发动机喘振裕度自适应控制

ADAPTIVE ENGINE STALL MARGIN CONTROL

本文研究飞行 /推进系统一体化控制中的发动机喘振裕度自适应控制。通过一定的控制作用 ,使发动机在所有飞行条件和工况下都保持一定的喘振裕度 ,从而充分发挥发动机的潜力。将发动机大偏差模型、进气道及飞机模型综合在一起 ,构成飞机 /推进系统一体化数学模型 ,以进行发动机自适应控制的仿真。计算机仿真表明 ,发动机自适应控制具有很好的性能效益 ,例如在飞行高度 H=10公里 ,飞机由 Ma=0 .65加速到 Ma=0 .90 ,在采用自适应喘振裕度控制后 ,双发动机推力提高 16 ,飞机加速时间缩短 2 3 ,大大提高了飞机性能。

This paper proposes an adaptive engine stall margin control(AESMC)for integration of flight and propulsion controls.Using the model reference adaptive control(MRAC)technique,the AESMC is to adjust exhaust nozzle area to uptrim the engine pressure ratio so that the engine stall margin remains a small constant value in all operation conditions and in full flight envelope.Benefit of the control system is to increase engine thrust and to reduce aircraft acceleration time.In order to evaluate the performance of the AESMC,a nonlinear integrated flight/propulsion model is developed.Digital simulation of the IFPC system is performed.The simulation results show that the IFPC system with the adaptive controller developed has good effectiveness for all operation conditions and for full flight envelope.For example,the thrusts of two engines are increased 16%,and aircraft acceleration time is reduced 23% at altitude 10km and Mach number from 0 65 to 0 9.