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Analysis of Near Rectilinear Halo Orbit Insertion with a 40-kW Solar Electric Propulsion SystemThis paper examines low thrust trajectories for delivery of a 40-kW solar electric propulsion spacecraft and potential additional payload to a desired NRHO. One option considered is a trans-lunar injection launch as a co-manifested payload on the Space Launch System. For this option, a reference trajectory is designed and a scan of launch dates is completed to understand the propellant mass sensitivity. A 15-day period cyclical variation in required propellant is observed that is attributed to solar gravity effects. A second option considered is to launch on a smaller commercial launch vehicle to a less energetic elliptical orbit and use SEP to spiral out to NRHO. For this option, analysis is completed to understand the trades between delivered mass to NRHO, total propellant required, time of flight, and solar array degradation. Results show that, while launching to lower altitudes can deliver greater payload mass to NRHO, significant solar array degradation can be observed.
Document ID
Acquisition Source
Glenn Research Center
Document Type
Mccarty, Steven L.
(NASA Glenn Research Center Cleveland, OH, United States)
Sjauw, Waldy K.
(NASA Glenn Research Center Cleveland, OH, United States)
Burke, Laura M.
(NASA Glenn Research Center Cleveland, OH, United States)
McGuire, Melissa L.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
February 9, 2019
Publication Date
August 19, 2018
Subject Category
Report/Patent Number
Meeting Information
Meeting: AAS/AIAA Astrodynamics Specialist Conference
Location: Snowbird, UT
Country: United States
Start Date: August 19, 2018
End Date: August 23, 2018
Sponsors: American Astronautical Society
Funding Number(s)
WBS: WBS 837933.02.12.03
Distribution Limits
Work of the US Gov. Public Use Permitted.
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