Design Method of Driving Moment of Large Overload Spacecraft Driving Mechanism

Abstract

The driving torque design method of the large overload spacecraft driving mechanism of the present invention considers the large deformation reaction of the flexible load battery wing, and solves it in real time through rigid-flexible coupling dynamics reverse, based on the generalized modal mass matrix full coupling algorithm in rigid-flexible coupling dynamics, determined in The torque design envelope of the driving mechanism under each working condition of the rail is selected, and the motor and harmonic reducer are selected through the recursive relationship of the transmission chain. The driving torque design method of the large overload spacecraft driving mechanism of the invention improves the design accuracy and work efficiency of the driving mechanism torque, and the driving mechanism design provides technical conditions with high reliability.

Description

technical field [0001] The invention relates to a design method of a driving mechanism torque in the field of manned spaceflight engineering, in particular to a design method of a driving torque of a large overload spacecraft driving mechanism. Background technique [0002] Orientation of the spacecraft battery wing to the sun is the primary condition for maintaining the normal operation of the spacecraft power system in orbit. Therefore, it is necessary to ensure the normal operation of the spacecraft battery wing drive mechanism without stalling, out-of-step, overshoot and other failures. In the field of manned spaceflight, the inertia moment of the flexible battery wing is very prominent under the action of large overload, and the driving torque design of the battery wing drive mechanism is particularly critical. [0003] In the prior art, the driving torque design of the spacecraft driving mechanism is mostly seen in the satellite engineering series, and methods such as ...

AI Technical Summary

Problems solved by technology

This method does not take into account the elastic vibration of the flexible load battery wing and the dynamic coupling characteristics of the on-orbit overload, and the consideration of the additional resistance moment of the bearing due to the deformation of the load battery wing is not very accurate, so it is only a rough design

[0004] After reviewing the literature, relevant scholars have conducted in-depth research on the coupling between the vibration of the battery wing and the output torque of the stepping motor, and have given relevant conclusions: when the rotation frequency of the motor magnetic field is close to the natural frequency of a certain order of the system, especially When a certain low-order frequency is close, the non-linear coupling of factors such as the output torque of the stepper motor, the flexible vibration of the load, and the dry friction torque may cause the drive system to stall

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