Colloid and pulsed plasma thrusters for spacecraft propulsion

Rosen, S.

doi:10.2514/6.1973-1254

9th Propulsion Conference 1973

DOI: 10.2514/6.1973-1254

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Colloid and pulsed plasma thrusters for spacecraft propulsion

S. Rosen

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Cited by 4 publications

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Small satellites and electric propulsion - a review

Lorenz

1991

Aeronaut. j.

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In recent years, interest has grown in the use of small satellites for a variety of applications. In certain missions, where propulsion systems are necessary, electric propulsion technology can offer advantages. Small satellite technology and applications are reviewed and some of the features of various types of electric propulsion are discussed: missions where small satellites might use electric propulsion are described.

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Small satellites and electric propulsion - a review

Lorenz

1991

Aeronaut. j.

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Survey of Electric Propulsion Capability

Clark

1975

Journal of Spacecraft and Rockets

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Solid Propellant Pulsed Plasma Propulsion System Design

Guman

1976

Journal of Spacecraft and Rockets

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Fundamental definitions, a few semiempirical correlations of experimental data, and two design constraints of solid propellant-pulsed plasma thrusters are used to illustrate the design analysis of such an electric propulsion system. The semiempirical relations presented have been generated from thruster data covering impulse bits extending from 2.7 dyne-sec (6/i Ib-sec) to 31 mN-sec (7 mlb-sec) and a specific impulse up to 5100 sec. They are descriptive to within about 8%. Basic ConsiderationsA PULSED plasma thruster utilizes the rapid discharge of energy E from an energy storage capacitor to accelerate a small quantity of mass of plasma to a high discharge velocity. J The ejection of this mass produces an impulse bit 7. If the thruster is operated at a fixed pulse frequency/, an equivalent steady state thrust Tis generated T=fl(1) where any consistent metric or engineering units can be used. The corresponding equivalent steady electric power P delivered to the thruster nozzle by the capacitor is then P=fE(2)If a power conditioner of efficiency rj p is used to charge the capacitor the required bus power will beThe relationship between the propellant mass m consumed per thruster discharge and its equivalent steady flow rate m is rh=fm The specific impulse I sp is thereforewith ing denoting the weight flow rate of propellant. The thrust efficiency 17 1 isIf the power conditioner is included, the system efficiency r? 5 becomesA given pulsed plasma thruster is unique because its thrust is varied at constant specific impulse and efficiency. Variable thrust is realized by merely varying the pulse rate. The electric power requirements are then directly proportional to the pulse frequency.

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Colloid and pulsed plasma thrusters for spacecraft propulsion

Cited by 4 publications

References 8 publications

Small satellites and electric propulsion - a review

Small satellites and electric propulsion - a review

Survey of Electric Propulsion Capability

Solid Propellant Pulsed Plasma Propulsion System Design

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