Cryogenic propellant tanks are critical components of space launch systems and future hypersonic/supersonic air vehicles. Significant vehicular weight reduction can be achieved by replacing industry-standard metallic tanks with composite cryogenic tanks. Foreign object impacts during vehicle assembly or launch can cause microcracking, which can provide pathways for leakage of cryogenic fuel, compromising the vehicle. Therefore, the objective of this study is to investigate the combined influence of impact damage and thermal fatigue on the gas permeability of composites. Carbon/epoxy composites () were subjected to 20 thermal cycles from ambient temperature to cryogenic temperature (). The specimens were subjected to impact testing at room and cryogenic temperatures before and after thermal cycling. Gas permeability of these composites was measured at selected numbers of cryogenic cycles, and the specimens were optically examined to observe the development of damage postimpact and thermal cycling. Experimental results show that impact damage caused the gas permeability of the composite specimens to increase significantly. Composite specimens impacted at cryogenic temperature had lower gas permeability, absorbed energy, and extent of damage when compared to composites impacted at room temperature. Gas permeability of all impacted composites was found to be less than the permeability allowable for composite cryogenic tanks for launch vehicles.
Gas Permeation of Composites Subjected to Impact for Cryogenic Applications
Journal of Spacecraft and Rockets ; 59 , 4 ; 1255-1261
2022-02-23
7 pages
Article (Journal)
Electronic Resource
English
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