Application of Self-Adaptive Control Techniques in the Design of a Normal Acceleration ContrOL System for a High-Performance Supersonic Aircraft.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The thesis presents a design appraoch for a self-adaptive normal acceleration control system which is required for a hypothetical aerospace vehicle that operates throughout a wide range of Mach numbers and dynamic pressures. The control problem includes the realistic complications of undesirable structural modes, a nonlinear servoactuator, and the statistical nature of the aircraft stability derivatives and bending mode parameters. A systematic design procedure is developed which employs a servoactuator control loop with a variable gain, in addition to the conventional pitch-rate and normal acceleration control loops, both of which use constant loop gains. The control system is simulated on an analog computer and tested at each flight condition, where variation of the servoactuator loop gain is accomplished manually. At each individual flight condition, this gain is adjusted to the value that would have ordinarily been dictated by an Off-Line Adaptive Computer OLAC4 WHICH USES ELEVATOR POSITION AND PITCH-RATE MEASUREMENTS FROM THE AIRCRAFT TO IDENTIFY AND COMPUTE CHANGES IN ELEVATOR EFFECTIVENESS. Collective examination of the analog results reveals that the aircraft responses to command inputs and wind gust disturbances meet the design specifications for the majority of the flight envelope. Author