Electromagnetic noise from an ion engine system

Kudo, Isao; Machida, Kazuo; Toda, Yoshitsugu; Murakami, Hiroyuki

doi:10.2514/3.28360

Cited by 8 publications

(4 citation statements)

References 3 publications

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“…A review by Sovey et al [1] describes results of ground-based and flight tests of electromagnetic interference (EMI) in electric propulsion systems that date back to the 1980s. As for ion propulsion systems developed after the SERT-I project, which is considered to be the first ion thruster flight, all of them including the Japanese ETS-III [2,3], ETS-VI [4], German RIT-10 [5], and British T5 [6] have undergone ground-based EMI tests. It is usual practice to follow the U.S. military standard MIL-STD-461 for EMI documentation of components onboard satellites, but such requirements have not been fully satisfied by any electric propulsion systems (whether they be ion thrusters or other type) developed up until now.…”

mentioning

confidence: 99%

Ground Chamber Measurements of the Electromagnetic Emissions from the Hayabusa Ion Engine

Nishiyama

Shimizu

Funaki

et al. 2007

Journal of Propulsion and Power

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Radiated electric field emissions from the prototype model of the ion engine system of the asteroid explorer Hayabusa (MUSES-C) were measured in approximate accordance to MIL-STD-461C. The typical noise level exceeded the narrowband specification at frequencies less than 5 MHz. The microwave discharge neutralizer generates broadband noise and narrowband oscillations that have a fundamental frequency of about 160 kHz and are accompanied by its harmonics up to the fifth. Leakage of 4.25 GHz microwaves for plasma production and its second harmonic were 65 dB and 35 dB above specifications, respectively. The X-band receiver onboard Hayabusa measured the noise from the ion engine system at the uplink frequency of 7.16 GHz through a horn antenna. This susceptibility test showed that the microwave discharge ion thruster is unlikely to interfere with deep space microwave communication.Nomenclature d = neutralizer orifice diameter I D = electron emission current of the neutralizer l = anode distance from the neutralizer _ m = xenon flow rate P = microwave power for plasma discharge of the neutralizer V D = voltage between the neutralizer and the anode in diode mode operation

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mentioning

confidence: 99%

Ground Chamber Measurements of the Electromagnetic Emissions from the Hayabusa Ion Engine

Nishiyama

Shimizu

Funaki

et al. 2007

Journal of Propulsion and Power

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“…11,30,31,45,46,53). The MPD arcjet aboard this flight was coupled to a 240 V capacitor bank and produced a current pulse of about 8 kA for 1 ms. Arcjet peak power was about 2 MW during the 1 ms pulse.…”

Section: Hall Current and Mpd Thrustersmentioning

confidence: 99%

“…During actual flight test operations, there was no indicated increase in the AGC level of vhf signals, implying compatibility of the ion thruster with vhf communications. 53 One of the thrusters had operated at least 27 h with 13 restarts, whereas a second thruster operated at least 182h and was restarted 111 times. All spacecraft operations and parameters were reported to be within allowable ranges during ion thruster operation, implying EM compatibility with ETS-III subsystems including power, telemetry, tracking, command, attitude control, and thermal control.…”

Section: Ion Propulsionmentioning

confidence: 99%

Electromagnetic emission experiences using electric propulsion systems

Sovey

Carney

Knowles³

1989

Journal of Propulsion and Power

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“…Signals with wavelengths comparable to the size of the discharge chamber will be stimulated. Kudo et al [1983] report observations of discharge noise characteristics in the laboratory for a 5-cm thruster (apparently using Mercury ions). They indicate a variety of coherent peaks, depending on operating mode, at least some of which are interpreted as two-stream instability generated ion-acoustic waves.…”

Section: Problem Of Satellite Chargingmentioning

confidence: 99%

Plasma wave observations during Ion Gun Experiments

Olsen¹,

Weddle²,

Roeder³

1990

J. Geophys. Res.

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Experiments in charge control on the AF/NASA P78‐2 (SCATHA) satellite were conducted with a plasma/ion source in the inner magnetosphere. These experiments were monitored with plasma wave instruments capable of high temporal and frequency resolution in the 0–6 kHz frequency range. Ion gun experiments revealed two distinct classes of behavior. Nonneutralized ion beam operation at 1 mA, 1 kV resulted in arcing signatures (spiky in time, broad frequency range), coincident with induced satellite potentials of −600 to −900 V. This signature disappeared when the accelerating voltage was switched off or the beam was neutralized (at which time the satellite body approached potentials of a few volts). The signal is attributed to arcing between differentially charged surfaces. An additional feature was noted in the 100‐kHz channel of the wave receiver. During emission of dense, low‐energy plasma, a signal is generated which may be at the upper hybrid, or plasma frequency for the local plasma.

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Electromagnetic noise from an ion engine system

Cited by 8 publications

References 3 publications

Ground Chamber Measurements of the Electromagnetic Emissions from the Hayabusa Ion Engine

Ground Chamber Measurements of the Electromagnetic Emissions from the Hayabusa Ion Engine

Electromagnetic emission experiences using electric propulsion systems

Plasma wave observations during Ion Gun Experiments

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