Listed
below is a sampling of 16mm films originally created as part of testing
and research activities at the Langley Research Center (LaRC). The
films were recently digitized into DVD format as part of a project to preserve
and disseminate these technically and historically significant motion
pictures. To date, 70 of the nearly 1,600 films have
been digitized. The yet-to-be-digitized films
are listed here in
alphabetical order. Many of the films supplement NASA and NACA technical
reports
published
between 1937 and 1985, while others are project and operations overviews.
The complete collection addresses both aircraft and space-vehicle configurations,
flight dynamics, takeoff/landing dynamics, reentry heating, orbital rendezvous,
EVA operations, flight tests, wind-tunnel tests, crash and impact tests,
materials tests, and many other related topics.
The DVDs, now available from the NASA Center
for AeroSpace Information (CASI), are listed here in chronological
order. Films that are supplements
to original research documents show the corresponding report and document
numbers. Each item includes links to low- and medium-resolution
versions, the
identification number for
ordering the high-resolution DVD
version of the film, and a link to the STI Order Form. If the description
is not already visible, click on 'Film Description' to expand
the
view. Please contact the STI Help Desk staff at help@sti.nasa.gov or
301-621-0390 for questions or comments.
Experimental
Ablation Cooling
1958
Silent, Black & White, 9 minutes
Supplement to NACA-RM-L58E15a (19930090170); High-Res DVD ID No.: 20070030959
- Film Description
- The film shows ablation
tests on Teflon, nylon, a 27 percent phenolic resin, Haveg Rocketon,
and graphite. Teflon hemisphere-shaped and flat face noses were tested
with laboratory-scale ceramic-heated, pilot-model ceramic-heated, and
electric-arc-powered air jets. Nylon hemisphere-shaped noses were tested
with laboratory-scale ceramic-heated and electric-arc-powered air jets.
Phenolic resin hemisphere-shaped noses were tested with laboratory-scaled
ceramic-heated air jets. Haveg Rocketon and graphite hemisphere-shaped
noses were tested with electric-arc-powered air jets.
Water
Landing Characteristics of a Reentry Capsule
1958
Silent, Color, 3min.
Supplement to NASA-MEMO-5-23-59L (19980228040); High-Res DVD ID No.: 20070030955
- Film Description
- Experimental and
theoretical investigations have been made to determine the water-landing
characteristics of a conical-shaped reentry capsule having a segment
of a sphere as the bottom. For the experimental portion of the investigation,
a 1/12-scale model capsule and a full-scale capsule were tested for nominal
flight paths of 65 deg and 90 deg (vertical), a range of contact attitudes
from -30 deg to 30 deg, and a full-scale vertical velocity of 30 feet
per second at contact. Accelerations were measured by accelerometers
installed at the centers of gravity of the model and full-scale capsules.
For the model test the accelerations were measured along the X-axis (roll)
and Z-axis (yaw) and for the full-scale test they were measured along
the X-axis (roll), Y-axis (pitch), and Z-axis (yaw). Motions and displacements
of the capsules that occurred after contact were determined from high-speed
motion pictures. The theoretical investigation was conducted to determine
the accelerations that might occur along the X-axis when the capsule contacted the water from a 90 deg flight path at a 0 deg
attitude. Assuming a rigid body, computations were made from equations
obtained by utilizing the principle of the conservation of momentum.
The agreement among data obtained from the model test, the full-scale
test, and the theory was very good. The accelerations along the X-axis,
for a vertical flight path and 0 deg attitude, were in the order of 40g.
For a 65 deg flight path and 0 deg attitude, the accelerations along
the X-axis were in the order of 50g. Changes in contact attitude, in
either the positive or negative direction from 0 deg attitude, considerably
reduced the magnitude of the accelerations measured along the X-axis.
Accelerations measured along the Y- and Z-axes were relatively small
at all test conditions.
Schlieren
Movies of the 8-Inch Diameter Rigid Parachute Model of the Cook Research Laboratory
Taken During the Fourth Phase of Testing in the Langley Unitary Plan Wind Tunnel
1958
Silent, Black & White, 23min.
High-Res DVD ID No.: 20070030956
- Film Description
- Canopy Model IV
was tested in four different configuration series. Shroud lines were
used in the first three series of tests; none were used in the fourth
series. Other variables were Mach number (1.77, 2.17, 2.76), dynamic
pressure (290, 250, 155 lb per sq ft), camera speed, and attitude.
Reentry
Body Stability Tests Conducted in Langley Spin Tunnel
1958
Silent, Black & White, 1min.
High-Res DVD ID No.: 20070030957
- Film Description
- Reentry body stability
tests were conducted in an initial configuration, with a small drogue
chute, with an extendable flare, and in an alternate configuration with
a covered flare.
Aerodynamic
Heating of Blunt Nose Shapes at Mach Numbers up to 14
1958
Silent, Black & White, 2min.
Supplement to NACA-RM-L58E05a (19710065515); High-Res DVD ID No.: 20070030958
- Film Description
- Results are presented
from investigations of the aerodynamic heating rates of blunt nose shapes
at Mach numbers up to 14. The wind-tunnel tests examined flat-faced cylinder
stagnation-point heating rates over the Mach number range. The tests
also examined heat transfer and angle of attack.
Water
Landing Characteristics of a 1/6-Scale Model Reentry Capsule with an 80-Inch
Heat Shield
1959
Silent, Color, 4min.
High-Res DVD ID No.: 20070030950
- Film Description
- Variables for the
reentry capsule water landing tests were flight path, vertical contact
velocity, and contact attitude. The capsule weighed 1900 pounds with
a center of gravity 16.8 inches above maximum diameter.
Dynamic
Model Tests of Models in the McDonnell Design of Project Mercury Capsule in the
Langley 20-Foot Free-Spinning Tunnel
1959
Silent, Black & White, 23min.
High-Res DVD ID No.: 20070030952
- Film Description
- On 11 May 1959,
24 tests of the aerodynamic response of the McDonnell model Project Mercury
capsule were conducted. The initial test demonstrated free-fall; a parachute
was used in the remaining test. Several tests included the addition of
baffles.
Flow
Studies of Decelerators at Supersonic Speeds
1959
Silent, Black & White, 10min.
High-Res DVD ID No.: 20070030953
- Film Description
- Wind tunnel tests
recorded the effect of decelerators on flow at various supersonic speeds.
Rigid parachute models were tested for the effects of porosity, shroud
length, and number of shrouds. Flexible model parachutes were tested
for effects of porosity and conical-shaped canopy. Ribbon dive brakes
on a missile-shaped body were tested for effect of tension cable type
and ribbon flare type. The final test involved a plastic sphere on riser
lines.
Studies
of Accelerations in Manned Vehicles During Exit and Reentry Flight
1959
Silent, Color, Black & White, 9.5min.
High-Res DVD ID No.: 20070030954
- Film Description
- Several experiments
with human centrifugation are shown with subjects wearing different flight
suits.
1/9-Scale
Saturn Model
1960
Silent, Color, 4min.
High-Res DVD ID No.: 20070030971
- Film Description
- The film shows technicians
assembling the nose cone on a Saturn model rocket in a test facility.
The booster configuration is show. After the nose cone is in place, a
meter is attached at the joint and vibration tests are conducted.
High
Speed Schlieren Studies of Flow Over Mercury Atlas Vehicle in the Langley 2-Foot
Transonic Aeroplasticity Tunnel
1960
Silent, Black & White, 15min.
High-Res DVD ID No.: 20070030972
- Film Description
- Test conditions
for the studies are: Mach number varying continuously from approximately
0.8 to 1.1 and Reynolds number (based on maximum diameter of Atlas) approximately
0.451 x 10(exp 6). Camera speed is 2000 frames per second.
High-Speed
Schlieren Movies of Decelerators at Supersonic Speeds
1960
Silent, Black & White, 7min.
High-Res DVD ID No.: 20070030973
- Film Description
- Tests were conducted
on several types of porous parachutes, a paraglider, and a simulated
retrorocket. Mach numbers ranged from 1.8-3.0, porosity from 20-80 percent,
and camera speeds from 1680-3000 feet per second (fps) in trials with
porous parachutes. Trials of reefed parachutes were conducted at Mach
number 2.0 and reefing of 12-33 percent at camera speeds of 600 fps.
A flexible parachute with an inflatable ring in the periphery of the
canopy was tested at Reynolds number 750,000 per foot, Mach number 2.85,
porosity of 28 percent, and camera speed of 36oo fps. A vortex-ring parachute
was tested at Mach number 2.2 and camera speed of 3000 fps. The paraglider,
with a sweepback of 45 degrees at an angle of attack of 45 degrees was
tested at Mach number 2.65, drag coefficient of 0.200, and lift coefficient
of 0.278 at a camera speed of 600 fps. A cold air jet exhausting upstream
from the center of a bluff body was used to simulate a retrorocket. The
free-stream Mach number was 2.0, free-stream dynamic pressure was 620 lb/sq ft, jet-exit static pressure ratio was 10.9, and camera speed
was 600 fps.
Flow
Over Blunt Body at M equals 20 in 2-Inch Helium Tunnel
1960
Silent, Black & White, 1min.
High-Res DVD ID No.: 20070030946
- Film Description
- The film shows flow
over blunt body alone, with internal spike, and with external spikes.
Tests
of Vortex-Ring Parachute at Supersonic Speed in the Langley Unitary Plan Wind
Tunnel
1960
Silent, Black & White, 8.5min.
High-Res DVD ID No.: 20070030947
- Film Description
- For the test, the
12-inch-diameter "Vortex-Ring" parachute was towed behind a conical-nosed cylindrical body 2.25 inches in diameter.
The tow-cable length was 24 inches, and was attached to the cylindrical
body through a large swivel and to the parachute through a smaller swivel.
The attachment between the large swivel an the cylindrical body failed
after about 1 minute's operation. Mach number was approximately 2.2,
dynamic pressure was approximately 150 pounds per square foot, and camera
speed was approximately 3000 frames per second.
High-Speed
Schlieren Movies of the Flow About Reefed Parachute Models Towed at Supersonic
Speeds Behind a Conical Body (4.875 Inches in Diameter). Drag Values Based on
the Unreefed Diameter of 1.73 F. Porosity of Unreefed Parachute is 28 Percent.
1960
Silent, Black & White, 15.5min.
High-Res DVD ID No.: 20070030948
- Film Description
- Flexible parachute
models reefed to one-eighth, one-fourth, one-third, and four tenths of
its diameter were towed at speeds of Mach 1.80, 2.00, 2.20 and 2.87.
Towline lengths tested were 23.40, 24.38, 26.81, and 29.25 inches. High-speed
Schlieren movies of the flow are shown.
Landing
Energy Dissipation for Manned Reentry Vehicles
1960
Silent, Color, 3.5min.
Supplement to NASA-TN-D-453 (19980228267); High-Res DVD ID No.: 20070030945
- Film Description
- The film shows experimental
investigations to determine the landing-energy-dissipation characteristics
for several types of landing gear for manned reentry vehicles. The landing
vehicles are considered in two categories: those having essentially vertical-descent
paths, the parachute-supported vehicles, and those having essentially
horizontal paths, the lifting vehicles. The energy-dissipation devices
include crushable materials such as foamed plastics and honeycomb for
internal application in couch-support systems, yielding metal elements
as part of the structure of capsules or as alternates for oleos in landing-gear
struts, inflatable bags, braking rockets, and shaped surfaces for water
impact.
Thermo-Lag
Ablation Tests
1960
Silent, Color, 31min.
High-Res DVD ID No.: 20070030949
- Film Description
- Thermo-lag, an ablation
material made by Emerson Electric Co., was tested in the preflight jet
at Wallops Island, VA. Variables included temperature and mach number.
Aerodynamic
Characteristics of Parachutes at Mach Numbers from 1.6 to 3
1961
Silent, Black & White, 31min.
Supplement to NASA-TN-D-752 (20010024158); High-Res DVD ID No.: 20070030970
- Film Description
- A wind-tunnel investigation
was conducted to determine the parameters affecting the aerodynamic performance
of drogue parachutes in the Mach number range from 1.6 to 3. Flow studies
of both rigid and flexible-parachute models were made by means of high-speed
schlieren motion pictures and drag coefficients of the flexible-parachute
models were measured at simulated altitudes from about 50,000 to 120,000
feet.
Wind
Tunnel Investigation of a Balloon as Decelerator at Mach Numbers from 1.47 to
2.50
1961
Silent, Black & White, 5.5min.
Supplement to NASA-TN-D-919 (19980227793); High-Res DVD ID No.: 20070030967
- Film Description
- A wind-tunnel investigation
was conducted to study the characteristics of a towed spherical balloon
as a drag device at Mach numbers from 1.47 to 2.50, Reynolds numbers
from 0.36 x 10(exp 6) to 1.0 x 10(exp 6) , and angles of attack from
-15 to 15 degrees. Tow-cable length was approximately 24 inches from
asymmetric body to cone on the upstream side of the balloon. As the tow
cable was lengthened the balloon reached a point in the test section
where wall-reflected shocks intersected the balloon and caused severe
oscillations. As a result, the tow cable broke and the inflatable balloon
model was destroyed. Further tests used a model rigid plastic sphere
6.75 inches in diameter. Tow cable length was approximately 24 inches
from asymmetric body to the upstream side of the sphere.
Dynamic
Model Tests of Models of the McDonnell Design of Project Mercury Capsule in the
Langley 20-Foot Free-Spinning Tunnel
1961
Silent, Black & White, 22min.
High-Res DVD ID No.: 20070030951
- Film Description
- On 10 June 1961,
33 tests of the aerodynamic response of the McDonnell model Mercury capsule
were conducted. Variables included spin, different parachute tethers,
and the addition of baffles.
Effect
of Load-Alleviating Structure on the Landing Behavior of a Reentry-Capsule Model
1961
Silent, Color, 2min.
Supplement to NASA-TN-D-811 (20040008118); High-Res DVD ID No.: 20070030968
- Film Description
- Model tests have
been made to determine the landing-impact characteristics of a parachute-supported
reentry capsule that had a compliable metal structure as a load-alleviating
device. A 1/6-scale dynamic model having compliable aluminum-alloy legs
designed to give a low onset rate of acceleration on impact was tested
at flight-path angles of 90 degrees (vertical) and 35 degrees, at a vertical
velocity of 30 ft/sec (full scale), and at contact attitudes of 0 degrees
and +/-30 degrees. Landings were made on concrete, sand, and water.
An
Exploratory Investigation of Jet Blast Effects on a Dust Covered Surface at Low
Ambient Pressure
1961
Silent, Black & White, 19min.
Supplement to NASA-TN-D-1017 (19620000062); High-Res DVD ID No.: 20070030966
- Film Description
- A preliminary investigation
has been conducted to determine the effects of jet blast, at low ambient
pressures, on a surface covered with loose particles. Tests were conducted
on configurations having from one to four nozzles at 0, 10, 20, and 30
degree cant angles and heights of 2 and 4 inches above the particle-covered
surface.
Landing
of Manned Reentry Vehicles
1961
Silent, Color, 4min.
High-Res DVD ID No.: 20070030969
- Film Description
- Landing characteristics
were investigated using dynamic models. The landing speeds for several
let-down systems are simulated. Demonstrations include: (1) the vertical
landing of parachute-supported capsules on water; (2) reduction of landing
acceleration by shaping the impact surface for water entry; (3) problems
created by horizontal velocity due to wind; (4) the use of energy absorbers
(yielding metal legs or torus bags) for land or water landings; (5) problems
associated with horizontal land landings; (6) the use of a paraglider
to aid in vehicle direction control; (7) a curved undersurface to serve
as a skid-rocker to convert sinking-speed energy into angular energy;
(8) horizontal-type landing obtained with winged vehicles on a hard runway;
(9) the dangers of high-speed water landings; and (10) the positive effects
of parachute support for landing winged vehicles.
United
States Space Explorations 1958
1962
Sound, Color, 19min.
High-Res DVD ID No.: 20070030963
- Film Description
- The film describes
preparation and launch of five satellites and two space probes during
1958. On January 31, a Jupiter vehicle launched Explorer I into space.
Data from this satellite was used to identify the van Allen radiation
belts. On March 17, a Vanguard I rocket launched an Earth satellite with
solar batteries. Data from the mission was used to determine that the
Earth is slightly pear-shaped. On March 26, Explorer III was launched
to further study the van Allen belts, micrometeoroid impacts, and internal
and external temperatures. Explorer IV, launched on July 26, was intended
to study radiation and temperature data. A lunar probe, ABLE I, was intended
to measure radiation, magnetic fields of Earth and the Moon, density
of micrometeoric matter, and internal temperatures. A four-stage rocket
was used in the launch. However, a turbo-pump failed and the liquid oxygen
pump stopped, resulting in a failed mission. On October 10, Pioneer I
was launched by an ABLE vehicle. First and second stage velocity was less than desired and the probe did not leave Earth orbit. Attempts to attain
escape velocity were unsuccessful. On December, a Jupiter boost vehicle
was used to launch Juno II, with Pioneer III as the payload. Escape velocity
was reached and Pioneer III left Earth's atmosphere. Failed launches,
such as those of Vanguard boost vehicles and several Explorer satellites,
also added to scientific knowledge.
Saturn:
A Giant Thrust into Space
1962
Color, Sound, 10 min
High-Res DVD ID No.: 20070030961
- Film Description
- The film provides
an introduction and overview of the Saturn launch vehicle. It is designed
with stages to drop off as fuel is spent. There may be two, three, or
four stages, depending on the payload. The Saturn rocket will be used
to send Apollo missions to the Moon and back. Guidance systems and booster
engine rockets are based on proven mechanisms. Scale models are used
to test the engines. Hardware, airframes, guidance systems, instrumentation,
and the rockets are produced at sites throughout the country. The engines
go to Marshall Space Flight Center for further tests. After partial assembly,
the vehicle is shipped to Cape Canaveral in large pieces where it is
assembled using specially built equipment and structures. Further trials
are performed to assure successful launches.
Unitary
Wind Tunnel Tests of 30-Degree Conical Ribbon Parachute and a Rotofoil Parachute
Towed in the Wake of a Conical Nosed Cylindrical Body
1962
Silent, Black & White, 24.5min.
High-Res DVD ID No.: 20070030965
- Film Description
- Multiple wind tunnel
test trials were conducted on a 30 degree conical ribbon parachute with
porosities of 30, 27, and 24 percent. Variables were Mach number, dynamic
pressure, towline length, and coefficient of drag. A Rotofoil parachute
having a porosity of approximately 24 percent was tested, but failed
after about 30 seconds of operation at a Mach number of 1.8 All of the
parachutes had a nominal diameter and shroud line length of 10 inches.
Drag coefficients were based on the area of a circle having a diameter
two-thirds of the nominal parachute diameter.
Tests
of Dynamic Scale Model of Gemini Capsule in the Langley 20-Foot Free-Spinning
Tunnel
1962
Silent, Black & White, 27min
High-Res DVD ID No.: 20070030989
- Film Description
- The film shows three
spin tunnel tests of a 1/20 scale model of the Gemini capsule. In the
first test, the capsule spins freely. In tests 2 and 3, a drogue parachute
is attached to the capsule.
Preliminary
Landing Tests of a 1/6-Scale Dynamic Model of a Lunar Excursion Vehicle
1962
Silent, Black & White, 6.5min.
High-Res DVD ID No.: 20070030974
- Film Description
- The film shows 21
trials made on 8 days of the scale Model 413 lunar landing vehicle. Attitudes
tested were a pitch of 0, -15, or 15 degrees and yaw of 0 or 45 degrees.
Velocities were vertical 10 and horizontal 10, though two trials were
simple vertical drops.
Unitary
Plan Wind Tunnel Tests of Cook Technological Center Parachutes in the Wake of
a Conical-Nosed Cylindrical Body Having a Base Diameter of 2.375-Inches (Part
5 of 6)
1962
Silent, Black & White, 17.5 min.
High-Res DVD ID No.: 20070030960
- Film Description
- The film depicts
two tests of a flat roof, conical inlet canopy parachute. The first test
is a series of wind tunnel trials with a flat circular ribbon roof of
22 percent porosity. The second test is a single series of wind tunnel
trials with a flat circular ribbon roof of 25 percent porosity. Variables
for both trials include Mach number, dynamic pressure, longitudinal separation
distances (x/d), and drag coefficient C(sub d).
Aerodynamic
Heating and Deceleration During Entry into Planetary Atmospheres
1962
Sound, Black & White, 29min.
High-Res DVD ID No.: 20070030962
- Film Description
- Dr. Chapman's lecture
examines the physics behind spacecraft entry into planetary atmospheres.
He explains how scientists determine if a planet has an atmosphere and
how scientists can compute deceleration when the atmospheric conditions
are unknown. Symbols and equations used for calculations for aerodynamic
heating and deceleration are provided. He also explains heat transfer
in bodies approaching an atmosphere, deceleration, and the use of ablation
in protecting spacecraft from high temperatures during atmospheric entry.
Launch
Vehicle Dynamics Demonstrator Model
1963
Silent, Color, 3min.
High-Res DVD ID No.: 20070030984
- Film Description
- The effect of vibration
on launch vehicle dynamics was studied. Conditions included three modes
of instability. The film includes close up views of the simulator fuel
tank with and without stability control.
Investigation
of the Landing Characteristics of a Re-entry Vehicle Having a Canted Multiple
Air Bag Load Alleviation System
1963
Silent, Color, 3min.
Supplement to NASA-TN-D-1934 (19630008895); High-Res DVD ID No.: 20070030986
- Film Description
- An investigation
was made to determine the landing-impact characteristics of a reentry
vehicle having a multiple-air-bag load-alleviation system. A 1/16-scale
dynamic model having four canted air bags was tested at flight-path angles
of 90 degrees (vertical), 45 degrees, and 27 degrees for a parachute
or paraglider vertical letdown velocity of 30 feet per second (full scale).
Landings were made on concrete at attitudes ranging from -l5 degrees
to 20 degrees. The friction coefficient between the model heat shield
and the concrete was approximately 0.4. An aluminum diaphragm, designed
to rupture at 10.8 pounds per square inch gage, was used to maintain
initial pressure in the air bags for a short time period.
Aeroelastic
Tests of an Eight Percent Scale Saturn C-1 Block II
1963
Sound, Color, 5.25min.
High-Res DVD ID No.: 20070030987
- Film Description
- Buffet and flutter
characteristics of Saturn Apollo mission were studied using a dynamically
scaled model. The model was built around a central aluminum tube for
scaled stiffness distribution and strength to resist loads imposed during
testing. Styrofoam sections attached to the core provided the correct
external contours. Lead weights were added for correct mass distribution.
An electromagnetic shaker was used to excite the model in its flexible
modes of vibration during portions of the test. The model was supported
on a sting, mounted by leaf springs, cables and torsion bars. The support
system provided for simulating the full scale rigid body pitch frequency
with minimum restraint imposed on elastic deflections. Bending moments
recorded by sensors on the aluminum tube. Several modified nose configurations
were tested: The basic configuration was tested with and without a flow
separator disk on the escape rocket motor, tests also were made with
the escape tower and rocket motor removed completely. For the final test, the Apollo capsule was replaced with a Jupiter nose cone. The test
program consisted of determining model response throughout the transonic
speed range at angles of attack up to 6 degrees and measuring the aerodynamic
damping over the same range for the basic model and the modified configurations.
Signals from the model pickup were recorded on tape for later analysis.
The data obtained were used to estimate bending moments that would be
produced on the full-scale vehicle by aerodynamic forces due to buffeting.
Apollo-Lunar
Orbital Rendezvous Technique
1963
Sound, Color, 5.5min.
High-Res DVD ID No.: 20070030988
- Film Description
- The film shows artists
rendition of the spacecrafts, boosters, and flight of the Apollo lunar
missions. The Apollo spacecraft will consist of three modules: the manned
Command Module; the Service Module, which contains propulsion systems;
and the Lunar Excursion Module (LEM) to carry astronauts to the moon
and back to the Command and Service Modules. The spacecraft will be launched
via a three-stage Saturn booster. The first stage will provide 7.5 million
pounds of thrust from five F-1 engines for liftoff and initial powered
flight. The second stage will develop 1 million pounds of thrust from
five J-2 engines to boost the spacecraft almost into Earth orbit. Immediately
after ignition of the second stage, the Launch Escape System will be
jettisoned. A single J-2 engine in the S4B stage will provide 200,000
pounds of thrust to place the spacecraft in an earth parking orbit. It
also will be used to propel the spacecraft into a translunar trajectory,
then it will separate from the Apollo Modules. Onboard propulsion systems will be used to insert the spacecraft into lunar orbit. Two astronauts
will enter the LEM, which will separate from the command and service
modules. The LEM will go into elliptical orbit and prepare for landing.
The LEM will lift off of the Moon's surface to return to the Command
and Service Modules, and most likely be left in lunar orbit. After leaving
the Moon's orbit, and shortly before entering Earth's orbit, the Service
Module will be ejected. The Command Module will be oriented for reentry
into the Earth's atmosphere. A drogue parachute will deploy at approximately
50,000 feet, followed by the main parachute system for touchdown.
Rendezvous
Docking Simulator
1963
Color, 5min.
High-Res DVD ID No.: 20070030983
- Film Description
- The simulation demonstrated
linear and gimbal motions of the capsule and a Gemini-Agena docking.
Landing
Characteristics of a Re-entry Vehicle with a Passive Landing System for Impact
Alleviation
1963
Silent, Color, 4.5min.
Supplement to NASA-TN-D-2035 (19640002968); High-Res DVD ID No.: 20070030981
- Film Description
- An experimental
investigation was made to determine the landing characteristics of a
1/8-scale dynamic model of a reentry vehicle using a passive landing
system to alleviate the landing-impact loads. The passive landing system
consisted of a flexible heat shield with a small section of aluminum
honeycomb placed between the heat shield and the crew compartment at
the point that would be the first to contact the landing surface. The
model was landed on concrete and sand landing surfaces at parachute letdown
velocities. The investigations simulated a vertical velocity of 30 ft/sec
(full scale), horizontal velocities of 0, 15, 30, 40, and 50 ft/sec (full
scale), and landing attitudes ranging from -30 degrees to 20 degrees.
The model investigation indicated that stable landings could be made
on a concrete surface at horizontal velocities up to about 30 ft/sec,
but the stable landing-attitude range at these speeds was small. The
aluminum honeycomb bottomed occasionally during landings on concrete.
When bottoming did not occur, maximum normal and longitudinal accelerations at the center of gravity
of the vehicle were approximately 50g and 30g, respectively.
Performance
Characteristics of a Preformed Elliptical Parachute at Altitudes between 200,000
and 100,000 Thousand Feet Obtained by In-Flight Photography
1963
Silent, Color, 35.5min.
Supplement to NASA-TN-D-2183 (19640005308); High-Res DVD ID No.: 20070030980
- Film Description
- The performance
characteristics of a pre-formed elliptical parachute at altitudes between
200,000 and 100,000 feet were obtained by means of in-flight photography.
The tests demonstrate that this type of parachute will open at altitudes
of about 200,000 feet if conditions such as twisting of the suspension
lines or draping of the suspension lines over the canopy do not occur.
Drag-coefficient values between 0.6 and 0.8 were found to be reasonable
for this type of parachute system in the altitude range between 200,000
and 100,000 feet.
Dynamic
Model Investigation of a 1/20 Scale Gemini Spacecraft in the Langley Spin Tunnel
1963
Silent, Black & White, 10.5min
Supplement to NASA-TN-D-2191 (19640010368); High-Res DVD ID No.: 20070030985
- Film Description
- The investigation
was conducted in the Langley spin tunnel. The tunnel is an atmospheric
wind tunnel with a vertically rising airstream in the test section and
a maximum airspeed of approximately 90 feet per second. For this investigation,
the model was hand launched into the vertically rising airstream. At
times the model, both with and without a drogue parachute, was launched
gently with as little disturbance as possible to determine what motions
of the spacecraft were self-excited. At other times, the spacecraft with
pre-deployed drogue parachute was launched into various spinning motions
to determine the effectiveness of the drogue parachute in terminating
these spinning motions. During drogue-parachute deployment tests, the
spacecraft was launched into various spinning and tumbling motions and
the drogue parachute was deployed. The motions of the model were photographed
with a motion-picture camera, and some of the film records were read
to obtain typical time histories of the model motion. The angles of attack indicated in the time histories presented are believed to be accurate
within +/-1 degree. The mass and dimensional characteristics of the dynamic
model are believed to be measured to an accuracy of: +/-1 percent for
the weight, +/-1 percent for z(sub cg)/d, +/-15 percent for x (sub cg),
and +/-5 percent for the moments of inertia. The towline and bridle-line
lengths were simulated to an accuracy of +/-1 foot full scale.
Characteristics
of a Lunar Landing Configuration Having Various Multiple-Leg Landing-Gear Arrangements
1963
Silent, Color, 15min.
Supplement to NASA-TN-D-2027 (19640005067); High-Res DVD ID No.: 20070030982
- Film Description
- An experimental
investigation has been made of some lunar-landing characteristics of
a 1/6-scale dynamic model of a landing module having multiple-leg landing-gear
systems. Symmetric four-point and five-point systems and an asymmetric
four-point system were investigated. The landing-gear legs were inverted
tripod arrangements having a telescoping main strut which incorporated
a yielding-metal strap for energy dissipation, hinged V-struts, and circular
pads. The landing tests were made by launching a free model onto an impenetrable
hard surface (concrete) and onto a powdered-pumice overlay of various
depths. Landing motion and acceleration data were obtained for a range
of touchdown speeds, touchdown speeds, touch attitudes, and landing-surface
conditions. Symmetric four-point and five-point systems and an Maximum
normal acceleration experienced at the module center of gravity during
landings on hard surface or pumice was 2g (full-scale lunar value in
terms of earth's gravity) over a wide range of touchdown conditions. Maximum angular acceleration experienced was 12-1/2 radians/sec(exp
2) and maximum longitudinal acceleration was 1-3/4 g. The module was
very stable with all gear configurations during landings on hard surface
(coefficient of friction, microns=0.4) at all conditions tested. Some
overturn instability occurred during landings on powdered pumice (microns=0.7
to 1.0) depending upon flight path, pitch and yaw attitude, depth of
pumice, surface topography, and landing-gear configuration. The effect
of stability of roll attitude for the limited amount of roll-attitude
landing data obtained was insignificant. Compared with the four-point
system, the five-point system with equal maximum gear radius increased
landing stability slightly and improved the static stability for subsequent
lunar launch. A considerable increase in landing stability in the direction
of motion was obtained with an asymmetric four-point gear having two
pads offset to increase gear radius by 33 percent in the direction of
horizontal flight.
Blast
Effects of Twin Variable-Cant Rocket Nozzles on Visibility During Landing on
a Particle-Covered Surface
1964
Silent, Black and White, 14.5min.
Supplement to NASA-TN-D-2455 (19650002904); High-Res DVD ID No.: 20070030964
- Film Description
- A limited investigation
has been conducted to determine the jet-blast effect of twin variable-cant
supersonic nozzles. These tests were made to examine the result of using
canted main rocket engines to sweep the blast debris outward from the
proposed landing area of a rocket-powered vehicle making a vertical approach
to a touchdown. Cant angles from 0 degrees to 75 degrees, at intervals
of 15 degrees, were tested at low ambient pressure and at atmospheric
ambient pressure. Nozzle chamber pressures used were 400 psi and 2000
psi.
Dynamic
Model Investigation of the Landing Characteristics of a Manned Spacecraft
1964
Silent, Color, 6min.
Supplement to NASA-TN-D-2497 (19650007935); High-Res DVD ID No.: 20070030978
- Film Description
- Investigations were
made to study the water-landing and certain grounds-surface landing characteristics
of a Gemini spacecraft model. The water landing experiments were made
by simulating paraglider and parachute letdowns with two 1/6- scale model
configurations. Parameters included various combinations of attitude,
horizontal speed, vertical speed, and landing skids extended and retracted.
Investigations were made in calm water and in waves. The paraglider landings
at horizontal speeds of 63 feet per second (19.8 m/sec) which resulted
in a noseover or tumbling shortly after initial water contact. The maximum
longitudinal acceleration of the model in calm water was about 14g units,
and the maximum angular acceleration was 66 radians per second squared.
In the parachute landings with the heat shield forward, the model skidded
along the water surface on the heat shield. Parachute landings with the
small end forward resulted in behavior similar to that of the paraglider
landings. The ground-surface landings were made with a 1/3-scale model by simulating a parachute letdown with braking rockets,
which were fired prior to touchdown to dissipate vertical velocity. In
these landings, control of timing and aligning the rockets on the model
was very critical, and violent behavior resulted when either rocket alignment
or timing was in error. In the landings that were correctly controlled,
the model either remained upright or slowly rolled over on its side.
Model
Test of Mars Entry Vehicles in Langley Spin Tunnel
1964
Silent, Black & White, 3.5min
High-Res DVD ID No.: 20070030979
- Film Description
- Four models of Mars
entry vehicles tested were a sphere with cg=35 percent (measured in percent
of diameter from surface); Apollo with cg=16 percent (measured in percent
of maximum diameter rearward of heat shield); a 103-degree cone with
cg=20 percent (measured in percent of maximum diameter rearward of small
end); and a tension structure: cg=25 percent (measured in percent of
maximum diameter rearward of small end).
Simulator
Study of Lunar Orbit Establishment
1965
Silent, Black & White, 6.75min.
High-Res DVD ID No.: 20070030976
- Film Description
- The film was made
using the Lunar Orbit and Landing Approach Simulator (LOLA). It represents
the view an astronaut would see if he were looking toward the lunar horizon
just prior to and during retrofire for orbit establishment. During this
period the astronaut is essentially flying backward, therefore the lunar
surface features appear to be moving away during the flight.
Model
Investigation of Technique for Full Scale Landing Impact Tests at Simulated Lunar
Gravity
1965
Silent, Color, 4min.
Supplement to NASA-TN-D-2586 (19650008606); High-Res DVD ID No.: 20070030977
- Film Description
- An investigation
of a 1/6-scale dynamic model has been made to develop and evaluate a
technique for conducting full-scale landing-impact tests at simulated
lunar gravity. Landings were made at touchdown pitch attitudes of -15
degrees, 0 degrees, and 15 degrees. All landings were made with two gear
pads forward and at a roll attitude of 0 degrees. Both roll and yaw attitudes
were constrained. Vertical landing speed was varied from 5 to 15 feet
per second (1.5 to 4.6 m/s) and horizontal speed was varied from 0 to
10 feet per second (0 to 3.0 m/s). Most of the landings were made at
a vertical and horizontal speed of 10 feet per second or 3.0 m/s (45
degree flight-path angle) while pitch attitude and surface characteristics,
friction and topography, were varied. These parameters were investigated
with the free-body earth-gravity and the simulated lunar-gravity test
techniques. The landings were made at a model mass corresponding to a
full-scale lunar weight (force due to gravity) of 1,440 pounds (6.41
kN) or an earth weight of 8,640 pounds (38.4 kN).
Landing
Characteristics of the Apollo Spacecraft with Deployed Heat Shield Impact Attenuation
Systems
1965
Silent, Color, 16min.
Supplement to NASA-TN-D-3059 (19660005612); High-Res DVD ID No.: 20070030975
- Film Description
- An experimental
investigation was made to determine the landing characteristics of a
1/4-scale dynamic model of the Apollo spacecraft command module using
two different active (heat shield deployed prior to landing) landing
systems for impact attenuation. One landing system (configuration 1)
consisted of six hydraulic struts and eight crushable honeycomb struts.
The other landing system (configuration 2), consisted of four hydraulic
struts and six strain straps. Tests made on water and the hard clay-gravel
composite landing surfaces simulated parachute letdown (vertical) velocities
of 23 ft/sec (7.0 m/s) (full scale). Landings made on the sand landing
surface simulated vertical velocities of 30 ft/sec (9.1 m/s). Horizontal
velocities of from 0 to 50 ft/sec (15 m/s) were simulated. Landing attitudes
ranged from -30'degrees to 20 degrees, and the roll attitudes were O
degrees, 90 degrees, and 180 degrees. For configuration 1, maximum normal
accelerations at the vehicle center of gravity for landings on water,
sand, and the hard clay-gravel composite surface were 9g, 20g, and 18g, respectively.
The maximum normal center-of-gravity acceleration for configuration 2
which was landed only on the hard clay-gravel landing surface was approximately
19g. Accelerations for configuration 2 were generally equal to or lower
than accelerations for configuration 1 and normal.
Dynamic
Model Investigation of the Rough-Water Landing Characteristics of a Spacecraft
1966
Silent, Color, 3.5min.
Supplement to NASA-TN-D-3774 (19670013952); High-Res DVD ID No.: 20070031004
- Film Description
- The investigation
was made to study the rough-water landing characteristics of a Gemini
type of spacecraft. The investigations were made with a 1/6-scale dynamic
model in a simulated sea state 4 rough water. Parachute letdown landings
were simulated with the model at various yaw angles and horizontal velocities.
The vertical velocity and landing attitude remained constant. The range
of maximum lateral and longitudinal acceleration was from about 3-1/2g
to 16g while that for the maximum normal acceleration was from lg to
15g. The range of maximum angular acceleration was from about 0 to 190
radians per second(exp 2). The smoothest behavior and the lowest angular
acceleration occurred at the 90 degree yaw angle. The normal acceleration
was near minimum at this condition.
The
Lunar Orbiter: A Spacecraft to Advance Lunar Exploration
1966
Sound, Color, 7.5min.
High-Res DVD ID No.: 20070031014
- Film Description
- The film describes
the Lunar Orbiter's mission to photograph landing areas on the Moon.
The Orbiter will be launched from Cape Kennedy using an Atlas Agena booster
rocket. Once it is boosted in a trajectory toward the Moon, the Orbiter
will deploy two-way earth communication antennas and solar panels for
electricity. Attitude control jets will position the solar panels toward
the sun and a tracker for a fix on its navigational star. The Orbiter
will be put in an off-center orbit around the Moon where it will circle
from four to six days. Scientists on Earth will study the effects of
the Moon's gravitational field on the spacecraft, then the orbit will
be lowered to 28 miles above the Moon's surface. Engineers will control
the Orbiter manually or by computer to activate two camera lenses. The
cameras will capture pictures of 12,000 square miles of lunar surface
in 25 and 400 square mile increments. Pictures will be sent back to Earth
using solar power to transmit electrical signals. The signals will be
received by antennas at Goldstone, CA, and in Australia and Spain. Incoming photographic
data will be electronically converted and processed to produce large-scale
photographic images. The mission will be directed from the Space Flight
Operations Facility in Pasadena, CA by NASA and Boeing engineers. After
the photographic mission, the Orbiter will continue to circle the Moon
providing information about micrometeoroids and radiation in the vicinity.
Scaled
Lunar Module Jet Erosion Experiments
1966
Silent, Color, 5.1min.
Supplement to NASA-TN-D-5051 (19690013268); High-Res DVD ID No.: 20070031010
- Film Description
- An experimental
research program was conducted on the erosion of particulate surfaces
by a jet exhaust. These experiments were scaled to represent the lunar
module (LM) during landing. A conical cold-gas nozzle simulating the
lunar module nozzle was utilized. The investigation was conducted within
a large vacuum chamber by using gravel or glass beads as a simulated
soil. The effects of thrust, descent speed, nozzle terminal height, particle
size on crater size, and visibility during jet erosion were determined.
Dynamic
Model Investigation of Water Pressures and Accelerations Encountered During Landings
of the Apollo Spacecraft
1967
Silent, Color, 5.7min.
Supplement to NASA-TN-D-3980 (19670027235); High-Res DVD ID No.: 20070031001
- Film Description
- An experimental
investigation was made to determine impact water pressures, accelerations,
and landing dynamics of a 1/4-scale dynamic model of the command module
of the Apollo spacecraft. A scaled-stiffness aft heat shield was used
on the model to simulate the structural deflections of the full-scale
heat shield. Tests were made on water to obtain impact pressure data
at a simulated parachute letdown (vertical) velocity component of approximately
30 ft/sec (9.1 m/sec) full scale. Additional tests were made on water,
sand, and hard clay-gravel landing surfaces at simulated vertical velocity
components of 23 ft/sec (7.0 m/sec) full scale. Horizontal velocity components
investigated ranged from 0 to 50 ft/sec (15 m/sec) full scale and the
pitch attitudes ranged from -40 degrees to 29 degrees. Roll attitudes
were O degrees, 90 degrees, and 180 degrees, and the yaw attitude was
0 degrees.
Flight
Test of 31.2 Diameter Modified Ringsail Parachute Deployed at Mach 1.39, Dynamic
Pressure 11 Pounds per Square Foot
1967
Silent, Color, 3.5min.
Supplement to NASA-TM-X-1414 (19670022936); High-Res DVD ID No.: 20070031000
- Film Description
- A 31.2-foot (9.51
meter) nominal diameter (reference area 764 ft(exp 2) (71.0 m(exp 2))
ringsail parachute modified to provide 15-percent geometric porosity
was flight tested while attached to a 201-pound mass (91.2 kilogram)
instrumented payload as part of the rocket launch portion of the NASA
Planetary Entry Parachute Program (PEPP). The parachute deployment was
initiated by the firing of a mortar at a Mach number of 1.39 and a dynamic
pressure of 11.0 lb/ft(exp 2) (527 newtons/m(exp 2)) at an altitude of
122,500 feet (37.3 kilometers). The parachute deployed to suspension-line
stretch (snatch force) in 0.35 second, and 0.12 second later the drag
force increase associated with parachute inflation began. The parachute
inflated in 0.24 second to the full-open condition for a total elapsed
opening time of 0.71 second. The maximum opening load of 3970 pounds
(17,700 newtons) came at the time the parachute was just fully opened.
During the deceleration period, the parachute exhibited an average drag
coefficient of 0.52 and oscillations of the parachute canopy were less than 5 degrees. During
the steady-state terminal descent portion of the test period, the average
effective drag coefficient (based on vertical descent velocity) was 0.52.
Performance
of 26 Meter Diameter Ringsail Parachute in a Simulated Martian Environment
1967
Silent, Color, 2.5min.
Supplement to NASA-TM-X-1356 (19670009951); High-Res DVD ID No.: 20070031003
- Film Description
- Inflation, drag,
and stability characteristics of an 85.3-foot (26-meter) nominal diameter
ringsail parachute deployed at a Mach number of 1.15 and at an altitude
of 132,600 feet (40.42 kilometers) were obtained from the first flight
test of the Planetary Entry Parachute Program. After deployment, the
parachute inflated to the reefed condition. However, the canopy was unstable
and produced low drag in the reefed condition. Upon disreefing and opening
to full inflation, a slight instability in the canopy mouth was observed
initially. After a short time, the fluctuations diminished and a stable
configuration was attained. Results indicate a loss in drag during the
fluctuation period prior to stable inflation. During descent, stability
characteristics of the system were such that the average pitch-yaw angle
from the local vertical was less than 10 degrees. Rolling motion between
the payload and parachute canopy quickly damped to small amplitude.
Low
Speed Dynamic Model Investigation of Apollo Command Module Configuration in the
Langley Spin Tunnel
1967
Silent, Black & White, 4.5min.
Supplement to NASA-TN-D-3888 (19670023693); High-Res DVD ID No.: 20070031002
- Film Description
- An investigation
has been conducted in the Langley spin tunnel to determine the dynamic
stability of the Apollo command module at low subsonic speeds, both with
and without drogue parachutes. The investigation consisted of tests to
determine (1) the dynamic stability of the command module alone, (2)
the motion of the command module during the deployment of a drogue parachute,
(3) the effect of various drogue-parachute configurations on the stability
of the command module, and (4) the effect of modifications to the command
module to prevent an apex-forward trim condition.
Flight
Test of a 30-Foot Nominal-Diameter Disk-Gap-Band Parachute Deployed at Mach 1.56
and Dynamic Pressure of 11.4 Pounds per Square Foot
1967
Silent, Color, 3min.
Supplement to NASA-TM-X-1451 (19670026287); High-Res DVD ID No.: 20070030999
- Film Description
- A 30-foot (9.1 meter)
nominal-diameter disk-gap-band parachute (reference area 707 sq ft (65.7
m(exp 2)) was flight tested with a 200-pound (90.7 kg) instrumented payload
as part of the NASA Planetary Entry Parachute Program. A deployment mortar
ejected the test parachute when the payload was at a Mach number of 1.56
and a dynamic pressure of 11.4 lb/sq ft (546 newtons per m 2 ) at an
altitude of 127,500 feet (38.86 km). The parachute reached suspension
line stretch in 0.37 second resulting in a snatch force loading of 1270
pounds (5650 N). Canopy inflation began 0.10 second after line stretch.
A delay in the opening process occurred and was apparently due to a momentary
interference of the glass-fiber shroud used in packing the parachute
bag in the mortar. Continuous canopy inflation began 0.73 second after
initiation of deployment and 0.21 second later full inflation was attained
for a total elapsed time from mortar fire of 0.94 second. The maximum
opening load of 3915 pounds (17,400 newtons) occurred at the time the canopy was first fully opened. The parachute exhibited an average
drag coefficient of 0.52 during the deceleration period and pitch-yaw
oscillations of the canopy were less than 5 degrees. During the steady-state
descent portion of the test period, the average effective drag coefficient
was about 0.47 (based on vertical descent velocity and total system weight).
Flight
Tests of a 40-Foot Nominal Diameter Modified Ringsail Parachute Deployed at Mach
1.64 and Dynamic Pressure of 9.1 Pounds Per Square Foot
1967
Silent, Color, 3.3min.
Supplement to NASA-TM-X-1484 (19680002451); High-Res DVD ID No.: 20070030998
- Film Description
- A ringsail parachute,
which had a nominal diameter of 40 feet (12.2 meters) and reference area
of 1256 square feet (117 m(exp 2)) and was modified to provide a total
geometric porosity of 15 percent of the reference area, was flight tested
as part of the rocket launch portion of the NASA Planetary Entry Parachute
Program. The payload for the flight test was an instrumented capsule
from which the test parachute was ejected by a deployment mortar when
the system was at a Mach number of 1.64 and a dynamic pressure of 9.1
pounds per square foot (43.6 newtons per m(exp 2)). The parachute deployed
to suspension line stretch in 0.45 second with a resulting snatch force
of 1620 pounds (7200 newtons). Canopy inflation began 0.07 second later
and the parachute projected area increased slowly to a maximum of 20
percent of that expected for full inflation. During this test, the suspension
lines twisted, primarily because the partially inflated canopy could
not restrict the twisting to the attachment bridle and risers. This twisting of the suspension lines hampered canopy inflation at a time when
velocity and dynamic-pressure conditions were more favorable.
Summary
of Attached Inflatable Decelerator (AID) Development
1968
Silent, Color, 6min.
High-Res DVD ID No.: 20070030992
- Film Description
- Attached inflatable
decelerators (AID) were tested in an environmental chamber, a spin tunnel,
and a wind tunnel. Deployment tests were conducted in environmental chamber
to examine guided and unguided water alcohol vapor inflation. Subsonic
performance tests were conducted in the spin tunnel. The full-scale wind
tunnel was used for AID gust and supersonic performance tests. The supersonic
tests were conducted at Mach number 3.0 with 12 ounces of fluid and Mach
number 2.2 with six ounces of fluid.
Flight
Test of a 30-Foot Nominal Diameter Cross Parachute Deployed at a Mach Number
of 1.57 and a Dynamic Pressure of 9.7 Pounds per Square Foot
1968
Silent, Color, 3.5min
Supplement to NASA-TM-X-1542 (19680012309); High-Res DVD ID No.: 20070030994
- Film Description
- A 30-foot (9.1-meter)
nominal-diameter cross-type parachute with a cloth area (reference area)
of 709 square feet (65.9 square meters) was flight tested in the rocket-launched
portion of the NASA Planetary Entry Parachute Program (PEPP). The test
parachute was ejected from an instrumented payload by means of a mortar
when the system was at a Mach number of 1.57 and a dynamic pressure of
9.7 psf. The parachute deployed to suspension-line stretch in 0.44 second
with a resulting snatch-force loading of 1100 pounds (4900 newtons),
Canopy inflation began at 0.58 second and a first full inflation was
achieved at approximately 0.77 second. The maximum opening load occurred
at 0.81 second and was 4255 pounds (18,930 newtons). Thereafter, the
test item exhibited a canopy-shape instability in that the four panel
arms experienced fluctuations, a "scissoring" type of motion predominating throughout the test period. Calculated values of
axial-force coefficient during the deceleration portion of the test varied
between 0.35 and 1.05, with an average value of 0.69. During descent,
canopy-shape variations had reduced to small amplitudes and resultant
pitch-yaw angles of the payload with respect to the local vertical averaged
less than 10 degrees. The effective drag coefficient, based on the vertical
components of velocity and acceleration during system descent, was 0.78.
Flight
Test of a 40-Foot Nominal-Diameter Disk-Gap-Band Parachute Deployed at a Mach
Number of 1.91 and a Dynamic Pressure of 11.6 Pounds per Square Foot
1968
Silent, Color, 5min.
Supplement to NASA-TM-X-1575 (19680014773); High-Res DVD ID No.: 20070030991
- Film Description
- A 40-foot (12.2
meter) nominal-diameter disk-gap-band parachute was flight tested as
part of the NASA Supersonic Planetary Entry Decelerator Program (SPED-I).
The test parachute was ejected by a deployment mortar from an instrumented
payload at an altitude of 140,000 feet (42.5 kilometers). The payload
was at a Mach number of 1.91 and the dynamic pressure was 11.6 pounds
per square foot (555 newtons per square meter) at the time the parachute
deployment mortar was fired. The parachute reached suspension line stretch
in 0.43 second with a resultant snatch force loading of 1990 pounds (8850
newtons). The maximum parachute opening load of 6500 pounds (28,910 newtons)
came 0.61 second later at a total elapsed time from mortar firing of
1.04 seconds. The first full inflation occurred at 1.12 seconds and stable
inflation was achieved at approximately 1.60 seconds. The parachute had
an average axial-force coefficient of 0.53 during the deceleration period.
During the steady-state descent portion of the flight test, the average effective drag coefficient was also 0.53 and pitch-yaw oscillations
of the canopy averaged less than 10 degrees in the altitude region above
100,000 feet (30.5 meters).
Excerpts
from Test Films: Langley Impacting Structures Facility, Lunar Module
1968
Sound, Color, 3min.
High-Res DVD ID No.: 20070030993
- Film Description
- The film includes
excerpts from three studies: (1) Landing characteristics of a dynamic
model of the HL-10 manned lifting entry vehicle, conducted by Sandy M.
Stubbs, in which the vehicle landed on water at horizontal velocities
of 240- and 250-feet per second (ft/sec). (2) Dynamic model investigation
of water pressures and accelerations encountered during landings of the
Apollo spacecraft conducted by Sandy M. Stubbs, in which horizontal velocity
was 50 ft/sec. and pitch attitude was -12 and -28 degrees. (3) Comparative
landing impact tests of a 1/6-scale model as a free body under earth
gravity and a tethered full-scale lunar module on the Lunar Gravity Simulator.
Landing 8 is shown, with a vertical velocity of 10 ft/sec. and a horizontal
velocity of 8 ft/sec. Motion pictures were taken at 400 and 64 pps.
Performance
of a 19.7 Meter Diameter Disk-Gap-Band Parachute in a Simulated Martian Environment
1968
Silent, Color, 4.25min.
Supplement to NASA-TM-X-1499 (19680004328); High-Res DVD ID No.: 20070030997
- Film Description
- Inflation and drag
characteristics of a 64.7-foot (19.7-meter) nominal-diameter disk-gap-band
parachute deployed at a Mach number of 1.59 and a dynamic pressure of
11.6 psf (555 newtons per m(exp 2)) were obtained from the second balloon-launched
flight test of the Planetary Entry Parachute Program. In addition, parachute
stability characteristics during the subsonic descent portion of the
test are presented. After deployment, the parachute rapidly inflated
to a full condition, partially collapsed, and then reinflated to a stable
configuration. After reinflation, an average drag coefficient of about
0.55 based on nominal surface area was obtained. The parachute exhibited
good stability characteristics during descent. The only major damage
to the parachute during the test was the tearing of two canopy panels;
a loss of less than 0.5 percent of nominal surface area resulted.
Performance
of a Towed, 48-Inch-Diameter (121.92) Ballute Decelerator Tested in Free-Flight
Mach Numbers from 4.2 to 0.4
1968
Silent, Color, 2min.
Supplement to NASA-TN-D-4943 (19690008066); High-Res DVD ID No.: 20070030990
- Film Description
- A ballute decelerator
inflated by ram air was tested in free flight to determine the inflation,
drag, and stability characteristics. The decelerator had a 40-inch (101.6-cm)
envelope equatorial diameter and a 10-percent burble fence. It was towed
13.5 feet (4.12 m) aft of a cone-cylinder-flare payload with a maximum
diameter of 18.21 inches (46.25 cm). The decelerator was deployed at
an altitude of 115,000 feet (35.1 km) at a velocity of 4400 ft/sec (1342
m/sec) and inflated at a Mach number of 4.2 and a freestream dynamic
pressure of 163 lb/ft(exp 2) (7.8 kN/m(exp 2)).
Performance
of a 16.6 Meter Diameter Cross Parachute in a Simulated Martian Environment
1968
Silent, Color, 3min.
Supplement to NASA-TM-X-1543 (19680012364); High-Res DVD ID No.: 20070030995
- Film Description
- Inflation and drag
characteristics of a 54.4-foot (16.6 meter) nominal-diameter cross parachute,
deployed at a Mach number of 1.65 and a dynamic pressure of 12.68 lb/sq
f t (607.1 N/m(exp2)), were obtained from the fourth balloon-launched
flight test of the Planetary Entry Parachute Program (PEPP). After deployment,
the parachute quickly inflated to a full condition, partially collapsed,
and then gradually reinflated while undergoing rapid oscillations between
over-inflation and under-inflation. The oscillations began while the
parachute was still at supersonic speeds and continued to low subsonic
speeds well below an altitude of 90,000 feet (27.4 km). These canopy
instabilities produced large cyclic variations in the parachute's drag
coefficient. The average value of drag coefficient was about 0.8 to 0.9
at subsonic speeds and slightly lower at supersonic speeds. These drag
coefficient values were based on the actual fabric surface area of the
parachute canopy. The parachute sustained minor damage consisting of two canopy tears and abrasions and tears on the riser line. It is believed
that this damage did not produce a significant change in the performance
of the parachute.
Performance
of a 16.6 Meter Diameter Modified Ringsail Parachute in a Simulated Martian Environment
1968
Silent, Color, 4.2min.
Supplement to NASA-TM-X-1500 (19680004623); High-Res DVD ID No.: 20070030996
- Film Description
- Inflation, drag,
and stability characteristics of a 54.5 -foot nominal-diameter (16.6-meter)
modified ringsail parachute deployed in the wake of a 15-foot-diameter
(4.6-meter) spacecraft traveling at a Mach number of 1.6 and a dynamic
pressure equal to 11.6 psf (555 N/m(exp 2)) were obtained from the third
balloon-launched flight test of the Planetary Entry Parachute Program.
After deployment, the parachute inflated rapidly to a full condition,
partially collapsed, and reinflated to a stable configuration. After
reinflation, an average drag coefficient near 0.6 based on nominal surface
area was obtained. During descent, an aerodynamic trim angle was observed
in a plane near several torn sails. Amplitude of the trim was approximately
15 degrees and oscillation about trim was less than 11 degrees.
Flight
Test of a 40-Foot Nominal Diameter Disk-Gap-Band Parachute Deployed at a Mach
Number of 2.72 and a Dynamic Pressure of 9.7 Pounds per Square Foot
1968
Silent, Color, 3min.
Supplement to NASA-TM-X-1623 (19680020521); High-Res DVD ID No.: 20070031009
- Film Description
- A 40-foot-nominal-diameter
(12.2 meter) disk-gap-band parachute was flight tested as part of the
NASA Supersonic Planetary Entry Decelerator (SPED-I) Program. The test
parachute was deployed from an instrumented payload by means of a deployment
mortar when the payload was at an altitude of 158,500 feet (48.2 kilometers),
a Mach number of 2.72, and a free-stream dynamic pressure of 9.7 pounds
per foot(exp 2) (465 newtons per meter(exp 2)). Suspension line stretch
occurred 0.46 second after mortar firing and the resulting snatch force
loading was -8.lg. The maximum acceleration experienced by the payload
due to parachute opening was -27.2g at 0.50 second after the snatch force
peak for a total elapsed time from mortar firing of 0.96 second. Canopy-shape
variations occurred during the higher Mach number portion of the flight
test (M greater than 1.4) and the payload was subjected to large amplitude
oscillatory loads. A calculated average nominal axial-force coefficient
ranged from about 0.25 immediately after the first canopy opening to about 0.50 as the canopy attained a steady inflated
shape. One gore of the test parachute was damaged when the deployment
bag with mortar lid passed through it from behind approximately 2 seconds
after deployment was initiated. Although the canopy damage caused by
the deployment bag penetration had no apparent effect on the functional
capability of the test parachute, it may have affected parachute performance
since the average effective drag coefficient of 0.48 was 9 percent less
than that of a previously tested parachute of the same configuration.
Flight
Test of a 40-Foot Nominal Diameter Disk-Gap-Band Parachute Deployed at a Mach
Number of 3.31 and a Dynamic Pressure of 10.6 Pounds per Square Foot
1969
Silent, Color, 3.2min.
Supplement to NASA-TM-X-1924 (19700010021); High-Res DVD ID No.: 20070031012
- Film Description
- A 40-foot-nominal-diameter
(12.2 meter) disk-gap-band parachute was flight tested as part of the
NASA supersonic high altitude parachute experiment (SHAPE) program. The
test parachute (which included an experimental energy absorber in the
attachment riser) was deployed from an instrumented payload by means
of a deployment mortar when the payload was at a Mach number of 3.31
and a free-stream dynamic pressure of 10.6 pounds per square foot (508
newtons per square meter). The parachute deployed properly, the canopy
inflating to a full-open condition at 1.03 seconds after mortar firing.
The first full inflation of the canopy was immediately followed by a
partial collapse with subsequent oscillations of the frontal area from
about 30 to 75 percent of the full-open frontal area. After 1.07 seconds
of operation, a large tear appeared in the cloth near the canopy apex.
This tear was followed by two additional tears shortly thereafter. It
was later determined that a section of the canopy cloth was severely
weakened by the effects of aerodynamic heating. As a result of the damage to the disk area
of the canopy, the parachute performance was significantly reduced; however,
the parachute remained operationally intact throughout the flight test
and the instrumented payload was recovered undamaged.
Flight
Tests Results from Supersonic Deployment of an 18-Foot Diameter (5.49 meter)
Towed Ballute Decelerator
1969
Silent, Color, 3min.
Supplement to NASA-TM-X-1773 (19690017080); High-Res DVD ID No.: 20070031011
- Film Description
- A ram-air-inflated,
towed ballute decelerator having a maximum frontal diameter of 18 feet
(5.49 meters) was deployed during free flight at a Mach number of 3.15
and a dynamic pressure of 38.5 lb/ft(exp 2) (1843.4 newtons/m(exp 2)).
Deployment and extraction of the test ballute were normal but inflation
stopped about 1 second after mortar firing and produced an average plateau
drag force of 1500 pounds (6.7 kN) for about 1 second. Approximately
30 percent of expected total frontal area was obtained.
Deployment
and Performance Characteristics of 5-Foot Diameter (1.5m) Attached Inflatable
Decelerators from Mach Numbers 2.2-4.4
1970
Silent, Color, 4.5min.
Supplement to NASA-TN-D5840 (19700026642); High-Res DVD ID No.: 20070031006
- Film Description
- Deployment characteristics
and steady-state performance data were obtained over the Mach number
range from 2.2 to 4.4 and at angles of attack from 0 degrees to l0 degrees.
All attached inflatable decelerator (AID) models deployed successfully
and exhibited flutter-free performance after deployment. Shock loads
commonly associated with inflation of parachutes during deployment were
not experienced. Force and moment data and ram-air pressure data were
obtained throughout the Mach number range and at angles of attack from
0 degrees to l0 degrees. The high drag coefficient of 1.14 was in good
agreement with the value predicted by the theory used in the design and
indicated other AID shapes may be designed on a rational basis with a
high degree of confidence.
High
Altitude Flight Test of a 40-Foot Diameter (12.2 meter) Ringsail Parachute at
Deployment Mach Number of 2.95
1970
Silent, Color, 3.2min
Supplement to NASA-TN-D-5796 (19700022313); High-Res DVD ID No.: 20070031005
- Film Description
- A 40-foot-nominal-diameter
(12.2-meter) modified ringsail parachute was flight tested as part of
the NASA Supersonic High Altitude Parachute Experiment (SHAPE) program.
The 41-pound (18.6-kg) test parachute system was deployed from a 239.5-pound
(108.6-kg) instrumented payload by means of a deployment mortar when
the payload was at an altitude of 171,400 feet (52.3 km), a Mach number
of 2.95, and a free-stream dynamic pressure of 9.2 lb/sq ft (440 N/m(exp
2)). The parachute deployed properly, suspension line stretch occurring
0.54 second after mortar firing with a resulting snatch-force loading
of 932 pounds (4146 newtons). The maximum loading due to parachute opening
was 5162 pounds (22 962 newtons) at 1.29 seconds after mortar firing.
The first near full inflation of the canopy at 1.25 seconds after mortar
firing was followed immediately by a partial collapse and subsequent
oscillations of frontal area until the system had decelerated to a Mach
number of about 1.5. The parachute then attained a shape that provided full drag area. During the supersonic part of the test, the average axial-force
coefficient varied from a minimum of about 0.24 at a Mach number of 2.7
to a maximum of 0.54 at a Mach number of 1.1. During descent under subsonic
conditions, the average effective drag coefficient was 0.62 and parachute-payload
oscillation angles averaged about &loo with excursions to +/-20 degrees. The recovered parachute was found to have
slight damage in the vent area caused by the attached deployment bag
and mortar lid.
Drag
Characteristics of Several Towed Decelerator Models at Mach 3
1970
Silent, Black & White, 1.75min.
Supplement to NASA-TN-D-5750 (19700017623); High-Res DVD ID No.: 20070031013
- Film Description
- An investigation
has been made to determine the possibility of using toroid-membrane and
wide-angle conical shapes as towed decelerators. Parameter variations
were investigated which might render toroid-membrane models and wide-angle-
cone models stable without loss of the high drag coefficients obtainable
with sting-mounted models. The parameters varied included location of
center of gravity, location of the pivot between the towline and the
model, and configuration modifications of the aft end as the addition
of a corner radius and the addition of a skirt. The toroid membrane can
be made into a stable towed decelerator with a suitable configuration
modification of the aft end.
High
Altitude Flight Test of a Reefed 12.2 Meter Diameter Disk-Gap-Band Parachute
with Deployment at Mach Number of 2.58
1971
Silent, Color, 5min.
Supplement to NASA-TN-D-6469 (19710024550); High-Res DVD ID No.: 20070031007
- Film Description
- A reefed 12.2-meter
nominal-diameter (40-ft) disk-gap-band parachute was flight tested as
part of the NASA Supersonic High Altitude Parachute Experiment (SHAPE)
program. A three-stage rocket was used to drive the instrumented payload
to an altitude of 43.6 km (143,000 ft), a Mach number of 2.58, and a
dynamic pressure of 972 N/m(exp 2) (20.3 lb/ft(exp 2)) where the parachute
was deployed by means of a mortar. The parachute deployed satisfactorily
and reached a partially inflated condition characterized by irregular
variations in parachute projected area. A full, stable reefed inflation
was achieved when the system had decelerated to a Mach number of about
1.5. The steady, reefed projected area was 49 percent of the steady,
unreefed area and the average drag coefficient was 0.30. Disreefing occurred
at a Mach number of 0.99 and a dynamic pressure of 81 N/m(exp 2) (1.7
lb/ft(exp 2)). The parachute maintained a steady inflated shape for the
remainder of the deceleration portion of the flight and throughout descent. During descent, the average effective drag coefficient was 0.57. There was
little, if any, coning motion, and the amplitude of planar oscillations
was generally less than 10 degrees. The film also shows a wind tunnel
test of a 1.7-meter-diameter parachute inflating at Mach number 2.0.
EVA
Assembly of Large Space Structure Neutral Buoyancy, Zero-Gravity Simulation:
NASA-LaRC Nestable Columns and Joints
1979
Silent, Color, 21.5min.
Supplement to NASA-TP-1872 (19810017623); High-Res DVD ID No.: 20070031008
- Film Description
- The film depicts
an extravehicular activity (EVA) that involved the assembly of six "space-weight" columns into a regular tetrahedral cell by a team of two "space"-suited test subjects. This cell represents the fundamental "element" of a tetrahedral truss structure. The tests were conducted under simulated zero-gravity
conditions, achieved by neutral buoyancy in water. The cell was assembled
on an "outrigger" assembly aid off the side of a mockup of the Shuttle Orbiter cargo bay. Both
manual and simulated remote manipulator system (RMS) modes were evaluated.
The simulated RMS was used only to transfer stowed hardware from the
cargo bay to the work sites. Articulation limits of the pressure suit
and zero gravity could be accommodated by work stations with foot restraints.
The results of this study have confirmed that astronaut EVA assembly
of large, erectable space structur is well within man's capabilities.
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