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针对实际动态工况条件下捷联惯导输出与静态条件下输出存在一定误差的问题,在仅考虑纵向振动的条件下,将飞行器仪器舱内的惯导系统等效为杆与阻尼弹簧振子的组合系统,利用复模态分析方法使方程解耦,并推导了动态扰动环境中惯导加速度响应的半解析表达式,给出了实际敏感加速度的包络范围,指出捷联惯导加速度计敏感值变为围绕真实值分布的随机变量是动态环境条件下产生加速度误差的根本原因之一。
Aiming at the problem that there is a certain error in the output of the SINS under static conditions under the actual dynamic operating conditions, the inertial navigation system in the aircraft instrument cabin is equivalent to the rod and the damped spring oscillator only considering the longitudinal vibration Combinatorial system, the equation is decomposed by complex modal analysis method, and the semi-analytical expression of inertial acceleration response in dynamic disturbance environment is deduced. The envelope of actual sensitive acceleration is given, and the sensitivity of SINS accelerometer is pointed out The change of value into a random variable around the true value distribution is one of the root causes of acceleration error under dynamic environmental conditions.