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本文对高超声速巡航飞行器惯性/导引头组合导航方案、模型和算法进行了研究。对末段的惯性/导引头组合导航系统的误差进行了分析和建模。利用导引设备提供的视线角测量信息,建立了惯性/导引头组合的测量模型和组合导航系统的卡尔曼滤波器。对末段视角辅助捷联惯性导航系统组合方案进行了仿真分析。结果表明利用导引头视线角信息辅助捷联惯性导航能提高末段制导的性能。
In this paper, inertial / seeker integrated navigation solutions, models and algorithms for hypersonic cruise vehicles are studied. The error of the inertial / seeker integrated navigation system in the final stage was analyzed and modeled. Based on the line of sight measurement information provided by the guidance equipment, a measurement model of the inertial / seeker combination and a Kalman filter of the integrated navigation system are established. Finally, a simulation analysis of the scheme of the terminal strapdown strapdown inertial navigation system was made. The results show that the guidance of the line of sight angle information assisted strapdown inertial navigation can improve the performance of the final guidance.