固体火箭发动机喷管喉部瞬态热流的测量技术

摘要

改进了美国Nanmac公司的自更新快速响应热电偶,并将改进后的热电偶用于测量固体火箭发动机喷管喉衬内壁面上的瞬态温度和热流密度.测量是在一小型试验发动机上进行的,其喷管喉径为18 mm.分别采用黑火药、双基推进剂和复合推进剂进行了点火试验,试验结果表明本文的测量方法是可行的.%The "self renewing" fast response thermocouple developed by the Nanmac Corporation, US A, was improved,and employed to measure the transient temperature and heat flux density at the inner surface of the nozzle throat insert of a solid rocket motor. Measurements were conducted with a laboratory scale motor,whose inner diameter of throat insert was 18 mm. Ignition tests were conducted with black powder, double base propellant and composite propellant respectively. The experimental results show that the present measuring technique is feasible.