固体火箭发动机火箭橇过载模拟试验方法  

Rocket sled acceleration experiment method of SRM

作　　者：张翔宇[1] 甘晓松[1] 高波[2] 马亮[1] 周艳青[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025 [2]中国航天科技集团公司第四研究院,西安710025

出　　处：《固体火箭技术》2016年第6期751-754,共4页Journal of Solid Rocket Technology

摘　　要：以火箭橇作为过载加载平台和回收载体,通过结构强度及振动模态仿真确定火箭橇系统结构,设计推力控制方案满足试验弹道要求,建立了固体发动机火箭橇地面过载模拟试验方法。在国内首次开展了全尺寸固体发动机火箭橇试验,橇体大于16g的航向过载持续时间约为2.258 s,满足设计要求,试验全程监测并采集到发动机压强及振动数据。被试发动机在过载条件下出现了与飞行试验相似的压强振荡特性,复现了导弹飞行过载诱发的固体发动机不稳定燃烧现象。An acceleration experiment method was established for full-scale solid rocket motor by using rocket sled as overload and recycling platform.The structure of rocket sled system was determined by the strength and vibration numerical simulation.The test trajectory was designed by controlling the thrust of the boost motor.A successful acceleration test of SRM was carried on by rocket sled system for the first time in China.The pressure and the vibration data were recorded and the heading acceleration of the test motor was more than 16 g with duration of 2.258 s.The pressure oscillation characteristic of the test motor was similar to the earlier flight test motor.It is concluded that the acceleration of the missile could induce the combustion instability of the solid rocket motor.

关 键 词：固体火箭发动机 火箭橇 过载 不稳定燃烧 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]