变推力液体火箭发动机试验研究

A TEST STUDY OF THE VARIABLE-THRUST LIQUID ROCKET ENGINE

关键词:  液体推进剂火箭发动机  可变推力  发动机试验

Key words:  Liquid propellant engine  Variable thrust  Engine test

摘要:

考虑到空间飞行器姿态控制和弹道导弹的多头分导及弹头机动飞行的需要,我们研制了液体双组元可变推力发动机.本文叙述该发动机的研制过程和有关性能.该发动机可使用多种推进剂,推力可在(137.3～686.5)N的范围内连续无级调节,调节比5:1.发动机阶跃响应低于80ms,混合比偏差小于±5%.

Abstract:

Considering the needs of attitude control of the space vehicle and maneuver trace of warheads of missiles, a bipropellant variable-thrust liquid rocket engine has been developed by the 11th research institute.In this qaper,the process of design and research and the performances of the engine are introduced. The engine can use many kinds of propellant, it’s thrust can be adjusted from 137.3 to 686.5N continously,the adjustment ratio is 5:1.The step response time of the engine is less than 80 ms,the O/F ratio error is less than ±5%.