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Frame panel type satellite configuration and modular satellite

A technology of satellite configuration and frame, applied in the field of satellites in aerospace technology, can solve the problem of not adapting to the four-point connection and direct-orbit launch mode, etc., and achieve the effects of being conducive to modular design, high space utilization, and good impact resistance.

Inactive Publication Date: 2014-06-18
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Summary
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The technical problem to be solved by the present invention is to provide a frame-panel satellite configuration to solve the technical problem that in the prior art, the satellite structure and the carrier are connected by a docking ring, which is not suitable for the launch mode of four-point connection and direct orbit entry

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  • Frame panel type satellite configuration and modular satellite
  • Frame panel type satellite configuration and modular satellite
  • Frame panel type satellite configuration and modular satellite

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Embodiment Construction

[0024] The specific implementation of the frame-panel satellite configuration provided by the present invention and the modular satellite assembled using the frame-panel satellite configuration will be described in detail below with reference to the accompanying drawings.

[0025] Firstly, the specific implementation of the frame-panel satellite configuration of the present invention is given in conjunction with the accompanying drawings.

[0026] attached figure 1 Shown is a schematic diagram of the structure of the frame-panel satellite configuration described in this specific embodiment. The frame-panel satellite configuration includes a quadrangular prism frame and a honeycomb structure panel 11 . The quadrangular prism frame is used to bear axial load when connected with the four-point connection interface of the carrier; the honeycomb structure plate 11 is connected to the quadrangular prism frame through the first fastener to provide a mounting surface for satellite st...

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Abstract

The invention provides a frame panel type satellite configuration and a modular satellite adopting the same. The frame panel type satellite configuration comprises a four-edge-column frame and honeycomb structure plates; the four-edge-column frame is used for bearing axial load when being connected with four connecting interfaces for carrying, wherein the four-edge-column frame comprises rod pieces and rod-piece joints; each rod piece is provided with a plurality of bosses; the bosses are provided with installing holes for connection with the honeycomb structure plates by first fasteners; a plurality of through holes are arranged in the extending surfaces of the end parts of the rod pieces and are used for connection with the rod-piece joints by second fasteners; the honeycomb structure plates provide installing surfaces for single satellite equipment and simultaneously provide in-plane shearing rigidity for the four-edge-column frame.

Description

technical field [0001] The invention relates to the technical field of satellites in aerospace technology, in particular to a frame-panel satellite configuration suitable for direct launch into orbit and a four-point connection installation method and a modular satellite adopting the configuration. Background technique [0002] Our country is a big space country, and the country invests a lot in space. At present, our satellite industry is in a period of vigorous development. The new type of satellite and the carrier adopt a four-point connection interface, which is directly put into orbit, without using the traditional tape connection. Satellite The mass of the satellite is about 1000Kg. According to these constraints, the structural configuration of the satellite needs to be determined. At the same time, the new satellite has high power and high heat flux density, which requires a large heat dissipation surface. Moreover, due to the launch method of direct entry into orbi...

Claims

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Application Information

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IPC IPC(8): B64G1/10
Inventor 林宝军安洋陈志峰
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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