A new type of flexible solar cell array deployment device

Abstract

The invention discloses a novel flexible solar cell array unfolding device and belongs to the technical field of civil aerospace engineering. The device is composed of a synchronous extending mechanism and a central driving mechanism. The synchronous extending mechanism is composed of a flexible solar cell array sailboard, a driving mechanism, an unfolding mechanism, a synchronizing mechanism and a locking mechanism, wherein the flexible solar cell array sailboard uses five annular amorphous silicon films, the driving mechanism uses a method that torsion spring driving and servo motor driving are combined, a torsion spring at the hinge position can complement driving torque required in an unfolding process, the unfolding mechanism uses a gap hinge, a driving pin shaft of the gap hinge is replaceable, the synchronizing mechanism uses a steel wire rope to drive a linkage mechanism, and the locking mechanism uses a cam pin type locking mechanism. The novel flexible solar cell array unfolding device provides a flexible solar cell array unfolding method, solves the problems that a traditional solar cell array is complex in structure, small in folding ratio and low in work reliability, fully utilizes the material characteristics of a flexible substrate and improves the power generation efficiency of a solar cell array and the use reliability of the solar cell array.

Description

technical field [0001] The invention belongs to the technical field of civil aerospace, and in particular relates to a novel flexible solar battery array deployment device. Background technique [0002] With the development of aerospace technology, the volume and scale of spacecraft are increasing day by day, carrying more and more payloads, and the energy demand is also increasing exponentially. The existing rigid foldable solar cell array can no longer meet the power requirements. [0003] Flexible substrate solar cell arrays, especially thin-film solar cell arrays, have become the development trend of a new generation of solar cell arrays because of their small mass, high power generation efficiency, and high specific power. Therefore, it is of great significance to study a new flexible solar cell array deployment mechanism with high folding ratio and high reliability to improve the power generation of spacecraft on orbit. [0004] According to the data of flexible solar...

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Problems solved by technology

[0004] According to the data of flexible solar cell arrays successfully used by spacecraft at home and abroad, combined with relevant literature, it is found that the existing flexible deployment devices mainly have the following problems: (1) The existing flexible solar cell arrays are mostly deployed gradually, so A large number of motors need to be driven, which cannot be deployed synchronously, such as U.S. Patent US6983914; (2) The deployment mechanism of the flexible solar cell array is complicated, including a large number of rope mechanisms, which reduces the reliability of the mechanism, such as Chinese patent CN101428690A; (3) Now The flexible solar cell array deployment mechanism has a small folding ratio and a small deployment area, which cannot meet the high power requirements of the spacecraft; (4) It is impossible to conveniently adjust the preload of the synchronization mechanism, and the value of the rope tension cannot be obtained in real time; (5 ) has only one set of deployment driving device, and it cannot be deployed reliably when the driving device fails, such as the failure of the US Hubble Space Telescope in 1990 (reference: [Feng Gang, An Xiang, Zhang Duo. Thermal Analysis of Large-area Solar Wing of Space Station [J ]. Strength and Environment, 2001(1):54-61])

(6) The spin-deployable thin-film solar cell array structure introduced by Chinese patent CN101013732 has high complexity and low reliability; the thin-film is deployed by spin centrifugal force, which increases the difficulty of adjusting the overall dynamic balance of the spacecraft

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