Optimal Design of Helicopter Precision Hover Control Systems.
Research and development technical rept.,
ARMY ELECTRONICS COMMAND FORT MONMOUTH N J
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1-F-162202-AA-9713helicopters, hovering, flight control systems, helicopters, stability, equations of motion, accuracy, optimizationcomputer aided analysisModern Control Theory is employed to analytically determine the limit of positional precision with which a helicopter can be hovered. Approaches based on Liapunovs Second Method and a Squared Root Locus Method are formulated to this optimal control problem. Both of these methods avoid iterative solution of the Matrix Riccati Equation. The Squared Root Locus Method is developed as a computer algorithm which generates optimal control designs as a function of performance index and helicopter stabilitycontrol derivatives. Practical design constraints can readily be interpreted from the results of this formulation. Author