基于动态逆控制的高超声速飞行器飞/发一体化控制方法研究  

Research on integrated aircraft-engine control method of hypersonic vehicle based on dynamic inversion control

作　　者：闫斌斌[1] 林泽淮 刘双喜 闫杰[4] YAN Binbin;LIN Zehuai;LIU Shuangxi;YAN Jie(School of Astronautics,Northwestern Polytechnical University,Xi′an 710072,China 2.College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;Hypersonic Technology Laboratory,National University of Defense Technology,Changsha 410073,China;Unmanned System Research Institute,Northwestern Polytechnical University,Xi′an 710072,China)

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]国防科技大学空天科学学院,湖南长沙410073 [3]国防科技大学高超声速技术实验室,湖南长沙410073 [4]西北工业大学无人系统技术研究院,陕西西安710072

出　　处：《西北工业大学学报》2023年第5期878-886,共9页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(62173274);陕西省自然科学基础研究计划(2020JC-19);航空科学基金(20200001053005);中央高校基本科研业务费(D5000220138);西北工业大学硕士研究生实践创新能力培育基金(PF2023046)资助

摘　　要：为了减小高超声速飞行器飞/发耦合效应对自身的影响,开展了高超声速飞行器飞/发一体化控制研究。建立面向控制的高超声速飞行器飞/发一体化数学模型。分别采用非线性动态逆控制与增量非线性动态逆控制方法,设计了姿态慢变外回路、角速率快变内回路控制算法。基于包含高超声速飞行器飞/发耦合特性的在线本体模型,以操纵交联的形式设计了高超声速飞行器姿态与发动机的耦合控制方案。在非线性动态逆控制器中引入参考模型、误差控制、在线估计等模块,保证了高超声速飞行器的飞行品质和鲁棒性要求。仿真实验结果表明,采用了非线性动态逆控制设计的飞/发耦合控制方案达到了预期的控制性能。In order to reduce the influence of the coupling characteristics between the aircraft and engine of hypersonic vehicle,an integrated aircraft-engine control method of hypersonic vehicle is studied in this paper.Firstly,the control-oriented aircraft-engine integrated mathematical model of the hypersonic vehicle is established.Then,by using the nonlinear dynamic inversion(NDI)and the incremental nonlinear dynamic inversion(INDI),the outer loop control algorithm with slow attitude change and the inner loop control algorithm with fast angular rate change are respectively designed.Moreover,based on the online ontology model including aircraft-engine coupling characteristics of the hypersonic vehicle,the coupling control scheme of flight posture and engine of the hypersonic vehicle is designed in the form of control linkage.Finally,the reference model,error control,online estimation and other modules are introduced into the NDI controller to ensure the flight quality and robustness requirements of the hypersonic vehicle.The simulation results show that the aircraft-engine coupling control scheme based on the NDI achieves the expected control performance.

关 键 词：高超声速飞行器 飞/发一体化 非线性动态逆 增量非线性动态逆 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]