Two-dimensional secondary unfolding solar wing

Abstract

The invention discloses a two-dimensional secondary unfolding solar wing which has a folding state, a primary unfolding state, a secondary unfolding state and a two-dimensional secondary unfolding state and comprises a root hinge, a connecting frame, an inner plate, a middle inner plate, a middle outer plate, an outer plate, an upper side plate, a lower side plate, a primary pressing and releasingdevice, a secondary pressing and releasing device and a side plate releasing device. The root hinge, the connecting frame, the inner plate, the middle inner plate, the middle outer plate and the outer plate are hinged in sequence; the root hinge is used for mounting the connecting frame on the side wall of a satellite body; an upper side plate and a lower side plate are hinged to the other two sides of the middle outer plate, and the upper side plate and the lower side plate are oppositely arranged when being unfolded; the primary pressing and releasing device and the secondary pressing and releasing device both have a pressing state and a releasing state. The solar wing can be unfolded step by step before and after orbital transfer of a satellite, the unfolding inertia of the solar wingduring orbital transfer of the satellite is reduced, and the strength requirement of the solar wing is reduced, so that the product quality is greatly reduced.

Description

technical field [0001] The invention relates to the technical field of spacecraft, in particular to a two-dimensional secondary deployment solar wing. Background technique [0002] As the power supply equipment of the spacecraft, the deployment of the solar wing is an important symbolic event for the successful launch of the spacecraft. At present, most of the solar wings used in China are one-dimensional one-time deployment structures, generally composed of 2 to 3 solar panels along a straight line, and the solar wings are driven to unfold through the unfolding hinges. During the unfolding process, the rope linkage device controls the unfolding process of each hinge. Constraints are made to reduce the degree of freedom to 1, forming a regular one-time expansion, which is called one-dimensional one-time expansion. [0003] However, when the deployment area of ​​the solar wing is large, the one-dimensional one-time deployment structure will lead to an excessively large deplo...

AI Technical Summary

Problems solved by technology

[0003] However, when the deployment area of ​​the solar wing is large, the one-dimensional one-time deployment structure will lead to an excessively large deployment inertia of the solar wing, and the solar wing and its driving mechanism will bear too much load when the orbit of the satellite engine changes, and even lead to zero damage such as the root hinge of the solar wing. Parts are damaged; currently, in order to reduce this effect, it is necessary to strengthen the structure of each force transmission part of the solar wing, thereby greatly increasing the weight of the solar wing product

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