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微纳卫星姿控的反作用飞轮输出力矩小,难以克服普通气浮转台的干扰力矩,为了解决上述问题,实现微纳卫星姿控地面半物理仿真验证,必须对干扰力矩进行有效补偿。为此,对干扰力矩分类并分析了各自的特性,针对性提出了干扰力矩主动补偿方法,研制了主动补偿式超低干扰力矩气浮转台,并基于此开发了微纳卫星姿控半物理仿真平台。研制的气浮转台的干扰力矩达到2×10-5 Nm,小于微纳卫星反作用飞轮的最小输出力矩,利用半物理仿真平台有效地验证了微纳卫星大角度姿态机动控制算法。
The output torque of reaction flywheel of micro-nano satellite attitude control is small, it is difficult to overcome the interference torque of ordinary air-floating turntable. In order to solve the above problems and achieve semi-physical simulations of ground-based micro-nano satellite attitude control, the disturbance torque must be effectively compensated. For this reason, the disturbance torque is classified and analyzed, and the active compensation method of disturbance torque is proposed. The active compensated ultra-low disturbance torque air-float turntable is developed. Based on this, a semi-physical simulation of attitude and attitude control of micro-nano satellite platform. The disturbance torque of the developed air floating turntable reaches 2 × 10-5 Nm, which is less than the minimum output torque of the flywheel reacting with the micro-nanosatellite. The half-physical simulation platform effectively validates the maneuvering control algorithm of large-angle attitude of the micro-nano satellite.