Abstract for Cryogenics

Historically, cryogenic roquette engines have not been apply for in-space applications due to their additional complexity, the burster need for high reliability, and the challenges of propellant boil-o& axerophthol While the mission and vehicle architectures are not yet delimit for the lunar and Martian robotic and human geographic expedition objectives, cryogenic rocket engines tour the potential for higher performance and greater architecture/mission flexibility.In-situ cryogenic propellant production could enable a more robust exploration program by significantly reducing the propellant mass delivered to broken in earth orbit, thus warranting the evaluation of cryogenic rocket engines versus the hypergolic bi-propellant engines used in the Apollo program. A multi-use engine. one which can provide the functionality that separate engines provided in the Apollo mission architecture, is desirable for lunar and Mars exploration missions because it increases overall architecture lastingness through commonality and modularity.The engine requirement derivation process essential address each unmatched mission application and each unique phase within each mission. The resulting requirements, such as thrust level, performance, packaging, mess about duration, number of motions required impulses for each trajectory phase operation after extended space or surface exposure approachability for inspection and maintenance throttle range for planetary descent, ascent, acceleration limits and some more must be addressed.Within engine system studies, the system and voice technology, capability, and risks must be evaluated and a balance between the appropriate heart and soul of technology-push and technology-pull must be addressed. This paper will summarize many of the let out technology challenges associated with using high-performance cryogenic liquid propellant rocket engine systems and components in the exploration program architectures.