基于敏感性的火星大气进入段自主导航方法  

Mars atmospheric entry autonomous navigation method based on sensitivity

作　　者：娄泰山[1] 傅惠民[2] 肖强[2] 王治华[2] 

机构地区：[1]郑州轻工业学院电气信息工程学院,郑州450002 [2]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《中国科技论文》2016年第14期1613-1618,共6页China Sciencepaper

基　　金：国家重点基础研究发展计划(973计划)资助项目(2012CB720000);国家自然科学基金资助项目(11202011);郑州轻工业学院博士基金资助项目(2015BSJJ026)

摘　　要：大气进入段的高精度导航是满足未来火星探测任务定点着陆要求的关键技术之一。针对导航精度对探测器升阻比的敏感性较大的问题,建立了升阻比不确定性的百分比误差模型,并给出了探测器状态估计误差对百分比参数的敏感性矩阵及相应的扰动矩阵。以探测器的导航状态估计误差对升阻比的敏感性为代价函数,通过调节增益矩阵进行导航滤波,可明显提高火星进入段自主导航的精度。IMU/无线电测距组合导航的数值仿真结果验证了该导航方法的有效性。High-precision atmospheric entry navigation is a key technology of the pinpoint landing capability in Mars exploration missions. The navigation accuracy is sensitive to the vehicle＇s lift-to-drag ratio. The uncertainty is modeled with the lift-to-drag ratio percentage, and the sensitivity matrices and perturbation matrices are proposed to describe the vehicle＇s state estimate errors respected to the percentage parameter. The cost function,including the sensitivity of the navigation state estimate errors respected to the lift-to-drag ratio, is minimized to obtain the gain matrix. The accuracy of the Mars entry auto-navigation could be obviously enhanced. The effectiveness of the method is shown in the results of the numerical simulations with the IMU/Radio measurement integrated navigation.

关 键 词：火星进入段 自主导航 升阻比 敏感性 弱敏扩展Kalman滤波 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]