摘要
为了增大飞行器速度,改善总体性能,提高运载能力,发动机完成任务后需要和头部分离以减小负载,需要反推火箭产生一个同火箭运动方向相反的力使分离顺利完成[1]。反推火箭安装于尾舱中,尾舱和发动机整体分离,在舱段分离之前,反推火箭的口盖需首先完成与尾舱分离。分离过程环境复杂、条件恶劣,所以需提高分离时的可靠性和精确性。本文针对反推火箭口盖分离的情况,设计了一种可靠的分离方案,并对其进行了最优化分析。通过分离状态的模拟仿真和地面分离试验,结合试验后口盖的破坏情况及分离状态,完成了反推火箭口盖的可靠性分析,为结构可靠性设计积累了数据。
In order to increase the speed of the aircraft,improve the overall performance and improve the carrying capacity,after a certain type of engine completes the task,it is necessary to separate the engine from the head to reduce the load when the engine off.During the separation,the rocket produces a opposite force to the movement direction of the rocket to make the separation complete smoothly.The retro-rocket was installed in the rear compartment.Before the separation of the rear compartment,the hatch cover of the retro-rocket should be separated from the rear compartment first.The separation process is complex and harsh,so it is necessary to improve the reliability and accuracy of separation.In this paper,a reliable separation scheme was designed for the hatch cover of retro-rocket separation and carried out its optimization analysis.By the simulation of separation state and test of ground separation,combined with the destruction situation of the hatch cover of retro-rocket and the high-speed photographic photos of the separation state.The reliability analysis of the hatch cover of retro-rocket was completed,and data was accumulated for the structural reliability design.
作者
李飞
郭胤
宁舜山
姜安林
LI Fei;GUO Yin;NING Shunshan;JIANG Anlin(The Design Department, Sichuan Academy of Aerospace Technology, Chengdu 610100, China)
出处
《兵器装备工程学报》
CAS
北大核心
2020年第S02期66-69,共4页
Journal of Ordnance Equipment Engineering
