Designing a Control Augmentation System for the H-53 Helicopter.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The thesis presents the procedures used in designing a control augmentation system CAS for the H-53 helicopter. The conventional root locus design techniques, along with an analog computer simulation, were used to design the system. Two control loops were formed the height rate control loop collective pitch control and the pitch control loop cyclic pitch control. When both loops are closed the helicopter does not respond correctly to pitch commands. The problem of improper height response during pitch commands was solved by cross coupling some of the pitch command to the height control loop. The results show that a simple CAS is feasible and desirable to improve the controllability of present day helicopters. Author0