FINAL SAFETY ANALYSIS REPORT. SNAP III THERMOELECTRIC GENERATOR
Abstract
The SNAP-III thermoelectric generator procedures power from the decay heat of 2100 curies of Po/sup 210/. This generator is to be used as a source of auxiliary power in a terrestrial satellite. For purposes of analysis, the satellite system postulated is launched from the Pacific Missile Bange into a 275- statute mile polar orbit with an orbital lifetime of about 1 year. Po/sup 210/ is an alpha emitter having a half life of 138 days and alpha and gamma decay energies of 5.3 and 0.8 mev, respectively. It is a natural component of the earth's crust, as a member of the uranium disintegration series. Sampling of polonium in the biosphere was conducted specifically for this program to determine background radiation levels. Since the fuel is primarily an alpha emitter, there is no direct radiation problem. An analysis was performed to determine the ability of the fuel container to withstand the various thermal, mechanical, and chemical forces imposed upon the generator by vehicle failures. Where theoretical analysis was impossible and experimental evidence was desired, capsules and generators were tested under simulated missile-failure conditions, Thus, the safety limits of SNAP-III in a satellite application were defined. SNAP-III is designed to be aerothermodynamicallymore »
- Authors:
- Publication Date:
- Research Org.:
- Martin Co. Nuclear Div., Baltimore
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 4110813
- Report Number(s):
- MND-P-2364
- NSA Number:
- NSA-15-008401
- DOE Contract Number:
- AT(30-3)-217
- Resource Type:
- Technical Report
- Resource Relation:
- Other Information: Orig. Receipt Date: 31-DEC-61
- Country of Publication:
- United States
- Language:
- English
- Subject:
- GENERAL AND MISCELLANEOUS; AEROSOLS; ALPHA DECAY; CORROSION; DISPERSIONS; FAILURES; GAMMA RADIATION; POLONIUM 210; RADIOACTIVITY; RE-ENTRY; SAFETY; SATELLITES; SNAP SYSTEMS; SPACE VEHICLES; TABLES; TENSILE PROPERTIES; TESTING; THERMAL STRESSES; THERMOELECTRIC CELLS; NESDPS Office of Nuclear Energy Space and Defense Power Systems
Citation Formats
Hagis, W, and Dix, G P. FINAL SAFETY ANALYSIS REPORT. SNAP III THERMOELECTRIC GENERATOR. United States: N. p., 1960.
Web. doi:10.2172/4110813.
Hagis, W, & Dix, G P. FINAL SAFETY ANALYSIS REPORT. SNAP III THERMOELECTRIC GENERATOR. United States. https://doi.org/10.2172/4110813
Hagis, W, and Dix, G P. 1960.
"FINAL SAFETY ANALYSIS REPORT. SNAP III THERMOELECTRIC GENERATOR". United States. https://doi.org/10.2172/4110813. https://www.osti.gov/servlets/purl/4110813.
@article{osti_4110813,
title = {FINAL SAFETY ANALYSIS REPORT. SNAP III THERMOELECTRIC GENERATOR},
author = {Hagis, W and Dix, G P},
abstractNote = {The SNAP-III thermoelectric generator procedures power from the decay heat of 2100 curies of Po/sup 210/. This generator is to be used as a source of auxiliary power in a terrestrial satellite. For purposes of analysis, the satellite system postulated is launched from the Pacific Missile Bange into a 275- statute mile polar orbit with an orbital lifetime of about 1 year. Po/sup 210/ is an alpha emitter having a half life of 138 days and alpha and gamma decay energies of 5.3 and 0.8 mev, respectively. It is a natural component of the earth's crust, as a member of the uranium disintegration series. Sampling of polonium in the biosphere was conducted specifically for this program to determine background radiation levels. Since the fuel is primarily an alpha emitter, there is no direct radiation problem. An analysis was performed to determine the ability of the fuel container to withstand the various thermal, mechanical, and chemical forces imposed upon the generator by vehicle failures. Where theoretical analysis was impossible and experimental evidence was desired, capsules and generators were tested under simulated missile-failure conditions, Thus, the safety limits of SNAP-III in a satellite application were defined. SNAP-III is designed to be aerothermodynamically consumed on reentry into the earth's atmosphere so that the polonium will be dispersed as aerosols in the upper stratosphere. Since heating rates will be lower for aborts occurring prior to orbiting, 65 abort cases have been considered to define the general consequences of vehicle failures. The spatial and temporal relations of vehicle aborts are summarized in cartographic and tabular form. (auth)},
doi = {10.2172/4110813},
url = {https://www.osti.gov/biblio/4110813},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Wed Jun 01 00:00:00 EDT 1960},
month = {Wed Jun 01 00:00:00 EDT 1960}
}