A pilot-controlled stability control system that employs direct lift control (spoiler control) with elevator control to control the flight path angle of an aircraft is described. A computer on the aircraft generates an elevator control signal and a spoiler control signal, using a pilot-controlled pitch control signal and pitch rate, vertical velocity, roll angle, groundspeed, engine pressure ratio and vertical acceleration signals which are generated on the aircraft. The direct lift control by the aircraft spoilers improves the response of the aircraft flight path angle and provides short term flight path stabilization against environmental disturbances.
Velocity Vector Control System Augmented with Direct Lift Control
1979
6 pages
Report
Keine Angabe
Englisch
Aircraft , Aerodynamics , Parachutes & Decelerators , Government Inventions for Licensing , Patents , Aircraft control , Direct lift controls , Directional control , Pitch (Inclination) , Stability augmentation , Airborne/spaceborne computers , Elevators (Control surfaces) , Flight paths , Manual control , Spoilers , PAT-CL-244-181 , PAT-CL-244-195 , PAT-CL-318-584 , PAT-CL-364-434 , NTISGPNASA