角度约束辅助测量的深空探测器自主天文测角导航方法

Autonomous celestial navigation method for a deep-space probe based on angle-constraint aided celestial angle measurement

高精度的天文量测信息是满足深空探测器高精度自主天文测角导航的必要条件.天文测角量测信息多种多样,之间具有几何约束关系,测量误差具有不同特性且符合相应的约束条件.本文提出了一种基于角度约束辅助测量的深空探测器自主天文测角导航方法,该方法以深空探测器轨道动力学模型作为状态模型,以火星、火卫一和火卫二与探测器之间的方位角作为量测量建立量测模型,并对量测量进行角度约束建模,然后利用遗传算法-序列二次规划混合非线性规划方法对角度约束模型进行非线性规划,由于系统模型均为非线性模型,因此本文利用容积卡尔曼滤波对系统状态进行估计,减小随机误差,并分析了天文测角的量测精度对导航精度的影响.仿真结果表明,本文所提方法可有效抑制多源随机量测误差,实现深空探测器高精度自主导航.

High-precision measurement is necessary for high autonomous navigation of deep-space probes.There are many kinds of astronomical measurement information and exist many geometric constraints between astronomical measurement information.Measurement error has different characteristics and meets the corresponding constraints.In this study,an autonomous celestial navigation method for deep-space probes based on angle-constraint assisted celestial angular navigation is proposed.The method takes the orbit dynamics model of the deep-space probe as the state model,and the azimuth between Mars,Phobos,and Phobos and the probe,as the measurement,to establish the measurement model.The angle-constraint model of the measurement is established,and then the genetic algorithm sequence Quadratic programming-mixed nonlinear programming method is used for nonlinear programming of angle constrained model.Cubature Kalman filter(CKF)is used to estimate the system state to reduce the random error because the system models are nonlinear,and the influence of astronomical measurement accuracy on navigation results is analyzed.Simulation results show that the proposed method can suppress the multi-source measurement error and achieve high-precision autonomous navigation of the deep-space detector.