摘要
火箭入轨通常是沿标准轨道面的飞行控制,常规发射任务只需侧向小偏航角校正,但当今一些特殊的入轨任务要求火箭制导控制能侧向大偏航角飞行,以克服较大初始侧向偏差对末级火箭入轨的影响。文中提出了一种末级火箭的侧向大偏航非线性自适应组合制导控制方法,结合土星-5火箭IMG方法和航天飞机LTG方法各自的优点,进行了大偏航角的非线性耦合补偿修正,并对动力飞行过程的迭代算法进行了鲁棒稳定性改造。基于姿态喷嘴开关控制的六自由度数值仿真表明,提出的控制策略和算法简单可靠、稳定性好、精度高,在火箭入轨控制和空间飞行器变轨控制中具有参考和应用价值。
Rocket orbital insertion is usually to control flight along standard orbital plane. Common launching mission only re quires small yaw correction, but currently some special tasks require rocket be able to fly in power with large lateral yaw guidance to eliminate large initial lateral disturbances to the end stage rocket orbital insertion. A kind of self adaptive nonlinear combined guid ance method with large yaw was researched and presented for the end stage rocket orbital insertion, which synthesized the advantages of IMG method of Saturn V and LTG method of Space Shuttle. The large yaw non-linear coupled compensation was performed and its iterative algorithm of powered flight was modified to improve robust stability. The numerical simulation of six DOF based on attitude nozzle control has demonstrated that the guidance strategy and algorithm are simple, stable and precise, which will be referential and applicable in the rocket orbital insertion and orbital maneuver.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第4期434-437,445,共5页
Journal of Solid Rocket Technology
基金
航天基金项目(UCS20110518)
关键词
火箭入轨
制导与控制
自适应控制
大偏航非线性控制
空间快速响应
rocket orbital insertion
guidance and control
self adaptive control
large yaw nonlinear control
space rapid re sponse
