Electrical bus applicable to micro satellites

A micro-satellite, bus technology, applied in electrical program control, program control in sequence/logic controllers, etc., can solve the problems of no explanation or report in the aerospace field, and no data has been collected, and achieve mass production, Guaranteed modularity and reduced weight

Inactive Publication Date: 2015-12-16
SHANGHAI SATELLITE ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] At present, there is no explanation or report on related technologies similar to the present invention in the field of aerospace, and no similar data at home and abroad have been collected yet.

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  • Electrical bus applicable to micro satellites

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Embodiment Construction

[0020] 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.

[0021] The core idea of ​​the present invention is to provide an electrical bus design method suitable for micro-satellites, including: physical topology, working mode and interface definition.

[0022] Please refer to figure 1 , the physical topology of the present invention includes a power bus 101 , a data bus 102 , a tee connector 103 and a stand-alone connector 104 . The power bus 101 and the data bus 102 are transmitted in parallel and independently. The power bus 101 includes voltage A and volta...

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Abstract

The invention provides an electrical bus applicable to micro satellites, comprising physical topology, working mode and interface definition. According to the physical topology, a power bus and a data bus are connected in parallel and carry out transmission independently. In the aspect of working mode, hot backup is adopted. In the aspect of interface definition, the electrical bus leads out a power signal and a data signal through a three-way electrical connector, and the electrical bus and an on-satellite standalone device are interconnected by the same electrical connector. According to the invention, the power bus and the data bus are integrated on the same electrical connector, the contact is defined as the general cable standard, the design ensures that power signals and data signals are transmitted independently and do not interfere with each other, the complexity of whole-satellite power supply and data transmission is reduced, the degree of product standardization and interface unification is improved, the complexity and weight of a whole-satellite cable are reduced, and the design idea of 'plug and play' for micro satellite electronic products is realized.

Description

technical field [0001] The invention relates to an electrical bus design method suitable for micro-satellites. The electrical bus design method is suitable for the technical field of micro-satellite cable networks and can meet the needs of rapid design and rapid manufacturing of micro-satellites. Background technique [0002] At present, the micro-satellite power signal transmission uses the power bus to carry out successful flight practice on many small satellites abroad. It has the characteristics of light weight and small space occupation. It is in its infancy in China. However, the traditional pure power bus often needs special customization. , Most of them use bus bars, which increases the cost of development. The information transmission on the tiny satellite adopts the data bus technology. Commonly used data buses include MIL-STD-1553B, SpaceWire, RS-232, RS-485, I2C, CAN and other types. The CAN bus has strong anti-interference, high efficiency, The advantage of goo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B19/04
CPCG05B19/04
Inventor 赵艳彬刘正全孙建亮杨雅倪涛
Owner SHANGHAI SATELLITE ENG INST
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