基于微元划分方法的空间站力矩平衡姿态计算

Torque Equilibrium Attitude Calculation of Space Station via Square Division Method

针对空间站构型的复杂性问题,建立了一种高效的姿态动力学数值分析方法。在建立飞行器姿态运动的刚体动力学模型和重力梯度力矩模型的基础上,对空间站构型进行有限微元划分,将其构型转化为微元集合用于进行气动力矩计算。基于该数值分析方法,提出了空间站力矩平衡姿态的动力学计算方法,从而避免全姿态遍历的大规模计算。仿真结果表明,微元划分方法能够有效的计算出复杂构型空间飞行器在任意姿态下的气动力矩影响,所提出的力矩平衡姿态计算方法能够快速收敛并得到稳态解。

In allusion to the configuration problem of the space station, a numerical analysis method for the attitude dynamics is proposed. The attitude dynamic model and the gravity gradient torque model are established. The configuration of the space station is divided into a finite set of micro squares to calculate the aerodynamic torque. A damping dynamical method is established to calculate the torque equilibrium method to avoid the large computation of the attitude-traverse search. Simulation result shows that the square division method is validated to calculate the aerodynamic influence to the space station of optional attitude, and the torque equilibrium attitude calculation can quickly converge to the stable solution.