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guration of the thruster was designed for steady-state ope- ration of the SX1 thruster at a power level of 12 kW (fig.3). Involved in ESA and EU (HIPER) programs in cooperation with Alta, IRS is aiming for the development of high power electric propulsion systems. Figure 2: Experimental results of AF-MPD ZT1 In the framework of these programs, a 100 kW AF-MPD thruster is to be developed and tested within 2011 [2]. Primarily designed for this project, AF-MPD ZT2 was improved to the SX3 (fig.4) configuration to guaranty a steady-state operation at a power level of 100 kW. Figure 3: Sectional view of new AF-MPD SX1 thruster (Improved AF-MPD ZT1) This design is currently being manufactured. The followed experimental investigation of the SX3 thruster will round up the data of SX1 thruster with respect to thrust, effi- ciency and scaling behaviour of AF-MPD thrusters. Figure 4: Sectional view of new 100 kW AF-MPD SX3 thruster (redesigned AF-MPD ZT2) [2] 2. Advanced Water-fed PPT Pulsed Plasma Thrusters (PPT) have been investigated for several decades leading to successful space application, recently on FalconSatIII [4]. They offer a robust and low cost design, high ce, low power consumption and easy thrust control. The common design uses a block of PTFE (TeflonTM) as propellant. However, possible benefits of using liquid propellants have been pointed out [5-7]. The self regulated ablation from a solid block of TeflonTM limits the thruster performance. Only a fraction of the ablated mass per pulse is properly ionized and accelerated. The rest evaporates at relatively low velocities [8], also known as late time ablation. The use of a pre-determined liquid mass can improve acceleration and performance. A thruster without late time ablation would provide insight into efficiency margins of the PPT technology. Further, a liquid system avoids depositions of carbon and fluoride residues on surfaces altogether. Also the use of waste liquids and combined operation with other liquid propulsion systems are feasible. In competition with other propulsion systems, any pulsed liquid system design needs to stay as close to the simplicity of a solid propellant PPT as possible, lest the feasibility degrades in terms of cost, reliability, size and performance. The complexity of handling liquid propellant and the increase in system mass must be minimized. A possible approach is to literally stick to the block, meaning to renew the area of the surface layer for ablation after each pulse, with the liquid being fed self regulated. This is realized similar to a candle using a wick to draw fuel. Fig. 5 shows a schematic overview of the respective system components, with arrows pointing downstream. Figure 5: Schematic Setup of Liquid PPT (upper) and photo during operation at IRS (lower) The liquid (purified water) is fed to the wick-element by means of the pressure gradient between tank and ambient space. It will saturate the wick. The tank is commonly heavy due to high pressure storage. However, the wick soaks up with the liquid and the PPT operation does only require mass flow rates in the μg-range. This allows for utilization of a very lightweight tank, shaped with regard to both volume and satellite demands. The short tubing and a singular shut-off valve have a low system mass. The valve prevents unwanted feeding during launch and PPT idle times. It is the only moving part of the system. Exposed to a space environment, a layer of ice is created on the wick-surface between the two PPT electrodes. PPT operation with liquid feeding is considered similar to PTFE feeding. After initiation of the pulse, a discharge arc forms between the electrodes, ablating propellant similar to its PTFE-pendant. After a pulse, no late time ablation can occur. To avoid ablation of the wick, ceramic materials are considered. The small system size suggests application on mini-satellites, prolonging orbital lifetime. This is supported by recent ESA studies and an increasing interest in cheap technology demonstration. First steps towards a liquid PPT design are made at IRS. An experimental laboratory model has been set up for testing of handling, feeding and pulsed operation with purified water. The feasibility has been successfully demonstrated inside an IRS test facility. The thruster performed flawless. The analysis of results and design are Advanced Plasma (Propulsion) Concepts at IRS 7,00 6,00 5,00 4,00 3,00 0,10 0,12 0,14 0,16 0,18 0,20 B/T Mass flow rate: 10 mg/s Ar (7 / 3, Anode / Cathode) Arc current: 88 A Tank pressure: 0.01 mbar 2 P / kWPDF Image | ADVANCES IN APPLIED PLASMA SCIENCE 2011
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