弹道导弹的过载段高精度捷联惯导系统多源误差分析与仿真

Multi-source error analysis and simulation of high accuracy strapdown inertial navigation system in overload section of ballistic missile

过载段弹道导弹受多种外力综合作用,形成的高动态环境使所载的惯性导航系统在关机点处产生较大的误差积累。在原有的常用低动态误差模型基础上,对传感器误差、标度因数误差、不正交误差、杆臂误差、二次项误差、圆锥运动及线振动以及初始失准角误差等多种误差源进行了分析,建立了多维、适于高动态的误差模型。以某过载段弹道导弹轨迹为对象进行了仿真实验,针对所述误差源对系统误差的影响进行了分析。仿真结果表明,与传统模型相比,所提出的误差模型在高动态环境下补偿后横向位置偏移精度提高了80倍,对关机点处导弹精度提高有明显作用,为后续进一步提高导弹落点精度提供了更丰富的理论支撑。

A high dynamic environment is formed by a combination action of various external forces on ballistic missile in overload section, which will produce large error accumulation of inertial navigation system at shutdown point. A multi-source error model is established, aiming at the high dynamic environment in boost phase. Based on the existing low dynamic model, some novel sources of SINS errors are analyzed, such as sensor errors, scale factor error, nonorthogonal error, level arm error, quadratic error, coning motion, linear vibration, and initial misalignment angle error of SINS. Then, simulations are done and influences of the error sources on the system errors are analyzed by a ballistic missile trajectory in boost phase. Simulation results show that, lateral positional deviation accuracy is improved by 80 times after the proposed error model compensation under the high dynamic environment, compared to the traditional error compensation model, which provides more theoretical support to improve missile landing accuracy further.