摘要
为研究室温点火建压阶段高能固体推进剂药柱的结构形变,利用建立的全液介质的新型冷增压试验系统成功开展了实际建压条件分别为8.65 MPa、269 ms和7.48 MPa、264 ms时硝酸酯增塑聚醚(NEPE)高能固体推进剂装填的Φ200 mm圆管型固体火箭发动机(SRM)结构试验器的室温冷态冲击试验,并基于有限元数值仿真计算获得了该试验器药柱结构在建压条件为7.5~9.0 MPa、250~400 ms时的体积变化率。试验结果表明,药柱内腔压强—时间变化曲线和容积式流量装置活塞位移—时间曲线均具有较好的可重复性和一致性,且压强—时间曲线变化特性与真实发动机的成功点火试车结果曲线特性保持一致;随着建压条件由7.48 MPa、264 ms升至8.65 MPa、269 ms,建压速率由28.33 MPa/s升高至32.16 MPa/s,药柱体积变化率由1.14%增大至1.27%。数值仿真结果表明,建压条件7.48 MPa、264 ms和8.65 MPa、269 ms时的药柱体积变化率分别为1.13%和1.29%,与试验结果的相对误差分别为0.88%和1.57%,即所建全液冷增压试验系统能够安全有效模拟测试室温点火建压阶段高能SRM药柱的结构形变量;其次,建压条件7.5~9.0 MPa、250~400 ms范围内,随建压时间增长和建压压强升高,药柱体积变化率均呈线性增加趋势,而且相较建压时间,建压压强对NEPE高能固体推进剂装药结构试验器药柱的体积变化具有更显著的影响效果。
To study the structural deformation of high-energy solid propellant grain during ignition process at room temperature,cold impact tests on a 200 mm diameter cylindrical solid rocket motor(SRM)structure tester loaded with nitrate ester plasticized polyether(NEPE)propellant under actual building pressure conditions of 8.65 MPa,269 ms and 7.48 MPa,264 ms at room temperature were conducted using a newly established all liquid medium cold pressurization testing system.Meanwhile,based on finite element numerical simulation,the volume change rate of the grain for the tester under building pressure conditions of 7.5—9.0 MPa and 250—400 ms.The experimental results show that the pressure—time curves of the inner hole of the grain and the displacement—time curves of the piston for the volumetric flow device have good repeatability and consistency,and the variation characteristics of the pressure—time curves are consistent with the successful ignition test results of the real SRM.As the pressure building conditions increases from 7.48 MPa and 264 ms to 8.65 MPa and 269 ms,the pressure building rate increases from 28.33 MPa/s to 32.16 MPa/s,and the volume change rate increases from 1.14%to 1.27%.The numerical simulation results show that the volume change rate of the grain under the building pressure conditions of 7.48 MPa,264 ms and 8.65 MPa,269 ms is 1.13%and 1.29%,respectively.The relative error with the experimental result is 0.88%and 1.57%,respectively.Therefore,the all liquid medium cold pressurization testing system can safely and effectively simulate and test the structural deformation of high-energy SRM propellant grain during ignition at room temperature.Secondly,under the pressure conditions of 7.5—9.0 MPa and 250—400 ms,the volume change rate of the grain shows a linear increase trend with the increase of time and pressure.Moreover,compared with the time,the pressure has a more significant impact on the volume change of the SRM grain with NEPE high-energy solid propellant grain.
作者
王哲君
郭琪
张峰涛
刘向阳
张旭
WANG Zhe-jun;GUO Qi;ZHANG Feng-tao;LIU Xiang-yang;ZHANG Xu(Rocket Force University of Engineering,Xi′an 710025,China;Xi′an Aerospace Chemical Power Co.,Ltd.,Xi′an 710065,China;Hubei Institute of Aerospace Chemotechnology,Xiangyang Hubei 441003,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)
出处
《火炸药学报》
北大核心
2025年第8期715-723,I0002,共10页
Chinese Journal of Explosives & Propellants
基金
国家自然科学基金(No.11772352,No.22205259)。
关键词
高能固体推进剂药柱
结构形变
冷增压测试试验
数值仿真
体积变化率
high-energy solid propellant grain
structural deformation
cold pressurization test
numerical simulation
volume change rate
