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针对航天器自主导航方法不适合高超声速临近空间飞行器的问题,研究了基于非开普勒轨道的高超声速临近空间飞行器自主天文导航方案.论述了基于非开普勒轨道的自主天文导航机理,通过对高超声速临近空间飞行器受力分析,建立了动力学方程;利用矢量倒数法则推导出空间运动方程;设计了基于非开普勒轨道的状态模型和基于星光折射间接敏感地平的观测模型,采用卡尔曼滤波进行了仿真验证.仿真结果表明,基于非开普勒轨道的高超声速临近空间飞行器自主天文导航可达到较高的位置和速度精度.
In view of the problem that the autonomous navigation method of spacecraft is unsuitable for hypersonic approaching space vehicles, a non-Keplerian orbital independent hypersonic approach spacecraft autonomous astronomical navigation scheme is studied. The autonomous astronomical navigation mechanism based on non-Keplerian orbit Based on the force analysis of hypersonic near-space vehicles, the dynamic equations were established, the equations of motion of the space were deduced by the vector reciprocal rule, the non-Keplerian orbit-based state model and the indirect sensitive horizon model based on the star-refraction were designed, The results of simulation show that the autonomous astronomical navigation based on non-Kepler orbits of Hypersonic spacecraft can achieve high position and velocity accuracy.