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14th High-Tech Plasma Processes Conference (HTPP 14) IOP Publishing IOP Conf. Series: Journal of Physics: Conf. Series 825 (2017) 012005 doi:10.1088/1742-6596/825/1/012005 Motivation Almost all known MPC types operate under high vacuum conditions (10-5-10 mbar) with very high discharge currents (10-200 kA) and low repetition frequencies (0,01-0,1 Hz). The overall system in all cases is based on bulky high-current switchers, heavy high voltage capacitor banks with tens of kV, complex control and diagnostics devices [1-7]. Nevertheless, all the previous work gave the main inspiration to develop new lightweight, highly miniaturized, lower voltage powered stable MPC-based plasma jet generator systems for flow control and propulsion purposes. The main initiation was given in 2010 by an informal request from an European aerospace company for a stratospheric high-thrust plasma propulsion with tens to hundreds of Newton. At the time this technology was not available and the request could not be addressed but the idea was born to develop a new propulsion system which combines electrohydrodynamic barrier discharge and field electron emission effects with magnetohydrodynamic flux compression aspects. The first breakthrough milestone goal was to realize a MPC system with 5-10 Hz repetition frequency which is able to operate under atmospheric pressures from 0.1-1.0 bar [13]. So far there was no known work about MPC operating at high-pressure and high-frequency. This challenge and the industrial request for a high-altitude propulsion systems was the main motivation to start a R&D programme for pulsed plasma “detonation” thrusters. It is not widely known that a hydromagnetic Rankine-Hugeniot model for detonation and deflagration can be also used to describe gas-fed (air-breathing) coaxial plasma accelerators which are based on pinching dense plasma focus discharge devices like the magneto-plasma compressor. The gas is in this case is resistively heated by the pinching discharge instead of the burning in the combustor. The hydromagnetic shock caused by the high magnetic pressure ionizes and compresses the gas volume ahead of itself [19-22]. Nevertheless, all the known studies focus on high-vacuum conditions with plasma jet velocities exceeding 100-200 km/s. Recent studies about sub-millimeter dense plasma focus (DPF) devices also reveal attempts and proposals towards higher pressures of 10-1000 Torr in hydrogen though limitations in confinement due to increased collisions at high pressures are expected [23]. Nevertheless, the same authors could recently demonstrate a DPF operating in 50-190 Torr Helium [24]. This specific type of pinching plasma accelerator is producing short nanosecond discharge pulses which are also relevant for x-ray and short pulse neutron emissions. DPF devices and their applications are again reconsidered for investigation in large-scale plasma fusion and space propulsion programs [26-31]. This is a further motivation to study air-breathing magneto-plasma jet thrusters. In previous experiments the authors used microsecond discharges for internal initiation of the propulsive main discharge and could already increase the MPC operation pressure from 30 to 250 Torr (0.33 bar), see Figure 2a-2c [13]. The use of nanosecond discharge was the next logical step which was also motivated by the fact that in experiments to chemical pulse detonation engines distributed or transient nanosecond spark discharges are significantly more efficient for detonation initiation than localized microsecond spark discharges of comparable pulse energy [17]. So high repetition nanosecond pulsed discharge are already in the focus of groups working on efficient combustion processes for several years [18], though no working group has obviously ever combined the nanosecond know-how with pinching dense plasma focus discharges. 5 4 3 2 1 0 0 50 100 150 200 250 Thrust (mN*s) Battery 2.0 kV Thrust (mN*s) Battery 1.8 kV Energy input *100(J) /pulse Battery 2.0 kV Energy input *100 (J) /pulse Battery 1.8 kV (a) Pressure (Torr) (b) (c) Figure 2a-2c. Thrust and pulse energy deposition in dependence of the air pressure for different battery voltages with internal microsecond sliding discharge exitation [13]. 2PDF Image | Breakthrough for Future Air-Breathing Magneto-Plasma Propulsion Systems 2017
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