A new rapid response emergency control method for turbo-shaft engines

According to the special need in helicopter's emergency state,a new fast response control method of integrated Helicopter/turbo-shaft engine system was proposed to solve this control problem for helicopter's emergency control.Turbine bleeding was another control input except for fuel flow in this new scheme,and the control law including three control loops was based on multi-variables robust control design theory.Specially in this hybrid control law,not only the helicopter climbing velocity was controlled,the gas turbine speed of turbo-shaft engines was also effectively controlled by turbine bleeding to realize engines' power rapid tracking while keeping the power turbine speed constant.In the final stage,the control law was implemented in an integrated UH-60 helicopter and T700 engine system and the transient performance of the closed-loop system in helicopter's climbing and desending emergency flights.The simulation results show clearly that the response time of the closed-loop system designed by the new fast response control law is much reduced compared with that designed by traditional PID(proportional integration differential) method,and it meets the special need of helicopter's emergency control.