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该文研究灵敏航天器快速倾斜机动时微型控制力矩陀螺(MCMG)的参数估算问题。所得到的估算结果可供微型控制力矩陀螺群初步设计时选择设计参数。从航天器的动力学模型出发,给出了倾斜机动模式下MCMG最大框架角速度和输出力矩的估算方法。然后在给定机动任务的前提下,以某小卫星为例,对采用标准金字塔构型的微型控制力矩陀螺群的姿态控制系统进行了仿真验证。仿真结果显示出该估算方法的可行性。
This paper studies the problem of parameter estimation of micromechanical moment control gyroscope (MCMG) when sensitive spacecrafts are rapidly tilted. The results obtained can be used to select the design parameters for preliminary design of micro-control moment gyroscope group. Based on the dynamics model of spacecraft, the method of estimating the maximum frame angular velocity and output torque of MCMG under tilting maneuvering mode is given. Then, given a small satellite as an example, the attitude control system of micro-control moment gyroscope group with standard pyramid configuration is simulated and verified on the premise of given maneuver task. Simulation results show the feasibility of this estimation method.