NASA NTRS · 19720011126
Task 1, Design Analysis Report: Pulsed plasma solid propellant microthruster for the synchronous meteorological satellite
Abstract
Thermal vacuum design supporting thruster tests indicate no problems under the worst case conditions of sink temperature and spin rate. The reliability of the system was calculated to be 0.92 for a five-year mission. Minus the main energy storage capacitor it is 0.98.
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Guman, W. J.. 1971-12-01. Task 1, Design Analysis Report: Pulsed plasma solid propellant microthruster for the synchronous meteorological satellite. https://ntrs.nasa.gov/citations/19720011126
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