Uwe Bauder - Academia.edu (original) (raw)

Papers by Uwe Bauder

Research paper thumbnail of Scheduled Development of the TIHTUS System: Geometric Optimisation and Alternative Propellant Operation

In order to further the performance and understanding of coupled DC-RF electric propulsion system... more In order to further the performance and understanding of coupled DC-RF electric propulsion systems, development of the TIHTUS (Thermal-Inductive Thruster of the University of Stuttgart) has been scheduled at the Institute for Space Systems (IRS). This development pursues two parallel objectives, being geometric optimisation of the thruster and an investigation into alternative propellants. Optimisation will focus on reducing distance between the DC and RF generators (in order to decrease losses due to species recombination), as well as decreasing the thickness of the inductive stage discharge tube (to increase power coupled into the flow). The study of propellants will investigate gases obtainable from locations of interest within the solar system, as well as those which are otherwise discarded as waste from crew life support systems. These studies will be conducted both experimentally, at the IRS TIHTUS facility, as well as numerically using the SINA (Sequential Iterative Non-equilibrium Algorithm) numerical model. The combination of these two programs are intended to allow a greater understanding of potential performance and potential mission-types for the TIHTUS system.

Research paper thumbnail of Numerical Modeling of Radiative And Convective Heat Flux For Entry Flights In CO<sub>2</sub> Containing Atmospheres

43rd AIAA Thermophysics Conference, 2012

Research paper thumbnail of Current Numerical and Experimental Investigations of the Hybrid DC-RF Thruster TIHTUS

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2010

Electric space propulsion delivers high exhaust velocities usually in combination with relatively... more Electric space propulsion delivers high exhaust velocities usually in combination with relatively low thrust levels. Raising the thrust level at a constant high exhaust velocity, fuel consumption for a specific mission is reduced and payload mass is increased. Also, an increase in mission flexibility and a reduction of duration can be achieved. Promising thrusters are hybrid concepts like TIHTUS. This thruster combines an arcjet and an ICP in series. The proof of concept already shows promising results. After a description of the thruster system actual experimental and theoretical optimizations of the standalone ICP are summarized. For a decrease of wall thickness from 2.3 mm to 1.25 mm the thermal plasma power is increased by 40 % and the thinner quartz tube can resist higher heat loads, too. These results show the potential for large improvements of the overall thruster parameters and motivate a research program for further optimization of the already promising TIHTUS engine. In this program, theoretical and experimental investigation will be accompanied by numerical simulations for a detailed understanding of the relevant processes and the identification of the prospects of success for further optimization. The current status of development of the numerical tool is also described.

Research paper thumbnail of Development of a Two Phase Solver Accounting for Solid Particles in Continuum Gas Flows

40th Thermophysics Conference, 2008

Research paper thumbnail of Examination of the Coupling of the Loosely Coupled Sequential Navier-Stokes Code SINA

40th Thermophysics Conference, 2008

Research paper thumbnail of Improvement and Extension of the Loosely Coupled Navier-Stokes Code SINA to Different Gases

10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, 2010

Research paper thumbnail of Hydrogen Chemistry and Transport Coefficients for Simulation of the DC-RF thruster TIHTUS with the Loosely Coupled Navier-Stokes Code SINA

Research paper thumbnail of Initiation of the Numerical Investigation of the Hybrid Plasma Thruster TIHTUS

Research paper thumbnail of Study of Solid Particle Behavior in High Temperature Gas Flows

The Euler-Lagrangian approach is used for the simulation of solid particles in hypersonic entry f... more The Euler-Lagrangian approach is used for the simulation of solid particles in hypersonic entry flows. For flow field simulation, the program SINA (Sequential Iterative Non-equilibrium Algorithm) developed at the Institut für Raumfahrtsysteme is used. The model for the effect of the carrier gas on a particle includes drag force and particle heating only. Other parameters like lift Magnus force or damping torque are not taken into account so far. The reverse effect of the particle phase on the gaseous phase is currently neglected. Parametric analysis is done regarding the impact of variation in the physical input conditions like position, velocity, size and material of the particle. Convective heat fluxes onto the surface of the particle and its radiative cooling are discussed. The variation of particle temperature under different conditions is presented. The influence of various input conditions on the trajectory is explained. A semi empirical model for the particle wall interaction...

Research paper thumbnail of Effect of Dust Particles on Space Vehicles Entering Mars at Hypersonic Speeds

Research paper thumbnail of Modeling of Dusty Plasma Flow and Determination of its Impact on Shield Materials

Research paper thumbnail of Particle Wall Interactions in Dusty Hypersonic Entry Flows

The Euler-Lagrangian approach is used for the modeling and simulation of solid particles in hyper... more The Euler-Lagrangian approach is used for the modeling and simulation of solid particles in hypersonic entry flows. For the simulation, the program SINA (Sequential Iterative Non-equilibrium Algorithm) developed at the Institut für Raumfahrtsysteme is being extended by the particle solver. The model for the effect of the carrier gas on a particle includes drag force and particle heating. The phase change of the particle due to high temperature of the flow field is taken into account. The heat fluxes onto the wall due to impingement of particles are also computed and compared with the heat fluxes from the gas. A semi empirical model for the particle-wall interaction is presented. Depending on the input conditions, the erosion mass loss of a charring ablator using an engineering correlation is also discussed.

Research paper thumbnail of Electrostatic Probe and Camera Measurements for Modeling the iMPD SIMP-LEX

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2007

Research paper thumbnail of Advanced plasma (propulsion) concepts at IRS

Vacuum, 2013

Several advanced plasma propulsion designs have been developed and characterized at IRS in the pa... more Several advanced plasma propulsion designs have been developed and characterized at IRS in the past years. Among them are the hybrid thruster TIHTUS, the steady state applied field thrusters AF MPD ZT1 and ZT2 and advanced iMPD designs. These concepts show promising potential for future missions. The paper will discuss the designs and their operational features.

Research paper thumbnail of Current Electric Propulsion Development Program at IRS

Research paper thumbnail of Scheduled Development of the TIHTUS System: Geometric Optimisation and Alternative Propellant Operation

In order to further the performance and understanding of coupled DC-RF electric propulsion system... more In order to further the performance and understanding of coupled DC-RF electric propulsion systems, development of the TIHTUS (Thermal-Inductive Thruster of the University of Stuttgart) has been scheduled at the Institute for Space Systems (IRS). This development pursues two parallel objectives, being geometric optimisation of the thruster and an investigation into alternative propellants. Optimisation will focus on reducing distance between the DC and RF generators (in order to decrease losses due to species recombination), as well as decreasing the thickness of the inductive stage discharge tube (to increase power coupled into the flow). The study of propellants will investigate gases obtainable from locations of interest within the solar system, as well as those which are otherwise discarded as waste from crew life support systems. These studies will be conducted both experimentally, at the IRS TIHTUS facility, as well as numerically using the SINA (Sequential Iterative Non-equilibrium Algorithm) numerical model. The combination of these two programs are intended to allow a greater understanding of potential performance and potential mission-types for the TIHTUS system.

Research paper thumbnail of Numerical Modeling of Radiative And Convective Heat Flux For Entry Flights In CO<sub>2</sub> Containing Atmospheres

43rd AIAA Thermophysics Conference, 2012

Research paper thumbnail of Current Numerical and Experimental Investigations of the Hybrid DC-RF Thruster TIHTUS

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2010

Electric space propulsion delivers high exhaust velocities usually in combination with relatively... more Electric space propulsion delivers high exhaust velocities usually in combination with relatively low thrust levels. Raising the thrust level at a constant high exhaust velocity, fuel consumption for a specific mission is reduced and payload mass is increased. Also, an increase in mission flexibility and a reduction of duration can be achieved. Promising thrusters are hybrid concepts like TIHTUS. This thruster combines an arcjet and an ICP in series. The proof of concept already shows promising results. After a description of the thruster system actual experimental and theoretical optimizations of the standalone ICP are summarized. For a decrease of wall thickness from 2.3 mm to 1.25 mm the thermal plasma power is increased by 40 % and the thinner quartz tube can resist higher heat loads, too. These results show the potential for large improvements of the overall thruster parameters and motivate a research program for further optimization of the already promising TIHTUS engine. In this program, theoretical and experimental investigation will be accompanied by numerical simulations for a detailed understanding of the relevant processes and the identification of the prospects of success for further optimization. The current status of development of the numerical tool is also described.

Research paper thumbnail of Development of a Two Phase Solver Accounting for Solid Particles in Continuum Gas Flows

40th Thermophysics Conference, 2008

Research paper thumbnail of Examination of the Coupling of the Loosely Coupled Sequential Navier-Stokes Code SINA

40th Thermophysics Conference, 2008

Research paper thumbnail of Improvement and Extension of the Loosely Coupled Navier-Stokes Code SINA to Different Gases

10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, 2010

Research paper thumbnail of Hydrogen Chemistry and Transport Coefficients for Simulation of the DC-RF thruster TIHTUS with the Loosely Coupled Navier-Stokes Code SINA

Research paper thumbnail of Initiation of the Numerical Investigation of the Hybrid Plasma Thruster TIHTUS

Research paper thumbnail of Study of Solid Particle Behavior in High Temperature Gas Flows

The Euler-Lagrangian approach is used for the simulation of solid particles in hypersonic entry f... more The Euler-Lagrangian approach is used for the simulation of solid particles in hypersonic entry flows. For flow field simulation, the program SINA (Sequential Iterative Non-equilibrium Algorithm) developed at the Institut für Raumfahrtsysteme is used. The model for the effect of the carrier gas on a particle includes drag force and particle heating only. Other parameters like lift Magnus force or damping torque are not taken into account so far. The reverse effect of the particle phase on the gaseous phase is currently neglected. Parametric analysis is done regarding the impact of variation in the physical input conditions like position, velocity, size and material of the particle. Convective heat fluxes onto the surface of the particle and its radiative cooling are discussed. The variation of particle temperature under different conditions is presented. The influence of various input conditions on the trajectory is explained. A semi empirical model for the particle wall interaction...

Research paper thumbnail of Effect of Dust Particles on Space Vehicles Entering Mars at Hypersonic Speeds

Research paper thumbnail of Modeling of Dusty Plasma Flow and Determination of its Impact on Shield Materials

Research paper thumbnail of Particle Wall Interactions in Dusty Hypersonic Entry Flows

The Euler-Lagrangian approach is used for the modeling and simulation of solid particles in hyper... more The Euler-Lagrangian approach is used for the modeling and simulation of solid particles in hypersonic entry flows. For the simulation, the program SINA (Sequential Iterative Non-equilibrium Algorithm) developed at the Institut für Raumfahrtsysteme is being extended by the particle solver. The model for the effect of the carrier gas on a particle includes drag force and particle heating. The phase change of the particle due to high temperature of the flow field is taken into account. The heat fluxes onto the wall due to impingement of particles are also computed and compared with the heat fluxes from the gas. A semi empirical model for the particle-wall interaction is presented. Depending on the input conditions, the erosion mass loss of a charring ablator using an engineering correlation is also discussed.

Research paper thumbnail of Electrostatic Probe and Camera Measurements for Modeling the iMPD SIMP-LEX

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2007

Research paper thumbnail of Advanced plasma (propulsion) concepts at IRS

Vacuum, 2013

Several advanced plasma propulsion designs have been developed and characterized at IRS in the pa... more Several advanced plasma propulsion designs have been developed and characterized at IRS in the past years. Among them are the hybrid thruster TIHTUS, the steady state applied field thrusters AF MPD ZT1 and ZT2 and advanced iMPD designs. These concepts show promising potential for future missions. The paper will discuss the designs and their operational features.

Research paper thumbnail of Current Electric Propulsion Development Program at IRS