基于準靜態(tài)載荷的航天器系統(tǒng)級正弦振動試驗力限條件

Force limited specifications ofthe sine vibration test for the spacecraft system based on quasi-static loads

摘要: 以運載火箭研制方提供的準靜態(tài)載荷為依據(jù)，提出了改進的航天器系統(tǒng)級正弦振動試驗力限條件，并結(jié)合典型算例與目前采用的傳統(tǒng)力限條件進行了對比研究。研究表明：改進的力（矩）限條件及相應的加速度下凹條件剔除了對界面合力（矩）無影響的過載項，物理概念更為清楚，計算方法更為合理；改進后的力限或加速度條件明顯低于傳統(tǒng)的試驗條件，有利于減少航天器系統(tǒng)級試驗中的過試驗現(xiàn)象。

Abstract: 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.