Status and Limited Life Test Results of the Cylindrical HEMP 3050 Thruster

Kornfeld, Guenter; Harmann, Hans-Peter; Koch, Norbert

doi:10.2514/6.2005-4223

Cited by 16 publications

(14 citation statements)

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“…Engineering models of the HEMP 3050 have reported efficiencies of 45% with thrust and specific impulse values of 50 mN and 3000 s [22] . More provocative is the lifetime estimate, stated to be in excess of 18,000 h based on reported erosion rates that are smaller than those measured in comparable thrusters by a factor larger than 200 [24] .…”

Section: Thruster Designationmentioning

confidence: 97%

Erosion Measurements in a Low-Power Cusped-Field Plasma Thruster

Gildea

Matlock

Martı́nez-Sánchez

et al. 2013

Journal of Propulsion and Power

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Section: Thruster Designationmentioning

confidence: 97%

Erosion Measurements in a Low-Power Cusped-Field Plasma Thruster

Gildea

Matlock

Martı́nez-Sánchez

et al. 2013

Journal of Propulsion and Power

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“…Hall-type thrusters [8][9][10], which utilize a DC electric field to realize both the ionization and acceleration processes, are faced with multiple unpredictable mode transitions [11] due to the strong coupling of the ionization and acceleration regions. As a reference, the ionization and acceleration in the cusped field thruster (CFT) have been widely studied by researchers in multiple countries [12][13][14]. It is generally accepted that the ionization is induced by the electron-neutral collision in the cusped magnetic field, and locates primarily downstream of the cusps [15].…”

Section: Introductionmentioning

confidence: 99%

Study on the ionization and acceleration of a microwave discharge cusped field thruster

Zhang¹,

Liu²,

Huang³

et al. 2023

J. Phys. D: Appl. Phys.

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The microwave discharge cusped field thruster (MD-CFT) is a novel concept electric micro propulsion device, also a candidate thruster for the gravitational detection mission. A coaxial transmission line resonator (CTLR) is utilized to feed the microwave into the thruster to generate Xe plasma steadily with a mass flow rate as low as 0.1sccm. Due to the separation of ionization and acceleration, the thruster performs high operation mode stability over a wide range of voltage in low mass flow conditions. Experimental and simulation methods are carried out to study the ionization and ion acceleration of the thruster. The results show that in operating conditions with a mass flow rate of 0.1sccm, an anode voltage of 0V to 1000V, and a microwave power of 2W, the right-hand circularly polarized wave (R wave) and the ordinary wave (O wave) play the most important role in the ionization process. The ion acceleration region locates around the exit magnetic separatrix, and the acceleration region tends to converge toward the separatrix as the anode voltage increases, resulting in an increased focus of the thruster plume and concentration of the ion energy distribution. Due to the separation of the ionization and acceleration regions, the thruster performs a divergence efficiency of 0.5-0.8, and an acceleration efficiency of 0.9.

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“…1). It will also be the first time that a Highly Efficient Multistage Plasma Thruster (HEMPT) will be employed in space [11,12].…”

Section: Introductionmentioning

confidence: 99%

An in-flight plasma diagnostic package for spacecraft with electric propulsion

et al. 2021

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The plasma diagnostics presented in this article target the plasma surrounding a spacecraft that is created by the electric thruster and its surface modifying effects. The diagnostic package includes a retarding potential analyzer, a plane Langmuir probe, and an erosion sensor. The paper describes the instrument as well as suitable test environments for mimicking the effects expected in space and shows test results. The system is to fly for the first time on the Heinrich Hertz satellite, which is scheduled to be launched in 2023. The spacecraft will be equipped with a pair of Highly Efficient Multistage Plasma Thrusters (HEMPT) and a pair of Hall thrusters for redundancy.

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Status and Limited Life Test Results of the Cylindrical HEMP 3050 Thruster

Cited by 16 publications

References 0 publications

Erosion Measurements in a Low-Power Cusped-Field Plasma Thruster

Erosion Measurements in a Low-Power Cusped-Field Plasma Thruster

Study on the ionization and acceleration of a microwave discharge cusped field thruster

An in-flight plasma diagnostic package for spacecraft with electric propulsion

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