The suitability of the baseline 30 cm thruster for future space missions was examined. Preliminary design concepts for several advanced thrusters were developed to assess the potential practical difficulties of a new design. Useful methodologies were produced for assessing both planetary and earth orbit missions. Payload performance as a function of propulsion system technology level and cost sensitivity to propulsion system technology level are among the topics assessed. A 50 cm diameter thruster designed to operate with a beam voltage of about 2400 V is suggested to satisfy most of the requirements of future space missions.
Advanced Electrostatic Ion Thruster for Space Propulsion
1978
400 pages
Report
Keine Angabe
Englisch
Electric & Ion Propulsion , Unmanned Spacecraft , Engine design , Ion propulsion , Rocket engines , Space missions , Cost analysis , Mission planning , Payloads , Performance prediction , Propulsion system configurations , Propulsion system performance , Satellite solar power stations , Space transportation system
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