NDLI: Solar electric propulsion demonstration mission 30 kW-class concept description

Content Provider	IEEE Xplore Digital Library
Author	Deininger, W.D. Enger, S. Hackel, J. Soto, J.C. Unruh, B. Murphy, D.M. DeGrys, K.
Copyright Year	2014
Description	Author affiliation: ATK Aerosp. Syst., Goleta, CA, USA (Murphy, D.M.) \|\| Ball Aerosp. & Technol. Corp., Boulder, CO, USA (Deininger, W.D.; Enger, S.; Hackel, J.; Soto, J.C.; Unruh, B.) \|\| Aerojet Rocketdyne, Redmond, WA, USA (DeGrys, K.)
Abstract	A 30 kW solar electric propulsion (SEP) technology demonstration mission (TDM) concept is described. The mission concept is formulated in response to NASA's BAA and demonstrates a modular and extensible solar electric propulsion system. It launches in early 2018 and flies multiple LEO-GEO transits over the 1-2 year-long operations period. The 30 kW SEP TDM Space Vehicle (SV) is based on integrated SEP and Bus Modules allowing parallel development and efficient integration. The SEP Module includes three 12 kW Hall thruster strings (3 + 0) which can be operated singly, in pairs or simultaneously for full power operations of all 3 together. Advanced, light-weight, blanket solar array technology is employed for the SEP TDM instead of typically used, rigid panel technology. MegaFlex technology, using two 10 m-diameter wings, is baselined. The power and propulsion systems are at sufficient specific power to demonstrate the movement of large payloads from LEO to higher energy orbits at performance values consistent with future higher power electric propulsion capabilities (Isp, thrust-to-power, power-to-mass). The SEP TDM, and its SEP Module concept, represents a key infusion point to a reusable electric propulsion stage by demonstrating transfers from LEO to GEO and back to LEO. This set of high ΔV trajectories demonstrates long-term SEP operations and flies the SEP TDM Space Vehicle through the radiation belts, sustained plasma environments, diverse distributed inertia spacecraft control environments and repeated spacecraft occultations. The space vehicle hosts several secondary payloads to enhance science and technology return from the mission.
Sponsorship	IEEE Aerosp. Electron. Syst. Soc.
Starting Page	1
Ending Page	8
File Size	1303169
Page Count	8
File Format	PDF
e-ISBN	9781479916221
DOI	10.1109/AERO.2014.6836468
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2014-03-01
Publisher Place	USA
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Space vehicles Time division multiplexing Propulsion Low earth orbit satellites Orbits Arrays
Content Type	Text
Resource Type	Article

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1	Ministry of Education (GoI), Department of Higher Education	Sanctioning Authority	https://www.education.gov.in/ict-initiatives
2	Indian Institute of Technology Kharagpur	Host Institute of the Project: The host institute of the project is responsible for providing infrastructure support and hosting the project	https://www.iitkgp.ac.in
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