航空发动机H_∞/LTR控制试验验证

Experimental Verification of H_(∞)/LTR Method for Aeroengine Control Systems

用半物理模拟试验验证了多变量鲁棒控制在航空发动机中的应用,给出了航空发动机中H∞/LTR控制模块的设计过程及注意事项。从半物理模拟试验结果可见:与LQG/LTR控制器不同,H∞/LTR控制器能在半物理模拟试验环境下稳定控制航空发动机;H∞/LTR控制器具有优良的噪声抑制功能;基于包线内一点设计的H∞/LTR控制器可适用于包线内其他区域的加力与非加力状态下的爬升、加速等仿真试验,验证了H∞/LTR方法的鲁棒性。推进了多变量鲁棒控制设计方法在航空发动机中的实际应用。

The application of multivariable robust control methods to aeroengines was testified by a semi-physical simulation. The detailed design procedure of an H∞/LTR control module for the aeroengine control system was also included. From the simulation results, it is clear that the H∞/LTR controller stabilized the whole system in semi-physical simulation environment. This is much different from the LQG/LTR controller that is unstable under the same condition. Further more, one can find that the H∞/LTR method has good noise rejection property. Thirdly, the controller, based only on the intermediate power level of one point in the envelope, offers satisfactory performance for a large area in the envelope in the augmented and un-augmented simulation. Therefore, it is experimentally testified that H∞/LTR method is a multivariable robust control design method that can be practically applied to engineering environment. Finally, the success of this semi-physical simulation shows that the research of multivariable control methods has a big progress in the direction of practical application to aeroengine control system.