基于质量矩技术的低轨微纳卫星星座相位部署方法研究

With the rapid development of information and miniaturization technology, the application of micro/nano satellites in the field of space science has gradually become the focus research of aerospace industries and commercial companies. The existing methods of satellite constellation deployment have some problems such as high cost and highly dependence on launchers. In this study, an concept of inplane maneuvering using differential-drag is proposed to complete the phase deployment of micro/nano satellite constellation. Firstly an integrate dynamic model of the attitude control system using mass moment control technology is deduced using Newton-euler method, to establish the function expressions between the actuators motion with the attitude angles. Subsequently a kind of dynamic sliding controller with nolinear characteristic is designed to control the attitude of each satellite. With regard to the inplane maneuvering between a chaser and a target satellite, a relative dynamic model is build and a Lyapunov function with the phase error as the state is constructed. An adaptive phase maneuvering controller associated with aerodynamic density is designed afterwards. Taking the constellation phase deployment time as optimization target, a genetic algorithm is finally used to select the target satellite and the target phase of the chaser satellites in the phase deployment strategy. This research provides a new and low cost technical approach to realize orbit deployment for the micro/nano satellite.

随着信息技术与小型化技术的飞速发展，微纳卫星在空间科学领域的应用逐渐成为航天工业部门与商业航天机构研究的焦点。针对目前现有的微纳卫星星座同轨道面部署方法成本高、对运载依赖性强的问题，提出利用气动差分方法实现低轨微纳卫星星座的同轨道面相位部署。基于牛顿欧拉法建立卫星质量矩姿态控制系统的完整动力学模型，构建活动质量块运动与姿态角运动之间的映射关系，开展动态非线性滑模控制器设计以实现单颗卫星的姿态控制；在星间相对相位转移方面，通过机动星与目标星之间的相对运动动力学建模，以目标星间相位误差为状态量构建Lyapunov函数，研究与气动密度相关联的自适应相位转移控制器设计；以星座相位部署时间为优化目标，利用遗传算法解决同轨道面星群相位部署策略中目标星以及机动星目标相位的选取问题。为未来微纳卫星实现低成本轨道部署提供一种新的技术途径。

针对目前微纳卫星星座同轨道面部署方法难度大、成本高、对运载依赖性强的问题，提出一种利用气动差分原理实现低轨微纳卫星星座同轨道面相位部署的方法。首先，在质量矩姿态控制方面，基于牛顿欧拉法建立卫星质量矩姿态控制系统的完整动力学模型，采用麦克斯韦模型推导了卫星气动力矩表达式，采用了质量矩与磁力矩器双执行机构的复合控制方式以避免系统欠驱动；数值仿真表明，内环基于前馈补偿的积分分离离散PID控制器能有效减小由滑块运动引起的快时变附加干扰力矩，外环基于干扰观测器的离散滑模控制器能有效估计系统复杂慢时变干扰，精确控制卫星机动到目标姿态。其次，在星间相对运动控制方面，探索了基于差分气动阻力和升力的多星编队控制方法；针对欠驱动系统，采用了考虑输入受限的LMI控制算法，并针对两种编队队形进行了数值仿真；结果验证了仅通过改变机动星姿态即可实现相对运动控制的可行性，检验了控制算法的有效性。最后，研究建立了星座星间相位漂移模型，给出了星座相位部署策略过程，以及各机动星相位机动的算法；综合仿真结果表明：利用差分气动技术进行星座相位部署的方法是可行的，且引入质量矩技术具有节省能耗的巨大优势，对于实现低成本星座部署具有重要意义。

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