Criteria for Design of Integrated Flight/Propulsion Control Systems for Stovl Fighter Aircraft
Criteria for Design of Integrated Flight/Propulsion Control Systems for Stovl Fighter Aircraft
- New search for: J. A. Franklin
- New search for: J. A. Franklin
As part of NASA's program to develop technology for short takeoff and vertical landing (STOVL) fighter aircraft, control system designs have been developed for a conceptual STOVL aircraft. This aircraft is representative of the class of mixed-flow remote-lift concepts that was identified as the preferred design approach by the U.S./U.K. STOVL Joint Assessment and Ranking Team. The control system designs have been evaluated throughout the powered-lift flight envelope on the Vertical Motion Simulator (VMS) at Ames Research Center. Items assessed in the control system evaluation were: maximum control power used in transition and vertical flight, control system dynamic response associated with thrust transfer for attitude control, thrust margin in the presence of ground effect and hot-gas ingestion, and dynamic thrust response for the engine core. Effects of wind, turbulence, and ship airwake disturbances are incorporated in the evaluation. Results provide the basis for a reassessment of existing flying-qualities design criteria applied to STOVL aircraft.
Document information
Criteria for Design of Integrated Flight/Propulsion Control Systems for Stovl Fighter Aircraft
1993
35 pages
Report
No indication
English
Aeronautics , Aircraft , Aircraft control , Aircraft design , Control systems design , Fighter aircraft , Flight characteristics , Flight control , Stovl aircraft , Attitude control , Criteria , Dynamic response , Engine control , Ground effect (Aerodynamics) , Thrust , Transition flight , Turbulence effects , Vertical flight , Wind effects