摘要
以运载火箭研制方提供的准静态载荷为依据,提出了改进的航天器系统级正弦振动试验力限条件,并结合典型算例与目前采用的传统力限条件进行了对比研究。研究表明:改进的力(矩)限条件及相应的加速度下凹条件剔除了对界面合力(矩)无影响的过载项,物理概念更为清楚,计算方法更为合理;改进后的力限或加速度条件明显低于传统的试验条件,有利于减少航天器系统级试验中的过试验现象。
This paper presents the modified force limited specifications of the sine vibration test for the spacecraft system based on the quasi-static loads given by the launch vehicle providers, and makes comparisons in three typical simulation cases with the traditional specifications used by engineers working for spacecraft programs. It is shown that the modified force limited specifications and their corresponding acceleration notch levels have a clearer physical concept and more rational calculation methods, since the futile items in the resultant interface forces or moments of the quasi-static loads are eliminated. Besides, the modified specifications specify evidently less restricted conditions than the traditional ones and thus help to reduce the over-test problems in the vibration tests for the spacecraft system.
出处
《航天器环境工程》
2013年第1期63-67,共5页
Spacecraft Environment Engineering
基金
国防973资助项目(编号:613133)
关键词
航天器
正弦振动
系统级试验
力限条件
准静态载荷
spacecraft
sine vibration
system-level test
force limited specification
quasi-static load
