Mission and System Advantages of Iodine Hall Thrusters

Dankanich, John; Szabo, James; Pote, Bruce; Oleson, Steven R.; Kamhawi, Hani

doi:10.2514/6.2014-3905

Cited by 21 publications

(12 citation statements)

References 12 publications

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“…Large thrusters like the BHT-8000 can be clustered to 100 kW and above for large orbital tugs, planetary exploration, and asteroid retrieval [34]. Additional mission concepts are described in [35].…”

Section: A Mission Applicationsmentioning

confidence: 99%

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Iodine Plasma Propulsion Test Results at 1–10 kW

Szabo

Robin

Paintal

et al. 2015

IEEE Trans. Plasma Sci.

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The near-term potential for iodine propellant in Hall thrusters is explored. The merits of iodine with respect to other propellants are presented. Recent performance measurements are summarized, and new measurements taken with an 8 kW thruster are presented. Thruster discharge power exceeded 10 kW, and peak measured anode efficiency exceeded 65%. Spacecraft interactions issues are also addressed and relevant data taken with a 1 kW thruster are presented. Plume data showed lower divergence with iodine than with xenon, and that a plume shield could effectively attenuate the far field plume. Material samples placed in the plume showed a strong reaction with iron, but little reaction with typical spacecraft materials. System level benefits, including low storage pressure and extremely high density, are also discussed. All results so far indicate iodine is a viable propellant for electric rockets, and for some missions is superior to xenon.

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Section: A Mission Applicationsmentioning

confidence: 99%

“…The system may also include a heater control module for the IFS and propellant reservoir. Multiple systems are described in [35].…”

Section: B Flight Systemsmentioning

confidence: 99%

Iodine Plasma Propulsion Test Results at 1–10 kW

Szabo

Robin

Paintal

et al. 2015

IEEE Trans. Plasma Sci.

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“…4 In addition to iodine based missions for commercial, military, human and scientific exploration, multiple concepts have been developed for a low-cost high value technology demonstration mission. In general, flight demonstrations would not typically be expected for new Hall thruster developments.…”

Section: Mission Concept Developmentmentioning

confidence: 99%

Iodine Hall Thruster Demonstration Mission Concept and Development

Dankanich¹,

Polzin²,

Kamhawi³

2014

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

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The use of iodine propellant for Hall thrusters has been studied and proposed by multiple organizations due to the potential mission benefits over xenon. In 2013, NASA Marshall Space Flight Center competitively selected a project for the maturation of an iodine flight operational feed system through the Technology Investment Program. Multiple partnerships and collaborations have allowed the team to expand the scope to include additional mission concept development and risk reduction to support a flight system demonstration, the iodine Satellite (iSAT). The iSAT project was initiated and is progressing towards a technology demonstration mission preliminary design review. The current status of the mission concept development and risk reduction efforts in support of this project is presented.

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“…Featuring a 200W thruster, this mission will demonstrate relatively high power propulsion in a Cubesat envelope. This program includes testing of a higher power BHT-600 iodine thruster, and in space validation of the iodine Hall thruster technology is seen a precursor for Nano-and Small satellite missions with high ∆v capabiliy, enabling future Near Earth Asteroid Orbiter and Lunar Orbiter missions [76].…”

Section: B Small Satellite Case Ep: Hall Thrustermentioning

confidence: 99%

Space Propulsion Technology for Small Spacecraft

2018

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Abstract-As small satellites become more popular and capable, strategies to provide in-space propulsion increase in importance. Applications range from orbital changes and maintenance, attitude control and desaturation of reaction wheels to drag compensation and de-orbit at spacecraft end-of-life. Space propulsion can be enabled by chemical or electric means, each having different performance and scalability properties. The purpose of this review is to describe the working principles of space propulsion technologies proposed so far for small spacecraft. Given the size, mass, power and operational constraints of small satellites, not all types of propulsion can be used and very few have seen actual implementation in space. Emphasis is given in those strategies that have the potential of miniaturization to be used in all classes of vehicles, down to the popular 1-liter, 1 kg CubeSats and smaller.

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Mission and System Advantages of Iodine Hall Thrusters

Cited by 21 publications

References 12 publications

Iodine Plasma Propulsion Test Results at 1–10 kW

Iodine Plasma Propulsion Test Results at 1–10 kW

Iodine Hall Thruster Demonstration Mission Concept and Development

Space Propulsion Technology for Small Spacecraft

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