摘要
介绍了一种低冲击分离装置的结构,并对其冷气驱动分离试验进行了分析。依据能量守恒定律和空气动力学原理,为分离装置的冷气驱动分离过程构建了数学模型;借助数学模型,对分离装置中扇形块两端的支撑角对分离过程的影响进行了仿真和分析。通过仿真结果可发现,扇形块顶端支撑角的变化对分离过程中分离时间和峰值气压的影响很小,而扇形块底端支撑角的改变则会引起分离时间和峰值气压的明显变化。因此,在保证分离功能可靠实现的前提下,可通过减小扇形块底端支撑角来降低分离过程的冲击响应。该结论对分离装置的设计和优化具有指导意义。
The structure and the bench test process of a kind of low-shock separation device were introduced. According to the law of conservation of energy and aerodynamics principle, a mathematical model was established. The influence of the support angle on the air-driven separation process was simulated. The simulation results show that the change of upper support angle has little influence on the separation time and peak pressure, while the influence on the separation time and peak pressure induced by the change of lower support angle is obvious. Reliable separation process can be guaranteed by increasing the upper support angle and decreasing the lower support angle. The simulation results are useful for the separation device design and optimization.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第1期20-22,32,共4页
Journal of Solid Rocket Technology
关键词
低冲击分离装置
冷气驱动试验
数学模型
仿真
low-shock separation device
bench test
mathematical model
simulation
