变推力发动机用高压强指数GAP推进剂的燃烧性能研究  

Combustion performance of GAP propellantin variable thrust motor

作　　者：王惠 张惠坤 池铁 翟峰 鲍海明 WANG Hui;ZHANG Huikun;CHI Tie;ZHAI Feng;BAO Haiming(Shanghai Space Propulsion Technology Research Institute,Huzhou 313000,China)

机构地区：[1]上海航天化工应用研究所,湖州313000

出　　处：《固体火箭技术》2021年第5期630-635,共6页Journal of Solid Rocket Technology

基　　金：空军预研项目(303040204);装发预研项目(41420020201)。

摘　　要：为了获得变推力发动机用高压强指数聚叠氮缩水甘油醚(GAP)推进剂配方,采用靶线法研究了氧化剂的种类、粒径及配比、燃速催化剂的种类及含量、以及增塑比对GAP推进剂静态燃烧性能的影响规律,采用∅118标准试验发动机对GAP推进剂进行了动态燃烧性能测试。研究表明,通过综合因素调节获得了一种高压强指数GAP推进剂配方,且当燃速催化剂RC-4含量1%时,GAP推进剂在1~15 MPa范围的动态压强指数高达0.66,满足变推力发动机对推进剂压强指数的要求,同时高压区间(9~15 MPa)的动态压强指数为0.51,低于1~15 MPa的压强指数,这有利于推进剂在高压范围内的稳定燃烧,为变推力发动机在高压范围内的正常工作提供依据。In order to obtain an optimum formulation of glycidyl azide polymer(GAP)propellant with high-pressure exponent in variable thrust motor,target line method was used to study the effects of the types,sizes and ratios of oxidizer,the types and contents of burning-rate catalyst,and the plasticizing ratios,on the static combustion performance of GAP propellant.The dynamic combustion performance was also characterized by∅118 standard testing motor.The research shows that an optimum formulation of GAP propellant with high-pressure exponent is obtained by the comprehensive adjustment.A dynamic pressure exponent 0.66 is obtained by the addition of 1%burning-rate catalyst(RC-4)at 1 MPa~15 MPa,which satisfies the requirements of propellant pressure index for variable thrust motor.Meanwhile,the dynamic pressure exponent is 0.51 at 9 MPa~15 MPa,which is lower than that at 1 MPa~15 MPa,being beneficial to the combustion stability of GAP propellant at high pressure range.This work should provide a basis for normal operation of variable thrust motor at high pressure range.

关 键 词：变推力 高压强指数 燃烧性能 GAP推进剂 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]