A Gravity Compensation Device for Solar Wing Low Temperature Deployment Test

Abstract

A gravity compensation device for solar wing low temperature unfolding experiment is capable of realizing one sixth gravity compensation and zero gravity compensation of solar wing at a temperature of -120 DEG C. The device also can carry out solar wing multi-angle repeated unfolding and folding experiments in a limit position by simulating a landing situation when the included angle between the moon surface and the horizontal plane is 15 degrees. A balance rod is adopted in the device to carry out gravity compensation, and is completely made of metals so as to adapt to the low temperature environment. The three-dimensional trace movement of the mass center of a solar wing is completed by the swinging of a guide rail and a suspension rod; the conventional bidirectional guide rail structure composed of a solar wing vertical guide rail and a solar wing horizontal guide rail is broken through, thus the system complexity is reduced, and the movement reliability is improved. A horizontal rotation assembly is adopted to enable the main beam to freely rotate in a horizontal plane, and the gravity compensation technology is broken through when the included angle between a solar wing and the horizontal plane is 15 degrees namely the extreme working condition. A pulley and a pulley structure are adopted to reduce the movement resistance. A main beam having an I-shaped aluminum structure is adopted, the weight of movable parts is reduced, and thus the inertia force during the folding and unfolding process of a solar wing is effectively reduced.

Description

technical field [0001] The invention relates to a gravity compensation device, in particular to a gravity compensation device used for low-temperature deployment tests of solar wings, which can realize the deployment of various postures of the solar wing in a -120° low-temperature environment and a low-gravity environment, and belongs to the field of deep space exploration . Background technique [0002] In the process of developing the solar wing of a deep space probe, it is necessary to simulate the working conditions on the surface of the moon to conduct 1 / 6 gravity and zero gravity deployment tests of the solar wing in a low temperature environment of -120°, and at the same time, it is necessary to simulate the extreme position of the probe when it lands, that is, the solar wing It is 15° from the horizontal plane, and it can be unfolded and retracted repeatedly in multiple postures and angles. [0003] The traditional solar wing deployment gravity compensation device i...

AI Technical Summary

Problems solved by technology

[0003] The traditional solar wing deployment gravity compensation device includes the balloon suspension gravity compensation type and the double guide rail gravity compensation type: the former may rupture the balloon inner bag plastic in a low temperature environment, and the inertial force of the balloon may cause the motor to fold in place signal to fail to trigger when the end of the solar wing is folded , the number of steps in the final deployment and retraction is inconsistent, which affects the reliability of deployment; the latter adopts a bidirectional guide rail operation structure with a combination of longitudinal guide rails and horizontal guide rails, with many moving parts and a complex system. Phenomenon, linear bearings are used, which contain plastic components, which will break and fail under low temperature conditions, and due to structural limitations, the traditional two-way guide rail structure cannot realize the three-dimensional movement of the solar wing's center of mass, and cannot complete various attitudes and angles of the solar wing. adjustment

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