摘要
针对力箭一号(PR-1)一二级分离时刻结构壳段不憋压失效,二级姿态可控,火箭滑行阶段零过载条件下,整流罩无过载分离以及三四级分离不因火工品而产生多余物的需求,进行分离系统设计。区别于传统设计,一二级分离采用被动排焰热分离,三四级分离采用非火工分离冲量装置,整流罩基于能量法设计零过载下旋转分离。通过大型地面和飞行试验,验证了PR-1采用的3种新型分离设计的可靠性。
For the PR⁃1 rocket,the structure does not fail at the moment of the first⁃stage and sec⁃ond⁃stage separation,and the second⁃stage attitude is controllable.Under the condition of zero over⁃load in the coast stage,there is a no overload separation of the fairing.The third and fourth stages of separation do not produce the need for excess matter due to pyrotechnics.Different from the tradi⁃tional design,the first and second stage separation applied passive flame and high pressure exhaust mechanism when it performed hot separation.The third stage adopted a non⁃pyrotechnical separation mechanism.The fairing conducted rotate⁃separation under zero overload based on energy method.By ground and flight tests,the reliability of PR⁃1 separation system were verified.
作者
杨浩亮
王英诚
张延瑞
薛子旺
YANG Haoliang;WANG Yingcheng;ZHANG Yanrui;XUE Ziwang(Beijing Zhongke Aerospace Technology Co.,LTD,Beijing 100176,China)
出处
《载人航天》
CSCD
北大核心
2024年第1期81-88,共8页
Manned Spaceflight
关键词
力箭一号
被动排焰热分离
非火工分离
整流罩零过载分离
PR⁃1
passive flame and high pressure exhaust mechanism with hot separation
non⁃py⁃rotechnical separation mechanism
fairing separation under zero overload
