Experimental verification method for a two-dimensional quadratic semi-rigid solar wing

Abstract

The invention relates to a test verification method for a two-dimensional quadratic semi-rigid solar wing, which belongs to the field of synchronous orbit long-life communication satellites; On the basis of the solar wing development process, combined with the characteristics of semi-rigid solar wings, the high-temperature loading pretreatment of fiber ropes and the high-temperature baking test before substrate patching are added, and a flow plan for the verification of distributed part assembly and deployment is proposed according to the characteristics of two-dimensional deployment to solve the problem. The problem of verification adequacy and effectiveness of the semi-rigid two-dimensional solar wing is solved; the invention not only ensures the adequacy of verification, but also improves the efficiency of product development, which is of great significance to product development.

Description

Technical field [0001] The present invention belongs to the field of synchronous orbit long-life communication satellites, relates to a two-dimensional secondary semi-rigid solar wing test verification method. Background [0002] The semi-rigid substrate of the semi-rigid solar wing adopts the fiber rope bandage design, and the thermal stability of the fiber rope plays an important role in maintaining the flatness of the wing surface and the angle of light in orbit. At present, the test verification method for the semi-rigid solar wing semi-rigid substrate is only the one-dimensional rigid solar wing test verification process, and the performance verification of the semi-rigid base of the semi-rigid solar wing is not comprehensive, and the test parameters provided during product development are not sufficient, which greatly reduces the success rate of product development. Contents of the Invention [0003] The technical problem solved by the present invention is: to overcome the...

AI Technical Summary

Problems solved by technology

At present, the test verification method for the semi-rigid substrate of the semi-rigid solar wing is only the test verification process of the one-dimensional rigid solar wing. The performance verification of the semi-rigid base of the semi-rigid solar wing is not comprehensive, and the test parameters provided during product development are not sufficient. , greatly reducing the success rate of product development

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