Space radiation effect bioequivalence evaluation method of aliphatic polymer insulation materials for space navigation

A technology of insulating materials and radiation effects, applied in the direction of analyzing materials, measuring devices, instruments, etc., can solve the problems of large evaluation errors and achieve high accuracy and simple operation

Active Publication Date: 2017-02-15
HARBIN INST OF TECH
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0010] The present invention aims to solve the technical problem of large evaluation error in the existing method for evaluating the space radiation effect of aliphatic polymers used in aerospace. Evaluation method

Method used

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  • Space radiation effect bioequivalence evaluation method of aliphatic polymer insulation materials for space navigation
  • Space radiation effect bioequivalence evaluation method of aliphatic polymer insulation materials for space navigation
  • Space radiation effect bioequivalence evaluation method of aliphatic polymer insulation materials for space navigation

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specific Embodiment approach 1

[0033] Specific implementation mode one: see figure 1 Describe this embodiment, the method for evaluating the equivalence of space irradiation effect of aliphatic polymer insulation materials for aerospace described in this embodiment, the method includes the following steps:

[0034] Step 1. Calculate the LET value, Ionization absorbed dose and range;

[0035] The material sample to be tested is an aliphatic polymer insulating material;

[0036] Each of the radiation sources described includes a Co source, electrons, protons and heavy ions;

[0037] Step 2. Determine the thickness of the material sample to be tested according to the range of each radiation source in the material sample to be tested, and use the minimum range of each radiation source in the material sample to be tested as the thickness of the material sample to be tested;

[0038] Step 3. Take four samples of the material to be tested, and the thickness of each sample of the material to be tested is the sam...

specific Embodiment approach 2

[0047] Embodiment 2: The difference between this embodiment and the method for evaluating the equivalence of space irradiation effects of aliphatic polymer insulating materials for aerospace as described in Embodiment 1 is that the analysis content of the microstructure analysis includes free radicals , group and chemical composition; the test content of the performance test includes mechanical properties, dielectric properties, insulation properties and optical properties.

specific Embodiment approach 3

[0048] Specific embodiment three: The difference between this embodiment and the space irradiation effect equivalence evaluation method of aliphatic polymer insulating materials for aerospace as described in specific embodiment two is that in step five, each physical quantity obtained by microstructure analysis is related to The relationship curve of ionized absorbed dose includes the relationship curve of free radicals and ionized absorbed dose, the relationship curve of group and ionized absorbed dose, and the relationship curve of chemical composition and ionized absorbed dose;

[0049] The relationship curves between various physical quantities and ionized absorbed dose obtained from the performance test include the relationship curve between mechanical properties and ionized absorbed dose, the relationship curve between dielectric properties and ionized absorbed dose, the relationship curve between insulating properties and ionized absorbed dose, and the relationship betwee...

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Abstract

The invention provides a space radiation effect bioequivalence evaluation method of aliphatic polymer insulation materials for space navigation, and relates to a bioequivalence evaluation method of the displacement radiation effect of different radiation sources of aliphatic polymer insulation materials for particle radiation environment. The problem of great evaluation error of the existing aliphatic polymer space radiation effect evaluation method for space navigation is solved. The LET value, the ionospheric absorption dosage and the ejection range of each radiation source in a sample of a material to be tested can be calculated; according to the ejection range of each radiation source in the sample of the material to be tested, the thickness of the sample of the material to be tested is determined, so that each radiation source performs radiation test correspondingly to one tested material, so that the radiation particles of each radiation source completely penetrate through the thickness of the corresponding sample of the material to be tested; after the radiation, a relationship curve of each physical quantity and the ionospheric absorption agent quantity obtained through microcosmic structure analysis of each radiation source under the radiation condition, and a relationship curve of each physical quantity and the ionospheric absorption agent quantity obtained through performance test are made. The method is used for evaluating the aliphatic polymer insulation materials.

Description

technical field [0001] The invention relates to an equivalence evaluation method for the displacement radiation effect of different radiation sources of an aliphatic polymer insulating material used in a particle radiation environment. Background technique [0002] With the continuous improvement of spacecraft reliability requirements, higher requirements are placed on the space environment reliability of electrical components such as electrical connectors, relays, and wires and cables. A large number of engineering practices have shown that because the insulation performance of electrical connectors, relays and wires and cables affects the stability and reliability of electronic equipment, and plays a decisive role in its life, it is necessary to use electrical connectors, relays and wires and cables for aerospace. research on insulating materials. [0003] Insulating materials can be divided into two categories, polymer insulating materials and inorganic insulating materi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N17/00
CPCG01N17/00
Inventor 杨剑群李兴冀马国亮刘超铭
Owner HARBIN INST OF TECH
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