VASIMR® VX-200 Improved Throttling Range

Longmier, Benjamin W.; Squire, Jared P.; Olsen, C.; Cassady, Leonard D.; Ballenger, Maxwell G.; Carter, Mark D.; Ilin, Andrew V.; Glover, T. W.; McCaskill, Greg; Díaz, Franklin R. Chang; Bering, Edgar A.

doi:10.2514/6.2012-3930

Cited by 10 publications

(11 citation statements)

References 14 publications

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“…Ion sputtering and thermal load significantly affect the electrode and wall damage and the resultant lifetime of the propulsion device. One of the candidates to overcome the problem relating to the electrode lifetime is an electrodeless plasma thrusters utilizing a radiofrequency (rf) plasma production/heating and a spontaneous plasma acceleration in magnetic nozzles, e.g., a variable specific impulse plasma rocket (VASIMR) [2], a helicon/rf plasma thruster [3][4][5], and an electron cyclotron resonance plasma thruster [6].…”

mentioning

confidence: 99%

Thrust imparted by a stepped-diameter magnetic nozzle rf plasma thruster

Takahashi

Takao

Andõ

2018

Applied Physics Letters

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A stepped-diameter source tube is employed on a magnetic nozzle radiofrequency plasma thruster, where the magnetic field lines intersecting the wall near the antenna is separated from the radial wall near the thruster exit. The thruster is operated at a rf power up to 5 kW. Comparison with the results for the cylindrical source tube shows the increase in the thrust by about 15-20 % for the stepped-diameter case in spite of the lower plasma density near the nozzle entrance, resulting in the lower electron-diamagnetic-induced thrust component. These indirectly show that the axial momentum lost to the radial wall is inhibited by separating the plasma flow from the radial source wall.

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mentioning

confidence: 99%

Thrust imparted by a stepped-diameter magnetic nozzle rf plasma thruster

Takahashi

Takao

Andõ

2018

Applied Physics Letters

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“…This variation in thrust and specific impulse is a great advantage since the engine can fit many mission profiles due to its flexibility. Additionally, the VASIMR can be scaled up in power (theoretically to MW capability), enabling crewed interplanetary flights using electric propulsion [7].…”

Section: Variable Specific Impulse Magnetoplasma Rocketmentioning

confidence: 99%

Low-Thrust Control Strategies for Earth-to-Mars Trajectories

Jenkins¹,

Nieto²

2018

Space Flight

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Recent advances in electric propulsion systems have demonstrated that these engines have the potential to be used for long-duration travels, with applications such as cargo and human transportation for interplanetary voyages. The Variable Specific Impulse Magnetoplasma Rocket (VASIMR) is an example of this type of engine, possessing the ability to operate at a wide range of specific impulse levels. This chapter presents the results of a study comparing three different thrust control strategies for Earth-Mars trajectories, using the VASIMR engine at a power of 150 kW. These are constant thrust trajectories, trajectories with coasting periods, and trajectories with variable specific impulse, resulting in variable thrust. To achieve this, an optimization tool was created using spherical coordinates to model the dynamics of the spacecraft, optimal control theory to setup the optimization problem, and a differential evolution algorithm to minimize the cost function. A novel approach to model variable specific impulse and coast-arcs in the trajectories for spherical coordinates is presented as well. The optimization tool was utilized to find optimal trajectories from Earth to Mars orbit, and it was concluded that using variable thrust reduces propellant consumption for a variety of trajectories, when compared to the other two methods.

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“…Extensive testing using the VASIMR ® VX-200 TM experiment for pulse lengths up to 30 s and at power levels up to 200 kW has established the system's DC-to-jet power performance while the injected-gas and plasma were operating in steady-state conditions 11 . Figure 1 shows the installed VX-200 TM device.…”

Section: Introductionmentioning

confidence: 99%

“…The thruster efficiency ranges from 60% to 72% in the specific impulse (Isp) domain of 3000 to 5000 s using argon propellant. 11 These measurements were performed using highly efficient (~ 95%) and light-weight (< 1 kg/kW) solid-state RF power processing units built by Nautel, Ltd and a superconducting magnet that is free of liquid cryogens. 11 Detailed mapping of the plasma plume over a large scale length (> 2 m) and low background pressure (< 2×10 -4 Torr) has shown that the plasma is detached from the VX-200 TM device's magnetic field at a distance of approximately 2 m from the exhaust exit.…”

Section: Introductionmentioning

confidence: 99%

“…11 These measurements were performed using highly efficient (~ 95%) and light-weight (< 1 kg/kW) solid-state RF power processing units built by Nautel, Ltd and a superconducting magnet that is free of liquid cryogens. 11 Detailed mapping of the plasma plume over a large scale length (> 2 m) and low background pressure (< 2×10 -4 Torr) has shown that the plasma is detached from the VX-200 TM device's magnetic field at a distance of approximately 2 m from the exhaust exit. 12 A recent study has evaluated the overall propulsion system specific mass, finding it to be in the range of 3 kg/kW at high power levels (~ 250 kW) using existing technology.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Advances in Duration Testing of the VASIMR^® VX-200SS^™ System

Squire¹,

Carter²,

Díaz³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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The VX-200SS program will complete design verification, testing and lifetime estimates of a VASIMR ® prototype engine, operating under thermal steady-state at power levels greater than 100 kW for at least 100 continuous hours. The work will bring the integrated VX-200SS VASIMR ® prototype to Technology Readiness Level of 5 (TRL-5), including RF Power Processing Units (PPUs), superconducting magnet, propellant management system, internal thermal management subsystems and the rocket core. The rocket core element resides down the bore of the magnet and is designed to utilize the RF power in conjunction with the high magnetic field to create and accelerate a high power-density plasma stream and manage any waste heat from the process. The accumulation of significant operating time will allow a measurement of the wear of plasma-facing components with sufficient accuracy to evaluate their projected lifetime. The VX-200SS program builds on the successful VX-200™ program and involves manufacturing of a new rocket core and significant upgrades to the RF subsystems, vacuum chamber, computer control, and performance measurement diagnostics. This paper describes the three-year multi-phase VX-200SS program that has been underway for one year.

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VASIMR® VX-200 Improved Throttling Range

Cited by 10 publications

References 14 publications

Thrust imparted by a stepped-diameter magnetic nozzle rf plasma thruster

Thrust imparted by a stepped-diameter magnetic nozzle rf plasma thruster

Low-Thrust Control Strategies for Earth-to-Mars Trajectories

Advances in Duration Testing of the VASIMR^® VX-200SS^™ System

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VASIMR® VX-200 Improved Throttling Range

Cited by 10 publications

References 14 publications

Thrust imparted by a stepped-diameter magnetic nozzle rf plasma thruster

Thrust imparted by a stepped-diameter magnetic nozzle rf plasma thruster

Low-Thrust Control Strategies for Earth-to-Mars Trajectories

Advances in Duration Testing of the VASIMR® VX-200SS™ System

Contact Info

Product

Resources

About

Advances in Duration Testing of the VASIMR^® VX-200SS^™ System