基于混合式惯导系统构型优化的弹道导弹落点精度研究

doi:10.7527/S1000-6893.2025.32815

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基于混合式惯导系统构型优化的弹道导弹落点精度研究

康林¹,王新龙¹,陈万春¹,雷文贵²

1. 北京航空航天大学宇航学院
2. 北京航空航天大学

收稿日期:2025-09-22 修回日期:2025-11-10 出版日期:2025-11-10 发布日期:2025-11-10
通讯作者: 雷文贵

Research on Ballistic Missile Impact Point Accuracy Based on Hybrid Inertial Navigation System Configuration Optimization

Received:2025-09-22 Revised:2025-11-10 Online:2025-11-10 Published:2025-11-10
Contact: LEI

摘要/Abstract

摘要： 为了提升弹道导弹落点精度，本文提出了一种高效的混合式惯导构型优化方法。该方法基于摄动法构建了混合式惯导误差快速计算模型，将落点圆概率误差计算时间大幅缩减至秒级，为射前快速构型寻优奠定了坚实基础。进一步深入分析惯性元件敏感轴指向对导航精度的影响，并以圆概率误差为性能指标，采用四元数描述构型参数，建立了能够避免计算奇异性并覆盖全姿态空间的优化模型。对该模型的仿真验证与机理分析表明，所提方法可使弹道导弹落点精度提升约20%~30%，且无需增加硬件成本或改变飞行弹道，在特定飞行轨迹下，相比静态最优构型表现出更高精度。这一提升主要得益于对惯性元件残余安装误差的有效抑制，从而在不同发射方向下均能实现导航精度的显著提升，验证了该方法的有效性与普适性。

关键词: 混合式惯导, 构型优化, 命中精度, 制导工具误差, 弹道导弹

Abstract: To improve the impact point accuracy of ballistic missiles, this paper presents an efficient configuration optimization method for a hybrid inertial navigation system (INS). A rapid error computation model for the hybrid INS is developed based on the perturbation method, reducing the computation time of the circular error probable (CEP) to seconds-level and enabling fast pre-launch configuration optimization. Furthermore, the influence of the sensitive-axis orientation of inertial components on navigation accuracy is investigated. Using CEP as the performance metric and representing configuration parameters with quaternions, an optimization model is established that avoids computational singularities while fully covering the attitude space. Simulation and mechanistic analysis indicate that the proposed approach can improve missile impact accuracy by approximately 20%–30% without additional hardware cost or trajectory modification, and, for certain flight trajectories, achieves higher accuracy than static optimal configurations. This improvement primarily results from the effective suppression of residual installation errors in inertial components, thereby significantly enhancing navigation accuracy across different launch directions and validating the effectiveness and generality of the proposed method.

Key words: Hybrid inertial navigation system, Configuration optimization, Impact accuracy, Guidance instrumentation error, Ballistic missile

中图分类号:

康林王新龙陈万春雷文贵. 基于混合式惯导系统构型优化的弹道导弹落点精度研究[J]. 航空学报, doi: 10.7527/S1000-6893.2025.32815.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于混合式惯导系统构型优化的弹道导弹落点精度研究

Research on Ballistic Missile Impact Point Accuracy Based on Hybrid Inertial Navigation System Configuration Optimization

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