Preliminary conclusions of continuous applied field electromagnetic thruster research at DFVLR

Kruelle, G.; Zeyfang, E.

doi:10.2514/6.1975-417

Cited by 9 publications

(13 citation statements)

References 0 publications

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“…With respect to DLR's X16 thruster higher thrust efficiency with the new SX coil at magnetic flux density of 0.6 T can be expected. 1 The insufficient cooling of insulator made of PEEK limits operation of the thruster to 1 min. However, improved version of ZT1 thruster is in consideration as passively cooled or active water cooled design for future experiments as SX1 thruster that should allow stationary conditions in steady-state operation.…”

Section: Iva Experimental Results Of Af-mpd Zt1 Thrustermentioning

confidence: 99%

“…8 The thruster's design is based on electrode geometry of DLR's X16 thruster, which achieved thrust efficiencies up to 39 % in steady-state operation with noble gases as propellant at applied magnetic flux density of 0.6 T. 1 The AF-MPD ZT1 thruster has passively cooled design and includes hollow single channel cathode (WT20) and the anode (WL10) with annular slit for separate anode gas injection (see Figure 2). …”

Section: Iiia Af-mpd Zt1 Thrustermentioning

confidence: 99%

“…1,2 The respective exhaust velocities vary depending on mass flow rate of used propellant in a range between 25 and 50 km/s. However Hydrogen driven devices can even reach exhaust velocities up to 70 km/s (Ref.…”

Section: Introductionmentioning

confidence: 99%

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Experimental Investigation of Steady-State Applied-Field Magnetoplasmadynamic Thrusters at Institute of Space Systems

Boxberger¹,

Bambach²,

Herdrich³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The applied-field magnetoplasmadynamic thruster AF-MPD ZT1 was successfully put in operation at IRS. The thruster operated in steady-state mode with Argon as propellant at low electric arc power of 6 kW. Discharge voltage and power increased as expected almost linear with applied magnetic flux density. The variation of mass flow rate ratio between anode and cathode gas towards higher cathode gas fraction showed increasing thrust and thrust efficiency at applied magnetic flux density of 0.1 T and are comparable with DLR's X13 thruster. Additionally a steady-state 100 kW AF-MPD thruster SX3 was developed, set in operation and preliminary characterized at IRS. The SX3 thruster was operated at relatively low arc powers up to 30 kW and applied magnetic flux density of 0.1 T generated by the modified ZT coil. Due to low arc current and magnetic flux level, the AF-MPD ZT1 thruster achieved thrust of 70 mN and exhaust velocity up to 10 km/s at 6 kW arc power and up to 6 % thrust efficiency. The SX3 thruster reached thrust of 362 mN and thrust efficiency more than 12 % in steady state-operation at 25 kW arc power and at applied magnetic flux density of 0.1 T. However both thrusters have been operated at limited magnetic fluxes only. For SX3 a total operation time of more than 3600 s together with 30 ignitions could be accumulated. The electrodes, however, do not show significant erosion nor a respective degradation. The performances of thrusters provide an outlook for future investigations on AF-MPD thrusters at IRS and give a hint to improvement in thrust efficiency of presented devices with the new applied-field coil, which will be manufactured in the future to produce magnetic flux densities up to 0.6 T allowing further increase in thrust efficiency up to 30 %.

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Section: Iva Experimental Results Of Af-mpd Zt1 Thrustermentioning

confidence: 99%

Section: Iiia Af-mpd Zt1 Thrustermentioning

confidence: 99%

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Experimental Investigation of Steady-State Applied-Field Magnetoplasmadynamic Thrusters at Institute of Space Systems

Boxberger¹,

Bambach²,

Herdrich³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

show abstract

“…26 the specifi c thrust (force/current) is shown to increase with the tank pressure (and, therefore, the gas density) decreasing [19,20]. IV.A.2, current AF-MPD thrusters show magnetic fi eld lines extending far downstream as B/n e increases.…”

Section: Testing Facilities-flight Testmentioning

confidence: 93%

“…Thrust per current as function of the tank pressure for experimental thruster X13 and prefl ight model X16[19,20].…”

mentioning

confidence: 99%