摘要
带有导向装置的新型探空火箭分离机构满足了套筒式伸杆展开机构在分离过程中无磕碰的特殊安装解锁要求。通过设计仿真和地面试验验证了分离机构的可行性,并成功应用于两发火箭飞行试验。
A new type of sounding rocket separation mechanism with guiding device is designed to meet the requirement of non-interference in the process of payload deployment. The payload is named sleeve-type of boom deployment mechanism. The feasibility of separation mechanism design has been verified by the nmhi-body dynamic simulation analysis and the ground experiments. And two sounding rockets with the new separation mechanism have been successfully launched.
作者
王蓉晖
吴俊全
王军辉
胥磊
WANG Ronghui;WU Junquan;WANG Junhui;XU Lei(The 41st Institute of the Fourth Academy of CASC,Xi＇ an 710025,China)
出处
《兵器装备工程学报》
CAS
北大核心
2018年第7期11-15,共5页
Journal of Ordnance Equipment Engineering
关键词
探空火箭
头体分离导向功能
sounding rocket
head-body separation mechanism
