一种微型航天器姿态控制系统建模与分析

从航天器微小型化的角度出发，提出了仅利用两个飞轮进行航天器姿态控制的飞轮配置方案。该方案还可以对高速旋转的飞轮所储存的能量进行管理，不需要磁力矩器等额外的卸载装置，从而简化了飞轮姿态控制系统的结构。详细描述了系统的结构和工作原理，推导了航天器姿态控制系统的非线性动力学模型，分析了影响航天器姿态机动性能的主要因素，并通过仿真验证了这种配置方案的有效性。

Modeling and Analysis of the Attitude Control System for Micro-Spacecraft

For the purpose of spacecraft miniaturization, a novel flywheel scheme using only two flywheels to control spacecraft attitude is presented. Moreover, this scheme can manage energy which is stored in flywheels with high rotary speeds. That no saturated- speed uninstalled devices such as magnetic moment apparatus are needed reduces the structure of the flywheel attitude control system. This paper describes the structure and principle of the system in detail, and deduces nonlinear dynamic model of the attitude control system. After analyzing the primary factor of influencing performance of attitude maneuver, this scheme is validated by model simulation.