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Thermal performance of an integrated thermal protection system for long-term storage of cryogenic propellants in space
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Boyle, R. J. Dewitt, R. L. |
| Copyright Year | 1977 |
| Description | It was demonstrated that cryogenic propellants can be stored unvented in space long enough to accomplish a Saturn orbiter mission after 1,200-day coast. The thermal design of a hydrogen-fluorine rocket stage was carried out, and the hydrogen tank, its support structure, and thermal protection system were tested in a vacuum chamber. Heat transfer rates of approximately 23 W were measured in tests to simulate the near-Earth portion of the mission. Tests to simulate the majority of the time the vehicle would be in deep space and sun-oriented resulted in a heat transfer rate of 0.11 W. |
| File Size | 102396734 |
| Page Count | 111 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770017239 |
| Archival Resource Key | ark:/13960/t46q6rc7p |
| Language | English |
| Publisher Date | 1977-05-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Cryogenic Fluid Storage Thermal Insulation Storage Tanks Liquid Hydrogen Multilayer Insulation Heat Transfer Coefficients 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 | Technical Report |
