On all-propulsion design of integrated orbit and attitude control for inner-formation gravity field measurement satellite
On all-propulsion design of integrated orbit and attitude control for inner-formation gravity field measurement satellite
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DOI：
10.1007/s11431-011-4621-8
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发表时间：
2011-11
期刊：
影响因子：
--
通讯作者：
Li Ji;Kun Liu;Junhua Xiang
中科院分区：
文献类型：
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作者：
Li Ji;Kun Liu;Junhua Xiang
编队内重力场测量卫星（IFS）是一种新型的纯重力轨道器。其目的是通过精密定轨和相对状态测量，以前所未有的精度和空间分辨率测量地球重力场。卫星外控制是保证星内卫星在纯引力轨道上稳定运行的关键因素之一。本文研究了惯性参考系在稳态阶段仅使用推力器的轨道和姿态综合控制问题。建立了六自由度平动和转动动力学模型，考虑了四元数表达引起的非线性和群体推力器引起的耦合。采用约束非线性模型预测控制（CNMPC）技术，建立了轨道姿态一体化控制的二次型优化模型。仿真实验表明，该算法能够实现快速计算，并克服部分约束的非凸性。推力器布局合理，推力消耗小，完全满足惯性力系统的使命要求。
The inner-formation gravity field measurement satellite (IFS) is a novel pure gravitational orbiter. It aims to measure the Earth’s gravity field with unprecedented accuracy and spatial resolution by means of precise orbit determination (POD) and relative state measurement. One of the key factors determining the measurement level is the outer-satellite control used for keeping the inner-satellite flying in a pure gravitational orbit stably. In this paper the integrated orbit and attitude control of IFS during steady-state phase was investigated using only thrusters. A six degree-of-freedom translational and rotational dynamics model was constructed considering nonlinearity resulted from quaternion expression and coupling induced by community thrusters. A feasible quadratic optimization model was established for the integrated orbit and attitude control using constrained nonlinear model predictive control (CNMPC) techniques. Simulation experiment demonstrated that the presented CNMPC algorithm can achieve rapid calculation and overcome the non-convexity of partial constraints. The thruster layout is rational with low thrust consumption, and the mission requirements of IFS are fully satisfied.