Abstract
In order to solve the problems of the existing solar wing, such as complex process and obvious structural vibration. a new space deployable solar wing mechanism composed of single DOF modularization was designed. The structure and working principle of the space deployable solar wing are described, and the driving system is briefly introduced. The single module of the solar wing is divided into two parts and the kinematics equations of the kite-shaped mechanism and origami mechanism are established respectively. Secondly, the output motion rule of the bar at the end was solved when the special driving is applied to the kite-shaped mechanism. And based on this output, changed the angle of the origami mechanism’ plates and the change curve of the centre of mass and the angle between the plates is obtained. The study results show that, synthesize considering the shrinkage and the ratio of folding to span, the optimal solution is the angle of plates φ=4°. Through the above research that provide the theoretical basis for the optimization and improvement of the mechanism.
Highlights
The solar wing was the main energy source of the satellites
Hou et al used the counterweight suspension method to carry out a horizontal deployment test on the satellite solar wing surface after the gravity was eliminated, which laid the foundation for the actual operation of the solar wing in orbit [4]
Zhang et al proposed a geometric modelling method for rotating solar sails, using ABAQUS software to simulate the dynamics of the solar sail during the second stage of
Summary
The solar wing (solar array) was the main energy source of the satellites. It was usually used to supply energy for satellites and spacecraft. Hou et al used the counterweight suspension method to carry out a horizontal deployment test on the satellite solar wing surface after the gravity was eliminated, which laid the foundation for the actual operation of the solar wing in orbit [4]. Ding et al proposed a method of using a solar array driven by a root hinge, established a multi-DOF dynamic model of the system, and verified the control effect of the drive assembly through ground tests. This paper proposed a modular space deployable solar wing mechanism, and that expounds the structure principle and driving mode, set up the kinematics model of kiteshaped mechanism and origami mechanism, through a given input motion law, solving the origami institutions change curve of angle and the centroid position, provide the theoretical basis for further research and application
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