Michael Lachenmann | Institut für Raumfahrtsysteme

Dipl.-Ing. Michael Lachenmann, Wissenschaftlicher Mitarbeiter

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Anschrift	Universität Stuttgart Institut für Raumfahrtsyteme Pfaffenwaldring 31 D-70569 Stuttgart

Forschungsthemen
Kleinsatellit Lunar Mission BW1 Kleinsatellit Flying Laptop Niedrige Mondorbits Auslegung und Entwicklung von Kamerasystemen
Ausbildung
seit 2006	Wissenschaftlicher Mitarbeiter am Institut für Raumfahrtsysteme der Universität Stuttgart
2000 - 2006	Diplomstudium Luft- und Raumfahrttechnik, Universität Stuttgart
	Diplomarbeit im Bereich Kleinsatelliten am Institut für Raumfahrtsysteme, Universität Stuttgart: "Utilization of Low-Cost-CMOS-/CCD-Cameras on a Small Satellite for Monitoring and Public Relations"
	Studienarbeit am Institut für Aerodynamik und Gasdynamik der Universität Stuttgart: "High-order Boundary Discretization of a Discontinuous-Galerkin Scheme"
1999	Abitur am Max-Planck-Gymnasium Nürtingen
Publikationen
Analyses of orbital lifetime and observation conditions of small lunar satellites O. Zeile, M. Lachenmann, E. Baumstark, A. Mohr, D. Bock, R. Laufer, N. Sneeuw, and H.-P. Roeser. Acta Astronautica. Vol. 66(3-4):516-527, Februar 2010. [Abstract] Abstract: The Moon's gravitational field shows large inhomogeneities that strongly influence the shape of an orbit and can severely influence the orbital lifetime and observation conditions of any spacecraft orbiting the Moon. Small lunar spacecrafts are especially affected by those unstable orbits because their limited mass leaves little to no fuel reserves for excessive orbit maintenance maneuvers. Therefore, it may be favorable to choose an orbit, which features not the ideal observation conditions, but requires less Delta-V for orbit maintenance. These limitations have to be considered during mission design as they affect both the potential capabilities and the lifetime of the satellite. To characterize these limiting factors, simulations and analyzes based on up-to-date high degree and order gravity models were conducted with regard to the upcoming small lunar satellite Lunar Mission BW1 of the Institute of Space Systems (IRS) of the Universitaet Stuttgart. The cubical-shaped spacecraft with an edge length of 1 m and a mass of approximately 200 kg will use its own all-electrical propulsion system to reach a high-inclined low lunar orbit. Due to the limited fuel mass and operational lifetime of the thrusters, we consider the orbit maintenance capabilities of the probe to be minimal. Measures to maximize orbital lifetime with the least amount of propellant have to be taken and target orbits have to be examined carefully. This paper shows the results of simulations, which analyze ground coverage and access times, as well as simulations of orbital lifetime and changes in orbital parameters. Additionally, suitable, long lasting target orbits for small lunar spacecrafts are discussed. Analyses of orbital lifetime and observation conditions of small lunar satellites O. Zeile, M. Lachenmann, E. Baumstark, A. Mohr, D. Bock, R. Laufer, N. Sneeuw, and H.-P. Roeser. 59th International Astronautical Congress (IAC), Glasgow, United Kingdom, 2008. [Abstract] Abstract: The Moon's gravitational field shows large inhomogeneities that strongly influence the shape of an orbit and can severely influence the orbital lifetime and observation conditions of any spacecraft orbiting the Moon. Small lunar spacecrafts are especially affected by those unstable orbits because their limited mass leaves little to no fuel reserves for excessive orbit maintenance maneuvers. Therefore, it may be favorable to choose an orbit, which features not the ideal observation conditions, but requires less Delta-V for orbit maintenance. These limitations have to be considered during mission design as they affect both the potential capabilities and the lifetime of the satellite. To characterize these limiting factors, simulations and analyses based on up-to-date high degree and order gravity models were conducted with regard to the upcoming small lunar satellite Lunar Mission BW1 of the Institute of Space Systems (IRS) of the Universitaet Stuttgart. The cubical-shaped spacecraft with an edge length of 1 m and a mass of approximately 200 kg will use its own all-electrical propulsion system to reach a high-inclined low lunar orbit. Due to the limited fuel mass and operational lifetime of the thrusters, we consider the orbit maintenance capabilities of the probe to be minimal. Measures to maximize orbital lifetime with the least amount of propellant have to be taken and target orbits have to be examined carefully. This paper shows the results of simulations, which analyze ground coverage and access times, as well as simulations of orbital lifetime and changes in orbital parameters. Additionally, suitable, long lasting target orbits for small lunar spacecrafts are discussed. Academic Small Lunar Satellite Mission Concept and Design R. Laufer, D. Bock, M. Lachenmann, H.-P. Roeser, and Lunar Mission BW1 Project Team. 59th International Astronautical Congress (IAC), Glasgow, United Kingdom, 2008. [Abstract] Abstract: Earth orbiting academic small satellites are without any doubt useful research platforms, technology demonstration tools as well as educational instruments for more than 25 years. On the basis of the increasing new and world wide interest in lunar exploration an academic lunar probe would be a next logical step in small satellite development. The Stuttgart Small Satellite Program of the Institute of Space Systems (IRS) of the Universitaet Stuttgart, Germany, consists of four different small satellite projects in the areas of technology demonstration, Earth remote sensing, astronomical observation, re-entry research and space exploration. The Lunar Mission BW1 is an all-electrical small lunar orbiter of approx. 1 m cube and around 200 kg launch mass. Planned to be launched as a piggyback payload into a Geosynchronous Transfer Orbit (GTO) later than 2010 the probe should use solar-electric propulsion systems to be transferred to the Moon into a highly inclined circular low lunar orbit. The orbiter will perform technology demonstrations, remote sensing and in-situ research experiments. The paper will describe the requirements, boundary conditions and challenges of implementing and accomplishing a lunar mission within an academic environment. Steps towards a small lunar satellite within a program with possibilities for verification and gaining experience will be shown. The integration within education and research activities will be presented as well as the established network of partners, facilities, cababilities and tools which were built up to achieve the program's goals. Experiments and Instruments of Lunar Mission BW1 M. Lachenmann, R. Laufer, and H.-P. Roeser. European Planetary Science Congress, Potsdam, Germany, Conference contribution, 2007. [Abstract] Abstract: As part of the Stuttgart Small Satellite Program, Lunar Mission BW1 - a small lunar orbiter - is currently developed at the Institute of Space Systems (IRS) of the Universität Stuttgart, Germany. The cubical shaped spacecraft with an edge length of 1 m and a mass of approximately 200 kg will be launched into GTO and will use its own all-electrical propulsion system, consisting of a thermal arcjet and a cluster of instationary magneto plasma dynamical (IMPD) thrusters to reach a high-inclined low lunar orbit. This paper gives an overview about the mission of the satellite and some possible experiments during its 2 year journey in cis-lunar space as well as during its operational phase in lunar orbit. Being a technology demonstration mission, one of its main experiments is the operation of the propulsion system whose behavior in space environment has to be monitored carefully. This paper describes a possible payload of the spacecraft including a matrix camera operating in the visual and near infrared spectral range, a micro-bolometer array to detect thermal infrared radiation in high resolution, an instrument to count lunar impact flashes on the lunar surface, and dust and space debris sensors. Furthermore, it gives information about requirements and constraints including access times and possible data rates using the Ka-band communication link. Video compression of the Flying Laptop for low bandwidth satellite links M. Lachenmann, S. Walz, and H.-P. Roeser. R. Sandau, H.-P. Roeser, A. Valenzuela, (ed.) Small Satellites for Earth Observation, Berlin, Germany, Conference contribution, April 2007. [Abstract] Abstract: The Flying Laptop is the first micro-satellite of the Stuttgart Small Satellite Program. It is currently being developed at the Institute of Space Systems of the Universität Stuttgart. This paper describes the concept to highly compress a steady stream of Earth observation images for non-scientific usage. This lossy compression technique uses data reduction combined with post-processing in order to fit a low bandwidth requirement. It uses an approach known as "Motion compensation" but was especially developed for space application.
Betreute Studien-, Diplom- und Projektarbeiten
Aufbau und Charakterisierung des Optikmessplatzes für das multispektrale Kamerasystem MICS des Kleinsatelliten Flying Laptop - Design and Characterization of the Optical Test Facility for the Multispectral Imaging Camera System MICS of the Small Satellite Flying Laptop A. Büttner. Advisors: M. Lachenmann, F. Böhringer, and H.-P. Roeser. University of Stuttgart, Institute of Space Systems. Diploma thesis, February 2010. Einbindung einer COTS-Industriekamera als Panoramakamera für die Kleinsatellitenmission Flying Laptop - Integration of a COTS Industrial Camera as Panoramic Camera for the Small Satellite Mission Flying Laptop T. Aust. Advisors: F. Böhringer, M. Lachenmann, and H.-P. Roeser. University of Stuttgart, Institute of Space Systems. Diploma thesis, August 2009. Anforderungen an die TICS Kamera der Lunar Mission BW1 unter Berücksichtigung der Verwendung von SERTIS-Daten - Requirements of the TICS camera of Lunar Mission BW1 considering the application of SERTIS data M. Horstmann. Advisors: M. Lachenmann and R. Laufer. University of Stuttgart, Institute of Space Systems. Technical report, October 2008. Detaillierte Auslegung der Primärstruktur und Konzeption des Ingenieurmodells der Lunar Mission BW1 - Detailed Design of the Primary Structure and Conception of the Engineering Model of the Lunar Mission BW1 V. Mariathasan. Advisors: M. Lachenmann, R. Laufer, M. Lengowski, and H.-P. Roeser. University of Stuttgart, Institute of Space Systems. Study thesis, October 2008. Prediction of the orbital elements and maneuver strategies of a low lunar orbit spacecraft in a non-spherical gravitational field - Parametervorhersage und Flugstrategien für eine Sonde im niedriegen Mondorbit im nichtsphärischen Gravitationasfeld E. Baumstark. Advisors: M. Lachenmann, O. Zeile, and H.-P. Roeser. University of Stuttgart, Institute of Space Systems. Study thesis, August 2008. Entwurf einer Niedrigschub Erde-Mond-Transferbahn mit STK - Developement of a Low-Thrust Earth-Moon-Trajectory with STK A. Zöllner. Advisors: M. Lachenmann, O. Zeile, and H.-P. Roeser. University of Stuttgart, Institute of Space Systems. Study thesis, August 2008. Lunar Mission BW1 Radio Experiment A. Delgado González. Advisors: M. Lachenmann and R. Laufer. University of Stuttgart, Institute of Space Systems. Technical report, September 2007. Lunare Erkundung im thermischen Infrarotbereich - Lunar Exploration in the thermal infrared J. Kuhlmann. Advisors: R. Laufer and M. Lachenmann. University of Stuttgart, Institute of Space Systems. Technical report, March 2007.