Abstract:

A synthesis design method using eigenstructure assignment/sensitivity analysis of minimum singular value/loop transfer recovery theories is studied, & the stability & control augmentation system in low altitude & small velocity or in hover flight state is designed. In the meantime, numerical simulations for change of aircraft system parameters & for transition response from some fliglt velocity to hover flight state are finished. The results show that the aircraft possesses good stability & satisfactory decouple when this synthesis design method is used to design the helicopter stability & control augmentation systems.

Key words: eigenstructur eassignment, singular-value sensitivity, LTR, control augmentation