Form 9.B Project Summary
Chron:
970640
Proposal Number:
06.04-9282
Project Title:
Reduced Order Free Wake Modeling
for Near Real Time Simulation of
Rotorcraft Flight Mechanics
Technical Abstract (Limit 200 words)
Rapid, realistic simulation of rotorcraft flight
mechanics is a continuing challenge for the
mission/flight simulation community, aircraft
designers, and control system specialists.
Accelerating flight dynamics models while
integrating them with state-of-the art performance
analysis tools is a particularly promising way to
streamline the design, testing, and certification of
new rotorcraft, particularly novel civil tiltrotors.
Efficient modeling of complex
wake/fuselage/empennage aerodynamic
interactions lies at the heart of this problem, though
rapidly evolving computational methods are now
bringing advanced aerodynamic modeling
techniques within reach for these applications. The
thrust of this proposed effort is to address the
limitations of current flight dynamics modeling tools
by developing dramatically accelerated, reduced
order embodiments of validated free wake models.
This will provide high fidelity treatments of
rotor/wake and rotor/body interaction for flight
mechanics and simulation activities while yielding
near real time performance on modern
workstations. This new model will also address
current limitations in predicting helicopter and
tiltrotor response to control inputs for general flight
conditions and will also incorporate
body/empennage effects. While integrating
smoothly with established performance analysis
tools and possessing strong "stand-alone"
capabilities, the model will be designed to be
operable with a variety of existing flight dynamics
codes for maximum utility.
Potential Commercial Applications (Limit 200 words)
Development of this capability would address the
need for new insight into the flight mechanics of
civil tiltrotor designs or other novel dual-rotor
configurations. It would also improve the fidelity of
fixed and moving-base helicopter flight simulators,
as well as aid the development of advanced flight
controls. In addition, better understanding of
helicopter and tiltrotor flow fields could also aid
commercial operators concerned with safe
operating procedures around ground obstructions or
in unusual attitudes or operating conditions caused
by environmental conditions or noise abatement
requirements.
Name and Address of Principal Investigator (Name,
Organization Name, Mail Address, City/State/Zip)
Todd R. Quackenbush
Continuum Dynamics, Inc.
P.O. Box 3073
Princeton , NJ 08543-3073
Name and Address of Offeror (Firm Name, Mail Address,
City/State/Zip)
Barbara A. Agans
Continuum Dynamics, Inc.
P.O. Box 3073
Princeton , NJ 08543-3073