Medium orbit sateLLite deorbit method based on soLar radiation pressure

A technology of solar light pressure and orbiting satellites, which is used in space navigation equipment, space navigation aircraft, space navigation aircraft guidance devices, etc., to shorten the de-orbit time and reduce the proportion of

Inactive Publication Date: 2018-11-23
PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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Problems solved by technology

[0004] Aiming at the existing MEO area, there is no clear treatment principle for abandoned satellites. The present invention provides a MEO satellite de-orbiting method based on solar light pressure, and proposes to combine a new type of power system, the solar light sail, with abandoned satellites. The design of the light sail system solves the disadvantages of the traditional deorbiting method and makes up for the lack of deorbiting schemes for abandoned mid-orbit satellites. The light sail system directly uses solar light pressure to generate power, which will not pollute the environment and reduce the risk of carrying fuel. percentage of payload

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  • Medium orbit sateLLite deorbit method based on soLar radiation pressure
  • Medium orbit sateLLite deorbit method based on soLar radiation pressure
  • Medium orbit sateLLite deorbit method based on soLar radiation pressure

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[0074] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0075] combine figure 1 , the present invention provides a method for deorbiting a mid-orbit satellite based on solar light pressure, comprising the following steps:

[0076] Step 1: Establish a perturbation force model;

[0077] During the movement of space debris, in addition to being affected by the gravitational force at the center of the earth, it will also be affected by complex perturbation forces. The perturbation force plays a decisive role in the change of the orbit of the debris. Let the motion acceleration of the debris be a sd can be decomposed into:

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Abstract

The invention provides a medium orbit sateLLite deorbit method based on soLar radiation pressure. In consideration of the situation that no definite waste sateLLite treatment principLe is estabLishedin the current medium orbit region and the deveLopment prospect of a soLar saiL technoLogy, a disturbing force modeL of waste sateLLites and a Long-term evoLvement modeL of the waste sateLLites are estabLished, Long-term evoLvement conditions with or without soLar saiLs are anaLyzed, the feasibiLity of the condition that the soLar saiLs enter the atmosphere again is verified, infLuences of initiaLorbit parameters on Long-term evoLvement of the waste sateLLites are researched, and references are provided for seLecting appropriate initiaL orbit parameters for entering the atmosphere again.

Description

technical field [0001] The invention belongs to the technical field of medium-earth orbit satellite de-orbiting, and in particular relates to a medium-earth orbit de-orbiting method based on solar light pressure. Background technique [0002] The deorbiting of traditional satellites mainly relies on propellant maneuvering, and for medium earth orbit satellites. Taking navigation satellites as an example, the orbital altitude is about 20,000km, and the propellant consumed to lower the orbital altitude to re-enter the atmosphere is too large. Propellant is a precious resource for satellite operation. Carrying nearly 100kg more propellant not only requires redesigning the satellite structure, but also increases the cost of satellite launch. Scholars have begun to explore the use of perturbations for orbital maneuvers. Among these perturbations, only atmospheric resistance and solar light pressure can be used, and other perturbations are conservative forces. Atmospheric resista...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 胡敏徐家辉宋俊玲胡一文旷鸿宇孙鸿强王怀鹏赵玉龙
Owner PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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