A new solar panel deployment and support mechanism based on ribbon springs

Abstract

A novel band-spring-based solar sailboard unfolding and supporting mechanism belongs to the field of unfolding mechanisms applied to satellite solar battery arrays and aims to solve the problems of low unfolding rigidity and low base frequency in the prior art. The mechanism comprises a solar sailboard, coil-spring driving hinges, a satellite body, strut hinges, a lower strut, a band spring and an upper strut; the solar sailboard and the satellite body are connected by the coil-spring driving hinges, two ends of the band spring are respectively connected with the upper and lower struts by adapters, the upper strut is connected with the solar sailboard by one strut hinge, and the lower strut is connected with the satellite body by the other strut hinge; coil springs in the coil-spring driving hinges, the band spring and the strut hinges provide unfolding moment so as to realize the unfolding of the solar sailboard. According to the novel band-spring-based solar sailboard unfolding and supporting mechanism, the solar sailboard, the satellite body and the upper and lower struts form a whole to constitute a stable supporting structure shaped like a spacial tetrahedron, so that the base frequency and the rigidity of a system under an unfolding state are improved.

Description

Technical field [0001] The invention belongs to the field of deployment mechanisms applied to satellite solar cell arrays, and particularly relates to a new type of solar sailboard deployment and support mechanism based on ribbon springs on "agile small satellites". Background technique [0002] The deployment mechanism of solar panels is one of the important sub-systems of space earth observation satellites. In history, there are dozens of cases where the deployment mechanism fails to work normally due to mechanical failures. Therefore, in aerospace satellite projects, the deployment mechanism of solar panels is an important part of design and experiment. [0003] The existing earth observation satellites are traditional large push-broom earth observation satellites. The solar windsurfing mechanism suitable for such observation satellites utilizes the hinge mechanism of energy storage elements such as coil springs and torsion springs to launch the satellite to a predetermined orbi...

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to solve the problems of low deployment stiffness, low fundamental frequency, and low damping ratio in the prior art, and propose a new type of solar panel deployment and support mechanism based on strip springs with high stability, which can meet the needs of agility on the ground Observation requirements for small satellites

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