用H^∞方法设计航空发动机鲁棒控制系统

DESIGN OF A ROBUST CONTROL S YSTEM FOR AEROENGINE BY MEAMS OF H ∞ METHODOLOGY

用Ｈ∞多变量系统设计方法为某型号航空发动机设计控制算法，并进行了数字仿真。在发动机的某一工作点设计了控制器，并在该点进行了非实时仿真。又在非设计点进行了非实时仿真，用以验证在非设计点是否解耦。给出了地面状态从慢车到最大状态的实时加速仿真曲线。

This paper employs a simplified linear m odel of a jet engine to demonstrate the use of H ∞ methodology.First,A state spa ce H ∞ controller is derived using Doyle and Glover formula.Then,the simulations both at designing point and non designi ng point are given to show what performa nce can be achieved by using H ∞ methodo logy.It is indicated that at designing p oint,the two loops are totally decouplin g.But at non designing point,the two loo ps are coupling at high frequency region which,however,does not cause any steady state error.The real time simulation fr om idle state to maximum regime of the j et engine has been done by using the H ∞ controller at one designing point.The r esults show that the system is stable ov er the whole envelope from idle state to maximum regime of the jet engine.The ac celeration time is about 5 seconds.The N L and AMH loops have no overshoot,and T6 is no overtemperatured.It has demonstra ted that the H ∞ theory provides a relia ble and direct method for achieving sing ular value loop shaping objectives.