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首页> 外文会议>Saint Petersburg International Conference on Integrated Navigation Systems; 20060529-31; Saint Petersburg(RU) >USE OF CORRECTED STRAPDOWN INERTIAL NAVIGATION SYSTEM BASED ON FIBER-OPTIC GYROSCOPES AND QUARTZ ACCELEROMETERS FOR INTERPLANETARY SPACECRAFTS MOTION CONTROL
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USE OF CORRECTED STRAPDOWN INERTIAL NAVIGATION SYSTEM BASED ON FIBER-OPTIC GYROSCOPES AND QUARTZ ACCELEROMETERS FOR INTERPLANETARY SPACECRAFTS MOTION CONTROL

机译：基于光纤陀螺仪和石英加速度计的校正捷联惯导系统在星际星际运动控制中的应用

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摘要

In article the opportunity of use strapdown inertial navigation system (SINS) on the base of fiber-optic gyroscopes and quartz accelerometers corrected from star sensors and satellite navigation equipment (SNE) for perspective interplanetary spacecrafts motion control on phases of interplanetary trajectory insertion, trajectory correction and braking during transition to Mars orbit is investigated. Results of onboard control complex accuracy characteristics estimation are presented at the given dynamic spacecraft scheme which is taking into account the liquid oscillations in tanks and structure elements elasticity. At modelling the errors of measuring devices installation, errors of SINS initial alignment and instrumental errors of SINS sensitive elements, variation of control engines parameters were taken into account. The structure of the developed complex of imitation modelling of interplanetary spacecraft controlled motion is resulted. Estimations of active flight legs realization accuracy were received by a method of statistical modelling of spacecraft controlled motion.
机译：在文章中，有机会利用基于陀螺仪的惯性导航系统（SINS）在光纤陀螺仪和石英加速度计的基础上进行校正，这些陀螺仪已从星形传感器和卫星导航设备（SNE）进行了校正，从而可以对透视行星际航天器在行星际轨迹插入，轨迹校正的阶段进行运动控制并研究了向火星轨道过渡期间的制动情况。在给定的动态航天器方案中给出了机载控制复杂精度特性估计的结果，该方案考虑了储罐中的液体振荡和结构元件的弹性。在对测量设备安装误差，SINS初始对准误差和SINS敏感元件的仪器误差建模时，要考虑到控制引擎参数的变化。得出了已开发的行星际航天器受控运动模拟模型的结构。通过对航天器控制的运动进行统计建模的方法，可以收到对主动飞行腿实现精度的估计。

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