Feedback Driven 6-DoF Modeling of a Tilt-Duct Aircraft STAR Global - - PowerPoint PPT Presentation
Feedback Driven 6-DoF Modeling of a Tilt-Duct Aircraft STAR Global Forum May 12, 2010 Paul Vasilescu AD-150 High Speed VTOL UAV - Designed around USMC Tier III requirements (Now Group IV) - VTOL from air capable ships - Exceed 200 kts airspeed
2
requirements (Now Group IV)
Length 14.5 ft Wing Span 17.5 ft Height 4.75 ft Takeoff Weight 2,200 lbs - 2,800 lbs Max Payload 500 lbs - 1,000 lbs Max Speed 300 kts Max Range 736 Nmi
Designed & Manufactured by ADFS in Jessup, MD Designed by ADFS, Manufactured by ADFS and/or Subcontractors Designed & Manufactured by Subcontractors
Turboshaft Powerplant HTAL System Drive System Main Landing Gear Vectoring Nozzle Flight Control Actuators Flaperon Ruddervator Mission Payload Avionics Navigation & Control Power Management Nose Landing Gear HTAL Nacelle Airframe HTAL Fan
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Duct angle relative to the fuselage
Angle-of-Attack
Run on top of the simulation
Read inertial data at each time step
Implement geometric and power changes
Split the propulsion model from the aircraft model
Verify data using multiple CFD methods
Validate CFD models with experimental tests
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Duct Angle
Feestream Velocity
Fan RPM
6 Component Forces and Moments
Fan Torque
Airflow Velocity (above and below fan disk)
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Enables rotation of the ducts without remeshing
In-place interfaces used between all volumes
Computed dynamically for each time step based on data from the propulsion system CFD
Validated by comparing 6 component forces and moments of both models
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Reduced 3000 hours of compute time to 48 hours for the stead state propulsion simulation test matrix
Reduced 93.4 hours of compute time per second of flight time of the unsteady / transient aircraft simulation to 2.4 hours of compute time per second of flight time
Built and tested a 1/3 scale model of the
AD-150 aircraft
Tests conducted at the Glen L. Martin Wind
Tunnel in Q1 2009
Performed static and dynamic tests over a wide
range of combinations of angle of attack, sideslip and forward speed
Confirmed CFD performance data and
validated airframe design
Funding provided by the state of Maryland
through the Maryland Industrial Partnerships program (MIPS)
“The American Dynamics Flight Systems team came to the wind tunnel test with a more complete set of CFD results directly comparable to the tunnel conditions than any other group we have worked with up to now.” -- Dr. Jewel Barlow, Director of the Glenn L. Martin Wind Tunnel
Build an test a scaled AD-150 propulsion
system in a wind tunnel
Simulate conditions experienced during
transition between hover and forward flight
Test will be conducted and the UMD Glenn L.
Martin Wind
Tests will include variances in freestream
velocity, fan velocity, and duct angle
Measurements will be taken and compared
to equivalent data taken from the computational models
Funding provided by the state of Maryland
through the Maryland Industrial Partnerships program (MIPS)
Build and integrate a fully instrumented test rig
for the AD-150 lift and propulsion system
Tests to be conducted at Aberdeen Proving
Grounds later this year
Mechanically validate propulsion and drive
components
Confirm CFD performance data for hover in
ground effect (HIGE) and hover out of ground effect (HOGE)
Provide a comprehensive data set of system
performance and reliability
Funding provided by the state of Maryland
through the Maryland Technology Transfer Fund (MTTF) program
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