Performance and lifetime assessment of MPD arc thruster technology

Abstract. Magnetoplasmadynamic (MPD) thrusters are capable of accelerating quasi-neutral plasmas to high exhaust velocities using Megawatts (MW) of electric power. These characteristics make such devices worthy of consideration for demanding, far-term missions such as the human exploration of Mars or beyond. Assessment of MPD thrusters at the system and mission level is often difficult due to their status as ongoing experimental research topics rather than developed thrusters. However, in order to assess MPD thrusters' utility in later missions, some adequate characterization of performance, or more exactly, projected performance, and system level definition are required for use in analyses. The most recent physical models of self-field MPD thrusters have been examined, assessed, and reconfigured for use by systems and mission analysts. The physical models allow for rational projections of thruster performance based on physical parameters that can be measured in the laboratory. The models and their implications for the design of future MPD thrusters are presented.

Section: Introductionmentioning

confidence: 99%

MPD Thruster Performance Analytic Models

Gilland

Johnston

2003

“…MID thrusters have been under development for over twenty five years (Sovey and Mantenieks 1988). During this period these devices have been tested under a wide variety of operating conditions and power levels both in steady state and pulsed modes.…”

Section: Magnetoplasmadynamic (Mpd) Thrustermentioning

confidence: 99%

Electric thruster models for multimegawatt nuclear electric propulsion mission design

Leifer

Blandino

Sercel

1991

Three types of electric thrusters currently under development at JPL have potential to support future missions which utilize multimegawatt nuclear elecUic propulsion. These electric thrusters are the electron bombardment ion thruster, the magnetoplasmadynamic (MID) thruster, and the electron-cyclotron-resonance (ECR) thruster. The electron bombardment ion thruster is a relatively mature technology which has been developed for operation at kilowatt power levels but will require new development for application in the multimegawatt regime. The MPD engine represents a technology which may be very well suited to steady-state multimegawatt applications but which has been limited to sub-scale (100's ofkW) and pulsed (MW) testing thus far. The ECR plasma engine represents a class of very promising new concepts which are still in the basic research phase of development, but which may possess important fundamental advantages over other electric thruster technologies. In this paper, models of these thrusters are described and used to make projections of thruster specific mass, efficiency, and power handling capacity for operation in the multimegawatt regime.

“…While specific impulses meeting performance requirements have been demonstrated with several thruster configurations (Sovey and Mantenieks 1988) the thruster efficieneies are still substantially below those required for missions of interest. However, substantial data exist indicating this problem can be overcome (Myers et al 1991a).…”

Section: Magnetoplasmadynamicmentioning

confidence: 99%

Multimegawatt MPD thruster design considerations

Myers

Parkes

Mantenieks

1992

Performance and lifetime requirements for multimegawatt magnetoplasmadynamic (MPD) thrusters were used to establish a baseline 2.5 MW thruster design. The chamber surface power deposition resulting from current conduction, plasma and surface radiation, and conduction from the hot plasma was then evaluated to establish the feasibility of thruster operation.It was determined that state-of-art lithium heat pipes were adequate to cool the anode electrode, and that the liquid hydrogen propellant could be used to cool the applied-field magnet, cathode, and backplate.Unresolved issues having an impact on thruster design are discussed to help focus future research.