Butt joint and regulation equipment for solar wings of moonlet

Abstract

The invention discloses butt joint and regulation equipment for solar wings of a moonlet. The equipment comprises a base part, a longitudinal movement part, a transverse movement part, a rotation part and a top layer platform part. Through the movements of the longitudinal movement part, the transverse movement part and the rotation part, the moonlet fixed in the top layer platform part can move in different directions at different angles, thereby realizing the regulation of six degrees of freedom of the body of the moonlet when the solar wings of the moonlet is butt-jointed, solving the problem of regulation for the body of the moonlet when the solar wings of the moonlet are butt-jointed, improving safety coefficient, improving regulation precision, greatly lowering the working intensity of personnel, and improving working efficiency.

Description

technical field [0001] The invention belongs to the technical field of satellite tests, and in particular relates to an adjustment device for small satellite solar wing docking tests. Background technique [0002] During the docking test between the small satellite and the solar wing, it is necessary to ensure the relative position of the interface between the small satellite and the solar wing. The specific process of docking the star and the solar wing is as follows: first use the simulation wall to adjust the position of the solar wing, and then dock the satellite star mounted on the support vehicle with the solar wing. When the satellite body is docked with the solar wing, it is difficult to ensure that the parking position of the support vehicle is exactly the position required for the docking test. At this time, the docking position can only be guaranteed by adjusting the position of the satellite, that is, adjusting the position of the support vehicle equipped with t...

AI Technical Summary

Problems solved by technology

Although this method can meet the docking requirements, it has a low safety factor, low adjustment accuracy, and high labor intensity.

[0004] At the same time, when improving the existing method, there are still some constraints: for example, the docking height of the whole satellite is limited, and the height of the satellite support vehicle must be less than 70mm during adjustment; the load of the satellite and the support vehicle is large, and the mass is about 1400kg; Due to size and width restrictions, the small satellite solar wing will mark the position on the ground when it is docked, and the adjustment equipment cannot block the position mark on the ground; the span limit, the fulcrum of the adjustment equipment must have a certain distance to ensure the stability requirements when the satellite solar wing is docked ; In addition, it is necessary to realize a certain amount of adjustment to the six degrees of freedom of the whole star

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