Spacecraft energy-complementing system based on sunlight reflection

A spacecraft and reflector technology, applied in the field of spacecraft systems, can solve problems such as system versatility and scalability constraints, and achieve the effects of avoiding precise pointing control requirements, reducing energy conversion links, and simplifying energy transfer links

Inactive Publication Date: 2013-09-04
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

The above methods also have a common disadvantage, that is, they require the service module satellite to be equ

Method used

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  • Spacecraft energy-complementing system based on sunlight reflection
  • Spacecraft energy-complementing system based on sunlight reflection
  • Spacecraft energy-complementing system based on sunlight reflection

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Embodiment Construction

[0028] Utilizing the energy supplement system of the present invention can provide a wireless energy supplement scheme, and the star cluster involved is composed of a plurality of spacecraft, such as figure 1 As shown, fly in groups in loose formation. The star cluster can contain multiple serviced spacecraft (target spacecraft) 2 and supplementary serving spacecraft (abbreviated as supplementary spacecraft) 1 . Each target spacecraft and one or more supplementary service spacecraft that provide services for it constitute a "cooperative group". There is a direct or indirect information channel between the target spacecraft 2 and the supplementary service spacecraft 1 in the "cooperation group", so that the supplementary service spacecraft 1 can know the space orientation and energy acceptance status of the target spacecraft 2. The information channel can be inter-satellite wireless communication, indirect communication through a ground station, or an inter-satellite relative ...

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Abstract

A spacecraft energy-complementing system based on sunlight reflection comprises an energy-complementing serving spacecraft which projects the sunlight to a battery cell which does not face the sunny side according to the space relation between the sun and a served spacecraft, and extra energy is provided for the served spacecraft. The energy-complementing serving spacecraft comprises a spacecraft body, a sun sensor, a sunlight reflector and a target guiding device. The sun sensor is used for measuring the incoming solar angle, the target guiding device is used for measuring the relative dimensional orientation between the served spacecraft and the energy-complementing serving spacecraft, a star computer on the energy-complementing serving spacecraft is used for calculating the pointing of the sunlight reflector according to the incoming solar angle and the relative dimensional orientation, the sunlight reflector is driven by controlling the attitude maneuver of the energy-complementing spacecraft to arrive at the appointed direction, and the sunlight reflector is used for reflecting the sunlight to the solar cell which does not face the sunny side of the served spacecraft.

Description

technical field [0001] The invention belongs to the spacecraft system technology and relates to the field of wireless energy transmission and supplementation. Background technique [0002] Sufficient energy supply is an important guarantee for spacecraft to achieve on-orbit missions. At present, most spacecraft obtain energy by using photovoltaic cells to generate electricity. The common arrangement of solar cells is solar sails or solar wings extending from the satellite body, and body-mounted solar cell arrays are often used for spinning satellites or small and medium-sized satellites with compact dimensions. However, since only the sunny side receives sunlight, only one side of the solar sail or solar wing can actually function; the side and shady side of the body-mounted satellite have solar arrays that are inefficient or even unable to generate electricity. It can be seen that at any moment, the area that can be used for solar energy acquisition accounts for only half...

Claims

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Application Information

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IPC IPC(8): B64G1/44G05D3/12
Inventor 范春石宋坚王文隽李勇周庆瑞王辉
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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