Aerospace vehicle micro-vibration test condition acquisition method

The invention discloses an aerospace vehicle micro-vibration test condition acquisition method. The method comprises the following steps: searching a micro-vibration disturbance source of an aircraft in an on-orbit working process; classifying micro-vibration disturbance sources, and determining disturbance sources which cannot be avoided; carrying out a micro-vibration environment measurement test of a disturbance source which cannot be avoided, and obtaining a maximum vibration environment time-domain curve of the disturbance source; establishing a micro-vibration response analysis finite element model; carrying out transient response analysis, and determining the micro-vibration response of the precise instrument; and converting the micro-vibration response time-domain curve of the precise instrument into a frequency-domain curve, and performing envelope design to obtain micro-vibration test conditions of the precise instrument for subsequent test verification. 一种空天飞行器微振动试验条件获取方法，搜寻飞行器在轨工作过程中的微振动扰源；对微振动扰源进