Detection device of on-orbit radiation risk of spacecraft

A technology of detection device and spacecraft, which is applied in the direction of measurement device, radiation measurement, X/γ/cosmic radiation measurement, etc., to achieve the effects of low power consumption, simple structure and small size

Active Publication Date: 2019-12-03
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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  • Abstract
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Problems solved by technology

[0015] At present, there is no detection device for spacecraft in-orbit radiation risk in China, and it is impossible to quickly detect comprehensive radiation effects through simple structural design and electronic components to diagnose possible space radiation risks

Method used

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  • Detection device of on-orbit radiation risk of spacecraft
  • Detection device of on-orbit radiation risk of spacecraft

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Embodiment Construction

[0026] The present invention will be described in further detail below in conjunction with the accompanying drawings, but this is only exemplary and not intended to limit the protection scope of the present invention. The present invention will be further described below in conjunction with the accompanying drawings and embodiments. It should be noted that the following embodiments are intended to facilitate the understanding of the present invention, and have no limiting effect on it.

[0027] see figure 1 , figure 1 It shows a schematic structural diagram of a spacecraft on-orbit radiation risk detection device according to a specific embodiment of the present invention, which includes a rectangular chassis (detector housing) 1 and seven groups of detection units arranged inside the housing, and the seven groups of sensors are in the form of Arranged in two parallel rows, three sets of detection units on one side, and shielding layers with different shielding thicknesses ar...

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Abstract

The invention discloses a detection device of an on-orbit radiation risk of a spacecraft. The detection device comprises a detector shell and seven built-in detection unit groups. Each detection unitgroup consists of a temperature sensor and a total dose detector; the shell part right above one detection unit group is opened to ensure detection without shielding limiting of the shell; the anotherdetection unit group uses the spacecraft shell as a shielding layer for detection and the other five detection unit groups are provided with metal shielding layers with different thicknesses to detect different space radiation effects. Each detection unit group is arranged on the intermediate circuit board for collecting the temperature and the total dose. The detection device has characteristicsof simple structure, small size, light weight, low power consumption and the like; risks of different space radiation effects such as a surface charge-discharge effect, a total dose effect, a singleparticle effect, a displacement damage effect, an internal electrification effect and the like can be determined.

Description

technical field [0001] The invention belongs to the technical field of spacecraft on-orbit situation detection, and in particular, the invention particularly relates to a detection device for spacecraft on-orbit radiation effect risk. Background technique [0002] The space radiation environment mainly comes from stellar radiation belts, solar cosmic rays, and galactic cosmic rays, and its main components are electrons, protons and a small amount of heavy ions. Among them, the Earth's radiation belt environment is one of the most important radiation environments affecting spacecraft in low-Earth orbit, and can usually be divided into the inner radiation belt and the outer radiation belt. During solar flares, a large number of high-energy protons, electrons, and heavy nuclear particles are emitted, which are called solar cosmic rays. Most of them are composed of protons, so it is also known as the solar proton event. The energy range of solar cosmic ray particles is general...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01T1/02G01T1/29G01T1/36G01K7/22B64G1/66
CPCB64G1/66G01K7/22G01T1/026G01T1/29G01T1/36
Inventor 沈自才杨艳斌夏彦王晶虎丁义刚
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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