The Iodine Satellite (iSat) Project Development through Critical Design Review (CDR)

Dankanich, John; Calvert, Derek; Kamhawi, Hani; Hickman, Tyler A.; Szabo, James; Byrne, Lawrence

doi:10.2514/6.2016-4540

Cited by 9 publications

(3 citation statements)

References 4 publications

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“…In related work, an iodine compatible version of the BHT-200 is being developed for NASA's iodine satellite (iSat) technology demonstration mission. 23,24,25 The top-level objectives of the project are focused on validating the use of iodine for future missions while demonstrating high ∆V viability on a secondary small spacecraft. The system is scheduled for launch readiness in 2017.…”

Section: B Iodine Compatible Thruster Systemmentioning

confidence: 99%

High Throughput 600 Watt Hall Effect Thruster for Space Exploration

Szabo

Pote²,

Tedrake³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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Section: B Iodine Compatible Thruster Systemmentioning

confidence: 99%

High Throughput 600 Watt Hall Effect Thruster for Space Exploration

Szabo

Pote²,

Tedrake³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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“…Busek Co. Inc. developed a high throughput, low power Hall thruster BHT-100 incorporating magnetic shielding structure to relieve or eliminate erosion and experimented with iodine and xenon as propellants, respectively. The results showed both had similar efficiency [15]. To reduce the complexity of the iodine Hall thruster, the NASA Marshall Space Flight Center (MSFC) used iodine propellant for the thruster and xenon propellant for the cathode [16].…”

Section: Introductionmentioning

confidence: 99%

Performance investigation of a low-power Hall thruster fed on iodine propellant

XU 徐,

WANG 王,

CAI 蔡

et al. 2024

Plasma Sci. Technol.

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The common propellants used for electric thrusters, such as xenon and krypton, are rare, expensive, and difficult to acquire. Solid iodine attracts much attention with the advantages of low cost, extensive availability, low vapor pressure, and ionization potential. The performance of a low-power iodine-fed Hall thruster matched with a xenon-fed cathode is investigated across a broad range of operation conditions. Regulation of the iodine vapor’s mass flow rates is stably achieved by using a temperature control method of the iodine reservoir. The thrust measurements are finished utilizing a thrust target during the tests. Results show that thrust and anode-specific impulse increase approximately linearly with the increasing iodine mass flow rate. At the nominal power of 200 W class, iodine mass flow rates are 0.62 and 0.93 mg/s, thrusts are 7.19 and 7.58 mN, anode specific impulses are 1184 and 826 s, anode efficiencies are 20.8% and 14.5%, and thrust to power ratios are 35.9 and 37.9 mN/kW under the conditions of 250 V 0.8 A and 200 V 1.0 A, respectively. The operating characteristics of iodine-fed Hall thruster are analyzed in different states. Further work on the measurements of plasma characteristics and experimental optimization will be carried out.

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“…NASA's Space Technology Mission Directorate (STMD), under the Small Spacecraft Technology Program (SSTP), approved the iSAT flight project for a rapid demonstration of iodine Hall thruster technology in a 12U configuration. 7,8 The mission is a partnership between NASA Marshall Space Flight Center (MSFC), NASA GRC, and Busek Co. Inc., with the U.S. Air Force supporting the propulsion technology maturation. The iSat mission will utilize a 200 W iodine Hall thruster propulsion system to demonstrate small spacecraft maneuverability and mitigate concerns regarding iodine deposition regardless of spacecraft size.…”

Section: Introductionmentioning

confidence: 99%

Overview of Iodine Propellant Hall Thruster Development Activities at NASA Glenn Research Center

Kamhawi

Haag²,

Benavides³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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NASA is continuing to invest in advancingHall thruster technologies for implementation in commercial and government missions. There have been several recent iodine Hall propulsion system development activities performed by the team of the NASA Glenn Research Center, the NASA Marshall Space Flight Center, and Busek Co. Inc. In particular, the work focused on qualification of the 200 W Busek BHT-200-I and the continued development of the 600 W BHT-600-I Hall thruster propulsion systems. This paper presents an overview of these development activities and also reports on the results of short duration tests that were performed on the engineering model BHT-200-I and the development model BHT-600-I Hall thrusters.

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The Iodine Satellite (iSat) Project Development through Critical Design Review (CDR)

Cited by 9 publications

References 4 publications

High Throughput 600 Watt Hall Effect Thruster for Space Exploration

High Throughput 600 Watt Hall Effect Thruster for Space Exploration

Performance investigation of a low-power Hall thruster fed on iodine propellant

Overview of Iodine Propellant Hall Thruster Development Activities at NASA Glenn Research Center

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