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Comparison of Optimal Small Spacecraft Micro Electric Propulsion Technologies for Mission OpportunitiesThe goal of this paper is to explore the mission opportunities that are uniquely enabled by U-class Solar Electric Propulsion (SEP) technologies. Small SEP thrusters offers significant advantages relative to existing technologies and will revolutionize the class of mission architectures that small spacecraft can accomplish by enabling trajectory maneuvers with significant change in velocity requirements and reaction wheel-free attitude control. This paper aims to develop and apply a common system-level modeling framework to evaluate these thrusters for relevant upcoming mission scenarios, taking into account the mass, power, volume, and operational constraints of small highly-constrained missions. We will identify the optimal technology for broad classes of mission applications for different U-class spacecraft sizes and provide insights into what constrains the system performance to identify technology areas where improvements are needed.
Document ID
20170008199
Acquisition Source
Jet Propulsion Laboratory
Document Type
Conference Paper
External Source(s)
Authors
Spangelo, Sara
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
September 1, 2017
Publication Date
August 8, 2015
Subject Category
Spacecraft Design, Testing And Performance
Spacecraft Propulsion And Power
Report/Patent Number
SSC15-IV-6
Meeting Information
Meeting: Annual AIAA/USU Conference on Small Satellites 2017
Location: Logan, UT
Country: United States
Start Date: August 8, 2015
End Date: August 13, 2015
Sponsors: American Inst. of Aeronautics and Astronautics, Utah State Univ.
Distribution Limits
Public
Copyright
Other

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