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subject to further research. The pulsed operation inside the vacuum chamber is shown in the lower half of fig. 5. 3. Hybrid Thruster TIHTUS A hybrid plasma thruster is under experimental [9-11] and numerical [12] investigation. TIHTUS (Thermal-Inductive Heated Thruster of Stuttgart University) is two-staged and consists of an arcjet as the first stage and an inductively heated plasma generator (IPG) as the second stage [13]. A photo of the device in operation is shown in fig. 7 together with a schematic. The plasma plume down-stream the arcjet of the 100 kW class, called HIPARC and developed by IRS with NASA, has high temperature and velocity at the core and lower energies in the surrounding flow. To increase the energy in the plasma flow, the second stage inductively couples energy into the colder region of the plasma near the wall due to the skin effect. This not only augments both specific impulse and thrust but also flattens the radial profile of the plasma flow which may be interesting for plasma technology processes. Further, between the two stages, an additional mass flow can be added. This may be erosive gases, which would destroy the first stage cathode. With the current technology demon- strator, a thrust level of about 2N is reached at a total power of 50kW and a mass flow of 300mg/s [9]. For a better understanding of the physics and for a comparison of the experimental results, numerical investigations of the thruster are ongoing. After the validation of the numerical code, optimization of thrust and efficiency can be performed. Figure 7: Schematic of TIHTUS (upper) and photo in operation (lower) [11] There are several interesting options for optimization. Some necessary experiments like changes in geometry are rather expensive both in money and time. This effort is intended to be reduced by numerical simulations. For the numerical simulation of TIHTUS, the program system SINA (Sequential Iterative Non-equilibrium Algorithm) will be used and improved. SINA was developed in order to numerically simulate the complex thermal and chemical phenomena in the DC plasma wind tunnel facilities at the IRS that are used for the testing of heat shield materials [14]. It can also be applied on axi- symmetric plasma sources or thrusters with an electric arc. SINA consists of three different semi-implicit and explicit independent solvers (Navier-Stokes solver, Chemistry / Vibrational / Electron energy (CVE) solver, discharge solver) which are loosely coupled (fig. 8). 3 Figure 8: Structure of the code SINA for TIHTUS 4. Magnetically Confined Fusion Propulsion One option to shorten interplanetary travel times consists in replacing lengthy conventional transfers such as Hohmann’s or gravity assist maneuvers by a transfer made up of two continuous burns and estimated by (1) ( 2 ) for its duration τ [15]. In these equations, F designates the thrust, ce the exhaust velocity, Md the vessel dry mass and ε the ratio of dry to initial mass. From Tsiolkovsky’s equation one concludes that high ce improves ε for a ma- neuver described by its velocity increment ∆v. Assuming a given ∆v and a limitation of the mass specific power P12Fce 1 α=m= m =2ace (3) with the absolute power P and characteristic mass m, one obtains that raising ce for a given value reduces the acceleration a. Hence, it has a detrimental effect on the duration to build up ∆v and consequently on the mission duration. However, if it was possible to raise α consi- derably, for example by using fusion, it would be possible to reap the benefits of high ce and high thrust at the same time. Therefore, nuclear fusion seems not only to be an alternative to terrestrial energy provision [16], but also to be a very attractive one for space propulsion [17-20]. Both Magnetically Confined Fusion Propulsion (MCFP) plasma and systems have been investigated at IRS [20-23]. MCFP is a thermal propulsion concept. The power is provided by the excessively hot magnetically confined fusion plasma. The propellant may consist in fusion products – the so called ash – but it is also thinkable to aliment the system with an additional coolant heated by the plasma and ultimately ejected as propellant [20, 23]. The propulsion system relies on the fusion plasma whose operation is defined by the fusion criterion yielded by an energy and particle balance from which the characteristic triple product niτETi made up of the first species’ ions’ particle density ni, the energy confinement time τE and the ions’ temperature Ti can be calculated [21]. The thermal power of the products in so called ash drives (AD) is assumed to be expanded with the exhaust velocity Advanced Plasma (Propulsion) Concepts at IRS c2 12 D=e M −1 for its voyage distance D and by ce 1 d Fε τ = F M d ε − 1 PDF Image | ADVANCES IN APPLIED PLASMA SCIENCE 2011
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