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http://dx.doi.org/10.7234/composres.2020.33.5.309

Evaluation of Permeability Performance by Cryogenic Thermal Shock in Composite Propellant Tank for Space Launch Vehicles  

Kim, Jung-Myung (ANH Structure ANH Design Center)
Hong, Seung-Chul (ANH Structure ANH Design Center)
Choi, Soo-Young (ANH Structure ANH Design Center)
Jeong, Sang-Won (ANH Structure ANH Design Center)
Ahn, Hyon-Su (ANH Structure)
Publication Information
Composites Research / v.33, no.5, 2020 , pp. 309-314 More about this Journal
Abstract
Polymer composites were used to reduce the weight of the spacecraft's cryogenic propellant tank. Since these materials were directional, the permeability performance of the gas permeated or delivered in the stacking direction was an indicator directly related to performance such as tank stability and onboard fuel quantity estimation. In addition, the results of permeation measurements and optical analysis of the surface to verify the effect of the number of cycles exposed to the cryogenic-room temperature environment are included. As a result, the permeability was inversely proportional to the thickness and was proportional to the number of thermal shocks, and it was verified that the permeability performance was suitable for the cryogenic propellant tank material for the space launch vehicle.
Keywords
Permeation; Cryogenic; Thermal-shock; Propellant tank;
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