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Modular micro-satellite platform configuration

A micro-satellite, modular technology, applied in the field of satellite platform configuration, to achieve the effect of simplifying the system interface, improving the satellite carrying capacity, and reducing the weight of the structure

Active Publication Date: 2014-01-01
SHANGHAI SATELLITE ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At present, there is no micro-satellite platform configuration that can meet the above requirements. Therefore, it is urgent to design an efficient and general micro-satellite platform configuration to meet the application requirements

Method used

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Embodiment Construction

[0031] 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 modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0032] The present invention proposes a configuration suitable for a 30kg-50kg sun-synchronous earth orbit satellite platform, the satellite platform is a hexahedral configuration, and consists of a payload interface module, a satellite-rocket docking module, an attitude control and integrated electronic module, and a mechanical solar wing Module, propulsion module, body-mounted solar cell array module and power supply and distribution module, the main structure size of the star is 295mm×262mm×500m...

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Abstract

The invention provides a modular micro-satellite platform configuration, which comprises a bottom plate, a top plate, a first side plate, a second side plate, a third side plate, a fourth side plate, a payload interface module, a satellite and rocket docking module, an altitude control and integration electronic module, a mechanical solar wing module, a propelling module, an integrated solar cell array module and a power supply and distribution module, wherein each side plate is connected with the bottom plate and the top plate respectively, and each of the second and fourth side plates has an embedded frame structure to form a box plate type configuration structure with embedded frames; the satellite and rocket docking module is connected with the bottom plate; the integrated solar cell array module is connected with the top plate; the payload interface module is connected with the first side plate; the altitude control and integration electronic module is connected to the embedded frame of the second side plate; the propelling module is connected with the third side plate; the power supply and distribution module is connected to the embedded frame of the fourth side plate; the mechanical solar wing module is connected to the second and fourth side plates respectively. The modular micro-satellite platform configuration has the advantages of light weight, high bearing capacity, short production cycle and high reliability and universality.

Description

technical field [0001] The present invention relates to a satellite platform configuration, in particular to a modular micro-satellite platform configuration. Background technique [0002] In order to achieve the purpose of commercial application and marketing, the micro-satellite platform pursues the design goals of low cost, versatility, speed and efficiency, and develops in the direction of fine-grained, multi-functional and multi-satellite simultaneous launch networking. Furthermore, new requirements for multi-load adaptation, parallel design, and mass production are put forward for the configuration of the micro-satellite platform. At present, there is no micro-satellite platform configuration that can meet the above requirements. Therefore, it is urgent to design an efficient and general micro-satellite platform configuration to meet the application requirements. Contents of the invention [0003] Aiming at the defects in the prior art, the object of the present inv...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10
Inventor 廖波刘利军裘俊张宗华
Owner SHANGHAI SATELLITE ENG INST
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