Evaluation method for degradation of thermal control performance of laser-driven flyer impacting MLI
A technology of laser-driven flyer and evaluation method, which is applied in the direction of impact testing, testing material strength using one-time impact force, measuring devices, etc., which can solve problems such as reducing heat insulation, MLI penetration, and endangering the normal operation of spacecraft. To achieve the effect of clear requirements and simple execution
Inactive Publication Date: 2017-02-22
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology
The impact of space debris causes the performance degradation of thermal control materials, which reduces the effect of heat insulation. Severe impacts may lead to MLI penetration, endangering the normal operation of spacecraft
Method used
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Experimental program
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Embodiment Construction
[0014] The following is a further description of the performance degradation evaluation method of the laser-driven flyer impacting the multi-layer heat insulation assembly of the present invention. This description is only exemplary and is not intended to limit the protection scope of the present invention.
[0015] The method is divided into five steps: sample design, fixture design, experimental design, test requirements, and data analysis. Among them, the sample design requires that the MLI surface is clean and the area exceeds 20cm 2 , to facilitate cutting; the design of the fixture requires that the front and rear surfaces of the MLI be covered by polytetrafluoroethylene plates, where the front surface of the polytetrafluoroethylene plate must have holes to expose the surface of the MLI to be impacted, and the MLI and the polytetrafluoroethylene plate are fixed by the clamp ; The test design includes the selection of flyer parameters before the test and the operation met...
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Abstract
The invention discloses a method of evaluating thermal control performance degradation of an MLI component impacted by a laser-driven flyer. The method comprises the steps: the MLI component is covered by a polyfluortetraethylene plate with the same area and fixed by a clamping device; the front surface to be impacted is provided with holes and exposed for impact tests and no hole is formed on the polyfluortetraethylene plate; the MLI component is stuck and fixed on a speed-measuring displacement platform and the exposed part is parallel with a flayer target; laser energy is regulated according to the relation between the preset laser energy and the impact speed of the flyer and then the impact test is carried out; after the test is finished, the mechanical damage characteristic and the thermal control characteristic of the MLI component is tested. The method has clear requirements and is simple to execute the test and the testing content of the MLI impacted by the laser-driven flyer at high speed; the high-speed impact test and the thermal control parameter testing of the MLI by using tiny fragments are carried out according to the method, and the thermal control performance degradation degree of the MLI impacted by tiny spatial fragments at high speed can be evaluated and simulated effectively.
Description
technical field [0001] The invention belongs to the technical field of spacecraft space debris protection, and in particular relates to a performance evaluation method for a laser-driven flyer impacting a multi-layer heat insulation assembly. Background technique [0002] MLI (Multilayer Insulation Assembly) has excellent thermal insulation performance and is often used for surface covering and insulation of spacecraft. It is a heat insulation material composed of multi-layer reflective screens, and it can also be composed of multi-layer reflective screens and spacers. The material of the reflective screen is usually aluminized polyimide or aluminized polyester, and the spacer material is usually polyester mesh. The impact of space debris causes the performance degradation of thermal control materials and reduces the effect of heat insulation. Severe impact may cause MLI to penetrate and endanger the normal operation of the spacecraft. The basic thermal control parameters ...
Claims
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IPC IPC(8): G01M7/08B64G7/00G01N1/28G01N3/30
Inventor 杨继运李宇马子良于兆吉郎冠卿
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG