Space environment monitoring suite (SEMS) for near-earth environment characterization during SEP ops

Hassler, Donald M.; Deininger, William D.; Nickles, Neal; Unruh, Bryce

doi:10.1109/aero.2014.6836466

Cited by 3 publications

(2 citation statements)

References 11 publications

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“…Additional enhancement payloads include: a space environments monitoring suite (SEMS) described in a companion paper at this conference [31], low power direct drive demonstration, several solar array string and cell experiments, two small Vis/IR cameras, four NEXT ion system strings (4 + 0) [32] along with additional mission destination options. NEXT strings are considered as an option to flight qualify this technology for future NASA high energy mission needs.…”

Section: Baseline Flight Segment Overviewmentioning

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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Section: Baseline Flight Segment Overviewmentioning

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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“…These options range from the inclusion of additional simple sensors, to experimental hardware enhancements such as a Space Environments Monitoring Suite (SEMS) [6], to operational enhancements up through full-up Autonomous Rendezvous and Docking (AR&D) concepts that include separate host and docking vehicles (beyond our present scope). Per the NASA BAA requirements [4], mission enhancements are constrained to a maximum of an additional $100M.…”

Section: Introductionmentioning

confidence: 99%

A Direct Drive Experiment as Part of a SEP Demonstration

Deininger¹,

Enger²,

Unruh³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The Solar Electric Propulsion (SEP) Technology Demonstration Mission (TDM) is a stepping stone leading to a reusable electric propulsion stage by demonstrating high power (10s kW) transfers from LEO to GEO and back to LEO. A TDM space vehicle is discussed which includes multiple enhancement payloads including a direct drive demonstration experiment. The baseline SEP TDM includes four 5 kW conventional Hall effect thrusters.The direct drive demonstration adds a 300 W direct drive Hall effect thruster system and associated high voltage, solar array strings and distribution to provide the power to the direct drive demonstration system. The complete direct drive demonstration system is based on heritage hardware. The focus is a system-level demonstration of direct drive in the space environment.

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Coherent integration of quasi-random pulse train based on phased array radar

Zhang

Tang

2015

2015 International Conference on Estimation, Detection and Information Fusion (ICEDIF)

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Space environment monitoring suite (SEMS) for near-earth environment characterization during SEP ops

Cited by 3 publications

References 11 publications

Solar electric propulsion demonstration mission 30 kW-class concept description

Solar electric propulsion demonstration mission 30 kW-class concept description

A Direct Drive Experiment as Part of a SEP Demonstration

Coherent integration of quasi-random pulse train based on phased array radar

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