General satellite sun wing expanding frame automatically adjusting levelness

Abstract

The invention discloses a general satellite sun wing expanding frame automatically adjusting levelness. The general satellite sun wing expanding frame automatically adjusting levelness is composed of a mechanical system and a control system. The mechanical system mainly comprises two upper guide rails, two driving mechanisms, a main beam, a hinged telescopic mechanism and a rigid connection telescopic mechanism. The mechanical system of the sun wing expanding frame is fixed to opposite brackets arranged on the two sides of an infrastructure, and the two upper guide rails are welded to the brackets. The upper guide rails are connected with the main beam. The main beam is driven by the driving mechanisms to move on the upper guide rails, and then the whole system can move in the appointed area. According to the general satellite sun wing expanding frame automatically adjusting levelness, a contact gap and unnecessary constraint are eliminated, a lifting mechanism ascends and descends freely, the clamping phenomenon in the lifting process is eliminated, swinging of a platform is eliminated, the leveling effect and stability of the system are guaranteed, the position of the expanding frame is changed freely, and the expanding frame ascends and descends freely in the height direction, and the accurate and automatic adjustment of 0.04 mm/m of the levelness of the guide rails is achieved.

Description

technical field [0001] The invention belongs to the technical field of spacecraft ground test tooling, and in particular relates to a general solar wing ground deployment test device for spacecraft with an automatic level adjustment function. Background technique [0002] In order to verify the various performance indicators of the solar wing during the development of the spacecraft, it is necessary to carry out multiple ground deployment tests of the solar wing. In order to meet the requirements of the ground deployment test of the solar wing between different platforms and models, it is necessary to design a universal deployment frame for satellites. Since the solar wing deployment in orbit is in a zero-gravity state, the solar wing deployment frame needs to unload the gravity of the solar wing during the test process. Higher requirements have been put forward. [0003] The current solar wing ground deployment frame of the spacecraft all adopts a grid structure (see fig...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a universal deployment frame for gravity unloading during the ground deployment test of satellite solar wings, which has an automatic high-precision level adjustment function, and aims to solve the problem that the current solar wing deployment frame occupies a large amount of site resources, has poor versatility, and poor accuracy. The problem of low adjustment efficiency, the present invention can realize the free transformation of the position of the unfolding frame, the free lifting of the height, and the precise automatic adjustment of the guide rail levelness of 0.04mm / m

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