进气道可变高超声速飞行器自适应一体化控制  

Adaptive integrated control for hypersonic variable inlet vehicle

作　　者：李家鑫 侯霖飞 李旦伟 吴国强[1] LI Jiaxin;HOU Linfei;LI Danwei;WUGuoqiang(Dalian University of Technology,Dalian 116024,China;Shenyang Aircraft Design&Research Institute,Shenyang 110035,China)

机构地区：[1]大连理工大学,辽宁大连116024 [2]沈阳飞机设计研究所,沈阳110035

出　　处：《兵器装备工程学报》2023年第10期120-126,共7页Journal of Ordnance Equipment Engineering

基　　金：自然科学基金项目(U2141229);航空科学基金项目(2019ZC063001)。

摘　　要：使用冲压发动机的高超声速飞行器多采用乘波体构型,由于飞行包线大、飞行环境变化显著,故采用变几何进气道设计以提高不同飞行条件下的综合推进性能,这使得飞行器动力学特性变化更加复杂,飞行和推进耦合效应更加显著。在此背景下,开展变进气道高超声速飞行器动力学建模研究,分析进气道构型变化情况下的动力学特性。提出了动力学参数依赖的自适应一体化控制方法,实现飞行/推进耦合反馈控制。在飞行环境和进气道构型改变导致动力学特性变化情况下,通过实时调整控制器参数,提升指令跟踪控制品质。Hypersonic aircrafts fixing with ramjet mostly adopt wave-rider configuration.Due to the large flight envelope and obvious aerodynamic changes,variable geometry inlet design is adopted to improve the comprehensive propulsion performance under different flight conditions,which makes the variation of dynamic characteristics more complicated,and the coupling effect between flight and propulsion more obvious.Under this background,the dynamic modeling of the hypersonic vehicle with variable inlet is studied.The flight mechanics and dynamics characteristics of aircraft in a wide-speed range are analyzed under different inlet configurations.On this basis,an adaptive integrated control method based on the dynamic parameter dependencies is proposed to realize the flight/propulsion coupling feedback control strategy.Meanwhile,by adjusting the controller in real-time,the command tracking quality is improved when the aerodynamic parameters are changed due to the flight environment and the variation of the inlet.

关 键 词：高超声速飞行器 变进气道建模 一体化控制 飞行动力学建模 飞行力学与操稳特性分析 

分 类 号：V249.122.2[航空宇航科学与技术—飞行器设计]