摘要
由飞行器级间分离性能分析的需要,文中针对所设计的新型级间分离机构分离过程做仿真分析。利用ANSYS分析了点火解锁的动力学细节,获得了准确的解锁时间;进而运用数值模拟对分离的全过程进行了仿真,获得了飞行器在分离前后的运动特性。通过将仿真结果与实验数据的对比验证了该分析方法的准确性和分离方案的可行性,为该分离机构的进一步应用与优化提供了可靠的参考依据。
In this paper the separation simulation of the new designed stage separation mechanism was made. The transient kinetic analysis of the unlock progress was made at first using ANSYS and acquired the true unlock time. Then the macro separation process was got by numerical simulation. Compared with the test data the result shows that the simulation method is credible and this new separation mechanism works well. The simulation provides basis for the application and optimization of this new mechanism.
出处
《弹箭与制导学报》
CSCD
北大核心
2014年第6期57-60,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
分离机构
有限元
数值解析
动力学仿真
separation mechanism
FEM
numerical simulation
dynamic simulation