Cryogenic thermal system analysis for orbital propellant depot

Chai, Patrick; Wilhite, Alan W.

doi:10.1016/j.actaastro.2014.05.013

Cited by 16 publications

(6 citation statements)

References 19 publications

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“…While it entries into the space, cryogenic tank would be subjected to variety kinds of space radiations. Among different space radiations, solar incident radiation, earth albedo radiation, earth infrared radiation and deep space infrared radiation are the main heat sources [2,26]. …”

Section: Space Radiationmentioning

confidence: 99%

“…During the rocket launch, cryogenic propellant tanks are subjected to serious aerodynamic heat and space radiations. Due to the low boiling point, liquid propellants are quite sensitive to heat leaks from the external thermal environment [2]. Complex heat and mass transfer are involved in the pressurization and thermal stratification process.…”

Section: Introductionmentioning

confidence: 99%

“…Zilliac and Karabeyoglu [6] proposed a quasi-phase equilibrium thermodynamic model to predict the tank pressurization. Grayson et al [7] adopted the Flow-3D software to research the pressurization performance of cryogenic LH 2 with the pressurized helium injection. Lopez et al [8,9] developed a CFD model to study the pressure control of an ellipsoidal-shaped LH 2 tank in both normal gravity and low gravity condition.…”

Section: Introductionmentioning

confidence: 99%

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Pressurization performance and temperature stratification in cryogenic final stage propellant tank

Liu

Yonghua

2016

Applied Thermal Engineering

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Section: Space Radiationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Pressurization performance and temperature stratification in cryogenic final stage propellant tank

Liu

Yonghua

2016

Applied Thermal Engineering

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“…q = 0.00024*(0.017+7E-6(800-T) +0.0228*ln(T))*(N*) 2.63 (Th-Tc)/Ns (8-4) + 4.944E-10*ɛ*(Th 4.67 -Tc 4.67 )/Ns + 1.46E4*P*(Th 0.52 -Tc Wilhite demonstrated analytically that with 60 layers, the rate of cryogenic boiloff stabilizes to approximately 0.5 -1.0% per month for LO2, and approximately 2.5 -5.0% per month for LH2. (Chai and Wilhite, 2013) Furthermore, their results pointed to the density of the MLI blankets (number of layers per centimeter) as being important, with more space between the layers being better. For this effort, Steven Sutherlin suggested a density of 10 layers per centimeter, and using inner layers of MLI with a low emissivity (S. Sutherlin, personal communication, May 7, 2015).…”

Section: Modified Lockheed Modelmentioning

confidence: 99%

Architecture Study for a Fuel Depot Supplied From Lunar Resources

Perrin

Casler

2016

Aiaa Space 2016

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I express my sincere appreciation to the members of my advisory committee for their guidance and support during my time in the master's program at the University of North Dakota. I also want to express my appreciation for my wife, Diana, and my daughter, Sarah, who kept the home fires burning while Dad spent many nights and weekends at the office working on "his space stuff". I want to thank Mr. Charles L. (Les) Johnson, Deputy Manager of the Advanced Concepts Office at Marshall Space Flight Center. Mr. Johnson was keenly interested in the work and assisted me in locating subject matter experts when needed. I also want to thank Mr. Patrick S. McRight, Manager of the Propulsion Systems Design & Integration Division at Marshall Space Flight Center. Mr. McRight tutored me on the complexities of cryogenic propellant storage and transfer, and frequently made himself available as a sounding board for my ideas. Mr. Steven G. Sutherlin, a Propulsion Systems Engineer in the Marshall Space Flight Center Advanced Concepts Office, also contributed enormously to my effort. We discussed spacecraft design and its influence on propellant boiloff. Mr. Sutherlin also helped me wrestle with characterizing the thermal environment at different points in space, and checked my boiloff calculations with in-house tools he uses in his work. I am deeply grateful. Mr. Larry Kos, a mission designer in the Marshall Space Flight Center Advanced Concepts Office, contributed his expertise regarding the thrust-to-weight ratio for lunar vehicles. xiii Mr. Robert Werka, a Senior Aerospace Flight Systems Engineer at Marshall Space Flight Center, contributed his expertise regarding rocket engine oxidizer-to-fuel ratios, as well as his friendship. Lastly, I want to thank Dr. Alan Wilhite, Distinguished Langley Professor of Advanced Aerospace Systems Architecture at the Georgia Institute of Technology. While we only corresponded by email, Dr. Wilhite introduced me to the Modified Lockheed Model, and responded to my many questions as if I were one of his own students. Dr. Wilhite retired in December, 2014. xiv ABSTRACT Heretofore, discussions of space fuel depots assumed the depots would be supplied from Earth. However, the confirmation of deposits of water ice at the lunar poles in 2009 suggests the possibility of supplying a space depot with liquid hydrogen/liquid oxygen produced from lunar ice. This architecture study sought to determine the optimum architecture for a fuel depot supplied from lunar resources. Three factorsthe location of propellant processing (on the Moon or on the depot), the location of the depot (on the Moon or in cislunar space), and if in cislunar space, where (LEO, GEO, or Earth-Moon L1), and the method of propellant transfer (bulk fuel or canister exchange) were combined to identify 18 potential architectures. Two design reference missions (DRMs)a commercial satellite servicing mission and a Government cargo mission to Marswere used to create demand for propellants, while a third DRMa propellant delivery missionwas used to exa...

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“…This will be critical for monitoring the propellant during the year the in space stage is being filled. 37 In all, cryogenic-related technologies will require the most significant advancements to bring the CCS-ISP (or any deep-space) architecture to fruition. NASA is currently funding the in-space demonstration Cryogenic Propellant Storage and Transfer program that will provide improved technology readiness for this architecture.…”

Section: Architecture Technologiesmentioning

confidence: 99%

The Utilization of Launch Vehicles Core Stages and Propellant Depots for Human Space Exploration

Wilhite

Arney

Chai

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A crewed mission to a near earth asteroid would yield both scientific and engineering advancements. Visiting one or several of these objects would not only validate technologies that could later be used to visit the Moon or Mars, but would also develop our scientific understanding of asteroids and the solar system. This study proposes an architecture that represents a paradigm shift in the way space exploration is conducted. By including the commercial space industry in this mission and encouraging competition, NASA can realize significant cost savings and schedule improvements. This architecture uses a commercial launch vehicle core stage, which can reach orbit if a rocket is launched with no payload, as the in space propulsion system for both outbound and inbound burns. Refueling the core stage with commercial launch systems separates the propellant from the mission-critical elements, and using multiple commercial partners shortens the mission life cycle time and increases mission reliability. Removing expensive and unnecessary systems and supplementing NASA hardware with existing commercial systems brings the program under the current human space exploration budget. Furthermore, this architecture is also extensible to other destinations of interest for human exploration.

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Cryogenic thermal system analysis for orbital propellant depot

Cited by 16 publications

References 19 publications

Pressurization performance and temperature stratification in cryogenic final stage propellant tank

Pressurization performance and temperature stratification in cryogenic final stage propellant tank

Architecture Study for a Fuel Depot Supplied From Lunar Resources

The Utilization of Launch Vehicles Core Stages and Propellant Depots for Human Space Exploration

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