Method for determining total fluence of space radiation environment effect test of thermal control coating

A technology of space radiation environment and thermal control coating, applied in the field of space radiation environmental effect test, can solve problems such as misjudgment, hidden danger of spacecraft thermal design work, and degradation of thermal control coating on-orbit performance, and achieves strong operability. Effect

Inactive Publication Date: 2015-02-25
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology

Over-testing or under-testing will lead to misjudgment of the degradation of the thermal control coa

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  • Method for determining total fluence of space radiation environment effect test of thermal control coating
  • Method for determining total fluence of space radiation environment effect test of thermal control coating
  • Method for determining total fluence of space radiation environment effect test of thermal control coating

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[0032] The following introduces the specific implementation mode as the content of the present invention, and the content of the present invention will be further clarified through the specific implementation mode below. Of course, the following specific embodiments are described only to illustrate different aspects of the present invention, and should not be construed as limiting the scope of the present invention.

[0033] Taking the electron irradiation effect of the Kapton film thermal control coating material in the 15-year GEO orbit environment as an example, the equivalent total fluence of electrons in the ground test is determined.

[0034] Firstly, two groups of irradiation experiments were carried out with electrons with energies of 20keV and 40keV respectively, where Φ 0 Optionally, get Kapton thermal control coating material Δα s degradation over time as figure 1 shown.

[0035] Substitute the experimental data into the formula In , the two sets of fitting for...

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Abstract

The invention discloses a method for determining the total fluence of a space radiation environment effect test of a thermal control coating. According to the method, an equivalent formula when the beam current density of space continuous spectrum radiating particles is conversed into a radiating particle beam current density under certain energy is obtained according to the principle of equivalent degradation in an in-orbit and ground test on the solar absorptance of a thermal control coating, a radiation test of two groups of charged particles is carried out, curve fitting is carried out according to thermal control coating performance degradation data and radiating time data so as to determine parameters in an equivalent beam current density formula, so that the total fluence of the ground-based test can be determined. Compared with the prior art, the method has the advantages that mono-energetic electrons or protons in ground-based test equipment are adopted to simulate the injuring effect of orbit space electrons or protons on thermal control materials, and the practical operability is strong.

Description

technical field [0001] The invention relates to the technical field of space radiation environmental effect test, in particular to a method for determining the total fluence (that is, the number of radiation particles) of thermal control coating space radiation environmental effect test, which is suitable for space radiation environmental effect of spacecraft thermal control coating material Design of ground simulation test parameters and material performance evaluation. Background technique [0002] Thermal control coating materials (including films such as Kapton, secondary surface mirrors such as OSR, paints such as S781) are the main materials used for spacecraft to exchange heat with the outside world, and are used to ensure that the structural components and instruments of the spacecraft are in good condition. The space environment is in the right temperature range for it to work properly. The solar absorption ratio (α s ) is the most important parameter to character...

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Application Information

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IPC IPC(8): G01N17/00
Inventor 刘宇明赵春晴丁义刚杨晓宁姜利祥沈自才刘向鹏李蔓
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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