A large-area flexible solar cell wing supported by a stretching mechanism for a double-sided array

Abstract

The invention discloses a stretching mechanism-supported double-side array large-area flexible solar cell wing. The stretching mechanism-supported double-side array large-area flexible solar cell wingcomprises a lifting mechanism, a stretching mechanism, two flexible solar cell arrays, pressing and releasing devices and box body unfolding and locking mechanisms; two ends of the top of the stretching mechanism are respectively connected with the two flexible solar cell arrays, and the bottom of the stretching mechanism is connected with the lifting mechanism; in an initial state, the two flexible solar cell arrays are symmetrical about the stretching mechanism; the stretching mechanism and the flexible solar cell array are each provided with a plurality of pressing points; and the pressingand release devices are arranged at the positions of the corresponding pressing points to press the stretching mechanism and the flexible solar cell arrays; the box body unfolding locking mechanismsare arranged at the connecting positions of the two ends of the top of the stretching mechanism and the first flexible solar cell array and the second flexible solar cell array and are used for unfolding the flexible solar cell arrays towards two sides in place and locking the flexible solar cell arrays. The stretching mechanism-supported double-side array large-area flexible solar cell wing has the advantages of small folding envelope, large unfolding area and stable unfolding configuration, and is suitable for a high-power spacecraft platform.

Description

technical field [0001] The invention belongs to the field of aerospace technology, in particular to a large-area flexible solar battery wing supported by a stretching mechanism for a double-sided array. Background technique [0002] With the development of my country's aerospace technology, the power demand of spacecraft is increasing rapidly. For example, communication satellites, electronic reconnaissance satellites, etc. require more than 10kW of power generation power, large space-based radar satellites, and deep space exploration electric propulsion satellites require as much as 40kW of electric energy, and my country's future space station power requirements even reach the order of hundreds of kilowatts. [0003] Taking a certain type of space station in the future as an example, the three cabins (core cabin, experimental cabin I and experimental cabin II) of this certain type of space station need to be used together with multiple sets of solar battery wings, and mult...

AI Technical Summary

Problems solved by technology

Japan's ADEOS-II and HIMAT satellites adopt a single-sided array flexible solar cell wing configuration, which is limited by the envelope of the folded state, and the utilization rate in the width direction is insufficient after deployment. To achieve large-area deployment, a longer stretch is required. Mechanism, dynamic characteristics and load-carrying capacity are poor

[0006] To sum up, with the rapid development of space science and technology, various high-power scientific research equipment has put forward higher and greater demands on the power of the spacecraft platform. It is difficult for traditional rigid and semi-rigid solar wings to guarantee high-power Under the circumstances, it meets the complex requirements of high stiffness, light weight, high storage ratio, etc., while the traditional flexible solar cell wings are not fully automatic deployment or the deployment area and stiffness are limited.

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