Robust control of a spin-stabilized spacecraft via a 1DoF gimbaled-thruster and two reaction wheels.
Robust control of a spin-stabilized spacecraft via a 1DoF gimbaled-thruster and two reaction wheels.
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DOI：
10.1016/j.isatra.2016.10.007
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发表时间：
2017
期刊：
影响因子：
7.3
通讯作者：
H. Kouhi;M. Kabganian;F. F. Saberi-F.;M. Shahravi
中科院分区：
文献类型：
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作者：
H. Kouhi;M. Kabganian;F. F. Saberi-F.;M. Shahravi
在脉冲轨道机动中，推力矢量偏离质心（C.M）会产生较大的扰动力矩。本文提出并研究了一种基于单自由度万向推力器、两个反作用轮和自旋稳定的推力机动系统。主要目标是在不使用反作用控制系统（RCS）的情况下抑制干扰和推力矢量稳定。所提出的系统的非线性两体动力学制定。将控制器的设计归结为一个多目标优化问题，其中控制输入的峰值和H ∞性能是目标函数。基于峰峰值增益最小化，线性化模型的精度可以得到保证。优化结果给出了许多最优控制器，这是可以接受的推力机动。仿真结果表明了该方法在控制输入存在采样效应的情况下的适用性。
In impulsive orbital maneuvers, thrust vector misalignment from the center of mass (C.M) results in a large disturbance torque. In this paper a thrusting maneuver system is proposed and studied which is based on the combination of a one degree of freedom (1DoF) gimbaled-thruster, two reaction wheels (RWs) and spin-stabilization. The main goals are disturbance rejection and thrust vector stabilization without using reaction control systems (RCS). The nonlinear two-body dynamics of the proposed system is formulated. The controller design is formulated as a multi-objective optimization problem where the peak-value of the control input andH∞performance are the cost functions. Based on the peak-to-peak gain minimization, the accuracy of the linearized model can be guaranteed. The optimization results give many optimal controllers which are acceptable for a thrusting maneuver. The simulation results illustrate the applicability of the proposed method in presence of the sampling effects of the control inputs.