Ion propulsion modules employing 8-cm thrusters and 30-cm thrusters were studied for Multimission Modular Spacecraft (MMS) applications. Recurring and nonrecurring cost elements were generated for these modules. As a result, ion propulsion cost drivers were identified to be Shuttle charges, solar array, power processing, and thruster costs. Cost effective design approaches included short length module configurations, array power sharing, operation at reduced thruster input power, simplified power processing units, and power processor output switching. The MMS mission model employed indicated that nonrecurring costs have to be shared with other programs unless the mission model grows. Extended performance missions exhibited the greatest benefits when compared with monopropellant hydrazine propulsion.
Ion propulsion cost effectivity
1978-12-01
Report
No indication
English
Ion propulsion cost effectivity
AIAA | 1979
|Ion propulsion cost effectivity
Tema Archive | 1979
|Ion Propulsion Cost Effectivity
NTIS | 1978
|Ion propulsion cost effectivity
NTRS | 1979
|Effectivity of Spacecraft Shield Protection
British Library Online Contents | 1996
|