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Round-Trip Solar Electric Propulsion Missions for Mars Sample ReturnMars Sample Return (MSR) missions could benefit from the high specific impulse of Solar Electric Propulsion (SEP) to achieve lower launch masses than with chemical propulsion. SEP presents formulation challenges due to the coupled nature of launch vehicle performance, propulsion system, power system, and mission timeline. This paper describes a SEP orbiter-sizing tool, which models spacecraft mass & timeline in conjunction with low thrust round-trip Earth-Mars trajectories, and presents selected concept designs. A variety of system designs are possible for SEP MSR orbiters, with large dry mass allocations, similar round-trip durations to chemical orbiters, and reduced design variability between opportunities.
Document ID
20160008159
Acquisition Source
Jet Propulsion Laboratory
Document Type
Preprint (Draft being sent to journal)
External Source(s)
Authors
Bailey, Zachary J.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Sturm, Erick J.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Kowalkowski, Theresa D.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Lock, Robert E.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Woolley, Ryan C.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Nicholas, Austin K.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
July 1, 2016
Publication Date
January 26, 2014
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AAS Paper 14-365
Meeting Information
Meeting: AAS/AIAA Space Flight Mechanics Meeting
Location: Sante Fe, New Mexico
Country: United States
Start Date: January 26, 2014
End Date: January 30, 2014
Sponsors: American Astronautical Society, American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Other
Keywords
Solar Electric Propulsion
MSR
Mars Sample Return
SEP
Orbiter

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