Cryogenic Boil-Off Reduction System

Plachta, David W.; Guzik, Monica C.

doi:10.1016/j.cryogenics.2013.12.006

Cited by 18 publications

(10 citation statements)

References 3 publications

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“…In conclusion, the power of the heat radiation heat into the storage tank from the sun and spacecraft via the sun shade is Fig. 2 e Temperature distribution of the sun shade, and the temperature of its center is set to be 150 K. (11) The radiation heat into the space environment from the liquid hydrogen tank The 5 cm foam around the liquid hydrogen tank has an emissivity ε n of 0.9. When calculating the temperature distribution of the foam, we use the steady-state assumption:…”

Section: Computational Processmentioning

confidence: 99%

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Passive zero-boil-off storage of liquid hydrogen for long-time space missions

Sun

Guo

Huang

2015

International Journal of Hydrogen Energy

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Section: Computational Processmentioning

confidence: 99%

“…Wang et al [10] conducted a study on optimal layer density of variable density multilayer insulation and put forward the best combination of the number of layers in different parts. Plachta and Guzik [11] also pointed out the importance of combining MLI, cryocoolers and broad area cooling shields.…”

Section: Introductionmentioning

confidence: 96%

Passive zero-boil-off storage of liquid hydrogen for long-time space missions

Sun

Guo

Huang

2015

International Journal of Hydrogen Energy

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“…The objectives in this test series were to determine the integrated system performance of a Cryogenic BoilOff Reduction System (CBRS) with a propellant tank, validate the existing scaling study model, 13 advance the technology of reduced and zero boil-off concepts, prove the viability of self-supporting MLI, and to robustly achieve ZBO by controlling tank pressure with the cryocooler system. The integrated performance goal necessitated performing an end-to-end test with the cooling system, the propellant tank, and the heat rejection system all incorporated together within the vacuum chamber.…”

Section: Test Objectivesmentioning

confidence: 99%

Cryogenic Boil-Off Reduction System Testing

Plachta

Johnson²,

Feller

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Cryogenic propellants such as liquid hydrogen (LH 2 ) and liquid oxygen (LO 2 ) are a part of NASA's future space exploration due to the high specific impulse that can be achieved using engines suitable for moving 10's to 100's of metric tons of payload mass to destinations outside of low earth orbit. However, the low storage temperatures of LH 2 and LO 2 cause substantial boil-off losses for missions with durations greater than several days. The losses can be greatly reduced by incorporating high performance cryocooler technology to intercept heat load to the propellant tanks and by the integration of self-supporting multi-layer insulation. The active thermal control technology under development is the integration of the reverse turboBrayton cycle cryocooler to the propellant tank through a distributed cooling network of tubes coupled to a shield in the tank insulation and to the tank wall itself. Also, the self-supporting insulation technology was utilized under the shield to obtain needed tank applied LH 2 performance. These elements were recently tested at NASA Glenn Research Center in a series of three tests, two that reduced LH 2 boil-off and one to eliminate LO 2 boil-off. This test series was conducted in a vacuum chamber that replicated the vacuum of space and the temperatures of low Earth orbit. The test results show that LH2 boil-off was reduced 60% by the cryocooler system operating at 90K and that robust LO2 zero boil-off storage, including full tank pressure control was achieved.

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“…Two similar test-bed test tank articles were constructed to meet the goal of evaluating both thermal and structural characteristics of the integrated MLI and BAC shield systems: the RBO test article (Figure 4) was built to thermally evaluate the system performance at the Glenn Research Center, and the Vibro-Acoustic Test Article (VATA, Figure 5) was built to evaluate structural performance under flight-like loading of the system at Marshall Space Flight Center [9][10][11] . The RBO and VATA tests were successfully completed demonstrating acceptable structural response with minimal degradation of thermal performance of the MLI/BAC insulation system.…”

Section: B Active Thermal Control Technologymentioning

confidence: 99%

The Cryogenic Propellant Storage and Transfer Technology Demonstration Mission: Progress and Transition

Meyer¹,

Taylor²,

Ginty³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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In support of its goal to find an innovative path for human space exploration, NASA embarked on the Cryogenic Propellant Storage and Transfer (CPST) Project, a Technology Demonstration Mission (TDM) to test and validate key cryogenic capabilities and technologies required for future exploration elements, opening up the architecture for large in-space cryogenic propulsion stages and propellant depots. Planning for a demonstration mission began in 2010, and over several years the project has evolved from a very large, hydrogen and oxygen Flagship Technology Demonstrator to a single fluid (hydrogen) TDM. Through the work of a dedicated team, the mission successfully passed critical milestones including Mission Concept Review (MCR), Systems Requirements Review (SRR) and Mission Definition Review (MDR), and Key Decision Point B giving the project management authority to proceed to Preliminary Design Review (PDR). Despite these technical and programmatic successes, inFebruary 2014, the funding appropriated to NASA by the Congress was not sufficient to continue with the flight mission, and the project was redirected to a less costly ground test and analysis activity to commence in Fiscal Year (FY) 2015. In addition to developing and maturing a concept for the flight demonstration, the team completed significant advances to the cryogenic fluid management technology field. Recognizing that key Cryogenic Fluid Management (CFM) technologies anticipated for on-orbit (flight) demonstration would benefit from additional maturation to a readiness level appropriate for infusion into the design of the flight demonstration, the NASA Headquarters Space Technology Mission Directorate (STMD) authorized funding for a 1-year technology maturation phase of the CPST project. The strategy, proposed by the CPST Project Manager, focused on maturation through modeling, concept studies, and ground tests of the storage and fluid transfer CFM technology subelements and components that were lower than a Technology Readiness Level (TRL) of 5. A technology maturation plan (TMP) was subsequently approved which described: the CFM technologies selected for maturation, the ground testing approach to be used, quantified success criteria of the technologies, hardware and data deliverables, and a deliverable to provide an assessment of the technology readiness after completion of the test, study or modeling activity. The specific technologies selected were grouped into five major categories: thick multilayer insulation, tank applied active thermal control, cryogenic fluid transfer, propellant gauging, and analytical tool development. Based on the success of the technology maturation efforts, the CPST project was approved to proceed to flight system development. NomenclatureAR&D = autonomous rendezvous and docking ATP = authority to proceed CFM = cryogenic fluid management CPST = cryogenic propellant storage and transfer technology demonstration mission KDP = key decision point LAD = liquid acquisition device 1 CPST Principal Investigator, M/S 301-3, 2100...

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Cryogenic Boil-Off Reduction System

Cited by 18 publications

References 3 publications

Passive zero-boil-off storage of liquid hydrogen for long-time space missions

Passive zero-boil-off storage of liquid hydrogen for long-time space missions

Cryogenic Boil-Off Reduction System Testing

The Cryogenic Propellant Storage and Transfer Technology Demonstration Mission: Progress and Transition

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