新一代大型运载火箭大推力直接入轨高精度姿态控制方法  

A High Precision Attitude Control Method for High Thrust Direct Orbit Entry of New Generation Large Launch Vehicle

作　　者：黄聪 张宇[1] 王辉[1] 李学锋[1] 王硕 Huang Cong;Zhang Yu;Wang Hui;Li Xue-feng;Wang Shuo(Beijing Aerospace Automatic Control Institute,Beijing,100854)

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《导弹与航天运载技术》2021年第2期21-24,共4页Missiles and Space Vehicles

摘　　要：为解决一级半构型的千吨级大推力新一代大型运载火箭直接入轨时刻5m直径机架变形结构干扰大、20吨级巨大载荷条件下刚晃与弹晃交联耦合严重、百吨级低温发动机氧涡轮泵停转后效干扰大、主发动机关机后姿态控制能力显著不足等难题,提出了一种分时段多维增益自适应调整技术,动态调整关机后效段姿控系统滚动通道增益,可以有效提升载荷分离时刻姿态控制精度,确保20吨级有效载荷分离安全。In order to solve the problems that the large interference of the 5 meter diameter frame deformation structure,the severe cross linking coupling of rigid-sloshing and elastic-sloshing under the 20 ton huge load,the large interference of the oxygen turbo pump of the hundred ton level low temperature after engine cutoff,the significant insufficient attitude control ability after the main engine shutdown.A time-segmented multi-dimensional gain adaptive technology is proposed,which can dynamically adjusts the roll channel gain of the attitude system after the core-level main engine shutdown,and this method can effectively improve the attitude control accuracy of the load separation moment,which ensures the safety of the 20 ton load separation.

关 键 词：新一代大型运载火箭 大推力入轨 姿态控制 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]