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.
Task 1, Design Analysis Report: Pulsed plasma solid propellant microthruster for the synchronous meteorological satellite
01.12.1971
Report
Keine Angabe
Englisch
Solid-propellant pulsed plasma microthruster studies.
AIAA | 1968
|Solid-propellant pulsed plasma microthruster studies
AIAA | 1968
|