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Physical discrete type satellite system structure

A satellite system, discrete technology, applied in the overall field of aircraft to achieve the effect of improving performance, shortening development cycle, and reducing risks

Active Publication Date: 2012-11-28
NO 513 INST THE FIFTH INST OF CHINA AEROSPACE SCI & TECH
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Problems solved by technology

[0004] In view of this, the present invention provides a physically discrete satellite system architecture, which can improve the rapid response capability of satellites and solve problems such as maintenance and replacement of in-orbit satellites

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  • Physical discrete type satellite system structure

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Embodiment Construction

[0015] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0016] This embodiment provides a physically discrete satellite system architecture, which discretely divides a traditional overall integrated satellite system into multiple spacecraft modules. The specific implementation process is: according to the requirements of the satellite flight mission, the functions of the satellite are decomposed into I basic functions, where I is an integer, and I≥2. The set of basic functions is denoted by G. N spacecraft modules are used to implement the I basic functions, where N is an integer, and N≥2. The N spacecraft modules include a single-function spacecraft module and a multi-function spacecraft module. Among them, the single-function spacecraft module realizes one basic function. The multifunctional spacecraft module realizes two or more basic functions. Let the nth (1≤n≤N) spacecraft module be able to realize i ...

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Abstract

The invention discloses a physical discrete type satellite system structure used for solving the maintenance and change problem of the on-orbit satellites and improving the quick response capability of the satellites. The physical discrete type satellite system structure disclosed by the invention decomposes the functions of the satellite into I basic functions according to the demand of flight tasks and realizes the I basic functions through N spacecraft modules. The N spacecraft modules comprise single-function spacecraft modules and multifunctional spacecraft modules. Each spacecraft module comprises an interaction interface unit used for realizing the interaction between the spacecraft modules. The interaction interface unit comprises a low speed wireless microwave communication interface and a high speed wireless laser communication interface, wherein the wireless microwave communication is realized through an omnidirectional antenna, the high speed wireless laser communication is realized through a directive antenna, and a wireless communication link of the satellite system is formed by the communication of the intelligent interfaces of the spacecraft modules. All the spacecraft modules are discrete to each other on physics, and the spacecraft modules can be emitted to the sky in a one-rocket-multi-satellite or multi-emission manner to finish the whole function of the satellite on the orbit.

Description

technical field [0001] The invention relates to a satellite system architecture, in particular to a physically discrete satellite system architecture, and belongs to the overall technical field of aircraft. Background technique [0002] With the deepening of the application of space systems and the continuous development of aerospace technology, the requirements for the flexibility and anti-risk capabilities of satellites are getting higher and higher. According to the characteristics of the current satellites, the functions are required to be stronger and stronger, the precision requirements are higher and higher, the lifespan is longer and longer, and the development cycle is shorter and shorter. However, satellites are composed of thousands of parts, and a certain technical detail controls If it is not in place, or a weak link of a single device will lead to the reduction of the life of the entire satellite or even the failure of the mission. In order to prevent the sate...

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Application Information

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IPC IPC(8): B64G1/10
Inventor 辛明瑞马宗峰石德乐李振宇
Owner NO 513 INST THE FIFTH INST OF CHINA AEROSPACE SCI & TECH
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