NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Advisory – Planned Maintenance: On Monday, July 15 at 9 PM Eastern the STI Compliance and Distribution Services will be performing planned maintenance on the STI Repository (NTRS) for approximately one hour. During this time users will not be able to access the STI Repository (NTRS).

Back to Results
Long-Term Cryogenic Propellant Storage on Mars with Hercules Propellant Storage FacilityThis report details the process and results of roughly sizing the steady state, zero boil-off thermal and power parameters of the Hercules Propellant Storage Facility. For power analysis, isothermal and isobaric common bulkhead tank scenarios are considered. An estimated minimum power requirement of 8.3 kW for the Reverse Turbo-Brayton Cryocooler is calculated. Heat rejection concerns in soft vacuum Mars atmosphere are noted and potential solutions are proposed. Choice of coolant for liquid propellant conditioning and issues with current proposed cryocooler cycle are addressed; recommendations are made, e.g. adding a Joule-Thomson expansion valve after the Reverse Turbo-Brayton turbine in order to have two-phase, isothermal heat exchange through the Broad Area Cooling system. Issues with cross-country transfer lines from propellant storage to flight vehicle are briefly discussed: traditional vacuum jacketed lines are implausible, and Mars insulation needs to be developed.
Document ID
20170011674
Acquisition Source
Kennedy Space Center
Document Type
Other
Authors
Liu, Gavin
(Arizona State Univ. Tempe, AZ, United States)
Date Acquired
December 12, 2017
Publication Date
September 21, 2017
Subject Category
Lunar And Planetary Science And Exploration
Fluid Mechanics And Thermodynamics
Report/Patent Number
KSC-E-DAA-TN47835
Funding Number(s)
CONTRACT_GRANT: NNX13AJ45A
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.
Keywords
Propellant Storage
Cryocoole
Reusable Launch Vehicle
Broad Area Cooling
Heat Transfer
Reverse Turbo-Brayton
Joule-Thomson
Hercules
Colonization
Cryogenic
Heat Rejection
Propellant Transfer
Vacuum Jacketed
Mars
No Preview Available