论文部分内容阅读
筒式偏心在轨分离是一类特殊的在轨分离问题,小卫星偏心安装而产生的分离力矩将导致分离角速度,进而影响小卫星的分离指向精度,甚至导致释放平台姿态失稳。而常规的姿态大角速度机动、姿态快速稳定控制方法难以在小卫星出筒前的极短时间内完成分离角速度抑制。因此,进行了卫星筒式偏心在轨分离动力学分析,基于分离角速度的产生,提出了抑制分离姿态干扰的前馈控制力矩法和角速度预偏置法。在此基础上,推导了关键控制参数的近似计算公式,给出了控制量的优化求解方法,并分析了控制干扰因素对抑制结果的影响。最后,通过仿真算例分析,对比验证了两种抑制方法的有效性,并给出了其工程应用的建议。
Cylindrical eccentric separation is a special kind of on-orbit separation problem. The separation moment generated by the eccentric installation of small satellite will lead to the separation angular velocity, which will affect the separation pointing accuracy of small satellite and even lead to the instability of release platform attitude. However, it is difficult for the conventional attitude angular velocity maneuvering and attitude attitude stabilization control method to accomplish the separation angular velocity suppression in a very short period of time before the small satellite launches. Therefore, satellite orbit eccentricity on-orbit separation dynamics analysis is carried out. Based on the generation of separation angular velocity, a feedforward control torque method and angular velocity pre-bias method are proposed to suppress the separation attitude disturbance. On this basis, the approximate calculation formulas of the key control parameters are derived, the optimal solution method of the control volume is given, and the influence of the control interference factors on the suppression results is analyzed. Finally, through the simulation example analysis, the validity of the two kinds of suppression methods is verified and compared, and the suggestions of engineering application are given.