基于攻角预测模型的航空发动机高稳定性控制  

Aero-engine high stability control scheme design based on angle of attack predictive model

作　　者：陈霆昊[1] 张海波[1] 孙健国[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2010年第7期1676-1682,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(50576033)

摘　　要：研究了发动机稳定性控制问题.作战飞机在超机动飞行时,发动机进口流场畸变严重,采用常规控制并不能保证其稳定工作.针对上述问题,提出了基于攻角预测的发动机超机动飞行高稳定性控制器:首先建立了进气道攻角预测模型,以实时估计发动机进口流场畸变,并在此基础上用增广线性二次型调节器(augmented linear quadratic regulator,简称ALQR)方法设计了高稳定性控制器,最后在发动机/三自由度飞机综合模型平台上模拟大攻角飞行任务进行了数字仿真验证.数字仿真结果验证了提出的控制思想的合理性和可行性.A study of engine stability control for super-maneuvering flight was carried out.High level of engine-face distortion often occurs during super-maneuvering flight of the combat aircraft.In this case,engine stall will be caused if conventional controller is still used.For this issue,an advanced predictive control system,in which an angle of attack（AOA） predictive model was used,for aero-engine was designed.Firstly,an angle of attack predictive model was established to estimate the engine-face distortion in real time.Then,a high stability predictive controller was designed using augmented linear quadratic regulator（ALQR） method based on the former estimator.Finally,digital simulation was carried out on the engine/three-degree-of-freedom aircraft nonlinear integrated model.The results show that the stability control concept proposed in this paper is effective and feasible.

关 键 词：航空发动机 超机动飞行 攻角预测模型 高稳定性控制 增广线性二次型调节器(ALQR) 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]