基于敏感性的火星大气进入段自主导航方法
首发时间:2014-06-03
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。
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
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Mars Atmospheric Entry Autonomous Navigation Method based on Sensitivity
Abstract:IHigh-precision atmospheric entry navigation is a key technology to meet the future Mars exploration missions required the pinpoint landing capability. Based on the problem that the navigation accuracy is sensitive to the vehicle's lift-to-drag ratio, this paper models the uncertainty with the lift-to-drag ratio percentage, and gives the sensitivity matrices and perturbation matrices of the vehicle's state estimate errors respected to the percentage pa-rameter. 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. Based on this method, the accuracy of the Mars entry auto-navigation are obviously enhanced. The results of the numerical simulations, based on the IMU/Radio measurement integrated navigation, denominated the effectiveness of the method.
Keywords: Mars entry autonomous navigation lift-to-drag ratio sensitivity desensitized extended Kalman filter
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No.4598319310790140****
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