus on the first goal, the acoustic detection portion of the collaborative effort.
ADA472587
Potential Military Use of Airships and Aerostats
Descriptive Note: Congressional rept.
Personal Author(s): Bolkcom, Christopher
Report Date: 11 Nov 2004
Media Count: 7 Page(s)
Descriptors: (U) *OPERATIONAL EFFECTIVENESS, *AIRSHIPS, DEPARTMENT OF DEFENSE, COSTS, TETHERING, BALLOONS, MISSIONS, VULNERABILITY
Identifiers: (U) BLIMPS, TETHERED BALLOONS, *AEROSTATS, LTA(LIGHTER THAN AIR)
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The Department of Defense (DOD) has a history of using lighter-than-air (LTA) platforms such as airships (blimps) and aerostats (tethered balloons). Aerostats have recently been fielded to protect U.S. troops in the field. Contemporary interest is growing in using airships for numerous missions. This report examines the various concepts being considered and describes the issues for Congress. This report will be updated as events warrant.
ADA461320
The Mobilus Initiative: Creating A New Component of the US Aerospace Industry Centered Upon Transport Airships
Descriptive Note: Journal article
Personal Author(s): Woodgerd, Michael
Report Date: Jan 2004
Media Count: 18 Page(s)
Descriptors: (U) *AIRSHIPS, AIRCRAFT INDUSTRY, INDUSTRIAL MOBILIZATION, TECHNOLOGY ASSESSMENT, AIR TRANSPORTATION, AIRLIFT OPERATIONS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The United States requires greater mobility to meet burgeoning military and commercial demands. The US aerospace industry shows signs of faltering; improving the efficiency of the existing air transportation system and its components cannot by itself provide enough overall gain in capability to meet future commercial and military needs. Only Lighter-Than-Air (LTA) technology--derided, often wildly misunderstood and largely ignored for the last 50 years--actually offers the potential to provide tremendous increases in volume, speed and accessibility for air movement around the world. LTA technology offers new types of aircraft, more complete utilization of airspace, and supports a more fully networked concept to air transportation. This article describes the key military/civilian/aerospace industry needs and opportunities to show how transport airships offer a common solution to multiple problem sets. The bulk of the paper describes the Mobilus Initiative in greater detail. Mobilus is fundamentally a Vision upon which many individuals and entities can focus effort and also the method to build a major new sector of the US, and then the world, aerospace industry. By building a broad, firm industrial base of airships and related LTA applications (stratospheric airships, for example) and building it in a new and commercially driven manner, our Nation gains mobility and economic power; perhaps even a dominant place in world aviation. Mobilus provides a coherent, logical development plan. The analysis of multiple platforms developmental paths, the high-payoff commercial applications, the methodology of how multiple public-private partnerships would create this broad capability will be the first of its kind. It will support the collaborative approach that will drive development across a broad array of technical types, varied geographic areas, and accelerate the broad capability faster than the old style approach of traditional contracts focused on one type of platform.
ADA451761
Development of an Aerodynamic Model and Control Law Design for a High Altitude Airship
Personal Author(s): Mueller, Joseph B; Paluszek, Michael A; Zhao, Yiyuan
Report Date: Jan 2004
Media Count: 18 Page(s)
Descriptors: (U) *HIGH ALTITUDE, *AUTONOMOUS NAVIGATION, *AIRSHIPS, EQUATIONS OF MOTION, ANTIMISSILE DEFENSE SYSTEMS, SPACE SURVEILLANCE, DRONES, BUOYANCY, MILITARY SATELLITES, DESIGN CRITERIA, MODELS, SOLAR ENERGY, MISSIONS, REMOTE DETECTORS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Lighter-than air vehicles are an attractive solution for many applications requiring a sustained airborne presence. The buoyancy force provides an energy-free form of lift, offering a non-traditional approach to long-duration missions for which traditional aircraft are not well-suited. Potential applications include roving or hovering surveillance and communication utilities for both military and commercial use, and a variety of remote-sensing instruments for the scientific community. In particular, the Missile Defense Agency plans to utilize unmanned airships at high-altitudes to provide a long-duration missile defense presence around the coast-line of the United States. Operated at 70 kft, each of these high altitude airships will fly above all regulated air traffic for several months to years, will reside in a steady atmospheric regime, and will utilize solar energy to provide all required power. Two key objectives for this type of mission are that the unmanned airship have exceptionally long endurance, and that it operate with a sufficiently high-level of autonomy. In order to achieve these objectives, a robust guidance and control system is required, capable of auto-piloting and controlling the airship under an extremely wide range of atmospheric and wind conditions. The successful design of such a system first requires an accurate model of airship dynamics across its expansive flight envelope, and a representative model of the expected disturbances. The dynamics of an airship are markedly different from traditional aircraft, with significant effects from added mass and inertia, and a much higher sensitivity to wind. In this paper, a typical airship configuration is first sized to meet energy balance and mass constraints. The geometry of this configuration is then used to develop a general aerodynamic model for the airship.
ADA427452
The Certification of Lighter-Than-Air UAV Systems
Descriptive Note: Briefing charts
Personal Author(s): Clot, Andre J
Report Date: 02 Sep 2003
Media Count: 25 Page(s)
Descriptors: (U) *REMOTELY PILOTED VEHICLES, *AIRSHIPS, SYMPOSIA, SIZES(DIMENSIONS), AIR SPACE, AVIATION SAFETY, REGULATIONS, AIRWORTHINESS, UNITED KINGDOM
Identifiers: (U) PROCEEDINGS, BRIEFING CHARTS, FOREIGN REPORTS, UAV(UNMANNED AERIAL VEHICLES), LTA(LIGHTER-THAN-AIR), CERTIFICATION
Distribution Statement: Availability: This document is not available from DTIC in microfiche.
Abstract: (U) Briefing charts from presentation on the certification of AIRSCAN, lighter-than-air(LTA) UAV systems.
ADA416208
Modern Airships: A Possible Solution for Rapid Force Projection of Army Forces
Descriptive Note: Monograph rept.
Personal Author(s): Newbegin, Charles E
Report Date: 22 May 2003
Media Count: 74 Page(s)
Descriptors: (U) *AIRSHIPS, *RAPID DEPLOYMENT, WARFARE, THEATER LEVEL OPERATIONS, STRATEGY, ARMY PERSONNEL, TRANSPORT, TAKEOFF, LETHALITY, DESIGN CRITERIA, ARMY AVIATION, VERTICAL TAKEOFF AIRCRAFT, PORTS(FACILITIES), INFRASTRUCTURE, TECHNOLOGY ASSESSMENT
Identifiers: (U) STOL(SHORT-TAKE OFF AND LANDINGS), VTOL (VERTICAL TAKE-OFF AND LANDINGS)
Distribution Statement: Availability: This document is not available from DTIC in microfiche.
Abstract: (U) The deployment process involves four phases: pre-deployment activities; movement to and activities at port of embarkation; movement to port of debarkation; and Joint Reception, Staging, Onward Movement, and Integration. This process is labor intensive and time consuming, especially for heavy forces. This process is very reliant on Aerial and Sea Ports of Debarkation (APOD/SPOD). This reliance makes JRSOI sites in a theater predictable and thus a target for the enemy. Current OSD belief is that a lighter and more lethal fighting force could complete the deployment process faster than current heavy forces. Operation Iraqi Freedom, however, demonstrated heavy forces are still needed to defeat the enemy. Airships represent a new way of quickly deploying Army forces into a theater of operation. Modern airships by design are capable of short-take off and landings (STOL), and vertical take-off and landings (VTOL). This VTOL capability enables the airship to land practically anywhere, independent of most infrastructure support. This ability would allow deploying heavy forces to be picked up at their home-station and transported directly to a location directed by the Combatant Commander, bypassing the labor intensive and time consuming portions of the deployment process. The challenge facing DoD is determining if this type of transport is feasible and acceptable for military use. DoD has already sponsored two studies on two very different airship designs, thus demonstrating DoD is interested in the airship heavy transport concept. This monograph highlights some of the findings from those studies and looks at historically proven uses of airships and some contemporary uses as well. Contemporary transports, the deployment process, and the associated challenges for deployments.
ADA404859
An Aerostat/Elevated Antenna Component to Aid VHF Radiotelemetry and Tracking of Right Whales in Critical Habitats
Descriptive Note: Final rept. 15 Aug 1998-14 Aug 2001
Personal Author(s): Hain, James H
Report Date: Aug 2001
Media Count: 5 Page(s)
Descriptors: (U) *RADIO TELEMETRY, *BALLOONS, MONITORING, TRACKING, RECEIVERS, ANTENNAS, REMOTE DETECTION, VERY HIGH FREQUENCY, WHALES
Identifiers: (U) AEROSTATS
Abstract: (U) Elevating the receiving antenna in projects to monitor movements and behaviors of right whales, Eubalaena glacialis, in critical habitats will increase range and efficacy. This was accomplished by mounting the antenna and receiver on an aerostat (tethered balloon). At altitudes of 200 ft or greater, ranges of 15-20 miles can be expected. This project evolved to include other applications, and demonstrated the use of aerostats for carrying antenna arrays, instrument packages, sensors, and cameras to altitudes of several thousand feet. An emerging area in the field of environmental technology has been identified.
ADA392293
Helikite Elevated Platform (HEP)
Descriptive Note: Final rept. 26 Dec 2000-26 Jun 2001, Phase 1
Personal Author(s): Rogers, Michael E
Report Date: 26 Jun 2001
Media Count: 32 Page(s)
Descriptors: (U) *PLATFORMS, *GLOBAL POSITIONING SYSTEM, *AIRSHIPS, SIGNAL PROCESSING, LOW COSTS, HELICOPTERS, NAVIGATION, RECEIVERS, COMBAT VEHICLES, JAMMING, HELIUM, ALTITUDE, WEAPON DELIVERY, ALL WEATHER, ELECTRONIC INTELLIGENCE, BALLOONS, TELEVISION CAMERAS, COMMUNICATIONS INTELLIGENCE, LOW ELEVATION
Identifiers: (U) SBIR(SMALL BUSINESS INNOVATION RESEARCH), *PSEUDOLITES, *HEP(HELIKITE ELEVATED PLATFORM), TETHERED BLIMP, HMMWV(HIGH MOBILITY MULTIPURPOSE WHEELED VEHICLE), VIDEO CAMERAS, COMINT(COMMUNICATIONS INTELLIGENCE), SIGINT(SIGNAL INTELLIGENCE)
Abstract: (U) The Army requires a method of deploying a GPS Pseudolite to several hundred or thousand feet altitude to provide augmented GPS signals. To meet this need Carolina Unmanned Vehicles, Inc. is developing the Helikite Elevated Platform (HEP), consisting of a small tethered blimp mounted in a special Carrier that allows operation by a single person. It can be towed by a HMMWV or other small vehicle. HEP may also be used for Differential GPS support to enhance areas such as helicopter all weather navigation. Other payloads can include video cameras, COMINT/SIGINT receivers, jammers or communication equipment. The project will provide an improved capability for the military and civilian agencies for continuous low cost elevation of a variety of payloads to several thousand feet, with minimum manpower, training and investment.
ADA392214
Helikite Elevated Platform (HEP)
Descriptive Note: Final rept. 26 Dec 2000-26 Jun 2001 on Phase 1
Personal Author(s): Rogers, Michael E
Report Date: Jun 2001
Media Count: 32 Page(s)
Descriptors: (U) *GLOBAL POSITIONING SYSTEM, *TRANSMITTERS, *AIRSHIPS, ELEVATION, BALLOONS, COMMUNICATIONS INTELLIGENCE
Identifiers: (U) BLIMPS, HELIKITES, PSUEDOLITES, COMINT, SIGINT(SIGNALS INTELLIGENCE)
Abstract: (U) The Army requires a method of deploying a GPS Pseudolite to several hundred or thousand feet altitude to provide augmented GPS signals. To meet this need Carolina Unmanned Vehicles, Inc. is developing the Helikite Elevated Platform (HEP), consisting of a small tethered blimp mounted in a special Carrier that allows operation by a single person. It can be towed by a HMMWV or other small vehicle. HEP may also be used for Differential GPS support to enhance areas such as helicopter all weather navigation. Other payloads can include video cameras, COMINT /SIGINT receivers, jammers or communication equipment. The project will provide an improved capability for the military and civilian agencies for continuous low cost elevation of a variety of payloads to several thousand feet, with minimum manpower, training and investment.
ADA397841
The American Approach to Aerial Reconnaissance and Observation During World War I
Descriptive Note: Research paper
Personal Author(s): Cobleigh, Kenneth E
Report Date: Mar 1997
Media Count: 37 Page(s)
Descriptors: (U) *AERIAL RECONNAISSANCE, *FLIGHT TRAINING, *RECONNAISSANCE AIRCRAFT, *BALLOONS, MILITARY FORCES(UNITED STATES), MILITARY HISTORY, MILITARY FORCES(FOREIGN), OBSERVATION, FIRST WORLD WAR
Abstract: (U) This premise of this report is that 'observation' was the motivation for the first employment of balloons and aircraft, and that in World War I, Allied assistance and equipment were absolutely crucial to the development and employment of the U.S. Army Air Service. This work will look at two main areas. First, the types of observation vehicles employed in World War I and secondly, the tremendous role the European Allies played in providing equipment, training, instruction, and combat experience to American aerial forces, both at home and abroad. 'The purposes of observation were to control friendly artillery fire and, through photographic and intelligence missions, to observe and report on friendly troop locations and movement, enemy ground and air activity, the terrain, and related matters. Most observation, especially where distance was a factor, was handled by two-seater aircraft, equipped with radio and visual signal equipment, armed with fixed guns in front and movable guns in the rear cockpit, and carrying, when necessary, photographic equipment; the remaining observation was carried out by observers in captive balloons. Now that the use of cavalry was not longer feasible, air observation was the eyes of the army''.
ADA397845
Zeppelinitis
Descriptive Note: Research paper
Personal Author(s): Lavelle, Brian C
Report Date: Mar 1997
Media Count: 32 Page(s)
Descriptors: (U) *MORALE, *PUBLIC OPINION, *AIRSHIPS, MILITARY HISTORY, PROPAGANDA, JOURNALISM, SECOND WORLD WAR
Identifiers: (U) ZEPPELINS, ENGLAND
Abstract: (U) This paper examines the development of the concept of the airship as a weapon of widespread destruction and the effect that entertainment literature and the popular press' presentation of this concept had on the English public and government's reaction to WWI Zeppelin attacks. The historical development of the concept of aerial attack on cities is traced from its first application in 1848, its portrayal in novels as a futuristic weapon of immense destructive power, German airship propaganda, and the many English press reports about the estimated capabilities and roles of the airship. When the airship was employed against England in WWI, the population reacted to the image planted in its mind by novels, nourished by propaganda and hyped by sensationalist press reports. Rumor, morbid curiosity, and a borderline hysterical fear of the airship and aerial attack spread throughout the English population to such an extent that industrial war production was affected. By the end of the war nearly a quarter million Londoners sought shelter each night from a relatively minor threat which over the course of four years inflicted casualties and property damage which amounted to less than that suffered on a quiet day in the trenches of the Western Front. This effect on the 'morale' of the public vice the physical damage inflicted became a driver of RAF airpower doctrine in the interwar years. The reaction of the citizenry of England to the airship raid is a testimony to the power of the written and spoken word and its ability to unsettle a nation.
ADA350388
Aero Propulsion and Power Directorate The McCook Field Years (1917-1927)
Descriptive Note: Final rept. Dec 90-Feb 95
Personal Author(s): Misenko, Albert
Report Date: Feb 1995
Media Count: 173 Page(s)
Descriptors: (U) *BALLOONS, WARFARE, AIR FORCE, GLOBAL, UNITED STATES, OHIO, AERONAUTICS, FLIGHT, HISTORY, CORPS LEVEL ORGANIZATIONS, TETHERING
Identifiers: (U) WORLD WAR 1, PE62203, WUAFRLAPPLTO02
Abstract: (U) This report details the early history of flight, from the invention of ballooning to the Wright B Flyer and beyond. It chronicles the progression of the United Sates Air Corps and its significance before, during, and after World War I. Most importantly, the book focuses on the formation of McCook Field in Dayton, Ohio and the critical role it played in the advancement of aeronautics in the United States.
ADA275163
Simulation of Complex Balloon Liftoff
Personal Author(s): Jumper, George Y; Blank, Jeffrey A; Dwyer, James F
Report Date: 28 Dec 1993
Media Count: 6 Page(s)
Descriptors: (U) *TAKEOFF, *AERODYNAMIC LIFT, *BALLOONS, SIMULATION, REPRINTS, PAYLOAD, EQUATIONS OF MOTION, OCEANS, CROSSWINDS, SHIP LAUNCHED, SHIP DECKS, LIFT, STRATEGIC DEFENSE INITIATIVE, WIND, FLIGHT, HIGH ALTITUDE
Identifiers: (U) WUPL9261EJ88, HIGH ALTITUDE BALLOONS, FLIGHT MECHANICS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The SDIO High Altitude Balloon Experiment (HABE) requires the launch of a large balloon from the deck of a ship, in moderate sea and wind conditions. In order to insure that the balloon would clear the obstacles on the deck in the required conditions, the liftoff was simulated using a modern continuous simulation applications software package. The system was modeled as two lumped masses (the balloon and the payload) connected by a ridged connection. The equations of motion were solved for various conditions to determine safe environmental conditions for liftoff. Simulation, Balloon, Liftoff, Flight mechanics.
ADA275164
Improved Viscous Brake Design Using Simulation
Personal Author(s): Jumper, George Y; Joslyn, Thomas B; Kirpa, Geoffrey R; Mironer, Alan B
Report Date: 28 Dec 1993
Media Count: 6 Page(s)
Descriptors: (U) *BRAKES, TEST AND EVALUATION, HIGH POWER, SIMULATION, REPRINTS, DENSITY, TEMPERATURE, PAYLOAD, JOBS, MODELS, BALLOONS, DESCENT, DYNAMICS, TIME, PLATFORMS, HIGH ALTITUDE, POWER, TRANSFER, VISCOSITY
Identifiers: (U) *VISCIOUS BRAKES., WUPL9261EJ88
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The SDIO High Altitude Balloon Experiment ( HABE) required a rapid controlled descent of a large, heavy payload from a balloon platform. An existing viscous brake concept was chosen for the job, but the short time and space available coupled to the heavy payload resulted in very high power densities. Existing rules of thumb for viscous brakes were insufficient ,or the design. Viscous brake phenomenology and the particular physical constraints were coded into a modern continuous simulation applications package. After investigating both full dynamic and quasi-steady models, it was decided that the latter was adequate for all but the first and last small fraction of the descent. The model includes temperature dependent viscosity and a beat transfer model. The model been used extensively to investigate the design space and to develop test plans. Simulation, Viscous brake, Thermal mechanical model, Viscous brake design.
ADA286832
Computing Optimum Heights for Balloon-Borne Radar
Descriptive Note: Project rept.
Personal Author(s): Squires, Michael F
Report Date: Nov 1993
Media Count: 17 Page(s)
Descriptors: (U) *COMPUTER PROGRAMS, *HEIGHT, *ATMOSPHERIC REFRACTION, *RADAR TRANSMITTERS, *METEOROLOGICAL BALLOONS, AIR DEFENSE, OPTIMIZATION, COMPUTATIONS, OPERATIONAL EFFECTIVENESS, ACCESS, TABLES(DATA), RADIOSONDES, TARGET DETECTION, CLIMATOLOGY, RAY TRACING, TETHERING
Identifiers: (U) ADI(AIR DEFENSE INITIATIVE)
Distribution Statement: Approved for public release; distribution unlimited
Abstract: (U) The Air Defense Initiative is considering the use of balloon-borne radar transmitters. Tethering the balloon at an optimum height based on atmospheric refractive effects maximizes the chances for effective target detection. This report provides information for determining optimum transmitter heights for balloon-borne radars by considering the effects of atmospheric refraction. The data is provided on a floppy disk as tables of radar detection data stratified by transmitter and target heights. The tables are accessible through a user-friendly interactive PC program that displays the data. Instructions for access to and interpretation of the tables are included. The report summarizes the assumptions, data, and methods used to create the tables.
ADA425995
The Airship's Potential for Intertheater and Intratheater Airlift
Descriptive Note: Master's thesis
Personal Author(s): Ryan, Donald E , Jr
Report Date: May 1992
Media Count: 90 Page(s)
Descriptors: (U) *AIRLIFT OPERATIONS, *AIRSHIPS, LOGISTICS SUPPORT, THEATER LEVEL OPERATIONS, THESES, TRANSPORT AIRCRAFT
Identifiers: (U) STRATEGIC AIRLIFT, STRATEGIC TRANSPORT, USTRANSCOM(UNITED STATES TRANSPORTATION COMMAND)
Abstract: (U) This paper asserts there exists a dangerous GAP in US strategic intertheater transportation capabilities, propounds a model describing the GAP, and proposes a solution to the problem. Logistics requirements fall into three broad, overlapping categories: Immediate, Mid-Term, and Sustainment requirements. These categories commence and terminate at different times depending on the theater of operations, with Immediate being the most time sensitive and Sustainment the least. Using the Gulf War logistics flow as a model, the three phase points are shown and their airlift/sealift tradeoffs discussed. Other logistics support options, which figured in the war, such as prepositioning and host nation support, are discussed and the Kuwaiti Theater of Operations shown to be, in many ways, a fortuitous theater of operations. This serendipitous combination of circumstances contributed greatly to our successful logistics buildup and is unlikely to recur. The airship is recommended as a suitable solution to the Mid-Term strategic transportation di lemma (GAP). The fundamentals of airship operation.11 are described, its history in both war and peace discussed, and some current private and military airship activities mentioned. Recent technological breakthroughs in materials technology are discussed and the potential for government-sponsored research and development yielding equally great propulsion and cargo capacity dividends explored. A discussion of the potential threat environment of the early twenty-first century shows the airship, properly constructed and used, would likely be no more vulnerable than jet air lifters while offering transportation capabilities currently unavailable. The airship's advantages as an inter/intratheater transporter are so great as to deserve further investigation for addition to the US strategic airlift fleet.
ADA240616
Engineering and Instrumentation Support of GL Research Balloon Program
Descriptive Note: Final rept. 1 Dec 87-10 Dec 89,
Personal Author(s): Seagraves, Squire B
Report Date: 26 Jul 1991
Media Count: 15 Page(s)
Descriptors: (U) *BALLOONS, *CONTROL, PAYLOAD, DETECTORS, AIRCRAFT, FABRICATION, CONTROL CENTERS, NAVIGATION, CREWS, LAUNCHING, INSTRUMENTATION, PARACHUTES, RIGGING, AIMING, GROUND SUPPORT, RECOVERY, GONDOLAS, OBSERVERS
Identifiers: (U) *BALLOONSONDES, *AIR FORCE OPERATIONS, PE62101F
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The activity during this report period was primarily concerned with command and instrumentation preflight support for the command and data acquisition systems, batteries, control room and launch systems support, balloon and parachute rigging support, payload support, aircraft observer and recovery crew support, design and fabrication support for balloon payload systems, including gondola systems, pointing controls, navigational systems, scientific instrumentation, and ground support instrumentation and services.
ADA233610
Airships and the Modern Military
Descriptive Note: Study project
Personal Author(s): Van Eaton, Errol H
Report Date: 10 Mar 1991
Media Count: 42 Page(s)
Descriptors: (U) *MILITARY OPERATIONS, COMMERCE, PILOTS, MISSIONS, AIRSHIPS
Identifiers: (U) *AIRSHIPS, *MILITARY OPERATIONS., COMMAND CONTROL COMMUNICATIONS, SURVEILLANCE, RECONNAISSANCE, HISTORY, ARMY AVIATION
Abstract: (U) The author, a dual-rated Master Army Aviator and a FAA certificated commercial airship pilot, takes a fresh look at potential application of the new generation airships to today's military missions. The paper presents a history of lighter-than-air flight. Application potential to current and projected military missions is then discussed with conclusions and recommendations offered.
ADA239526
The Naval Airship and the Revolution at Sea
Descriptive Note: Master's thesis
Personal Author(s): Shelby, James R
Report Date: Sep 1990
Media Count: 147 Page(s)
Descriptors: (U) *AIRSHIPS, MILITARY OPERATIONS, SHIPS, SIZES(DIMENSIONS), NAVAL VESSELS, OCEAN SURFACE, MODELS, THREATS, NAVY, TEAMS(PERSONNEL), COSTS, SURFACES, MILITARY FORCE LEVELS, AREA DEFENSE, FIRE CONTROL SYSTEMS, BATTLE GROUP LEVEL ORGANIZATIONS, EXTRAPOLATION, SURFACE LAUNCHED
Identifiers: (U) *AIRSHIP, *FIRE CONTROL SYSTEMS, BLIMP, LIGHTER-THAN-AIR, SLAT MISSILE, ANTI SHIP CRUISE MISSILE(ASCM), OVER-THE-HORIZON TARGETING, THESES
Abstract: (U) A system is proposed to combine an airship based fire control system (using-off-the-shelf hardware) with surface ship launched SAMs (NTU/SM-2-ER) to provide OTH wide area ASCM defense for convoys and surface battle groups currently without organic airborne AAW assets. The effectiveness of surface ship AAW area defense is compared, both with and without the airship system, against low-flying ASCMs. The proposed airship system is based on combining the F-14 fire control system (AWG-9) with extrapolations from the current DARPA sponsored design for an operational development model airship (ODM). The impact on the required airship size for obtaining a given level of performance from the airship/surface ship team is examined by varying the number of fire control units (AWG-9s) carried by the airship from 2 to 12. Costs of the proposed system are estimated. Scenarios are developed for convoy missions in a low to moderate ASCM threat environment and for surface battle group operations in a high threat (60, closely spaced ASCMs) environment.
ADA224398
High Altitude Balloon Flight Test of the GRAD Experiment
Descriptive Note: Final patent rept.
Personal Author(s): Hicks, Robert J; Jenkins, David H
Report Date: Apr 1990
Media Count: 1 Page(s)
Descriptors: (U) *DETECTORS, AIMING, GONDOLAS, SUN, BALLOONS, TELEMETER SYSTEMS, ACCURACY, ROTATION
Identifiers: (U) GRAD EXPERIMENT.
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The responsibilities were: (1) Design and construct the gondola which would carry the GRAD experiment, solar and battery power, and appropriate telemetry beneath a balloon. (2) Design and build a Sun sensor which would provide input to a rotator system designed to position the gondola for accurate pointing. (3) Participate in the integrating and testing of all the equipment and systems prior to flight. (rrh)
ADA223298
Multi-Address Digital Command System
Descriptive Note: Environmental research papers (Final) 1984-1987,
Personal Author(s): Laping, H
Report Date: 07 Nov 1989
Media Count: 26 Page(s)
Descriptors: (U) *BALLOONS, TELEMETER SYSTEMS, GROUND LEVEL, DIGITAL SYSTEMS, HIGH FREQUENCY, PAYLOAD, FREQUENCY MODULATION, COMMAND AND CONTROL SYSTEMS, OPERATION, INSTRUMENTATION, COMMUNICATION AND RADIO SYSTEMS, ERROR CORRECTION CODES, ULTRAHIGH FREQUENCY, VERY HIGH FREQUENCY, AMPLITUDE MODULATION, DECODERS, CONTROL, STATIONS
Identifiers: (U) PE62101F, WUGL76591210
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The Model 2A Multi-address Digital Command System can provide 95 commands for transmission to each of 10 addresses in a balloon-borne scientific payload. To prevent false-command activation, the balloon-borne decoder checks the station address, performs a double-scan parity check, and generates a reply code that is telemetered back to ground control for verification before the Execute command is issued. The system is operable with high frequency, very high frequency and ultrahigh frequency communications systems, both AM (amplitude modulation) and FM (frequency modulation). Since 1986 it has been flown routinely on Geophysics Laboratory scientific balloon payloads with error-free operation. (jg)
ADA309826
Long Duration Balloon Technology Survey
Descriptive Note: Final rept. 11 Aug 88-28 Feb 89,
Personal Author(s): Scott, P G; Lew, T M; Wilbeck, J S; Rand, J L; Brezinsky, R H
Report Date: 11 Mar 1989
Media Count: 65 Page(s)
Descriptors: (U) *BALLOONS, HEAT TRANSFER, SCENARIOS, METHODOLOGY, RATIOS, PAYLOAD, FABRICATION, PROTOTYPES, HIGH PRESSURE, SPHERES, LONG RANGE(TIME), GASES, ENDURANCE(GENERAL), FEASIBILITY STUDIES, FLIGHT, HIGH STRENGTH, MATHEMATICAL ANALYSIS, WEIGHT, LIFT, MECHANICAL COMPONENTS, SCIENTIFIC ORGANIZATIONS
Abstract: (U) This feasibility study addresses the design and fabrication of a long endurance balloon vehicle capable of supporting 50 pounds at 120,000 feet for up to one year. The concept makes use of the experience gained by the scientific community over the past two decades in flying smaller payloads for long periods of time. The result of the effort is a prototype balloon which has a better lift to weight ratio than previous designs. This was achieved by the use of a novel shape (multiple intersecting spheres) and the use of a material new in the area of ballooning (Emblem , a biaxially oriented Nylon 6). This film demonstrates very high strength without displaying the susceptibility of prior films to pinholing. Other results of the effort are two analytical tools and specialized fabrication techniques. The analytical tools are a heat transfer model for predicting maximum and minimum supertemperatures of the balloon gas, and mechanical model to design the superpressure balloons for particular flight scenarios.
ADA213574
Feasibility of Lighter-than-Air Vehicles for Strategic Mobility
Descriptive Note: Master's thesis
Personal Author(s): Gasper, Bruce J
Report Date: Apr 1988
Media Count: 153 Page(s)
Descriptors: (U) *MILITARY STRATEGY, *AIRSHIPS, MOBILITY, AIRCRAFT, COST EFFECTIVENESS, THESES, FEASIBILITY STUDIES, CARGO, RIGIDITY
Identifiers: (U) *LIGHTER THAN AIR AIRCRAFT
Abstract: (U) The purpose of this master thesis is to determine whether conventional rigid lighter-than-air vehicles with a range of 8,000 miles are feasible for supporting strategic mobility. The basis for the conventional rigid approach is design efficiency and cost effectiveness, and will be discussed later in this paper. The 8,000 mile range will allow the LTAV to reach the critical regions of the world where U.S. forces may need to be deployed. Characteristics and performance of a proposed LTAV will be compared to current cargo airplanes which will be the standard used to determine feasibility of strategic mobility lighter-than-air vehicles.
ADA183786
A Heat Transfer Model for a Heated Helium Airship
Descriptive Note: Master's thesis
Personal Author(s): Rapert, Ray M
Report Date: Mar 1987
Media Count: 85 Page(s)
Descriptors: (U) *HEAT TRANSFER, *HOT GASES, *AIRSHIPS, COMPUTER PROGRAMS, LINEAR SYSTEMS, CONTROL, INJECTION, RADIATION, MODELS, CONDUCTIVITY, THESES, CONVECTION, FORTRAN, NONLINEAR SYSTEMS, SOLUTIONS(GENERAL), HEATING, ENGINES, HELIUM, EQUATIONS, HEAT, LIFT, STEAM, ENVELOPE(SPACE)
Abstract: (U) Basic heat transfer empirical and analytic equations are applied to a double envelope airship concept which uses heated Helium in the inner envelope to augment and/or control gross lift. The convective and conductive terms lead to a linear system of five equations for the concept airship, with the nonlinear radiation terms included by an iterative solution process. A FORTRAN program, is used to perform the tedious calculations, and graphed results are obtained for the variables of interest. These indicate that the simple use of airship engine exhaust heat will give more than a 30% increase in gross airship lift. Possibly more than 100% increase can be achieved if a 'steam injection' heating system, with associated design problems, is used. (Theses)
ADA167360
Wind Tunnel Test of the Modified Goldschmied Model with Propulsion and Empennage: Analysis of Test Results
Descriptive Note: Final rept. 3 Mar 81-30 Nov 82
Personal Author(s): Goldschmied, Fabio R
Report Date: 01 Feb 1986
Media Count: 115 Page(s)
Descriptors: (U) *JET PROPULSION, *BOUNDARY LAYER CONTROL, *AIRSHIPS, STEADY STATE, RATIOS, VOLUME, EXPERIMENTAL DATA, INTEGRATED SYSTEMS, OPTIMIZATION, MODELS, NEUTRAL, PARAMETERS, TAIL ASSEMBLIES, AERODYNAMIC STABILITY, FLIGHT, COEFFICIENTS, WIND TUNNEL TESTS, AERODYNAMIC DRAG, SLOTS, FANS, TRANSITIONS, LEADING EDGES, VEHICLES, PUMPS, DRAG, BODIES, HYDRODYNAMICS, AIR POWER, THRUST, TEST FACILITIES, REYNOLDS NUMBER, FINS, AERODYNAMICS, SUCTION SLOTS, STATIC STABILITY, AFTERBODIES, PLANFORM, AERONAUTICAL BOOMS, STREAMLINE SHAPE
Identifiers: (U) PROPULSION FANS
Abstract: (U) An extensive test program was carried out in DTNSRDC's 8x10 low-speed wind-tunnel for experimental verification of the integrated hull boundary-layer control/propulsion lighter-than-air design. The 1957 Goldschmied wind-tunnel model was overhauled with a new suction-slot inlet configuration, a suction/ propulsion fan, a new aftbody and a tailboom/empennage assembly. The fan air power coefficient of the operational model with empennage ranged in steady flight from 0.0130 (free transition) to 0.0155 (transition tripped at 10% length) at the volume Reynolds number of two millions. Considerable excess thrust could be generated with an average incremental propulsive efficiency of 72%. As compared to wind-tunnel tests of conventional streamlined bodies with empennage at exactly the same volume Reynolds number, the integrated design offers 50% less equivalent drag for both free and tripped transitions. The empennage provided neutral static stability over the complete test range of 8 degrees; the ratio of total fin planform over volume equivalent was 0.404. It was found that efficient and stable BLC could be achieved only by the combination of Ringloeb cusp at the slot's leading-edge with suction flow and with the presence of the tailboom. The fan (or pump) design is an essential part of the system design: a procedure was developed for determining the optimum fan design parameters from the vehicle's wind-tunnel test data. As an example, a tested NACA axial rotor/stator stage could be employed with 93% adiabatic efficiency for the vehicle with empennage and tripped transition. Keywords: Airships; Aerodynamics; Hydrodynamics; Jet propulsion.
ADA133996
Some Trends in Airship Technology Developments
Personal Author(s): Balis Crema, Luigi; Castellani, Antonio
Report Date: Aug 1983
Media Count: 15 Page(s)
Descriptors: (U) *COMPOSITE MATERIALS, *AIRSHIPS, PERFORMANCE(ENGINEERING), CARBON FIBERS, WEIGHT REDUCTION
Identifiers: (U) LTA(LIGHTER THAN AIR), DIRIGIBLES, NATO FURNISHED
Distribution Statement: Approved for Public Release; Distribution Unlimited.
Abstract: (U) Recent advances in aerospace technology, and in particular the application of new materials and novel structures, have special relevance to the development of dirigibles. This paper demonstrates that significant reductions in structure weight can be achieved through the use of, for example, carbon fibre composites. It goes to show what corresponding improvements in operational performance can be gained.
ADA127553
Polyethylene Free Balloon Design from the Perspectives of User and Designer
Descriptive Note: Final rept.
Personal Author(s): Dwyer, James F
Report Date: 12 Nov 1982
Media Count: 112 Page(s)
Descriptors: (U) *EXPERIMENTAL DESIGN, *RESEARCH MANAGEMENT, *POLYETHYLENE PLASTICS, *BALLOONS, PAYLOAD, PERFORMANCE TESTS, MISSION PROFILES, STRENGTH(MECHANICS), POLYMERIC FILMS, LAUNCHING, USER NEEDS, TAPES, SYSTEMS ANALYSIS, STATISTICAL ANALYSIS, INFLATABLE STRUCTURES, AIR FORCE PLANNING, CONSTRUCTION MATERIALS, BALLOON EQUIPMENT
Identifiers: (U) PE62101F, WUAFGL76591108
Abstract: (U) Those who use large polyethylene balloons for experimental programs are presented with background information on the processes of selecting and designing balloons to meet their respective mission requirements. The effects of payload weight, altitude, duration, and vertical control on both the total payload weight and the balloon size are discussed with respect to these processes. The need to define missions success in terms of realistic requirements is emphasized and a mission planning procedure is proposed. Assumptions and problems in contemporary balloon design are discussed, and design and analysis procedures based on the loads and geometry at the time of launch are developed. Dynamic launch shock is proposed as a criterion for shell thickness, and a model of polyethylene film modulus is developed to account for strain rate and stress and strain relaxation at a launch temperature of 23 degrees C. Computer codes have been written for the processes of balloon selection and balloon design to meet mission requirements. They are intended to be a basis for more efficient, interactive mission planning. Finally, improvements to the balloon design process are proposed and discussed.
ADA120830
Naval Airship Program for Sizing and Performance (NAPSAP), Computer Program Development: Program Update Number 2
Descriptive Note: Final rept.
Personal Author(s): Lancaster, Jon W
Report Date: 01 Oct 1982
Media Count: 77 Page(s)
Descriptors: (U) *COMPUTER PROGRAMS, *PATROL AIRCRAFT, *AIRSHIPS, *COMPUTER AIDED DESIGN, PERFORMANCE(ENGINEERING), NAVAL AIRCRAFT, COAST GUARD SHIPS, CORE STORAGE, NAVAL VESSELS, SIZES(DIMENSIONS), INPUT, COMPUTERIZED SIMULATION, MISSION PROFILES
Identifiers: (U) MARITIME PATROL AIRSHIPS, NAPSAP COMPUTER PROGRAM
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) A computer program called NAPSAP, for Naval Airship Program for Sizing and Performance, performs preliminary vehicle design and performance evaluations for both rigid and non-rigid Lighter Than Air (LTA) vehicles. Program capabilities have been tailored to vehicle sizes and missions currently being investigated as part of the joint U.S. Navy - U.S. Coast Guard Maritime Patrol Airship, MPAS, Program and U.S. Navy Operational Mission Applications. The program has been designed to operate on a minimum of input data (only five cards are necessary) but has the capability to examine the influence of some 40 key parameters. Once the design section of NAPSAP converges on a vehicle which meets the input requirements (such as maximum speed, payload, enduracne, etc.) this vehicle can then be operated against a specified mission profile. Program developments include the addition of more detailed static aerodynamic coefficients, configuration/geometry details, static weight and balance calculations and the capability to analyze mission performance in towing operations in considerable detail. In its present form core memory size is 150K octal words on CD 6600 or 600 K bytes on IBM equipment. Normal run time is less than 4.0 CPU seconds.
ADA113958
The Air-Launched Balloon System (ALBS) Development Program, Phase 2
Descriptive Note: Instrumentation papers
Personal Author(s): Carten, Andrew S , Jr
Report Date: 15 Dec 1981
Media Count: 99 Page(s)
Descriptors: (U) *BALLOONS, *CRYOGENIC STORAGE DEVICES, RECOVERY, DEGRADATION, HEAT EXCHANGERS, FEASIBILITY STUDIES, HIGH ALTITUDE, INFLIGHT, RELEASE MECHANISMS, EXTRACTION, HELIUM, INFLATABLE STRUCTURES, AIR LAUNCHED, REINFORCING MATERIALS, AERIAL DELIVERY, DEWAR FLASKS, RADIO RELAY SYSTEMS, PARACHUTE DESCENTS, INFLATING
Identifiers: (U) ALBS(AIR LAUNCHED BALLOON SYSTEM), PE62101F, WUAFGL76591101
Abstract: (U) The circumstances leading to the second phase of the Air-Launched Balloon System Development Program are described, along with the governing design constraints. Individual component development efforts and system design modifications are described in turn: the procurement and testing of the new dewar, the qualification of the updated cryogenic unit, the redesign of the balloon/parachute interface, the solution of the extraction line recoil problem, and the development of a reliable cryogenic unit recovery system. The complicated command, control, and telemetry subsystem is also described in detail. The results of component tests and a system dress rehearsal system test are summarized. Preparations for two full-scale system tests conducted in 1981 are covered in considerable detail. The results of those tests are presented and the test data are analyzed. It is concluded that the system's air-launch and mid-air inflation techniques are acceptable. The balloon requires structural reinforcements, however, before the system can be said to be fully developed. (Author)
ADA115197
The Lateral Response of an Airship to Turbulence
Descriptive Note: Master's thesis
Personal Author(s): Wrobleski, John J , Jr
Report Date: Dec 1981
Media Count: 151 Page(s)
Descriptors: (U) *TURBULENCE, *ATMOSPHERIC MOTION, *AIRSHIPS, TRANSFER FUNCTIONS, LOADS(FORCES), THESES, NUMERICAL METHODS AND PROCEDURES
Identifiers: (U) LATERAL RESPONSE
Abstract: (U) A method is derived for finding the linear response and loading transfer functions for the lateral aerodynamic case of airship flight through atmospheric turbulence. The functions obtained are in a form that can be applied to the various spectral analysis methods used to predict survivability currently employed by designers. A numerical example using the USS AKRON (ZR-4) is presented. The results show that peak motion response and loading occur when the encountered spectral component has a wavelength equal to the airship length, and that simple feedback of heading angle does not significantly decrease this peak.
ADA112164
Lighter-Than-Air (LTA) Vehicles: A Technical Bibliography
Descriptive Note: Final rept.
Personal Author(s): Bailey, David B; Adams, Richard E
Report Date: 07 Oct 1981
Media Count: 122 Page(s)
Descriptors: (U) *BIBLIOGRAPHIES, *AIRSHIPS, LITERATURE SURVEYS, REPORTS, INDEXES
Identifiers: (U) LTA(LIGHTER THAN AIR), DIRIGIBLES, PE62241N, LPN-A03P-03PA-001B/ F41-411
Abstract: (U) This technological bibliography provides a systematic accounting of Lighter-Than-Air (LTA) documents. This report should enable rapid review of past and present activities for specific individual applications. Both author and subject indices are included.
ADA102575
Twin-Rotor Patrol Airship Flying Model Design Rationale
Descriptive Note: Phase rept.
Personal Author(s): Eney, John A
Report Date: 01 Jun 1981
Media Count: 15 Page(s)
Descriptors: (U) *ROTORS, *AIRSHIPS, STABILITY, ATTITUDE CONTROL SYSTEMS, SCALE MODELS, NEUTRAL, DAMPING, AERODYNAMIC CHARACTERISTICS, TRANSITIONS, AIRCRAFT MODELS, TILT, HOVERING, BUOYANCY, MOORING, PATROL AIRCRAFT
Identifiers: (U) LTA(LIGHTER THAN AIR), TILT ROTORS, TRANSITION FLIGHT, CONTRAROTATING ROTORS, PE62241N, WUDH814
Abstract: (U) To gain experimental data on the controllability of tilt-rotor airships operating near neutral buoyancy, a 32-foot long 1/10 scale flying model is being developed using two contrarotating tilt-rotor representing those on the NASA/Bell XV-15 research aircraft. It is planned to demonstrate controlled hover and transition in an engine - out condition with one rotor stopped to emphasize the natural attitude stability and damping of such vehicles.
ADA088148
Feasibility Study of Applying Laminar Flow Control to an LTA Vehicle
Descriptive Note: Final rept.
Personal Author(s): Warner, Dwight J; Ozgur, Suphi A; Haigh, Wayne W
Report Date: Apr 1980
Media Count: 49 Page(s)
Descriptors: (U) *LAMINAR FLOW, *BOUNDARY LAYER CONTROL, *AIRSHIPS, SURFACE ROUGHNESS, SURFACES, FEASIBILITY STUDIES, HIGH ALTITUDE, AERODYNAMIC DRAG, SOLAR RADIATION, HEAT FLUX, THERMAL INSTABILITY
Identifiers: (U) LIGHTER THAN AIR VEHICLES, PE62241N, WUDH832, LPN-A03P-03PA/001-B/OF41-411-000
Abstract: (U) The feasibility of applying laminar boundary-layer control with body shaping to a high altitude, Lighter-Than-Air vehicle was investigated. Solar- radiation-induced surface heating was shown to have a destabilizing effect on laminar flow and caused the laminar flow to break down on regions of the vehicle surface exposed to high levels of solar radiation. Aerodynamic drag estimates were made for the vehicle. Surface waviness and roughness criteria for achieving laminar flow were determined.
ADA089483
Maritime Patrol Airship Study (MPAS)
Descriptive Note: Final rept.
Personal Author(s): Bailey, David B; Rappoport, Harold K
Report Date: 19 Mar 1980
Media Count: 330 Page(s)
Descriptors: (U) *AIRSHIPS, OPERATIONAL EFFECTIVENESS, FEASIBILITY STUDIES, MISSIONS, LOGISTICS, NAVAL OPERATIONS, LIFE CYCLE COSTS, COAST GUARD, PATROL AIRCRAFT
Identifiers: (U) PE62241N, WUDH814, LPN-A03P-03PA-001B/0F41-411-000
Distribution Statement: Approved for public release; distribution unlimited.
Abstract: (U) The Maritime Patrol Airship Study is an airship system applications study sponsored by the U.S. Navy and U.S. Coast Guard. Eight Major Cost Guard programs are analyzed for cost effective benefits of modern Lighter-Than-Air (LTA) vehicles. Representative script scenarios are developed for the eight programs based on actual Coast Guard mission experience. The scenarios are then used to size conceptual vehicles. In addition to in-house vehicle analysis, two independent efforts for comparative purposes based on the same scenarios were performed by contractor support.
ADA068449
Goodyear Aerospace Conceptual Design Maritime Patrol Airship ZP3G
Descriptive Note: Final rept.
Personal Author(s): Brown, N D
Report Date: 01 Apr 1979
Media Count: 65 Page(s)
Descriptors: (U) *AIRSHIPS, PAYLOAD, COASTAL REGIONS, MISSION PROFILES, PATROLLING, COMMAND AND CONTROL SYSTEMS, WEIGHT, FUEL CONSUMPTION, RANGE(DISTANCE), SEA RESCUES, WATER TRAFFIC, HOVERING, OCEAN SURVEILLANCE, OIL SPILLS, COAST GUARD, OIL POLLUTION CONTAINMENT, AERIAL PROPELLERS, AIRSHIP ENVELOPES, ICE REPORTING
Identifiers: (U) PE62241N, WUDH814
Abstract: (U) A Conceptual design of a modern technology airship with precision hover capability for use in maritime patrol is described. The size and major characteristics are established by a series of United States Coast Guard missions set forth by the contracting agency.
ADA070131
Maritime Patrol Airship Concept Study
Descriptive Note: Final rept. 18 Apr-31 Oct 78
Personal Author(s): Bell, James C; Marketos, James D; Topping, A D
Report Date: 16 Nov 1978
Media Count: 242 Page(s)
Descriptors: (U) *AIRSHIPS, COMPUTERIZED SIMULATION, OPTIMIZATION, COASTAL REGIONS, PARAMETRIC ANALYSIS, COMPUTER AIDED DESIGN, SIZES(DIMENSIONS), MISSION PROFILES, WEIGHT, TAKEOFF, TRADE OFF ANALYSIS, LIFT, COAST GUARD, PATROL AIRCRAFT
Identifiers: (U) Lighter Than Air Craft
Abstract: (U) Results of a preliminary conceptual parametric design study for a maritime patrol airship to be used by the U.S. Coast Guard or Navy are presented. Eight different Coast Guard mission profiles are considered, and an optimum airship point design is developed for each. The report discusses mission requirements, airship operational requirements, the conceptual design approach, and the parametric design study which uses a computer program to assist in optimizing the critical parameters for each airship mission design. The study includes airship sizes from 220,000 cu ft (18,000 lb vertical takeoff weight) to 3,000,000 cu ft (230,000 lb vertical takeoff weight). Results show the unique features of the Bell unballasted, reversible thrust airship design and the critical need for design optimization, owing to the sensitivity of the airship design parameters. The computer design program shows airship conceptual differences and design trends rather than absolute design configurations, since it uses the preliminary subsystem weight relationships developed for recent airship parametric studies. Although the study design trends should remain valid, additional studies are recommended to establish better subsystem weight estimates and to incorporate life-cycle costing.
ADA058237
Assessment of Selected Lighter-Than-Air Vehicles for Mission Tasks of the U.S. Coast Guard
Descriptive Note: Final rept. Jun 1975-Aug 1977
Personal Author(s): Beatty, Ralph E , Jr; Linnel, Richard D
Report Date: May 1978
Media Count: 788 Page(s)
Descriptors: (U) *AIRSHIPS, MAINTENANCE, COMPUTERIZED SIMULATION, COST EFFECTIVENESS, COST ANALYSIS, PATROLLING, MISSIONS, ENERGY CONSUMPTION, LAW ENFORCEMENT, SEARCH AND RESCUE, OCEAN SURVEILLANCE, COAST GUARD
Identifiers: (U) *LIGHTER THAN AIR VEHICLES, BLIMPS, DIRIGIBLES, DESIGN
Abstract: (U) This study examines the role of lighter-than-air (LTA) vehicles in performing several United States Coast Guard missions including enforcement of laws and treaties, marine environmental protection, and search and rescue. Reconnaissance tasks required for surveillance of the 200-mile coastal economic zones are emphasized. Before assessing how well LTA vehicles performed these missions, basic lighter-than-air craft needed to be designed. The study develops a conceptual design model to estimate the characteristics of a family of modern airships with varing range and speed. All the LTAs considered are semibuoyant hybrids that use aerodynamic lift to increase fuel capacity. The effect of different design features (such as envelope material, engine type, and design altitude) are also investigated. The family of LTAs is compared with existing and proposed Coast Guard vehicles that were previously examined in the CNA study (no. 1061) of hydrofoils for the Fisheries Law Enforcement mission of the U.S. Coast Guard. The comparisons, based on cost and effectiveness in patrol tasks, are made by evaluating miles and square miles on station per dollar. For trail tasks, the measure used to compare vehicles is hours on station per dollar. Some comparison of how efficiently vehicles consumed fuel is also made.
ADA057610
Flight Tests of the Air-Launched Balloon System (ALBS) Prototype Model
Descriptive Note: Final rept.
Personal Author(s): Carten, Andrew S , Jr
Report Date: 23 Mar 1978
Media Count: 133 Page(s)
Descriptors: (U) *BALLOONS, *PARACHUTE DESCENTS, FLIGHT TESTING, DEPLOYMENT, AIRBORNE, DROP TESTS, INFLATABLE STRUCTURES, AIR LAUNCHED, CRYOGENICS, TACTICAL COMMUNICATIONS, AERIAL DELIVERY, DROGUE PARACHUTES, RADIO RELAY SYSTEMS
Identifiers: (U) ALBS(AIR LAUNCHED BALLOON SYSTEM), AIR LAUNCHED BALLOON SYSTEM, PE62101F, WUAFGL66651101, WUAFGLILIR5H01
Abstract: (U) The requirements for the Air Launched Balloon System (ALBS) development program and the highlights of that program, prior to the flight test phase, are presented. The rationale behind an ambitious ALBS parachute subsystem test flight series, using C-130 aircraft, at the National Parachute Test Range is given, along with the initial system configuration chosen for that series. The test-demonstrated inadequacy of the 32-ft drogue chute is documented. The successes achieved subsequently in flights with a 28-ft drogue chute (in combination with the 42-ft main chute) are described, both for tests employing a dummy balloon and for later tests in which a real balloon was used. Attempts at partial balloon inflation at the NPTR are discussed. The unsolved parachute coning problem is also described, along with tests aimed at its solution. Planning and preflight preparations for the January 1978 balloon drop test over the White Sands Missile Range are covered in considerable detail. The abortive launch of that flight is related and an analysis of the reasons for the flight failure is presented. Five (5) appendices are included with supporting calculations.
ADA047812
The military airship; a Bibliography
Descriptive Note: Special bibliography
Personal Author(s): Miller, Lester L , Jr
Report Date: 15 Dec 1977
Media Count: 14 Page(s)
Descriptors: (U) *BALLOONS, SCHOOLS, ARMY TRAINING, LITERATURE SURVEYS, MILITARY EQUIPMENT, BIBLIOGRAPHIES, MILITARY APPLICATIONS, LIBRARIES, ARTILLERY, PERIODICALS, BOOKS, AIRSHIPS
Abstract: (U) Morris Swett library holdings on the subject of the military balloon are covered in this survey.
ADA045315
Aerodynamics and Hovering Control of LTA Vehicles
Descriptive Note: Final rept.
Personal Author(s): Putman, W F; Maughmer, M; Curtiss, H C , Jr; Traybar, J J
Report Date: May 1977
Media Count: 155 Page(s)
Descriptors: (U) *AERODYNAMIC CONFIGURATIONS, *AIRSHIPS, PARAMETRIC ANALYSIS, AERODYNAMIC STABILITY, AERODYNAMIC CHARACTERISTICS, DELTA WINGS, AERODYNAMIC LIFT, HOVERING, BOUNDARY LAYER CONTROL, DRAG REDUCTION, BODIES OF REVOLUTION, AEROSTATICS
Abstract: (U) Recent U.S. Navy interest in air vehicles for application to advanced naval missions has pointed out a need for technology development in certain areas to support parametric and point design studies in the Advanced Naval Vehicle Concepts Evaluation (ANVCE) program. Among those technologies requiring study were the aerodynamics and precision hover control characteristics of Lighter-Than-Air (LTA) vehicles. LTA, or buoyant assisted lift, vehicles offer potentially significant increases in on-station endurance over conventional aircraft. To evaluate fully this potential, however, it is important to have a sound aerodynamic description of these aircraft that can be relied upon to give accurate representations of their performance, stability and control requirements. The present study is intended to provide a basis for the aerodynamic characterization of LTA vehicles suited to parametric studies, point design and even preliminary design efforts. The study employs combinations of applicable theory, experiment and empiricisms to represent the aerodynamic characteristics of conventional airship (body-of-revolution) and delta shapes, the latter shape having applicability to hybrid aircraft utilizing both aerodynamic and aerostatic lift. Additionally, the potential of boundary layer control for drag reduction in conventional airships is reviewed and the basic aspects of hovering control of LTA vehicles are developed. (Author)
ADA081353
Structures Technology for Lighter-Than-Air Vehicles
Descriptive Note: Technical memo.
Personal Author(s): Hess, T E
Report Date: 02 Mar 1977
Media Count: 34 Page(s)
Descriptors: (U) *STRUCTURAL ANALYSIS, *STRUCTURES, *AIRSHIPS, MATHEMATICAL MODELS, AIRCRAFT, GRAPHS, AIRFRAMES, DIAGRAMS, SANDWICH CONSTRUCTION, STRUCTURAL ENGINEERING
Identifiers: (U) ANVCE(ADVANCED NAVAL VEHICLE CONCEPTS EVALUATION)
Abstract: (U) This technical memorandum documents the work performed in the area of airship structures technology in support of the Advanced Navy Vehicle Concepts Evaluation Program. This work provides an assessment of contemporary rigid airship structural design technology and recommendations for future work. It was concluded that modern airship structures will be significantly more efficient than historical designs, and that the most attractive concepts for achieving these improvements are the geodetic design, the modernized versions of the Akron/Macon construction as was used in the ANVCE point designs, and the sandwich structure for very large sizes.
ADA036248
Balloon Command-Control
Descriptive Note: Final rept. 1 Aug 75-31 Jul 76
Personal Author(s): Williamson, P R
Report Date: 07 Jan 1977
Media Count: 24 Page(s)
Descriptors: (U) *COMMAND AND CONTROL SYSTEMS, *BALLOONS, FLIGHT TESTING, MODIFICATION, TRANSMITTER RECEIVERS, DECODERS, TELEMETER SYSTEMS, FIRING CIRCUITS, PHASE LOCKED COMMUNICATIONS
Identifiers: (U) Flight termination systems, WUNR211185, PE61153N
Abstract: (U) Testing and modification of a low-cost expendable flight termination device for small balloon operators. This is a tonal control transmitter/receiver system using phase-locked loop circuitry to insure safe interference free operation. Design circuitry is included in this report.
ADA012292
POBAL-S, The Analysis and Design of a High Altitude Airship
Descriptive Note: Final rept. Oct 1972-Mar 1975
Personal Author(s): Beemer, Jack D; Parsons, Roger R; Rueter, Loren L; Seuferer, Paul A; Swiden, LaDell R
Report Date: 15 Feb 1975
Media Count: 183 Page(s)
Descriptors: (U) *AIRSHIPS, *AIRSHIP ENVELOPES, COMPUTER PROGRAMS, FUEL CELLS, AUTOMATIC PILOTS, BALLOONS, TETHERING, AERIAL PROPELLERS, GONDOLAS
Identifiers: (U) POBAL-S AIRSHIPS
Abstract: (U) An engineering analysis and development effort has been executed to design a superpressure airship, POBAL-S, capable of station keeping at an altitude of 21 kilometers for a duration of 7 days while supporting a payload weighing 890 newtons and requiring 500 watts of electrical power. A detailed parametric trade-off between various power sources and other design choices was performed. The computer program used to accomplish this analysis is described and many results are presented. The system concept which resulted was a fuel cell powered, propeller driven airship controlled by an on-board autopilot with basic commands telemetered from a ground control station. Design of the balloon, power train, gimbaled propeller assembly, and electronic/electrical systems is presented. Flight operations for launch and recovery are discussed.
ADA396439
Proceedings of the Interagency Workshop on Lighter than Air Vehicles
Personal Author(s): Vittek, Joseph F
Report Date: Jan 1975
Media Count: 697 Page(s)
Descriptors: (U) *AIRSHIPS, SYMPOSIA, ECONOMIC ANALYSIS, COST EFFECTIVENESS, AIR TRANSPORTATION, AIRCRAFT DESIGN
ADB001454
Blast Simulation with Balloons Containing Detonable Gas
Descriptive Note: Final technical rept.,
Personal Author(s): Fields, Stephen F; Fugelso, Leif E;
Report Date: 11 Dec 1974
Media Count: 60 Page(s)
Descriptors: (U) *BLAST, *BALLOONS, NUCLEAR EXPLOSIONS, SIMULATION, AIR, SHOCK WAVES, FIELD TESTS, INTENSITY, OVERPRESSURE, HYDROGEN, GASES, MIXTURES, TIME, CHEMICAL COMPOSITION, OXYGEN, CYLINDRICAL BODIES, THERMOCHEMISTRY, PRESSURE, HIGH ALTITUDE, METHANE, ARRIVAL, SEA LEVEL, WAVEFRONTS, DETONATIONS, HEIGHT OF BURST, PROPANE, TETHERING, HEMISPHERICAL SHELLS
Identifiers: (U) GAS DETONATIONS, PRESSURE SIGNATURES, DETONABLE GAS, DISTANT PLAIN OPERATION.
Abstract: (U) This report summarizes the experimental data on air blast generation by detonable gas in balloons from various projects conducted by the staff of the General American Research Division for the Defense Nuclear Agency. Blast data, including peak overpressures, shock wave arrival times, positive phase durations and positive phase overpressure impulses, were gathered from these sources and are condensed and presented, together with descriptions of the balloons and the field operations. (Author)
ADA008489
Proceedings (Supplement), AFCRL Scientific Balloon Symposium (8th) 30 September to 3 October 1974
Descriptive Note: Biennial rept.
Personal Author(s): Carten, Andrew S , Jr
Report Date: 02 Dec 1974
Media Count: 282 Page(s)
Descriptors: (U) *BALLOONS, MATERIALS, HOT GASES, INFLATABLE STRUCTURES, AERODYNAMICS, TETHERING, METEOROLOGICAL BALLOONS, TELEMETER SYSTEMS, MECHANICAL CABLES
Identifiers: (U) POWERED BALLOONS, TETHERED BALLOONS, ENGINEERING DESIGN
Abstract: (U) This publication, in conjunction with the main volume, AFCRL-TR-74- 0393, dated 21 August 1974, contains the papers presented at the Eighth AFCRL Scientific Balloon Symposium, 30 September to 3 October 1974, held at Hyannis, MA. The papers are grouped in accordance with the five symposium sessions: Powered Balloons, Tethered Balloons, Free Balloon Technology, Balloon-Borne Experiments, and Special Applications.
ADA003344
An Investigation of the Applicability of High Altitude, Lighter-Than-Air (LTA) Vehicles to the Tactical Communications Relay Problem
Descriptive Note: Instrumentation papers
Personal Author(s): Carten, Andrew S , Jr
Report Date: 20 Aug 1974
Media Count: 62 Page(s)
Descriptors: (U) *BALLOONS, *RADIO RELAY SYSTEMS, AIRBORNE, PLATFORMS, HIGH ALTITUDE, AIR LAUNCHED, TACTICAL COMMUNICATIONS, FREE FLIGHT
Identifiers: (U) SEEK STAR PROGRAM, HASPA PROGRAM
Abstract: (U) The various types of large balloon systems in use today, or under development, are examined with regard to potential use in the SEEK STAR multi- mode transmission system. Tethered balloons are shown to satisfy many communications applications, but to lack the altitude capability needed by SEEK STAR. The powered free balloon is seen to offer the best potential. The AFCRL powered balloon system, POBAL, is described and test results are presented. Its successor system, POBAL-S, is also described and evaluated. The demise of the POBAL-S development at AFCRL and the reappearance of the concept under the Navy's HASPA program is discussed and the applicability of HASPA to the SEEK STAR mission is evaluated. It is shown that, although the HASPA can theoretically satisfy or exceed all SEEK STAR needs, a delay of about three years must be endured before definitive results are available. Free-flying (that is, unpowered) balloon systems, both zero-pressure and superpressure, are evaluated and the advantages of the ground-launched and air-launched systems are pointed out. A status report on the Air-Launched Balloon System (ALBS) development is given.
AD0782107
Balloon Marker
Descriptive Note: Final rept.
Personal Author(s): Wood, Benjamin F
Report Date: Jun 1974
Media Count: 17 Page(s)
Descriptors: (U) *BALLOONS, *NIGHT WARFARE, *MARKERS, INFLATING, TETHERING, CARTRIDGES, STROBOSCOPES, WEIGHT, RELIABILITY, HYDROGEN, FIELD EQUIPMENT
Identifiers: (U) *BALLOON MARKER SYSTEMS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) A tethered balloon position marker was developed for use by troops operating in heavy forests. The system consists of a ten cubic-foot aerodynamically shaped balloon, two solid chemical hydrogen generator inflation cartridges, a strobe light for night time use, a tether line, and a carrying case. The system is an improved version of a system developed earlier which used a spherical balloon and a cylinder of compressed helium for inflation. The improved balloon shape provides better vertical flying qualities, and the hydrogen generator reduces weight. A battery with improved shelf life is used in the strobe light. An evaluation quantity of the marker systems was furnished to user units for evaluation; the results were not available for inclusion in the report.
AD0775463
Improved Elevated Site Marker
Descriptive Note: Final rept. Apr 1970-Oct 1973
Personal Author(s): Wood, Benjamin F
Report Date: Dec 1973
Media Count: 47 Page(s)
Descriptors: (U) *BALLOONS, *MARKERS, VISIBILITY, TARGET DESIGNATORS, CLOSE SUPPORT, AERIAL RECONNAISSANCE, AIR DROP OPERATIONS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) There has been a continuing need for an efficient position marking device for use in heavily forested areas by personnel of all three services. The position marking device must enable personnel on the ground, under a heavily forested canopy, to make known their precise location to friendly and support aircraft overhead. The needs of the three services are similar, but vary according to the function of each. The Naval Air Arm and Air Force require a fast acting, lightweight device that can mark the position of downed airmen for air rescue teams. The Army and Marine Corps depend upon position marking for medical evacuation, resupply and direct fire support and, therefore, require a longer lasting marker. Speed of deployment, while valuable, is not as essential to ground units as for the downed airmen. The development described in the report is of a system designed for ground units and is not directly applicable to the downed airmen problem.
AD0911292
MK82 BALLUTE Retarder System Structural Qualifications
Descriptive Note: Final rept. 16 Jun-31 Aug 1972
Personal Author(s): Robinson, Wiley J
Report Date: May 1973
Media Count: 57 Page(s)
Descriptors: (U) *PARACHUTES, *GENERAL PURPOSE BOMBS, STRESSES, FLIGHT TESTING, VIBRATION, STRUCTURAL PROPERTIES, TENSILE PROPERTIES, CALIBRATION, DECELERATION, FREE FALL MISSILES, PARACHUTE FABRICS, BOMB FINS, BALLOONS, CAPTIVE TESTS, INFLATABLE STRUCTURES, BENDING, INSTALLATION, SHEAR STRESSES, AERODYNAMIC LOADING, STRAIN GAGES, DROP TESTS
Identifiers: (U) *BALLUTES, *MARK-82 BOMBS(500-LB.)., BOMB RETARDATION SYSTEMS, DECELERATORS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) When the Mk82 ballute retarder system was received from the contractor to be qualified for flight testing, certain areas of analyses usually required had been omitted from the data package. This report details the completed in-house design work and the ground testing necessary to verify the analyses and to qualify the retarder system.
AD0767582
Proceedings of the AFCRL Scientific Balloon Symposium (7th), Held at Portsmouth, New Hampshire, in September 1972
Descriptive Note: Special repts.
Personal Author(s): Nolan, George F
Report Date: 03 Jan 1973
Media Count: 486 Page(s)
Descriptors: (U) *SYMPOSIA, *BALLOONS, PAYLOAD, FLIGHT PATHS, TEXTILES, ATMOSPHERIC SOUNDING, CORDAGE, MECHANICAL CABLES, NONPOWERED FLIGHT
Identifiers: (U) BALLOONS, TETHERING, DESIGN
Abstract: (U) The report contains the papers presented at the Seventh AFCRL Scientific Balloon Symposium held in September 1972. The papers were presented in three sessions: Tethered and powered balloons, balloon-borne experiments, and instrumentation and balloon technology. In the area of tethered balloons, papers were presented on cables, drag and stability characteristics, hull design and analysis, and the results of scientific experiments using tethered balloons as sensor platforms. Papers were presented on a powered spherical balloon and a survey of possible power sources for use by this system. Presentations during the balloon-borne experiments and instrumentation session included manned balloon flights, precision pointing and control platforms and instrumentation, recovery parachute performance, gondola motion analyses, a balloon radar altimeter, and an overview of French scientific ballooning activities. During the balloon technology session a review was made of the flight results and performance of balloons with volumes in excess of 20 million cubic feet, shape and stress analysis of both nonreinforced and reinforced materials, and fabric tinting to increase solar absorptivity.
AD0733892
United States Air Force History. An Annotated Bibliography
Personal Author(s): Cresswell, Mary Ann; Berger, Carl
Report Date: 01 Oct 1971
Media Count: 110 Page(s)
Descriptors: (U) *AIR FORCE, *BIBLIOGRAPHIES, AERIAL WARFARE, HISTORY, AEROSPACE CRAFT, PICTURES, AVIATION PERSONNEL, GEOGRAPHY, AIRSHIPS, BALLOONS
Identifiers: (U) *ANNOTATED BIBLIOGRAPHIES, REVIEWS, ARMED FORCES OPERATIONS, AIRPLANES, JET PLANES
Abstract: (U) Reports of American aircraft events at Fort Myer, Virginia, in 1908 and published extensively in the United States and Europe, marked the beginning of an immense flood of literature about military aviation and aviators, and air deeds in war and peace. This annotated bibliography on U. S. Air Force history is a sampling of that literature, prepared primarily for the student and scholar.
AD0725708
Definition of Tethered Balloon Systems
Descriptive Note: Scientific rept. no. 1
Personal Author(s): Myers, Philip F; Vorachek, Jerome J
Report Date: 31 Mar 1971
Media Count: 97 Page(s)
Descriptors: (U) *BALLOONS, AERODYNAMIC LOADING, WEIGHT, MECHANICAL CABLES, BALLOON EQUIPMENT, MASS, AERODYNAMIC CHARACTERISTICS
Identifiers: (U) PE62101F, WUAFCRL76590601
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) An analytical investigation of the behavior of tethered balloons is in progress. The report covers balloon system definition for three design altitudes, 5,000, 10,000, and 20,000 feet above sea level. Three balloon shapes being considered are the Vee-Balloon, the Bateman and Jones (BJ) barrage balloon, and Goodyear Aerospace Corporation Model No. 1649 single-hull balloon. Tether constructions are Columbian Rope Company's NOLARO utilizing prestretched polyester filaments, and 9US Steel Corporation's Amgal-Monitor AA wire ropes. Eight specific balloon/cable combinations are defined, covering the three design altitudes. Total cable curve, downwind displacement, etc., have been calculated by computer program and results are tabulated. Aerodynamic characteristics, weight, inertias, and dynamic characteristics are developed and tabulated.
AD0864891
Aerial Very Heavy Lift Concepts for the 1990 Army. Volume 3. Academic and Industrial Presentations
Descriptive Note: Final rept.
Report Date: Nov 1969
Media Count: 200 Page(s)
Descriptors: (U) *VERTICAL TAKEOFF AIRCRAFT, *AIRSHIPS, VELOCITY, ROTARY WINGS, VIBRATION, CONTROL SYSTEMS, LOADS(FORCES), HELICOPTERS, WEIGHT, POWER EQUIPMENT, NOISE, RANGE(DISTANCE), ARMY OPERATIONS, TRANSPORT AIRCRAFT, BUOYANCY
Identifiers: (U) AERIAL HEAVY LIFT, LIGHTER THAN AIR VEHICLES, TIP DRIVEN HELICOPTERS
Abstract: (U) The document covers the technical feasibility of developing a very heavy aerial lift vehicle to be operational by 1990. The mission spectrum for such a vehicle was assumed similar to the proposed QMR for the heavy-lift helicopter except that the payload requirement was increased to approximately 50-60 tons. Shaft-driven and tip-driven helicopter concepts were given major consideration. Power-plant and transmission development and problems relating to subsystems, such as load handling and control, are treated. Vertical take-off and landing (VTOL) concepts that are not high disc loading are discussed.
AD0862287
Aerial Very Heavy Lift Concepts for the 1990 Army. Volume 1. Basic Report
Descriptive Note: Final rept.
Report Date: Nov 1969
Media Count: 43 Page(s)
Descriptors: (U) *ARMY OPERATIONS, *VERTICAL TAKEOFF AIRCRAFT, CONTROL SYSTEMS, LOADS(FORCES), PROBLEM SOLVING, HELICOPTERS, PLANNING, LOGISTICS, DISKS, AIRSHIPS, TURBOJET ENGINES, STABILIZATION SYSTEMS, DRIVE SHAFTS, CYCLOIDAL PROPELLERS, WIRE GUIDANCE
Identifiers: (U) LIGHTER THAN AIR VEHICLES, TIP DRIVEN HELICOPTERS, VERY HEAVY LIFT CONCEPTS
Abstract: (U) An ad hoc working group (AHWG) was convened by the US Army Advanced Materiel Concepts Agency (AMCA) to consider the technical feasibility of developing a very heavy aerial lift vehicle to be operational by 1990. The mission spectrum for such a vehicle was assumed similar to the proposed QMR for the heavy-lift helicopter except for the payload requirement which was increased in these considerations to approximately 50-60 tons. Shaft-driven and tip-driven helicopter concepts were given major consideration. Powerplant and transmission development and problems relating to subsystems, such as load handling and control, were treated. Vertical take-off and landing (VTOL) concepts that were not high disc loading were discussed. Short take-off and landing (STOL) was not considered.
AD0833958
PARAMETRIC STUDY OF DYNAMIC LIFT AEROSTATS FOR FUTURE NAVAL MISSIONS
Descriptive Note: Technical rept.
Report Date: 31 Jan 1968
Media Count: 343 Page(s)
Descriptors: (U) *AIRSHIPS, VELOCITY, STABILITY, PERFORMANCE(ENGINEERING), STRUCTURAL PROPERTIES, VULNERABILITY, FEASIBILITY STUDIES, NAVAL AIRCRAFT, MATHEMATICAL PREDICTION, PLANNING, HELIUM, LIFT, ALTITUDE, TEXTILES, ENGINE NACELLES, AEROSTATICS, AIRSHIP ENVELOPES
Identifiers: (U) GRAPHS(CHARTS)
Abstract: (U) This investigation is a parametric performance study of the capabilities of future large airships into the 1980 period. It is a considerable extrapolation from past actual constructions as to physical size and gross weight, speeds, and altitudes. Previous airships reached weights of 400,000 pounds, speeds of 80 knots, and normal altitudes of 5-10,000 feet. This study covers gross weights to 1,500,000 pounds, speeds to 210 knots, and design altitudes of 20,000 feet. It also examines the possibilities of a combined static-dynamic lift configuration as contrasted with the all-state lift airship of the past.
AD0665853
AFCRL SPACE SCIENCE RESEARCH DURING 1967 (ANNUAL REPORT TO COSPAR)
Descriptive Note: Special repts. no. 70, 1 Jan-31 Dec 1967
Personal Author(s): McIntyre, A
Report Date: Jan 1968
Media Count: 53 Page(s)
Descriptors: (U) *AIR FORCE RESEARCH, LUNAR ENVIRONMENTS, ARTIFICIAL SATELLITES, METEOROLOGY, LABORATORIES, SOLAR RADIATION, RESEARCH MANAGEMENT, SPACE FLIGHT, RADIOFREQUENCY INTERFERENCE, AIR MASS ANALYSIS, SOUNDING ROCKETS, BALLOONS, IONOSPHERIC PROPAGATION, SPECTROPHOTOMETERS, GEODESICS, BLACKOUT(PROPAGATION), METEORITES, ATMOSPHERICS, REENTRY VEHICLES, MAGNETIC FIELDS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) A summary of the space science organization and facilities of Air Force Cambridge Research Laboratories (AFCRL); its international activities in space science; rockets, satellites, and balloons launched; results of experiments associated with the moon, planets, micrometeoroids, solar physics, energetic particles and magnetic fields, upper atmosphere physics, meteorology, geodesy, and terrestrial photography; planned research in 1968; and a space science research related bibliography are included. The definition of space science for the purpose of this report is limited to in-situ observations and measurements using the broad definition of space.
AD0666446
FLIGHT CONTROL SYSTEMS AND LAUNCHING TECHNIQUES FOR AIR BALLAST SYSTEMS
Descriptive Note: Technical note
Personal Author(s): Davidson, Jr, Allen R
Report Date: 06 Nov 1967
Media Count: 79 Page(s)
Descriptors: (U) *FLIGHT CONTROL SYSTEMS, *BALLOONS, STRESSES, AERODYNAMIC CONFIGURATIONS, EXHAUST VALVES, OPERATION, POWER SUPPLIES, HELIUM, PRESSURIZATION, ALTITUDE, BALLAST, GAS FLOW, DIURNAL VARIATIONS, INFLATABLE STRUCTURES, HANDLING, MONITORS, INSTRUMENTATION, LAUNCHING, PERFORMANCE(ENGINEERING), TEMPERATURE, PAYLOAD
Identifiers: (U) SUNRISE, SUNSET
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) This report examines some of the more practical aspects in the application of air ballast systems to the control of free-flight balloons. Each type of air ballast system, as defined in Scientific Report No. 1, is analyzed for the cost, availability of materials, components, and instrumentation required. In addition, for each type of air ballast system deemed feasible, the possible flight system configurations, associated launching problems, and methods to solve the problems are investigated. It is the conclusion of this report that most air ballast systems can be instrumented and flown with conventional or off-the-shelf components and equipment. Systems using very large payloads are more difficult to handle and launch than smaller payload systems and probably will require some development in new launching techniques and associated equipment.
AD0654744
THERMAL RADIATION PROPERTIES OF SOME POLYMER BALLOON FABRICS
Descriptive Note: Technical rept.
Personal Author(s): Dingwell, I W
Report Date: Jun 1967
Media Count: 53 Page(s)
Descriptors: (U) *POLYESTER PLASTICS, *POLYETHYLENE PLASTICS, *TEXTILES, ABSORPTION, REINFORCED PLASTICS, EMISSIVITY, BALLOONS, REFLECTION, FILMS, COMPOSITE MATERIALS, THERMAL RADIATION
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) As the absorption of solar and earth atmosphere thermal radiation is an important factor in the vertical motion of high altitude balloons, the thermal radiation properties of the thin films that compose balloon fabrics must be determined. This report presents the results of property measurements made with spectrophotometer, emissometer, and thermal radiation measuring equipment. The films considered were polyethylenes, mylar composites and other fabrics.
AD0819915
AERODYNAMIC DEPLOYABLE DECELERATOR PERFORMANCE-EVALUATION PROGRAM PHASE 2
Descriptive Note: Final rept. Apr 1964-Apr 1967
Personal Author(s): Bloetscher, Frederick
Report Date: Jun 1967
Media Count: 219 Page(s)
Descriptors: (U) *DROGUE PARACHUTES, *BALLOONS, AERODYNAMIC CONFIGURATIONS, AERODYNAMIC LOADING, AERODYNAMIC HEATING, STRESSES, HIGH ALTITUDE, SUPERSONIC CHARACTERISTICS, DRAG, INFLATABLE STRUCTURES, WIND TUNNEL MODELS, PARACHUTE FABRICS, METALLIC TEXTILES, TEXTILES, MANUFACTURING, HYPERSONIC CHARACTERISTICS, WIND TUNNELS, PERFORMANCE(ENGINEERING), DECELERATION
Identifiers: (U) BALLUTES, DECELERATORS, PARACHUTE CANOPIES
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The Aerodynamic Deployable Decelerator Performance-Evaluation Program (ADDPEP) aims to advance the state of the art by developing the most effective analytical and empirical techniques for designing aerodynamic deployable decelerators and for evaluating these engineering techniques through wind-tunnel and free-flight tests. During ADDPEP Phase 2, two types of decelerators were investigated: large reefed supersonic parachutes and raminflated balloon-type BALLUTEs. The areas investigated included analytical and engineering design, material capabilities, fabrication techniques, and wind-tunnel and free-flight tests. Free-flight tests were performed on a hemisflo parachute having a nominal 16-ft-diameter canopy, a 10-percent extended skirt, and a 14-percent porosity. This design was tested for 200,000-lb opening loads, deployment Mach numbers were 1.50, 1.63, and 1.84 at altitudes of 13,700, 15,500, and 10,500 ft, respectively. The results confirmed that this parachute has excellent aerodynamic characteristics and adequate strength. Five-foot-diameter BALLUTEs, both textile and metal, were fabricated. These were designed for a broad spectrum of deployment conditions ranging from Mach 2.7 at 73,000 ft to Mach 10 at 225,000 ft. The textile BALLUTEs were wind-tunnel and free-flight tested; the metal BALLUTEs were wind-tunnel tested only. Flight tests were limited to Mach 9.7, and wind-tunnel tests to Mach 3. The flight test data supported wind-tunnel data, which indicated that excellent stability and structurally adequate designs can be attained with five-foot-diameter BALLUTEs.
AD0659400
HIGH ALTITUDE RADIO RELAY SYSTEMS
Descriptive Note: Semiannual rept. Aug 1966-Feb 1967
Personal Author(s): Fales, David; Lorence, Robert J; Hauptman, Robert; Hesse, George L; Gaze, Ralph H
Report Date: May 1967
Media Count: 323 Page(s)
Descriptors: (U) *RADIO EQUIPMENT, *FLYING PLATFORMS, *RADIO RELAY SYSTEMS, MILITARY REQUIREMENTS, AIRCRAFT, COST EFFECTIVENESS, AIRBORNE, RELIABILITY, HELICOPTERS, TACTICAL WARFARE, RADIO TRANSMISSION, BALLOONS, RADIO REPEATERS
Identifiers: (U) AGILE PROJECT
Abstract: (U) Theoretical and analytical investigations are aimed at determining the key characteristics and parameters of a system to enable the use of military communications equipment over difficult paths. The technique being investigated is the use of a radio relay installed in a high altitude platform, for the purpose of extending the range of remote area radio communications. The operational parameters considered were: traffic, transmission range, terrain, foliage, frequency range, modulation, and types of relay capabilities. The equipment parameters considered were: relay control, transmission modes, size and weight, radio frequency power levels, receiver sensitivities, power requirements, operational life, interference, jamming, platform performance, platform payloads, compatibility, basing, availability, and costs. The goal was to define the best relay-platform configurations for extending jungle communications ranges over difficult terrain. Within this context, the effort was one of synthesis, study, and selection of appropriate configurations, finalizing in a system design plan for implementation of the selected systems.
AD0803766
SKYHOOK CHURCHILL 1966
Descriptive Note: Final rept.
Personal Author(s): White, Paul S
Report Date: 01 Nov 1966
Media Count: 386 Page(s)
Descriptors: (U) *METEOROLOGICAL BALLOONS, RECOVERY, PAYLOAD, PERFORMANCE(ENGINEERING), SCHEDULING, HIGH ALTITUDE, LAUNCHING, INSTRUMENTATION, BAROMETRIC PRESSURE, HANDLING, FLIGHT PATHS, GROUND SUPPORT EQUIPMENT, OPTICAL TRACKING, UPPER ATMOSPHERE, BALLOONS, BALLOON EQUIPMENT
Identifiers: (U) SKYHOOK BALLOONS
Abstract: (U) This report describes high altitude balloon flights, equipment used, altitude and trajectory data, and an analysis, where applicable, of all program functions. Conclusions and recommendations for future programs are included.
ADA400692
Preliminary Analytical Investigation of Booster Recovery by Use of a Hot-Air Balloon for Both Deceleration and Final Recovery
Descriptive Note: Technical note
Personal Author(s): Scher, Stanley H; Dunavant, James C; Young, Irene G
Report Date: Oct 1966
Media Count: 44 Page(s)
Descriptors: (U) *RECOVERABLE BOOSTER ENGINES, DECELERATION, BUOYANCY, BALLOONS
Identifiers: (U) AMPTIAC COLLECTION
Abstract: (U) An analytical investigation has been made of the flight mechanics, aerodynamic heating, and system weight for a booster recovery system in which a single large balloon is used as both a decelerator for reentry and a buoyant device for final recovery. The balloon was assumed to use ram air for maintenance of inflation and to use burners to heat the internal air to provide buoyancy in the atmosphere at low altitude for final recovery. The specific application of the system investigated was for the recovery of the Saturn S-1C booster. The study indicated that a balloon made of conventional glass-fiber cloth, treated by a relatively inexpensive process to provide added heat resistance, could withstand the conditions encountered during both the deceleration and the buoyant phases, and that the deceleration levels were within acceptable levels for the booster. A balloon diameter of 275 feet (84 meters), or possibly less, was adequate for the task, and the total recovery-system weight was of the order of 45,000 to 50,000 pounds (20,412 to 22,680 kilograms). The use of a recovery system of this weight would result in a reduction in mission payload weight of about 3.5 percent. Although the subject recovery system appears feasible from the standpoint of factors studied in this investigation, there are many possible problem areas, particularly in the area of flight mechanics, that would have to be investigated before it could be considered feasible.
AD0485279
AN INVESTIGATION OF VARIOUS TYPES OF DECELERATORS AT MACH NUMBER 2.8
Descriptive Note: Technical rept.
Personal Author(s): MacLanahan, Jr, D A
Report Date: Jul 1966
Media Count: 33 Page(s)
Descriptors: (U) *DROGUE PARACHUTES, EXPERIMENTAL DATA, PERFORMANCE(ENGINEERING), WATER, REDUCTION, TIME, MODEL TESTS, PARACHUTES, SUPERSONIC FLOW, DRAG, SUPERSONIC CHARACTERISTICS, INFLATABLE STRUCTURES, WIND TUNNEL MODELS, ALCOHOLS, BALLOONS, STABILITY, DEPLOYMENT
Identifiers: (U) BALLUTES
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) A test was conducted in the 16-ft supersonic wind tunnel to obtain deployment and steady-state drag, inflation, and stability characteristics of a metal ballute, a cloth ballute, a cloth ballute with a burble fence, a parasonic parachute, and a hyperflo parachute. All decelerators were tested at a Mach number of 2.8 at a dynamic pressure of 120 psfa. The data obtained show that a method of pre-inflation utilizing a methyl alcohol/water solution reduced the time required for the drag load to reach the steady-state value. This reduction of time permitted the metal ballute to attain full inflation.
AD0485401
VERTICAL MOTION OF HIGH ALTITUDE BALLOONS
Descriptive Note: Technical rept.
Personal Author(s): Germeles, A E
Report Date: Jul 1966
Media Count: 91 Page(s)
Descriptors: (U) *BALLOONS, HEAT TRANSFER, MATHEMATICAL MODELS, FLIGHT TESTING, TEMPERATURE, EXPERIMENTAL DATA, EQUATIONS OF MOTION, PERFORMANCE(ENGINEERING), DYNAMICS, MATERIALS, COMPUTER PROGRAMMING, ENERGY, FILMS, MOTION, GASES, HIGH ALTITUDE, HELIUM, CORRELATION TECHNIQUES, CONVECTION(HEAT TRANSFER), LIFT, TEXTILES, THERMAL RADIATION, BUOYANCY, BALLAST, EXHAUST GASES
Abstract: (U) The analysis and the computer program have been extended and improved. The mathematical formulation of the model is presented. The computer program is described in great detail. Some computed and actual flights were correlated. The results from the ADL-NCAR flight have increased the confidence in the validity and accuracy of the computer model.
ADA400429
Collected Works of K. E. Tsiolkovskiy. Volume III - Dirigibles
Descriptive Note: Technical translation
Personal Author(s): Blagonravov, A A
Report Date: Oct 1965
Media Count: 519 Page(s)
Descriptors: (U) *AIRSHIPS, MATERIALS, SHAPE, AERODYNAMIC CHARACTERISTICS, RUSSIA, AERONAUTICAL ENGINEERING, BALLOONS, AIRSHIP ENVELOPES
Identifiers: (U) AMPTIAC COLLECTION, DIRIGIBLES, AEROSTATS
Abstract: (U) Translation of works by K. E. Tsiolkovskiy, as collected by Department of Technical Sciences, Academy of Sciences, Moscow, USSR.
AD0621959
TETHERED AEROLOGICAL BALLOON SYSTEM
Personal Author(s): Elliott, Shelden D , Jr; McKay, J M; McKee, J B
Report Date: Sep 1965
Media Count: 44 Page(s)
Descriptors: (U) *METEOROLOGICAL BALLOONS, TENSILE PROPERTIES, INSTRUMENTATION, DRAG, LIFT, INFLATABLE STRUCTURES, EPOXY RESINS, GROUND SUPPORT EQUIPMENT, MANNED, POLYETHYLENE PLASTICS, STRATOSPHERE, MOORING, TELEMETER SYSTEMS, GLASS TEXTILES
Abstract: (U) The tethered aerological balloon system (TABS) currently under development at NOTS is designed to maintain a captive balloon and payload at stratospheric altitudes for an indefinite period of time, taking advantage of the region of minimum wind velocity nearly always present at some level in the lower stratosphere. The system consists of (1) a conventional polyethylene balloon fitted with a self-deploying reefing system to reduce lateral drag; (2) an airborne telemetry-command package capable of monitoring up to six aerological or other parameters concurrently (additional packages may be distributed along the tether as needed); (3) a NOTS-developed glass fiber tether having a tensile strength comparable to that of steel, at one-fourth the latter's weight, fabricated in splice-free lengths exceeding 100,000 feet; and (4) a mobile ground vehicle from which all functions subsequent to launch can be performed, carrying a crew, control winch, and equipment to communicate with a ground telemetry and command station; the vehicle can run with the wind to reduce lateral drag loads on ascent or descent. The system is expected to become operational the fall of 1965. Various uses and possible further developments of such a stratospheric moored platform are discussed, including applications to manned systems.
AD0613203
DETERMINATION OF THE SHAPE OF A FREE BALLOON: CYLINDER, CYLINDER-END, TAPER-TANGENT, AND TANGENT-HARNESS BALLOONS
Personal Author(s): Smalley, Justin H
Report Date: 01 Nov 1964
Media Count: 44 Page(s)
Descriptors: (U) *SHAPE, *BALLOONS, VOLUME, SPHERES, SURFACES, MATHEMATICAL ANALYSIS, WEIGHT, DIFFERENTIAL EQUATIONS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Modifications of the basic balloon-shape equations are developed for cylinder and cylinder-end balloons, tapertangent balloons, and tangent-harness balloons. Examples of the shape of these balloons are presented, and corresponding meridional stresses are determined. Zero and non-zero circumferential stresses are considered.
AD0436845
DETERMINATION OF THE SHAPE OF A FREE BALLOON. THEORETICAL DEVELOPMENT
Personal Author(s): Smalley, Justin H
Report Date: Aug 1963
Media Count: 37 Page(s)
Descriptors: (U) *BALLOONS, STRESSES, CONFIGURATIONS, PRESSURE VESSELS, EQUATIONS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) A survey is presented of the literature on thin, flexible, pressure vessels. Equations for the stresses in an axi-symmetric balloon are determined. The equations are then rearranged to be most suitable for computation of shape. Derivation of the balloon design parameter sigma is presented.
AD0408300
AMERICAN AND SOVIET INTEREST IN AIRSHIPS
Personal Author(s): Hill, L S
Report Date: Jun 1963
Media Count: 18 Page(s)
Descriptors: (U) *MILITARY OPERATIONS, *AIRSHIPS, FEASIBILITY STUDIES, CARGO, LOGISTICS, OPERATIONS RESEARCH, AIR TRANSPORTATION
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Recent expressions of interest in lighter-than air craft are summarized. In particular, certain Soviet recognition of the potential value of the airship as an economical means for carrying bulky cargo is emphasized. This Memorandum should be of interest to those Air Force personnel charged with the responsibility for development of methods and equipment for transporting oversized items. Such facilities must have size and/or weight capabilities considerably exceeding those of current aircraft, yet remain free from high way, underpass, bridge, and tunnel limitations. This Memorandum should also be of interest to those within the Air Force concerned with the determination of new concepts or new and useful applications for existing concepts. Operational planners in other Governmental agencies and contractual establishments may also find this Memorandum of interest.
AD0409533
THE EFFECT OF VERTICAL AIR MOTION ON ATMOS PHERIC DENSITY DETERMINATION FROM ROBIN FLIGHTS
Descriptive Note: Memorandum rept.
Personal Author(s): Kern, L C; Rapp, R R
Report Date: Jun 1963
Media Count: 34 Page(s)
Descriptors: (U) *ATMOSPHERIC MOTION, *ATMOSPHERIC DENSITY, WIND, BALLOONS, PERTURBATIONS, DRAG
Identifiers: (U) ROBIN, VERTICAL
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) In order to study possible perturbations of the ROBIN density calculations, a consistent set of velocities was computed between 70 km and 38 km for a standard atmosphere using simplified fall velocity equations. Consistency was achieved by iterating the calculations until variations in the drag coefficient produced insignificant changes in the fall velocities. Fall velocities were then computed using an equation that in cluded an arbitrary distribution of vertical atmospheric motions. The resulting fall velocities were used to compute air density, assuming, as is donhe ROBIN calculations, that there is no vertical air motion. These computations are used to demonstrate the error in density resulting from the neglect of the vertical-motion term. The effect of the vertical motion on the iterative process used to obtain the drag coefficients and on the process used to check the balloon's sphericity is also discussed.
AD0414130
STUDY OF PHYSICAL AND CHEMICAL CHARACTERISTICS OF BALLOONS AND BALLOON MATERIALS
Descriptive Note: Quarterly progress rept. no. 1, 1 Mar-31 May 1963
Personal Author(s): Kantor, John; Nelson, Eric
Report Date: 31 May 1963
Media Count: 69 Page(s)
Descriptors: (U) *BALLOONS, ZINC COMPOUNDS, SYMPOSIA, DAMAGE, PERFORMANCE(ENGINEERING), PHYSICAL PROPERTIES, MATERIALS, POLYMERS, PROCESSING, REPORTS, FILMS, ORGANIC COMPOUNDS, INFRARED RADIATION, ESTERS, CRYOGENICS, SYNTHETIC RUBBER, RADIATION EFFECTS, OXYGEN COMPOUNDS, FLIGHT TESTING, MECHANICAL PROPERTIES
Identifiers: (U) NEOPRENES, POLYISOPRENE, SEBACATE/DIBUTYL
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Contents: Properties of balloons and balloon films, study of the literature, evaluation of raw materials, neoprene polymers, polymers other than neoprene, other materials; Evaluation of processing techniques, molecular structure of balloon films, development of optimum compounds; Effect of flight conditions on balloon performance, behavior on inflation and rupture, effect of pre-elongation, effect of ozone, effect of radiation.
AD0406210
HYDROGEN GENERATION FOR HIGH ALTITUDE BALLOONS
Descriptive Note: Quarterly progress rept. no. 3, 1 Jan-1 Apr 1963
Personal Author(s): Carter, W J; Spencer, R A; McGoff, M J
Report Date: 31 May 1963
Media Count: 51 Page(s)
Descriptors: (U) *BALLOONS, *GAS GENERATOR ENGINES, HYDRIDES, BOROHYDRIDES, CATALYSTS
Identifiers: (U) *HYDROGEN GENERATORS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) During this report period ninety small and large scale tests (up to 270 cu ft H2 STP) were run. Data obtained from these tests enabled the design and packaging of fifty NaBH4, fifty NaAlH4 charges and the design and fabrication of a test model Hydrogen Generator (Model XI). Two runs with the test model hydrogen generator were conducted, each reacting three NaBH4 charges and evolving the required 135 cu ft H2. Parameters investigated during this period included the forming pressure and physical packaging technique of large and small quantities of NaBH4; and the mixing of various amounts and combinations of catalysts These efforts were primarily directed toward obtaining a uniform hydrogen generation rate from NaBH4. The best package developed was a 550 gm NaBH4 charge containing 40 gm LiH, 11 gm CoCl2 pressed in a 3 in. x 8 7/8 in. canister. A uniform H2 generation rate has been achieved with NaAlH4. Shelf life tests indicated NaBH4 samples stored at 50 C gave lower yields than fresh control samples and required a longer time for H2 evolution. The NaAlH4 runs showed no significant differences from similar fresh controls.
AD0405852
PRODUCTION ENGINEERING MEASURE FOR MANUFACTURE OF METEOROLOGICAL BALLOONS TYPE ML-541 ( )/UM
Descriptive Note: Quarterly progress rept. no. 4, 19 Jan-18 Apr 1963
Personal Author(s): Miner, Murray; Kantor, John
Report Date: 18 Apr 1963
Media Count: 17 Page(s)
Descriptors: (U) *METEOROLOGICAL BALLOONS, SPECIFICATIONS, PRODUCTION ENGINEERING, SYNTHETIC RUBBER
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The cross-bar dipping conveyor concept has been abandoned in favor of a one-cylinder turntable. Careful analysis indicates that the one-cylinder turntable has advantages of economy, simplicity, and safety. The major portion of the head balloon dipping machine is now specified. Several components have already been received. The basic functions of the various components of the dipping machine have been described.
AD0295940
PROJECT SKY HOOK
Personal Author(s): ENDERSON, ROBERT M
Report Date: 05 Feb 1963
Media Count: 24 Page(s)
Descriptors: (U) *BALLOONS, *METEOROLOGICAL BALLOONS, INSTRUMENTATION, FLIGHT PATHS, CLOUD CHAMBERS, MAGNETOMETERS, HYGROMETERS, HIGH ALTITUDE, FLIGHT TESTING
Distribution Statement: Approved for public release; distribution is unlimited.
AD0292960
REPORT ON LOW LEVEL BALLOON PILOT TRAINING FLIGHTS
Report Date: 04 Jan 1963
Media Count: 40 Page(s)
Descriptors: (U) *BALLOONS, BALLOON EQUIPMENT, MILITARY TRAINING, FLIGHT PATHS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) A series of low level balloon-pilot training flights was conducted. In the jump balloon flights the pilot was suspended from the balloon, through an extended 24 ft diameter parachute, in a nylon harness and seat arrangement. Flight control is afforded by a manual valve located in the balloon apex and by sand ballast secured in bags to the pilot's harness. The flights were of short duration and to very low altitudes. The Sky Car flights employed two-man and fourman open gondolas. The primary objective of the operation, to qualify free balloon pilots, was not achieved, because of unsuitable weather, which limited the number of flights that could be conducted, and adverse trajectories on those flights launched.
AD0295477
BALLOON FLIGHTS OF APRIL 9 AND MAY 23, 1962
Personal Author(s): Murcray, David G; Brooks, James N; Green, Jay O; Working, Marie M
Report Date: 27 Dec 1962
Media Count: 93 Page(s)
Descriptors: (U) *BALLOONS, *INFRARED DETECTORS, INSTRUMENTATION, RADIOMETERS, AUTOMATIC, INDIUM ANTIMONIDES, LIQUID OXYGEN, LIQUID COOLING, COMPUTER PROGRAMMING, FLIGHT TESTING, INFRARED RADIATION
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) This report presents the results obtained on balloon flights made with an automatic programmed radiometer system. The equipment was launched from Holloman AF3, New Mexico, April 9 and May 23, 1962. The radiometer was equipped with a liquid oxygen cooled In Sb cell as a detector and measurements were made of the infrared background radiation from 1. 8 % to 5. 0 %.
AD0402700
STUDY OF PHYSICAL AND CHEMICAL CHARACTERISTICS OF BALLOONS AND BALLOON MATERIALS
Descriptive Note: Final rept. 25 Apr 1960-21 Dec 1962
Personal Author(s): Nelson, Eric; Newstein, Herman
Report Date: 21 Dec 1962
Media Count: 453 Page(s)
Descriptors: (U) *POLYMERS, *FILMS, *BALLOONS, *SYNTHETIC RUBBER, MECHANICAL PROPERTIES, ELASTOMERS, HIGH ALTITUDE, INFRARED RADIATION, PLASTICIZERS, RADIATION EFFECTS, ANTIOXIDANTS, OZONE, CATALYSTS, CONFIGURATIONS, ULTRAVIOLET RADIATION, DAMAGE
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Contents: Study of balloon films and their effect on balloon flight performance: Study of the literature; Study of raw materials; Development of formulations with desirable film properties; High-altitude balloon compounds; Dual-purpose balloon compounds, Fast-rise balloon compounds; Correlation of film properties with flight data. Effect of flight conditions on balloon film performance: Effect of pre-elongation; Effect of ozone; Effect of infra-red radiation; Effect of ultra-violet and other short-wave radiation; Correlation of physical properties with flight performance; Pre diction of balloon performance. Study of balloon configuration.
AD0297099
SUPERPRESSURE BALLOON FOR CONSTANT LEVEL FLIGHT
Personal Author(s): Grass, L A
Report Date: Aug 1962
Media Count: 77 Page(s)
Descriptors: (U) *BALLOONS, *ASTROPHYSICS, MATHEMATICAL ANALYSIS, CONFIGURATIONS, INSTRUMENTATION, FLIGHT PATHS, PLASTICS, POLYETHYLENE PLASTICS, STRATOSPHERE, STABILITY, STRESSES, GEOPHYSICS
Identifiers: (U) SUPERPRESSURE BALLOONS
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) The superpressure balloon is a sealed, virtually non-extensible plastic cell that will float at a constant density altitude despite diurnal fluctuations in the superheat of the lifting gas. This type of balloon does not require ballast to maintain altitude. Instead, it depends upon the ability of the plastic cell to retain all of the lifting gas without significant change in volume, at varying pressures that always remain higher than ambient. The superpressure balloon is more efficient, and is considerably smaller than the valved balloon designed for the same altitude, payload and duration. It provides a highly stable platform for long-duration experiments in the stratosphere. General equations relating superpressure, superheat and free lift are derived and the allowable temperature-fluctuation limits for maintaining altitude are considered. The stringent physical requirements imposed upon suitable materials and some of the special materials-testing procedures for superpressure application are discussed. Design equations are given for the cylindrical, tetrahedral, onion and spherical shapes.
AD0270084
WIND-TUNNEL TESTS OF A 1/20-SCALE AIRSHIP MODEL WITH STERN PROPELLERS
Personal Author(s): MCLEMORE, H CLYDE
Report Date: Jan 1962
Media Count: 142 Page(s)
Descriptors: (U) *AIRSHIPS, PROPULSION SYSTEMS, MODEL TESTS, AERODYNAMIC CHARACTERISTICS, WIND TUNNEL TESTS, WAKE, WIND TUNNEL MODELS, BOUNDARY LAYER FLOW, AERIAL PROPELLERS
Abstract: (U) An investigation was conducted on a 1/20-scale airship model to determine the characteristics and effects of sternmounted propellers. The investigation included tests of two different propellers, measurements of propeller thrust and power characteristics, airship force and moment characteristics, hull pressure distributions, and hull boundary-layer and wake characteristics. The tests were conducted for several propellerblade angles and rotational speeds for test velocities of about 94 and 139 ft/sec. The stern-mounted propeller gave a much higher propulsive efficiency than did a conventionalmounted or a fin-mounted-propeller. Sternpropeller operation had very small effects on the model aerodynamic characteristics.
AD0272754
FEASIBILITY STUDY OF AN INFLATABLE TYPE STABILIZATION AND DECELERATION SYSTEM FOR HIGH-ALTITUDE AND HIGH-SPEED RECOVERY
Descriptive Note: Final rept.
Personal Author(s): Nebiker, F R
Report Date: Dec 1961
Media Count: 167 Page(s)
Descriptors: (U) *REENTRY VEHICLES, *RECOVERY, *BALLOONS, *PNEUMATIC EQUIPMENT, STABILIZATION, STRESSES, ORBITS, EXPERIMENTAL DATA, THERMODYNAMICS, SPHERES, COATINGS, MODEL TESTS, MATHEMATICAL ANALYSIS, TEST VEHICLES, ARTIFICIAL SATELLITES, AERODYNAMIC CHARACTERISTICS, HIGH ALTITUDE, OPERATION, PRESSURE VESSELS, TABLES(DATA), CONTAINERS, SUPERSONIC FLOW, DRAG, EXTERIOR BALLISTICS, WIND TUNNEL MODELS, DECELERATION, SYNTHETIC RUBBER, SCHLIEREN PHOTOGRAPHY, TOWED BODIES, DACRON
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) On the basis of the theoretical and experimental wind tunnel test data obtained, it was concluded that an inflatable sphere is a practicable stabilization and deceleration system for initial recovery from high-altitude, high-speed flight regimes (up to Mach 4.0 at 200,000 feet). Inflatable spheres tested were fabricated utilizing standard manufacturing methods and readily available materials. The recovery system tested exhibited considerable potential as an initial stabilization and deceleration recovery system for a disoriented or tumbling high-altitude, high- speed payload. Included are theoretical and wind tunnel test data on the effects of various shaped primary bodies on a secondary spherical body at various trailing distances. Also included is a limited amount of experimental data on flight testing of a full-scale operational unit.
AD0266236
STRATO-LAB OPEN GONDOLA - HIGH ALTITUDE OBSERVATORY BALLOON FLIGHT NO. 1
Descriptive Note: Final rept.
Report Date: 15 Sep 1961
Media Count: 57 Page(s)
Descriptors: (U) *SKY BRIGHTNESS, *BALLOONS, FLIGHT, HIGH ALTITUDE, INSTRUMENTATION, PHYSIOLOGY, ASTRONOMY, FLIGHT PATHS, PROTECTIVE CLOTHING, ASTRONOMICAL OBSERVATORIES, FLIGHT CLOTHING, BALLOON EQUIPMENT
Identifiers: (U) COMMUNICATION SYSTEMS
AD0262552
AN INVESTIGATION OF THE EFFECTS OF INDUCED NONSYMMETRIC PRESSURE DISTRIBUTIONS ON THE AERODYNAMIC STABILITY OF AN AIRSHIP FORM
Personal Author(s): Boatwright, Donald W
Report Date: 11 Aug 1961
Media Count: 47 Page(s)
Descriptors: (U) *CONTROL SYSTEMS, *AERODYNAMIC CHARACTERISTICS, *SUBSONIC FLOW, *AIRSHIPS, *SPOILERS, FLIGHT TESTING, DRAG, AERODYNAMIC STABILITY, MOMENTS, PRESSURE
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Installations which would induce nonsymmetric pressure distributions about the airship hull or create high off-center drag forces were suggested for evaluation as possible control devices for the finless airship. Inflatable, compartmented rings or bulges, and extensible spoilers are examples of the type of devices considered worthy of investigation. The results of a study of the effects of induced nonsymmetric pressure distributions on the aerodynamic stability of an airship model are presented as a first step toward the evaluation of such control devices. Flight test measurements of the pressure distributions of a ZS2G-1 model were integrated to obtain force and moment parameters acting on the model and were compared to conventional airship data. An analysis of the results using geometric devices and air ejection for inducing nonsymmetric pressure distributions are presented.
AD0259026
THE KITING MOTION OF A MASTED AIRSHIP AS DETERMINED BY ANALYTIC EVALUATION OF WATER MODEL TESTS
Report Date: 01 May 1961
Media Count: 96 Page(s)
Descriptors: (U) *AERODYNAMIC STABILITY, *AIRSHIPS, *SAFETY EQUIPMENT, WIND, DAMPING, MOMENTS, MODEL TESTS, MATHEMATICAL ANALYSIS, AERODYNAMIC DRAG, DIFFERENTIAL EQUATIONS, AIRCRAFT EQUIPMENT, AERODYNAMIC LIFT
Identifiers: (U) KITING
Abstract: (U) Efforts to establish the necessary parameters by which the problem of damage due to kiting of a masted airship may be analyzed resulted in 2 experimental investigations utilizing airship models. As a result both the aerodynamic and the AERODYNAMIC DAMPING CHARACTERISTICS OF A KITING AIRSHIP WERE DETERMINED WITH SUFFICIENT ACCURACY TO PERMIT A MATHEMATICAL DESCRIPTION OF THE MOTIONS OF A KITING AIRSHIP. The feasible means by which a reduction of the likelihood of damage due to kiting were reviewed. Having considered each of these schemes, the most promising single solution appeared in the employment of a weight attached to the stern handling lines of the airship. It was concluded that although this anti-kiter design did reduce kiting appreciably, large and impractical weights were required to reduce contact velocities to acceptable values. To remedy this, a redesign of the anti-kiter attachment system which keeps the anti-kiting unit close to the ground was studied. With this modification, both the kiting and the contact velocities were reduced appreciably at all wind speeds with practical anti-kiter weights.
AD0259726
AEROSPACE VEHICLE PROTECTION FROM ATMOSPHERIC ELECTRICAL HAZARDS
Descriptive Note: Technical note, Quarterly rept. no. 1, Jan-Mar 1961
Personal Author(s): Newman, M M; Stahmann, J R; Robb, J D
Report Date: 30 Apr 1961
Media Count: 27 Page(s)
Descriptors: (U) *AIRSHIPS, *ATMOSPHERIC ELECTRICITY, *AIRSHIP ENVELOPES, *LIGHTNING ARRESTERS, HAZARDS, MATERIALS, ELECTRICAL CONDUCTIVITY, LIGHTNING, TAPES, AVIATION SAFETY, PROTECTIVE COVERINGS
Identifiers: (U) *ELECTRIC INSULATION
Distribution Statement: Approved for public release; distribution is unlimited.
AD0246191
AN EXPERIMENTAL INVESTIGATION OF FILLET DESIGN FOR APPLICATION TO AIRSHIP FINS
Personal Author(s): BOATWRIGHT, DONALD W
Report Date: 01 Nov 1960
Media Count: 38 Page(s)
Descriptors: (U) *AERODYNAMIC CONFIGURATIONS, *BOUNDARY LAYER CONTROL, *AIRSHIPS, AERODYNAMIC CHARACTERISTICS, DRAG, FINS
Distribution Statement: Approved for public release; distribution is unlimited.
AD0322239
A STUDY OF AIRSHIP ROTARY DERIVATIVES
Report Date: Nov 1960
Media Count: 55 Page(s)
Descriptors: (U) *AIRSHIPS, VELOCITY, STABILITY, YAW, DAMPING, DEFLECTION, MOTION, TEST METHODS, MOMENTS, MATHEMATICAL PREDICTION, AERODYNAMIC CHARACTERISTICS, AIRFRAMES, FLAPS(CONTROL SURFACES), LIFT
Identifiers: (U) PITCH (MATERIAL), PITCH (MOTION), TAILS (AIRCRAFT)
Abstract: (U) OF THE FOUR EXPERIMENTAL METHODS UTILIZED TO OBTAIN AIRSHIP ROTARY DERIVATIVES, THE WHIRLING ARM TECHNIQUE AND THE METHOD OF CURVED OR BOWED MODELS APPEAR TO OFFER THE BEST RESULTS. The meager amount of data obtained with these methods along with some of the aerodynamic oscillator data forms the basis for the combined theoreticalempirical method developed to predict the rotary derivatives of airships.
AD0317134
APPLICATION OF FULL SCALE BOUNDARY LAYER MEASUREMENTS TO DRAG REDUCTION OF AIRSHIPS
Descriptive Note: Research rept. no. 26
Personal Author(s): CORNISH III, JOSEPH J; BOATWRIGHT, DONALD W
Report Date: 18 Jan 1960
Media Count: 39 Page(s)
Descriptors: (U) *BOUNDARY LAYER, *DRAG, *AIRSHIPS, AERODYNAMIC CONFIGURATIONS, FLIGHT TESTING, MEASUREMENT, TEST EQUIPMENT, HELICOPTER ROTORS, REDUCTION
AD0227244
Development And Test of A Balloon-Borne Manned Vehicle
Descriptive Note: Technical rept.
Personal Author(s): Geer, Richard L; Rayfield, John F
Report Date: Jun 1959
Media Count: 48 Page(s)
Descriptors: (U) *BALLOONS, *PARACHUTE JUMPING, TRAINING, FLIGHT TESTING, TRAINING DEVICES
Distribution Statement: Approved for public release; distribution is unlimited.
ADA323109
Contributions of Balloon Operations to Research and Development at the Air Force Missile Development Center Holloman Air Force Base, N. Mex 1947-1958
Report Date: Jan 1958
Media Count: 165 Page(s)
Descriptors: (U) *BALLOONS, *TARGET DRONES, FLIGHT TESTING, MILITARY REQUIREMENTS, WEAPON SYSTEMS, OPERATIONAL EFFECTIVENESS, AIR FORCE FACILITIES, AIR TO AIR MISSILES, GUIDED MISSILE TARGETS, AIR FORCE OPERATIONS, UPPER ATMOSPHERE, SURFACE LAUNCHED
Abstract: (U) Among the many activities at the Air Force Missile Development Center contributing to the expanding fields of guided missiles and space technology, that of the Balloon Branch is among the more important. Upon first consideration, the contributions of ballooning may seem detached from the development of missile weapon systems or the conquest of space. Actually, the connection is direct and of greatest importance. Over the past twelve years the accomplishments of Holloman's Balloon Branch have contributed significantly to the work of many other units; various missile projects, research in space biology and biodynamics, the exploration of the upper atmosphere, and the development of artificial cabin environments which will be required for manned space flight. In addition, they have materially furthered the entire state of the art of ballooning, itself. The historical monograph presented here carefully documents the contributions of twelve years of balloon operations at this major test, research, and development center.
ADA323780
Altitude Balloon Dummy Drops. Part 1 The Unstabilized Dummy Drops
Descriptive Note: Technical rept.,
Personal Author(s): Madson, Raymond A
Report Date: Oct 1957
Media Count: 44 Page(s)
Descriptors: (U) *HIGH ALTITUDE, *PARACHUTE DESCENTS, *FREE FALL MODELS, ACCELEROMETERS, AERODYNAMIC STABILITY, DROP TESTS, EXPOSURE(PHYSIOLOGY), BAROMETRIC PRESSURE, SURVIVAL(PERSONNEL), AVIATION SAFETY, OXYGEN CONSUMPTION, PARACHUTISTS, BALLOONS, ACCELERATION TOLERANCE, COLD TOLERANCE, PARACHUTE JUMPING, PARACHUTE CANOPIES, FALLING BODIES
Abstract: (U) The characteristics of instrumented dummies carried aloft to predetermined altitudes were studied during the free fall in unstabilized situations. These were observed to assume an attitude permitting spins about a transverse axis, and the angular velocities recorded on accelerometers exceeded rates compatible with human tolerance. This study justifies further tests to develop a method of stabilizing a man descending from high altitudes.
AD0149456
GUST LOADS ON AIRSHIP FINS
Personal Author(s): Flomenholf, H I
Report Date: Jun 1957
Media Count: 38 Page(s)
Descriptors: (U) *GUST LOADS, *FINS, *AIRSHIPS, AERODYNAMIC CHARACTERISTICS
Distribution Statement: Approved for public release; distribution is unlimited.
AD0117710
CONSTANT PRESSURE TRAJECTORIES
Report Date: Sep 1956
Media Count: 95 Page(s)
Descriptors: (U) *FLIGHT PATHS, *METEOROLOGICAL BALLOONS, METEOROLOGY, BAROMETRIC PRESSURE, DETERMINATION
Abstract: (U) The purpose if this effort is to aid AWS personnel in constructing trajectories for constant pressure balloon f1ights.
ADA323108
Flight Summary Non-Extensible Balloon Operations 6580th Test Squadron (Special)
Descriptive Note: Rept. for Jun 50-Oct 54.
Report Date: Oct 1954
Media Count: 44 Page(s)
Descriptors: (U) *FLIGHT TESTING, *METEOROLOGICAL BALLOONS, TEST AND EVALUATION, AIR FORCE RESEARCH, HIGH ALTITUDE, TABLES(DATA), AIR FORCE OPERATIONS, ATMOSPHERIC CHEMISTRY
Abstract: (U) The first plastic balloon was flown at Holloman Air Force Base on 3 July 1947 by an Air Materiel Command contractor, New York University. There was considerable plastic balloon activity by this same University and General Mills, Incorporated, during 1948 and 1949 at Holloman Air Force Base. In 1949, Air Force personnel from Holloman Air Force Base first organized the present Balloon Unit. Flights were made with clusters of neoprene balloons during that year to study atmospheric composition and diffusion at high altitudes. At the time that HAFB Number 1 was flown, the Balloon Unit was under Electronic and Atmospheric, Holloman Air Force Base. Since that time the same organization has been called Research Test Branch and is now the 6580th Test Squadron (Special). This report contains data concerning balloon test flight data and equipment.
ADA459988
Project Clinker, Hydraulic Carriage for Airship Installation of Optical Equipment
Personal Author(s): Daly, P; Rosenberg, T
Report Date: 22 Sep 1954
Media Count: 11 Page(s)
Descriptors: (U) *OPTICAL EQUIPMENT, *AIRSHIPS, MIRRORS, INSTALLATION, CARRIAGES, RIGGING, HYDRAULIC EQUIPMENT
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Airship installation of delicate optical equipment often requires special rigging equipment not available commercially. One problem at this Laboratory called for the installation of an 8.5-foot-diameter mirror weighing nearly 2000 pounds, in a type ZPM-4 airship. The mirror was required to pass beneath a conical windscreen having a 5-foot clearance above the ground and be mounted within the screen at an angle of 45 degrees. One answer to this problem was a carriage having a top deck pivoted at one end. The movable deck was raised to the required angle by a motor driven hydraulic hoist of the type used commercially for dump trucks. The mirror was mounted on this movable deck by means of a wooden cradle which could then be drawn up the incline into position for installation in the airship. The inclined deck contains steel rollers to reduce friction and the cradle moves upward by means of an electric chain hoist. This hydraulic carriage was used successfully in many operations involving installation and removal of the mirror and resulted in a great saving of man-hours of rigging time.
AD0047060
High Altitude Balloon Research
Descriptive Note: Progress rept. annex 12
Personal Author(s): BARTHOLOMEW, F
Report Date: 01 Aug 1954
Media Count: 53 Page(s)
Descriptors: (U) *METEOROLOGICAL BALLOONS, *BALLOON EQUIPMENT, INSTRUMENTATION
Distribution Statement: Approved for public release; distribution is unlimited.
AD0044562
HIGH ALTITUDE AIR SAMPLING
Descriptive Note: Progress rept. for Apr and May 1954
Personal Author(s): Whitnah, G R
Report Date: 10 Jun 1954
Media Count: 41 Page(s)
Descriptors: (U) *UPPER ATMOSPHERE, *METEOROLOGICAL BALLOONS, SAMPLING, INSTRUMENTATION
Distribution Statement: Approved for public release; distribution is unlimited.
AD0041757
High Altitude Balloon Research. Final Report Annex 2
Descriptive Note: Final rept.
Personal Author(s): GILES, KEITH C
Report Date: 10 Jun 1954
Media Count: 17 Page(s)
Descriptors: (U) *UPPER ATMOSPHERE, *METEOROLOGICAL BALLOONS, INSTRUMENTATION, HIGH ALTITUDE, FLIGHT PATHS
Distribution Statement: Approved for public release; distribution is unlimited.
AD0047101
High Altitude Balloon Research
Descriptive Note: Progress rept. annex 12
Personal Author(s): BARTHOLOMEW, F
Report Date: 01 Jun 1954
Media Count: 56 Page(s)
Descriptors: (U) *METEOROLOGICAL BALLOONS, UPPER ATMOSPHERE, MATERIALS, INSTRUMENTATION
Identifiers: (U) DESIGN, TESTS
Distribution Statement: Approved for public release; distribution is unlimited.
AD0041526
BASIC PERFORMANCE OF NON-POWERED, TETHERED LIGHTER-THAN-AIR VEHICLES FOR ANTENNA SUPPORT
Descriptive Note: Interim engineering rept.
Report Date: 07 May 1954
Media Count: 37 Page(s)
Descriptors: (U) *ANTENNAS, *ANTENNA MASTS, *BALLOONS
Distribution Statement: Approved for public release; distribution is unlimited.
AD0032520
FINAL REPT. ANNEX IX (HIGH ALTITUDE BALLOON RESEARCH)
Descriptive Note: Annex IX
Personal Author(s): GILES, KEITH C
Report Date: 04 Apr 1954
Media Count: 20 Page(s)
Descriptors: (U) *METEOROLOGICAL BALLOONS, INSTRUMENTATION, UPPER ATMOSPHERE, COSMIC RAYS, ATMOSPHERIC SOUNDING, HIGH ALTITUDE, SOUNDING ROCKETS
Distribution Statement: Approved for public release; distribution is unlimited.
AD0030902
TECHNIQUES DEVELOPED FOR HEAVY LOAD NON-EXTENSIBLE BALLOON FLIGHTS
Personal Author(s): GILDENBERG, BERNARD D
Report Date: Mar 1954
Media Count: 43 Page(s)
Descriptors: (U) *BALLOONS, BALLOON EQUIPMENT, LAUNCHING, HANDLING
Identifiers: (U) TESTS
Distribution Statement: Approved for public release; distribution is unlimited.
AD0024204
RESEARCH AND DEVELOPMENT IN THE FIELD OF HIGH ALTITUDE PLASTIC BALLONS
Descriptive Note: Progress rept., Vol. 8, 20 Jan-4 Feb 1953.
Report Date: 04 Feb 1953
Media Count: 166 Page(s)
Descriptors: (U) *METEOROLOGICAL BALLOONS
Identifiers: (U) DESIGN, RH-1 AIRCRAFT, SKYHOOK BALLOONS
Distribution Statement: Approved for public release; distribution is unlimited.
AD0020131
RESEARCH AND DEVELOPMENT IN THE FIELD OF HIGH ALTITUDE PLASTIC BALLOONS. VOLUME 5
Descriptive Note: Progress rept. no. 2, 15 Jun-22 Dec 1952
Report Date: 22 Dec 1952
Media Count: 378 Page(s)
Descriptors: (U) *BALLOONSONDES, SHAPE, FLIGHT, VERTICAL ORIENTATION, DUCTS, LAUNCHING, COMMUNICATION AND RADIO SYSTEMS, TELEMETER SYSTEMS, REQUIREMENTS, CYLINDRICAL BODIES
Distribution Statement: Approved for public release; distribution is unlimited.
Abstract: (U) Contents: Launching summary; Balloon design: (a) Considerations on balloon shape; (b) Calculations of cylinder balloon shapes; (c) Cylinder balloons; (d) Computed natural balloon shape for a specific requirement of the Moby Dick project; (e) Duct appendix. Weeksville inflation tests, Diffusion in balloons, Vertical flight, Instrumentation, Telemetering and Communication. (Not abstracted)
ADA800203
Test of 1/36-Scale Materiel Center Design Barrage Balloon X41K660 with Six Different Tail Assemblies Five-Foot Wind Tunnel Test Number 285
Descriptive Note: Technical rept.
Personal Author(s): Young, D W; Gilmore, J H
Report Date: 11 Aug 1942
Media Count: 100 Page(s)
Descriptors: (U) *BALLOONS, TAIL ASSEMBLIES
Identifiers: (U) BARRAGE BALLOONS, ATI-022791, ATI COLLECTION
Distribution Statement: Approved for public release; distribution is unlimited.
