固体捆绑火箭联合摇摆控制方法  

Swing Combined Attitude Control Scheme for Solid Strap-On Launch Vehicle

作　　者：胡存明 徐超 周静 吴康 陈晓 HU Cunming;XU Chao;ZHOU Jing;WU Kang;CHEN Xiao(Shanghai Institute of Spaceflight Control Technology,Shanghai 201109,China)

机构地区：[1]上海航天控制技术研究所,上海201109

出　　处：《航天控制》2024年第4期3-9,共7页Aerospace Control

摘　　要：针对固体捆绑运载火箭固体发动机大范围推力变化、推力不同步问题,提出了一种固体捆绑火箭联合摇摆控制方案。首先利用燃烧室压强估算各台固体发动机实时推力,根据推力变化在线修正控制器参数,以适应固体发动机大范围推力变化;然后采用推力不同步前馈控制,消除推力不同步影响;最后采用固体发动机下沉角实时补偿控制方法,消除固体发动机摆心漂移影响。经仿真验证,该方法可有效解决固体助推器间推力不确定和推力不同步带来的控制难题,大幅提高姿态控制精度,提升固体捆绑火箭飞行适应能力。A solid strap-on launch vehicle joint swing control scheme is proposed,which is dedicated to handle large range thrust variation and the non-synchronous thrust among solid boosters.Firstly,the combustion chamber pressure is used to estimate the real-time thrust of each solid booster,and the controller parameters are accordingly modified on-line due to the thrust variation.Secondly,by adopting the feed-forward control to eliminate the loss of thrust synchronism.Finally,the real time swing subsidence angle compensation for solid booster is adopted to solve the effect of pivot point excursion.The simulation results show that the proposed adaptive control scheme is able to efficiently solve control matters caused by the thrust uncertainties and the non-synchronization thrust among solid boosters,which takes advantage of increasing the attitude control precision with large scale and improving the launch vehicle’s adaptive capability in the real flying environment.

关 键 词：联合摇摆控制 推力不同步 摆心漂移 自适应控制 固体捆绑火箭 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]