摘要
以某单室双推力发动机为研制基础,设计了两端人工脱粘层结构、准包覆套筒结构及准包覆套筒结构+导气条三种试验方案验证发动机绝热结构的安全可靠性。通过改变发动机绝热结构,并根据阶段性试验结果对其不断优化,最终完成了满足发动机应用要求的安全可靠的绝热结构设计,并通过地面静止试验对绝热结构进行了验证。试验结果表明:一级内孔、二级端燃药型结构的单室双推力发动机,绝热结构设计为准包覆套筒绝热结构可有效释放药柱在硫化、降温及贮存过程中药柱收缩变形而产生较大的应力,能够保证药柱及各粘接界面不被撕裂;在绝热套筒和绝热底层之间铺设导气结构,可确保点火瞬间燃烧室内压强平衡;对于此类单室双推力发动机,绝热设计采取准包覆套筒+导气条结构可以有效提高发动机工作可靠性。
Based on the development of a single-chamber dual-thrust SRM,three insulated projects for the test motor,including the ends stress release boot structure,the quasi coated sleeve structure and the quasi coated sleeve structure with gas-guide strips,were designed to verify the safety and reliability of the insulated structure.According to the periodic test results,the insulated structure was continuously optimized by improving the insulated structure of test motor.Finally,a safe and reliable insulated structure meeting application requirements of the SRM was verified by means of the ground static test.The results show that the insulated structure of quasi coated sleeve enables a single-chamber dual-thrust SRM with internal burning grain for stage 1 and end-burning grain for stage 2 to effectively release the induced stress caused by the shrinkage and deformation of the grain during the curing,cooling and storing process,thus avoiding the debonding of grain and interfaces;A gas-guiding structure laid between insulated sleeve and insulation bottom can ensure pressure balance in chamber at ignition point;For the single-chamber dual-thrust SRM,the insulated structure of quasi coated sleeve with gas-guide strips can effectively improve the reliability of the motor.
作者
官鹏
何天军
王峰
李天祥
刘虎
吴喆昊
GUAN Peng;HE Tianjun;WANG Feng;LI Tianxiang;LIU Hu;WU Zhehao(Xi’an Aerospace Chemical Propulsion Co.,Ltd.,Xi’an 710025,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2020年第5期629-634,共6页
Journal of Solid Rocket Technology
关键词
单室双推力
绝热结构
导气槽
发动机试验
single-chamber dual-thrust
insulated structure
gas-guide groove
motor test
