固体火箭发动机装药结构完整性冷增压试验研究

Experimental study on solid rocket motor grain structure integrity by cold pressurization

为研究固体火箭发动机(Solid rocket motor,SRM)点火阶段药柱的结构完整性,建立了气/液组合介质冷试车快速建压试验系统。该系统建压速率达300 MPa/s以上,可有效模拟发动机低温点火冲击过程。采用该系统对两台某发动机进行了多次低温冷增压试验,并完成冷增压试验后的热试车试验,获得了装药结构完整性失效边界,并初步验证了冷增压试验系统对某发动机安全工作无影响。

To study the influence of the ignition and pressure construction process of solid rocket motor(SRM)on the structural integrity of the grain,a set of gas/liquid combined medium cold test rapid pressure construction experiment system is developed.The system has a pressure construction rate of more than 300 MPa/s,which can effectively simulate the impact process of low temperature ignition of the motor.The system is used to carry out multiple low temperature cold pressurization experiments on two motors,and the hot test after the cold pressurization experiment is completed.The failure boundary of the structural integrity of the grain is obtained,and it is preliminarily verified that the cold pressurization experimental system could not influence the safety work of the motor.