摘要
固冲发动机转级时进气道出口堵盖通常采用火工品爆炸方式打开,会对固冲发动机产生很大的瞬时冲击作用,进而影响弹体飞行姿态和弹上仪器的正常工作。借助Autodyn软件的显式动力学方法,对进气道出口堵盖打开时爆炸冲击响应进行了数值仿真分析,获得了固冲发动机不同位置的冲击加速度时域曲线和冲击响应谱曲线,并与试验结果进行了对比分析。结果表明,数值仿真结果与试验结果基本一致,轴向冲击加速度的最大值偏差为6.2%,径向冲击加速度的最大值偏差为4.9%。通过仿真分析,揭示了固冲发动机进气道出口堵盖打开时最大冲击加速度和冲击响应谱的变化规律,对评估全弹飞行过程中进气道出口堵盖打开时振动冲击环境以及对弹上仪器的影响具有重要的意义。
The inlet port cover is most commonly opened by explosive during the transition of solid rocket ramjet.High transient shock response is generated on solid rocket ramjet,which tends to influence missile flight attitude and instrument normal operation.In this article,the pyroshock response at the moment of the inlet port cover opening in solid rocket ramjet was numerically simulated by using the explicit dynamics method of Autodyne software.The shock acceleration time history curve and the shock response spec⁃trum curve of solid rocket ramjet at different locations were obtained and compared with the test results.The results demonstrate that the numerical simulation results are basically consistent with the test results.The maximum deviation of the axial shock acceleration is 6.2%,and the maximum deviation of the radial shock acceleration is 4.9%.Through simulation analysis in this paper,the variation law of maximum shock acceleration and shock response spectrum are revealed at the moment of the inlet port cover opening in solid rocket ramjet.It is great significance to evaluate the vibration and shock environment at the moment of the inlet port cover opening during the missile flight and the influence on the missile instruments.
作者
郑凯斌
董新刚
喻琳峰
曾庆海
李岩芳
ZHENG Kaibin;DONG Xingang;YU Linfeng;ZENG Qinghai;LI Yanfang(National Key Laboratory of Combustion,Flow and Thermo-structure,the 41st Institute of the Fourth Academy of CASC,Xi’an 710025,China;The Fourth Academy of CASC,Xi’an 710025,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2021年第2期247-253,共7页
Journal of Solid Rocket Technology
