Active space vehicle potential control system and control method based on energy conversion

A technology of active potential control and energy conversion, applied in electric vehicles, current collectors, electrical components, etc., can solve problems such as high technical difficulty, consumption, and increase the weight of spacecraft, and achieve the effect of reducing the risk of discharge

Inactive Publication Date: 2017-05-17
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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However, this method not only needs to consume extra energy or greatly inc

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  • Active space vehicle potential control system and control method based on energy conversion
  • Active space vehicle potential control system and control method based on energy conversion

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Embodiment Construction

[0025] The energy conversion-based spacecraft potential active control system of the present invention will be further described below in conjunction with the accompanying drawings. This description is only exemplary and is not intended to limit the protection scope of the present invention.

[0026] see figure 1 , the active control system of spacecraft potential based on energy conversion of the present invention includes an upper collector and a lower collector, electrically connected to an electric energy conversion memory and a detection unit arranged between the upper and lower collectors, and the electric energy conversion memory is electrically connected to the load, Among them, the upper collector and the lower collector are respectively electrically connected and arranged on two parts of the spacecraft with a large potential difference or the two parts of the spacecraft with a large potential difference are correspondingly used as the upper and lower collectors. When ...

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Abstract

The invention discloses an active space vehicle potential control system based on energy conversion. The active space vehicle potential control system comprises an upper collector, a lower collector, an electric energy conversion storage and a detection unit, wherein the electric energy conversion storage and the detection unit are arranged between the upper collector and the lower collector, the electric energy conversion storage is connected with a load (or effective load), and the upper collector and the lower collector are respectively and electrically connected and arranged on two parts large in potential difference of a space vehicle. When the detection unit detects the potential difference of the two collectors, whether a potential difference signal reaches a certain potential difference or not through a power management system. When the potential difference signal reaches the certain potential difference, energy conversion is enabled to charge the electric energy conversion storage. When the potential is reduced to a certain potential, charging is stopped, and it is achieved that the potential of the space vehicle is reduced to a safety threshold. Charging charge is led out through the space vehicle parts different in potential and serving as the two collectors for energy storage and charging and is reduced to be below the safety threshold, the discharging risk is reduced, and meanwhile energy with the magnitude of 10W can be obtained.

Description

technical field [0001] The invention belongs to the technical field of protection against space environmental effects. Specifically, the invention relates to a system and a control method for active protection against the charging and discharging effects of a spacecraft. use. Background technique [0002] Satellite charging effect, also known as charging and discharging effect, means that the charging and discharging process of satellites is divided into surface charging and discharging effect and internal charging effect. [0003] In fact, during the orbital operation of the spacecraft, it will interact with the environment such as space plasma and high-energy electrons to cause electrostatic charge accumulation and discharge, that is, the charging and discharging effect. Among them, the main components of the low-energy plasma environment are low-energy electrons and protons, which mainly come from the solar wind from coronal mass ejections. The particle flux and energy ...

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Application Information

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IPC IPC(8): B64G1/52H02J7/00
CPCB64G1/52H02J7/007H02J7/0077
Inventor 沈自才刘业楠马子良王志浩白羽丁义刚田东波
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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