摘要
固体火箭发动机前封头内绝热层在飞行加速过程中的烧蚀率是地面静止试验的１．０～２．３倍。概述了国外在飞行加速对烧蚀影响这方面的研究结果，对国内３台固体火箭发动机内绝热层烧蚀率进行了估算和分析，认为，由于绝热层设计安全裕度比较大，因而这三种发动机飞行条件下的烧蚀仍在安全范围之内。
The ablation rate of solid motor forward dome internal insulation durins nigth acceleration is 1. o～2.3 times larger than that during static test. The investigated results about effects of flight acceleration oninsulation ablation abroad are summarized in this paper'Based on the results, the ablation rates of the internal insulation for three solid rocket motors made at home are analyzed and evaluated. It is considered that theablation rates of the motors during flight acceleration are in the safety scope, because of the greater safetymargin desighed for the motors.
出处
《固体火箭技术》
EI
CAS
CSCD
1996年第3期7-11,共5页
Journal of Solid Rocket Technology
关键词
固体推进剂
火箭发动
隔热材料
烧蚀试验
Solid propellant rocket motor Thermal insulating material Ablation test Accelerationtest
