在动机座发射条件下,为了评估初始参数误差对平台惯导影响,建立由遥测视速度、视加速度和初始参数计算导航参数的微分方程。初始参数分为两类,原点坐标转换参数和积分初始参数。建立了初始参数对导航输出影响的微分模型,通过仿真数据,检验了导航参数计算模型的逼近精度。利用添加不同误差的初始参数计算导航输出与真实轨道偏差评估初始参数误差对导航输出的影响;利用蒙特卡洛打靶法和绝对误差界确定方法评估初始参数误差导致的关机时刻轨道散布。模型分析计算发现,发射装订初始速度参数只有作为积分初始参数时才对导航输出有影响,特征段导航计算结果的逼近精度降低。关机时刻轨道误差随初始参数误差线性增加,初始北向和东向速度误差引起的轨道偏差量级相同。

In moving base state, for estimating the influence on platform INS by initial launched parameter error, a differential equation was built to calculate navigation parameters by using telemetry apparent velocity, apparent acceleration and initial launched parameters. Initial launched parameters were separated into two kinds: parameters for original coordinate transformation and initial values of integration. Differential models were built to calculate the influence on navigation by initial parameter. Artificial data was built; The approximation accuracy of computation model for navigation parameter was given out; the deviation between navigation and real trajectory calculated using initial parameter with errors was used to estimate the influence on navigation by initial parameter errors; Monte Carlo method and method of absolute error bound determination were used to estimate the scatter of trajectory on shutdown point caused by initial parameter error. It is concluded form model analysis and calculation that launch initial velocities affects the navigation only as initial values of integration, approximation accuracy of computation model reduces between stages, the trajectory error on shutdown point increases linearly with initial launched parameter error, and the trajectory errors caused by initial north and east velocity errors are same in magnitude.