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Thermal optimization and assessment of a long duration cryogenic propellant depot
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kutter, Bernard Honour, Ryan O'Neil, Gary Kwas, Robert |
| Copyright Year | 2012 |
| Description | A Cryogenic Propellant Depot (CPD) operating in Low Earth Orbit (LEO) could provide many near term benefits to NASA space exploration efforts. These benefits include elongation/extension of spacecraft missions and reduction of launch vehicle up-mass requirements. Some of the challenges include controlling cryogenic propellant evaporation and managing the high costs and long schedules associated with new spacecraft hardware development. This paper describes a conceptual CPD design that is thermally optimized to achieve extremely low propellant boil-off rates. The CPD design is based on existing launch vehicle architecture, and its thermal optimization is achieved using current passive thermal control technology. Results from an integrated thermal model are presented showing that this conceptual CPD design can achieve propellant boil-off rates well under 0.05% per day, even when subjected to the LEO thermal environment. |
| File Size | 7373002 |
| Page Count | 26 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20110013691 |
| Archival Resource Key | ark:/13960/t3421zk5j |
| Language | English |
| Publisher Date | 2012-01-09 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Leakage Centaur Launch Vehicle Propellant Evaporation Saturation Propellant Tanks Propulsion System Configurations Optimization Low Earth Orbits Liquid Oxygen Heat of Vaporization Thermodynamic Properties Liquid Hydrogen Multilayer Insulation Cryogenic Rocket Propellants Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
