摘要
对于吸气式导弹,其级间分离的约束强,使得级间冷分离方式下安全分离与稳定起控的矛盾更为突出。为解决安全分离所带来的大姿态偏差下导弹稳定起控问题,提出了通过最佳分离飞行状态点选择来提高起控稳定性的思路,并明确了选择原则。在最佳级间分离状态基础上,通过理论分析建立了纵向、横侧向通道不同静稳定性下的起控策略。经仿真表明,提出的起控策略利用导弹的静稳定特性,可降低通道间的耦合,合理分配控制能力,有利于实现大姿态偏差下的快速稳定起控。
At the cooling stage-separation mode,the contradiction in safe separation and stability control is obvious.In order to solve the stability control problem at the big initial attitude deviation bringing by safety separation,a thinking to choose the best flight status of stage-separation is proposed.And the basic principles were confirmed.The control strategy for the longitudinal and transverse lateral channel under different static stability is researched by theory analysis method.The simulation results show that the technology in this paper can realize stabilization control quickly for cooling stage-separation mode of static unstable missile and lateral coupling missile.
作者
宋少倩
周国峰
刘娟
迟学谦
韩英宏
Song Shao-qian;Zhou Guo-feng;Liu Juan;Chi Xue-qian;Han Ying-hong(China Academy of Launch Vehicle Technology,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2018年第5期10-15,共6页
Missiles and Space Vehicles
关键词
级间冷分离
大起控偏差
起控策略
稳定性
cooling stage separation
attitude angle deviation
control strategy at initial time
static stability
