Human Mars transportation applications using solar electric propulsion

Donahue, Benjamin; Martin, Jim; Potter, Seth; Henley, Mark; Carrington, Connie

doi:10.2514/6.2000-5360

Cited by 4 publications

(1 citation statement)

References 2 publications

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“…Cargo transport to support human exploration beyond LEO is one key application. Potential missions to the moon [9,10], near-Earth objects [11][12][13][14], LaGrange points [15], and Mars [16][17][18][19][20][21][22][23][24] all have variations that leverage high power SEP systems.…”

Section: Introductionmentioning

confidence: 99%

Solar electric propulsion demonstration mission 30 kW-class concept description

Deininger¹,

Enger²,

Hackel³

et al. 2014

2014 IEEE Aerospace Conference

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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 mdiameter 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-tomass). 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.

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