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基于刚柔耦合动力学理论,在充分考虑空间各干扰力矩、柔性太阳翼惯性力矩、以及轴承附加阻力矩等作用基础上,建立了相应动力学仿真模型,针对目标飞行器驱动机构开展了各工况下的驱动力矩设计工作。仿真计算比较了“部分耦合”与“全耦合”两种算法计算结果间的差异,给出了该驱动机构“驱动力矩”及“止动力矩”设计指标,并据此进行了电机、谐波减速器等的选型工作。
Based on the theory of rigid-flexible coupling dynamics, a corresponding dynamic simulation model is established on the basis of full consideration of space disturbance torque, inertial moment of flexible solar wing, and additional bearing moment of bearing, and aiming at various operating conditions of target aircraft driving mechanism, Under the driving torque design work. The difference between calculation results of “partial coupling” and “full coupling” is compared with the simulation calculation, and the design indexes of “driving torque” and “stopping torque” of the driving mechanism are given. According to the selection of the motor, harmonic reducer and other work.