This research aimed to replace the combustion chamber material of a solid propellant rocket engine, which was traditionally made from aluminum (Al), with carbon fiber reinforced plastic (CFRP) to reduce theengine’s weight. Through structural analysis, potential failure causes in CFRP combustion chambers were identified and addressed, leading to a 10% weight reduction compared to the Al-based engine at the same thrust. The engine’s suitability was verified through thrust tests.
HANul 
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