冲量法固体推进剂燃速测试原始数据有效性判定  

Determination of Validity of Original Data of Burning Rate Test of Solid Propellant by Impulse Method

作　　者：王英红[1] 张鑫鹏 唐梓辰 顾涛 梁超[1] 庞爱民[2] 李伟[2] WANG Ying-hong;ZHANG Xin-peng;TANG Zi-chen;GU Tao;LIANG Chao;PANG Ai-min;LI Wei(Science and Technology on Combustion,Internal Flow and Thermal-Structure Laboratory,Northwestern Polytechnical University,Xi’an 710072,China;Science and Technology on Aerospace Chemical Power Laboratory,Hubei Institute of Aerospace Chemical Technology,Xiangyang 441003,China)

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,陕西西安710072 [2]湖北航天化学技术研究所航天化学动力技术重点实验室,湖北襄阳441003

出　　处：《推进技术》2023年第4期225-231,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金(NSFC21875061,NSFC21975066);航天化学动力技术重点实验室基金(STACPL 320201B03)。

摘　　要：为了定义并明确冲量法燃速测试的应用边界,通过对“推进剂药柱点火不同步”、“存在侵蚀”、“推进剂药柱同心度不好”3种情况下终了燃面偏离设计值的分析,提出以最大压强尤其是最大推力处的下降速率作为冲量法燃速测试数据有效性的判据,该判据同时解决了“裸露的推进剂药柱表面同步点火”无法评判的问题。根据燃烧室在无加质条件下燃气质量的变化规律,计算获得燃烧室压强随时间的改变趋势,与试验压强-时间曲线进行对比,提出数据有效性因子K,给出了原始数据有效性的数值判定方法。研究表明,当数据有效性因子K=1~1.2时,冲量法燃速测试结果与恒压发动机燃速测试结果一致性较好,数据有效。同时验证了喷管烧蚀会影响冲量燃速测试的压强范围,但不影响燃速测试结果。In order to define and clarify the application boundary of the impulse burning rate test,the descending rate at the maximum pressure,by analyzing the deviation,which comes from“inconsistent ignition”“erosion combustion”or“propellant eccentricity”,between the final combustion surface and design value,is proposed as the criterion for the validity of the burning rate test data of impulse method.Besides,the criterion is capable of judging whether the surface of bare propellant grain has been ignited synchronously.Based on the principle of conservation of mass,a numerical method to determine the validity of the original data is given.The data validity factor K is obtained by calculating the ratio of the theoretical pressure drop time to the actual value.The research shows that when the data validity factor K=1~1.2,the combustion rate test results of the impulse method are in good agreement with those of the constant pressure engine.Furthermore,it is verified that nozzle ablation can affect the pressure range of impulse burning rate test,but does not affect the burning rate test result.

关 键 词：固体推进剂 燃速测试 冲量法 点火同步性 原始数据 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]