Satellite structure for platform and load integration

A satellite structure and load technology, applied in the aerospace field, can solve problems such as high structural redundancy, large volume, and heavy system quality

Inactive Publication Date: 2015-05-27
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] The present invention solves the problems that the existing satellite structure system adopts independent design of platform and load, which has low resource utilization rate and high structural redundancy, resulting in heavy system mass and large volume, etc., and provides a satellite for platform load integration structure

Method used

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  • Satellite structure for platform and load integration
  • Satellite structure for platform and load integration
  • Satellite structure for platform and load integration

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specific Embodiment approach 1

[0018] Specific implementation mode 1. Combination figure 1 with figure 2 Describe this embodiment, the satellite structure used for platform load integration, the structure consists of an upper plate 1, a central bearing cylinder 2, a side plate 3, a docking ring 7, a bottom plate 8, three rod brackets 9 and twelve upper plates The bracket 10 is composed.

[0019] Taking the docking ring 7 as the assembly reference, the docking ring 7 adopts the standard star-arrow interface and is made of aluminum; the base plate 8 is installed on the docking ring 7, and the base plate 8 adopts a honeycomb sandwich structure. The advantage of the honeycomb sandwich structure is that it is light in weight and relatively High rigidity; the central load-bearing tube 2 is installed on the bottom plate 8, and the central load-bearing tube 2 is made of carbon fiber composite materials. They are not only the main load-bearing structure of the satellite, but also play the role of eliminating misce...

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Abstract

The invention discloses a satellite structure for platform and load integration, which relates to the technical field of aerospace and solves the problems of large system mass, large size and the like caused by low resource utilization rate and high structure redundancy of an existing satellite structure system adopting a method that a platform and a load are separately designed. The satellite structure comprises an upper plate, a center bearing cylinder, side plates, a docking ring and a bottom plate, wherein the docking ring is used as an assembling reference, the bottom plate is installed on the docking ring, the center bearing cylinder is installed on the bottom plate, the upper plate is installed on the center bearing cylinder, the side plates are fixed on the side surfaces of the upper plate and the bottom plate, a plurality of upper plate brackets are uniformly arranged in the circumferential direction of the center bearing cylinder, and the upper plate is installed on the center bearing cylinder through the plurality of upper plate brackets. The satellite structure has the advantages of compactness, small size, light weight, high structure function density, high rigidity, large structure safety margin and high reliability.

Description

technical field [0001] The invention relates to the field of aerospace technology. It specifically relates to a structure for platform-load integrated satellites, which can realize the high-integration integration of high-performance small satellite platforms and payload structures, while taking into account the modularization and standardized function expansion task requirements of different types of small satellites. Background technique [0002] A satellite generally consists of a payload and a satellite platform (or public cabin). Traditional satellite designs mostly use a combination of general-purpose satellite platforms and different payloads to meet different satellite missions. The so-called satellite platform is a public cabin with strong versatility that can adapt to different payload configurations and complete their specific flight missions. Based on this design concept, in the satellite manufacturing process, the design method of the black box is mostly adopt...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10
CPCB64G1/10
Inventor 谷松金光张雷安源高飞徐振徐伟
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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