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Study of reactor brayton power systems for nuclear electric spacecraft
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1979 |
| Description | The feasibility of using Brayton power systems for nuclear electric spacecraft was investigated. The primary performance parameters of systems mass and radiator area were determined for systems from 100 to 1000 kW sub e. Mathematical models of all system components were used to determine masses and volumes. Two completely independent systems provide propulsion power so that no single-point failure can jeopardize a mission. The waste heat radiators utilize armored heat pipes to limit meteorite puncture. The armor thickness was statistically determined to achieve the required probability of survival. A 400 kW sub e reference system received primary attention as required by the contract. The components of this system were defined and a conceptual layout was developed with encouraging results. An arrangement with redundant Brayton power systems having a 1500 K (2240 F) turbine inlet temperature was shown to be compatible with the dimensions of the space shuttle orbiter payload bay. |
| File Size | 10973994 |
| Page Count | 184 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820016413 |
| Archival Resource Key | ark:/13960/t58d4qh0q |
| Language | English |
| Publisher Date | 1979-09-28 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Economic Analysis Electric Rocket Engines Propulsion System Performance Nuclear Electric Propulsion Space Shuttle Payloads Brayton Cycle Propulsion System Configurations Spacecraft Propulsion Heat Pipes Mathematical Models Nuclear Reactors Heat Radiators Rocket Engine Design Spacecraft Configurations 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 |
