摘要
飞行器在发射之前,往往要受到地面风的作用,这将引起飞行器的振动响应,并影响到惯性测量单元(IMU)的初始对准过程。特别是当采用自瞄准技术时,需要知道IMU安装位置处可能出现的最大角速率。本文提出采用低风速条件下的实物试验结果,加上理论分析方法外推高风速条件下最大角速率响应的思路。解决了实物试验难以达到所要求的风速,而模型试验又较难模拟边界条件和真实刚度分布的困难,获得了较为满意的结果。
Before taking off, space vechicles are almost always exposed for high winds. As a result, oscillation of the vechicle will occur and it make inertial self-alignment unaccuracy. Thus it is important to know the maximum radian velocity at the location of IMU when self-aligning. This paper proposed a method which uses full size experimental data at low wind speed and theoretical formula to extrapolate the radian velocity at high wind speed. It can avoid the difficulties of obtaining the required wind speed in a full size experiment and simulating the actual boundary condition in a scaled model experiment.
出处
《强度与环境》
2006年第4期8-12,共5页
Structure & Environment Engineering
