惯组飞行角振动环境测量与环境条件设计

Measure of IMU's Angular Vibration Environment During a Rocket Flight and Design of Test Condition

在多维振动环境下的惯组动态导航精度试验是考核惯组在接近真实飞行环境下精度指标能否满足要求的重要试验,如何合理制定多维振动环境条件一直是型号面临的难题。本文提出了一种火箭飞行中惯组角振动环境的测量方案,通过多个振动传感器的合理布置方式,并进行数据分析处理,实现了利用普通振动传感器测量飞行过程的角振动环境。应用此技术,在某型号飞行试验中首次成功获取惯组在主动段和再入段飞行的角振动环境,制定出了接近真实飞行状态的多维振动环境试验条件,避免了以往仅凭经验制定试验条件带来的风险。

Dynamic navigation accuracy test of a IMU(Inertial Measurement Unit)under multidimensional vibration environment is an important experiment to verify its environmental adaptability.The primary difficulty is designing the multi-dimensional vibration test condition which can simulate the real flight environment of a flying rocket.In this paper,a new approach is presented to measure the angular vibration environment of IMU in a flying rocket.By adopting a new spacial-locating manner of sensors and data processing,the new approach can measure the target's angular vibration envirionment using usual vibration sensors.In a rocket's flight test,this approach is actualized to measure IMU's angular vibration envirionment during ascent and reentry stages.And the multi-dimensional vibration test condition is desinged which covers the real flight environment.This approach can provide more accurate vibration test condition for IMU's precision experiment,and avoid the risk of designing test condition only according to previous experience.