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A common solar electric upper stage for multi-mission applications.The concept of using a solar-electric upper stage for multi-mission application is practical, economical, and versatile approach to space expMission capabilities include a Mercury orbiter, asteroid and comet rendezvous, a solar probe, and extra-ecliptic probe, and outer planet flybys and orbiters. The 17.5-kw vehicle has an injected mass of 1500 to 2500 kg and carries up to 500 kg of attached or separable payload packages. Mission characteristics, performance tradeoffs and a concepegn configuration are presented, and program plans, cost estimates and advanced technology requirements are identified.
Document ID
19720042533
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Meissinger, H. F.
Goldin, D. S. (TRW Systems Group Redondo Beach, Calif., United States)
Mascy, A. C. (NASA Office of Advanced Research and Technology, Advanced Concepts and Missions Div., Moffett Field Calif., United States)
Date Acquired
August 6, 2013
Publication Date
April 1, 1972
Subject Category
Propulsion Systems
Report/Patent Number
AIAA PAPER 72-464
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Electric Propulsion Conference
Location: Bethesda, MD
Start Date: April 17, 1972
End Date: April 19, 1972
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
72A26199
Funding Number(s)
CONTRACT_GRANT: NAS2-6040
Distribution Limits
Public
Copyright
Other

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