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针对平台式机载天文自主导航系统载体振动对导航系统定位精度的影响问题,理论分析了载体对导航平台影响的振动形式,给出振动角位移是主要影响量的结论。研究了天文导航系统的单星定位导航建模思路,根据振动角位移的特点给出了角位移补偿中近似坐标转换矩阵。设计了振动实验,建立了定位模型,给出了载体振动主要以角位移的形式将误差传递给导航系统平台。试验结果表明:振动角位移带来的误差为天文导航定位的主要影响因素,X、Y轴200″的轴向振动角位移带给天文导航系统的定位误差近似为600 m。
In order to solve the problem of the influence of carrier vibration on the positioning accuracy of navigation system in platform-mounted astronautics autonomous navigation system, the vibration modes of the carrier on the navigation platform are analyzed theoretically. The results show that the displacement of vibration angle is the main influence. The single-satellite positioning and navigation modeling method of celestial navigation system is studied. According to the characteristics of vibration angle displacement, the approximate coordinate transformation matrix in angular displacement compensation is given. The vibration experiment is designed and the positioning model is established. The error of the carrier vibration is mainly transmitted to the navigation system platform in the form of angular displacement. The experimental results show that the error caused by the displacement of the vibration angle is the main influence factor of the positioning of the astronomical navigation. The positioning error brought by the axial vibration angle displacement of 200 "on the X and Y axes to the celestial navigation system is approximately 600 m.