Characteristics of primary electric propulsion systems

Byers, D. C.

doi:10.2514/6.1979-2041

Cited by 5 publications

(2 citation statements)

References 15 publications

(1 reference statement)

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“…A NASA/Hughes NSTAR xenon electrostatic propulsion unit masses ~17 kg and the power conditioning and control electronics (PCCE) 24,25,26,27 masses about 30 kg. An operating thruster exclusively uses one PCCE, but a network topology of redundant, cross-switchable PCCEs serving more than one thruster serially in time avoids separate PCCEs for every thruster placed on board.…”

Section: Propulsion System Massmentioning

confidence: 99%

UMBRAS - Design of a free-flying occulter for space telescopes

Jordan¹,

Schultzt²,

Hart³

et al. 2000

Space 2000 Conference and Exposition

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Section: Propulsion System Massmentioning

confidence: 99%

UMBRAS - Design of a free-flying occulter for space telescopes

Jordan¹,

Schultzt²,

Hart³

et al. 2000

Space 2000 Conference and Exposition

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“…(1) A number of pertormance-related investigations have dealt with coniponent and d ► schary optimization of thrusters employing divergent ( ^ and multipole (3,4,5,6) magnetic field discharge chambers. Tne multipole magnetic confinement schemes generally tend to improve primary electron contineiient, increase plasma density and uniformity, and increase inert gas propel- Basic optimization of the thruster discharge chamber was performed without ion extraction by the use of plasma probes to measure ion density.…”

Section: Introductionmentioning

confidence: 99%

Performance of a magnetic multipole line-cusp argon ion thruster

Sovey

1981

15th International Electric Propulsion

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A 17-cm diameter line-cusp ion thruster was evaluated with inert gases which arc candidate propellants for on-orbit and orbit transfer propulsion functions for Large Space Systems. A semi-empirical relationshio was generated to predict thruster beam current in terms of plasma parameters which would allow initial thruster optimization without ion extraction and the associated large vacuum facilities. The sensitivity of performance to changes in discharge electrode configurations and magnetic circuit was evaluated and is presented. After final optimization a propellant utilization efficiency of 0.9 at a discharge chamber power expenditure of about 260 w per beam ampere was obt;,ined. These performance parameters are the highest yet achieved with argon propellant.

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Characterization of advanced electric propulsion systems

Ray

1983

Journal of Spacecraft and Rockets

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Characteristics of several advanced electric propulsion systems are evaluated and compared. The propulsion systems studied are mass driver, rail gun, MPD thruster, hydrogen free radical thruster and mercury electron bombardment ion engine. These are characterized by specific impulse, overall effiCiency, input power, average thrust, power to average thrust ratio and average thrust to dry weight ratio. Several important physical characteristics such as dry system mass, accelerator length, bore size and current pulse requirement are also evaluated in appropriate cases. Only the ion engine can operate at a specific impulse beyond 2000 sec. Rail gun, MPO thruster and free radical thru.ster are currently characterized by low efficiencies. Mass drivers have the best performance character1st1cs in terms of overall efficiency, power to average thrust ratio and average thrust to dry weight ratio. But, they can only operate at low specific impulses due to large power requirements and are extremely long due·to limitations of dri vi ng current. Mercury ion engines have the next best performance characteristics while operating at higher specific impulses. It is concluded that, overall, ion engines have somewhat better characteristics as compared to the other electric propulsion systems.17.

show abstract

Characteristics of primary electric propulsion systems

Cited by 5 publications

References 15 publications

UMBRAS - Design of a free-flying occulter for space telescopes

UMBRAS - Design of a free-flying occulter for space telescopes

Performance of a magnetic multipole line-cusp argon ion thruster

Characterization of advanced electric propulsion systems

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