In-orbit expansion-type satellite structure

A satellite structure and unfolding technology, applied in the field of satellite structure design, can solve the problems of no description or report, and data has not been collected, so as to solve the conflict between carrying constraints and load requirements, novel configuration, large-load installation structure and other problems. The effect of the workspace

Active Publication Date: 2015-11-11
SHANGHAI SATELLITE ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The expandable satellite structure involved in the present invention has not found descriptions or reports similar to the present invention, and has not yet collected similar data at home and abroad.

Method used

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  • In-orbit expansion-type satellite structure
  • In-orbit expansion-type satellite structure

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Embodiment Construction

[0030] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0031] The present invention proposes a satellite platform structure that is folded in the launching stage and unfolded in orbit, which is mainly composed of a star module 1, a star connection and unlocking device 2, an unfolded truss 3 and other parts. During the launch phase, the star module 1 is folded in the carrier fairing by the star connection and unlocking device 2 to meet its envelope requirements; Separated, so as to realize the process of on-orbit reconstruction of the satellite body, and pro...

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Abstract

The invention provides an in-orbit expansion-type satellite structure which comprises a plurality of satellite body modules with the same configuration arranged along circumference, wherein the adjacent satellite body modules are connected by an expansion-type truss, and a corresponding satellite body connecting and unlocking device is disposed between the adjacent satellite body modules; at a launch stage, the satellite body modules are connected by the satellite body connecting and unlocking device into a whole, so a satellite body is retracted and satisfies a demand for carrying and enveloping during the launch; when the satellite body enters an orbit, the satellite body connecting and unlocking device works to realize unlocking among the satellite body modules, and the satellite body modules realize in-orbit expansion under effect of the expansion-type truss; and during in-orbit work, in-orbit high-rigidity locking of the expansion-type truss is realized by a locking mechanism of the expansion-type truss. The in-orbit expansion-type satellite structure provided by the invention solves the contradiction between that the satellite body cannot exceed a carrying limit and that the satellite shall satisfy a structural configuration demanded by an in-orbit large load, and provides an engineering solution manner for subsequent applications of the large load.

Description

technical field [0001] The invention relates to satellite structure design, in particular to an in-orbit deployable satellite structure. Background technique [0002] Satellite bodies are usually divided into propulsion cabins, service cabins (or platform cabins), load cabins, etc. according to their functions. Each cabin provides a mechanical installation interface for each single machine and its cables. Each compartment is reliably connected as a whole by bolts and other fasteners. However, due to the limitation of the carrying envelope, the size of the satellite structure is also limited. [0003] In order to meet the requirements of large load configuration, and to realize the modular design and high stability of the satellite structure, the unfolded satellite structure can achieve a larger on-orbit size and ensure the stability of the structural platform through a modular and expandable design. On-orbit high stability, while meeting the requirements of large size on-o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10
Inventor 周伟敏张伟江世臣王智磊张嵬
Owner SHANGHAI SATELLITE ENG INST
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