2014 IEEE Aerospace Conference 2014
DOI: 10.1109/aero.2014.6836468
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Solar electric propulsion demonstration mission 30 kW-class concept description

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 H… Show more

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Cited by 4 publications
(5 citation statements)
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“…[1,2] All non-payload subsystems have direct flight heritage and large performance margins to reduce risk, given risk posture of this To fully understand the system impacts of electric propulsion operations in space, it is extremely important to characterize the environment around the SV to understand how the propulsion system may perturb measurements of the ambient plasma, ion and interplanetary magnetic field [5][6][7]. One straight-forward prospect for a mission enhancement to the SEP TDM Baseline Mission includes flying a Space Environments Monitoring Suite (SEMS).…”
Section: Introductionmentioning
confidence: 97%
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“…[1,2] All non-payload subsystems have direct flight heritage and large performance margins to reduce risk, given risk posture of this To fully understand the system impacts of electric propulsion operations in space, it is extremely important to characterize the environment around the SV to understand how the propulsion system may perturb measurements of the ambient plasma, ion and interplanetary magnetic field [5][6][7]. One straight-forward prospect for a mission enhancement to the SEP TDM Baseline Mission includes flying a Space Environments Monitoring Suite (SEMS).…”
Section: Introductionmentioning
confidence: 97%
“…To this end, this paper describes a set of three space environment monitoring instruments (SEMS) to fully characterize the local environment around the SV. Figure. 2 presents a mission profile while illustrating the environmental and operational challenges [4]. The SEP TDM objective is to reliably and repeatedly demonstrate SEP operation in geocentric space while flying high energy trajectories through the radiation/plasma belts.…”
Section: Introductionmentioning
confidence: 99%
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“…The SEP TDM SV architecture is a modular, single string design with use of selective redundancy at critical points to prevent credible single-point failures. [1][2][3] All non-payload subsystems have direct flight heritage and large performance margins to reduce risk, given risk posture of this Category 3, Class D mission. To reduce cost, Space Vehicle hardware is flight-ready through protoflight testing in flight-like environments or flight-qualified at the component level.…”
Section: Introductionmentioning
confidence: 99%
“…A near-term flight demonstration mission validates SEP for near-term applications and firmly establishes the 'capability.' The SEP Technology Demonstration Mission (TDM) SV [1][2][3] concept was developed for NASA in response to their BAA [4]. The SEP TDM Space Vehicle (SV) operates in geocentric (near-Earth) space starting at an altitude of 400 km, a likely orbit for a staging location or departure orbit for a SEP tug, and transits through the radiation and plasma belts out to GEO then returns to LEO [5].…”
Section: Introductionmentioning
confidence: 99%