Single- and Repetitive-Pulse Conical Theta-Pinch Inductive Pulsed Plasma Thruster Performance

Hallock, Ashley K.; Martin, Adam; Polzin, Kurt A.; Kimberlin, Adam C.; Eskridge, Richard

doi:10.1109/tps.2014.2368835

Cited by 10 publications

(11 citation statements)

References 14 publications

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“…These calculations also found a local maximum in the efficiency (though not an absolute maximum) for a cone angle less than 90 • , as was observed experimentally in Ref. [4].…”

Section: Conical Theta-pinch Thruster Modelingsupporting

confidence: 84%

“…Even when the gas was injected against the coil face, the efficiencies based on thrust measurements were below 6% on argon [4]. These data compare unfavorably with the ∼15-30% efficiencies measured with argon in the PIT MK I and MK V planar thrusters [7].…”

Section: Conical Theta-pinch Thrustersmentioning

confidence: 51%

“…Specifically, since the accelerating force is in the direction perpendicular to the coil face, radially-inward motion will be imparted to the gas that must be converted by some means to axial motion if it is to produce thrust. Hallock et al [4,19] performed testing on CTP-IPPTs proof-of-concept devices fabricated with cone angles of 20 • , 38 • , and 60 • , measured from the centerline of the thruster. The exit diameters for these three coils were approximately 15, 23, and 25 cm, respectively.…”

Section: Conical Theta-pinch Thrustersmentioning

confidence: 99%

“…An issue with this method is the presence of the gas injection pylon in the downstream flow as the propellant accelerates away from the coil and the bombardment and sputtering that can occur when the high speed plasma inpacts the pylon head. CTP-IPPTs performed best with gas injected against the conical coil face with azimuthal swirl imparted to the propellant [4]. Pulsed gas injection was not attempted in CTP-IPPT testing, but it is expected that there would be significant latent propellant remaining in the feed lines when the thruster was pulsed, resulting in a low propellant use efficiency.…”

Section: Propellant Management and Injectionmentioning

confidence: 99%

“…These thrusters are characterized by open magnetic flux surfaces in the gap between the coil and the plasma current loops, with the flux surfaces exiting the gap at the extents of the coil and current sheet. The main thruster of this type in the literature is the Pulsed Inductive Thruster (PIT) [3], though theta-pinch and conical theta-pinch devices can also be operated in this mode [4]. The other category is comprised of thrusters in which closed magnetic flux surfaces are embedded within and aid in confinement of the plasma.…”

Section: Introductionmentioning

confidence: 99%

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State-of-the-Art and Advancement Paths for Inductive Pulsed Plasma Thrusters

et al. 2020

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An inductive pulsed plasma thruster (IPPT) operates by pulsing high current through an inductor, typically a coil of some type, producing an electromagnetic field that drives current in a plasma, accelerating it to high speed. The IPPT is electrodeless, with no direct electrical connection between the externally applied pulsed high-current circuit and the current conducted in the plasma. Several different configurations were proposed and tested, including those that produce a plasma consisting of an accelerating current sheet and those that use closed magnetic flux lines to help confine the plasma during acceleration. Specific impulses up to 7000 s and thrust efficiencies over 50% have been measured. The present state-of-the-art for IPPTs is reviewed, focusing on the operation, modeling techniques, and major subsystems found in various configurations. Following that review is documentation of IPPT technology advancement paths that were proposed or considered.

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“…These calculations also found a local maximum in the efficiency (though not an absolute maximum) for a cone angle less than 90 • , as was observed experimentally in Ref. [4].…”

Section: Conical Theta-pinch Thruster Modelingsupporting

confidence: 84%

Section: Conical Theta-pinch Thrustersmentioning

confidence: 51%

Section: Conical Theta-pinch Thrustersmentioning

confidence: 99%

Section: Propellant Management and Injectionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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State-of-the-Art and Advancement Paths for Inductive Pulsed Plasma Thrusters

et al. 2020

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Optimization of Electric Thrust Based on Pulse Arc Plasma Using Pulsed Magnetic Field

Nefedtsev

Zjulkova

2020

Russ Phys J

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A thruster using magnetic reconnection to create a high-speed plasma jet

Bathgate

Bilek

Cairns

et al. 2018

Eur. Phys. J. Appl. Phys.

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Plasma thrusters propel spacecraft by the application of Lorentz forces to ionized propellants. Despite evidence that Lorentz forces resulting from magnetic reconnection in solar flares and Earth's magnetopause produce jets of energetic particles, magnetic reconnection has only recently been considered as a means of accelerating plasma in a thruster. Based on theoretical principles, a pulsed magnetic reconnection thruster consisting of two parallel-connected slit coaxial tubes was constructed. The thruster was operated in argon plasma produced by RF energy at 13.56 MHz. A 1.0 ms current pulse of up to 1500 A was applied to the tubes. Three results provide evidence for magnetic reconnection. (1) The production of high-energy electrons resembling the outflow that is observed in the reconnection of field lines in solar flares and in laboratory experiments. (2) The high-energy electron current coincided with the rise of the magnetic field in the thruster and was followed by a large ion current. (3) In accordance with known physics of magnetic reconnection, ion currents were found to increase as the plasma became less collisional. The Alfvén speed of the outflowing ions was calculated to be 8.48 × 103 m s−1 corresponding to an Isp of 860 s.

show abstract

Single- and Repetitive-Pulse Conical Theta-Pinch Inductive Pulsed Plasma Thruster Performance

Cited by 10 publications

References 14 publications

State-of-the-Art and Advancement Paths for Inductive Pulsed Plasma Thrusters

State-of-the-Art and Advancement Paths for Inductive Pulsed Plasma Thrusters

Optimization of Electric Thrust Based on Pulse Arc Plasma Using Pulsed Magnetic Field

A thruster using magnetic reconnection to create a high-speed plasma jet

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