Problems of Designing EPS's with SPT's Working on Krypton-Xenon Mixture

Arkhipov, B. A.; Khoromsky, I.; Murashko, V.

doi:10.2514/6.2002-3682

38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit 2002

DOI: 10.2514/6.2002-3682

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Problems of Designing EPS's with SPT's Working on Krypton-Xenon Mixture

B. A. Arkhipov¹,

I. Khoromsky²,

V. Murashko³

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“…3,4,5 However, for a 50 kW HET similar thrust efficiency was attained with krypton propellant. 6 Russian studies 4,7,8 have investigated using a mixture of krypton and xenon propellant for SPT thrusters to achieve a performance compromise at a cost cheaper than either pure xenon or pure krypton. This mixture of xenon and krypton is a byproduct of liquid oxygen manufacturing and costs 15 times less than pure xenon and 2-3 times less than pure krypton.…”

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confidence: 99%

A Performance and Plume Comparison of Xenon and Krypton Propellant on the SPT-100

Nakles¹,

Hargus²,

Delgado³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The use of krypton as an alternative to xenon for Hall thruster propellant is an interesting option for satellite system designers due to its lower cost. However, this cost-savings comes at the expense of thrust efficiency. Reduction in efficiency can be caused by energy losses from Joule heating, radiation, and the ionization process as well as degradation of plume quality from an increase in velocity distribution spread (most often from an increase in multiply charged ion populations) and geometric beam divergence. 1 In order to quantify this performance reduction for the case of the flight model SPT-100 HET (1.35 kW), performance measurements were made using an inverted pendulum thrust stand. The plume was also characterized by a Faraday probe and RPA measurements to examine how plume qualities change with operating condition. Krypton operating conditions were tested over a large range of operating powers from 800 W to 3.9 kW. Analysis of how performance is impacted by propellant and operating condition is presented. A simple mission analysis was done based on the performance measurements to evaluate the practicality of krypton propellant for an SPT-100 subsystem using krypton propellant for north-south station keeping (NSSK) for a typical communications spacecraft in geosynchronous orbit.Nomenclature e elementary charge g e gravitational constant I axial axial component of integrated thruster beam current I b integrated thruster beam current I d anode discharge current I sp specific impulse j plume charge flux m atomic masṡ m a anode propellant mass flow ratė m i anode ion mass flow rate M 0 initial spacecraft mass M P propellant mass for a spacecraft P anode power * Research Engineer, AFRL/RZSS, q multiple for units of elementary charge r radial distance in thruster coordinate system V ion acceleration voltage V mean ion acceleration voltage from a distribution function V d anode discharge voltage V 0 ion retarding grid potential for retarding potential analyzer Γ current collected by retarding potential analyzer ∆V average ion acceleration voltage for the thruster plume or velocity change for a spacecraft η a anode efficiency θ angular position in thruster coordinate system or thruster cant angle λ plume momentum divergence half-angle, λ = arccos(< cos(θ) > mv ) ≈ arccos(< cos(θ) > j ) Φ P propellant utilization efficiency Ψ B beam efficiency (divergence loss factor) <> j charge flux weighted average quantity in the plume <> m mass weighted average quantity in the plume <>mv momentum weighted average quantity in the plume Introduction F or a number of engineering reasons, xenon is the propellant of choice for Hall effect thrusters. These include its high mass (131 amu) and its relatively low ionization potential (12.1 eV). Furthermore, the inert nature of xenon eliminates the safety concerns that plagued early electrostatic propulsion efforts when mercury and cesium were the propellants of choice. Although xenon is a noble gas, it is the most massive, and due to its non-ideal gas behavior, it is possible to...

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mentioning

confidence: 99%

A Performance and Plume Comparison of Xenon and Krypton Propellant on the SPT-100

Nakles¹,

Hargus²,

Delgado³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

show abstract

“…Russian studies 4,7,8 have investigated using a mixture of krypton and xenon propellant for SPT thrusters to achieve a performance compromise at a cost cheaper than either pure xenon or pure krypton. This mixture of xenon and krypton is a byproduct of liquid oxygen manufacturing and costs 15 times less than pure xenon and 2-3 times less than pure krypton.…”

mentioning

confidence: 99%

A Performance Comparison of Xenon and Krypton Propellant on an SPT-100 Hall Thruster (Preprint)

Nakles¹,

Hargus²,

Delgado³

et al. 2011

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)10-08-2011 REPORT TYPE Conference Paper DATES COVERED (From -To) TITLE AND SUBTITLE 5a. CONTRACT NUMBER A Performance Comparison of Xenon and Krypton Propellant on an SPT-100 Hall SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force Research Laboratory (AFMC) AFRL/RZS SPONSOR/MONITOR'S Pollux Drive NUMBER(S)Edwards AFB CA 93524-7048 AFRL-RZ-ED-TP-2011-342 DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution unlimited (PA #11558). SUPPLEMENTARY NOTESFor presentation at the 32 nd International Electric Propulsion Conference, Wiesbaden, Germany, 11-15 Sep 2011. ABSTRACTThe use of krypton as an alternative to xenon for Hall thruster propellant is an interesting option for satellite system designers due to its lower cost. However, this cost-savings comes at the expense of thrust efficiency. Reduction in efficiency can be caused by energy losses from Joule heating, radiation, and the ionization process as well as degradation of plume quality from an increase in velocity distribution spread (most often from an increase in multiply charged ion populations) and geometric beam divergence.1 In order to quantify this performance reduction for the case of the flight model SPT-100 HET (1.35 kW), an ongoing series of experimental measurements is being conducted to measure how various thruster efficiency terms change with propellant and operating condition. This study will combine thrust measurements with plume data from electrostatic probes. This paper presents the results of performance measurements made using an inverted pendulum thrust stand. Krypton operating conditions were tested over a large range of operating powers from 800 W to 3.9 kW. Analysis of how performance is impacted by propellant and operating condition is presented. A simple mission analysis was done based on these measurements to evaluate the practicality of krypton propellant for an SPT-100 subsystem using krypton propellant for north-south station keeping (NSSK) for a typical communications spacecraft in geosynchronous orbit.. SUBJECT TERMS

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Problems of Designing EPS's with SPT's Working on Krypton-Xenon Mixture

Cited by 2 publications

References 0 publications

A Performance and Plume Comparison of Xenon and Krypton Propellant on the SPT-100

A Performance and Plume Comparison of Xenon and Krypton Propellant on the SPT-100

A Performance Comparison of Xenon and Krypton Propellant on an SPT-100 Hall Thruster (Preprint)

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