국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Cryogenic Propellant Storage and Transfer Technology Demonstration For Long Duration In-Space Missions
저자	Meyer, Michael L.;; Motil, Susan M.;; Kortes, Trudy F.;; Taylor, William J.;; McRight, Patrick S.
Keyword	CRYOGENIC FLUIDS;; CRYOGENIC ROCKET PROPELLANTS;; LAUNCHING;; LIQUID HYDROGEN;; LIQUID OXYGEN;; MICROGRAVITY;; MISSION PLANNING;; NASA PROGRAMS;; PROPELLANT STORAGE;; PROPELLANT TRANSFER;; ROBOTICS;; SPECIFIC IMPULSE;; SYSTEMS ENGINEERING;; TEMPERATURE CONTROL
URL	http://hdl.handle.net/2060/20120009208
보고서번호	NASA/TM-2012-217642
발행년도	2012
출처	NTRS (NASA Technical Report Server)
ABSTRACT	The high specific impulse of cryogenic propellants can provide a significant performance advantage for in-space transfer vehicles. The upper stages of the Saturn V and various commercial expendable launch vehicles have used liquid oxygen and liquid hydrogen propellants;; however, the application of cryogenic propellants has been limited to relatively short duration missions due to the propensity of cryogens to absorb environmental heat resulting in fluid losses. Utilizing advanced cryogenic propellant technologies can enable the efficient use of high performance propellants for long duration missions. Crewed mission architectures for beyond low Earth orbit exploration can significantly benefit from this capability by developing realistic launch spacing for multiple launch missions, by prepositioning stages and by staging propellants at an in-space depot. The National Aeronautics and Space Administration through the Office of the Chief Technologist is formulating a Cryogenic Propellant Storage and Transfer Technology Demonstration Mission to mitigate the technical and programmatic risks of infusing these advanced technologies into the development of future cryogenic propellant stages or in-space propellant depots. NASA is seeking an innovative path for human space exploration, which strengthens the capability to extend human and robotic presence throughout the solar system. This mission will test and validate key cryogenic technological capabilities and has the objectives of demonstrating advanced thermal control technologies to minimize propellant loss during loiter, demonstrating robust operation in a microgravity environment, and demonstrating efficient propellant transfer on orbit. The status of the demonstration mission concept development, technology demonstration planning and technology maturation activities in preparation for flight system development are described.