Scharringhausen, Marco
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Preferred name
Scharringhausen, Marco
Official Name
Scharringhausen, Marco
Alternative Name
Scharringhausen, M.
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GND
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Item-typ:Veröffentlichung, Thermal and Mechanical Design and Simulation for the first high precision Quantum Optics Experiment on a Sounding Rocket(2016-10-07); ; ; The MAIUS-1 payload is a high precision quantum optics experiment about to fly on a VSB-30 sounding rocket with the scientific objective to demonstrate the feasibility of creating the first Bose-Einstein condensates and performing atom interferometry in Space. To achieve these goals the experiment is using various sensitive instruments imposing strong requirements on the thermal and mechanical design. In the introduction this thesis gives a short overview and characterization of available microgravity platforms in Europe. Moreover a detailed characterization of the environment aboard the VSB-30 sounding rocket is presented based on flight data from former MASER and TEXUS missions. In the main chapters the mechanical and thermal design of the MAIUS-1 scientific payload is described in detail. This includes various technical solutions as for example a low-cost vibration isolation, a sealing for RADAX hull segments of pressurized payloads or umbilicals to provide water cooling until lift-off. In addition the test methods and results for the different payload components is presented. The design and test of the ultra-high vacuum system with a nominal pressure of 1E-10 hPa is described in a dedicated chapter. This includes theoretical background on outgassing of technical surfaces and calculation of the conductance of a vacuum system. Different pumping and sealing techniques are introduced. Furthermore the results of intensive testing of Conflat (CF) and Indium sealings under vibrational and static loads are presented as well as test results for the entire pumping system. The thermal control system of the MAIUS-1 scientific payload has been designed using multiple MATLAB codes in combination with ANSYS to estimate the heat flux into the rocket hull by aerodynamic heating during ascent as well as the heat transfer from the heated rocket hull to the system housing walls by natural convection. These codes and their theoretical background are presented herein as well. The thesis closes with recommendations and possible improvements for future space-born quantum optics experiments.Dissertation619 401 - Some of the metrics are blocked by yourconsent settings
Item-typ:Veröffentlichung, Methodology for the Design and Verification of Small Body Landers with a Crushable Impact Absorber(2023-05-15); ; ; ; The interest for the exploration of small solar system bodies has increased significantly over the past 2 decades and has since evolved from a side topic to one of the corner stones in the international science community. Major disciplines include studying the formation of the solar system, the evolution of life within, planetary defense against potential hazardous objects, as well as human exploration and resource utilization. Recent missions and studies showed that a common understanding was established to enhance high-class missions with carrying-along capabilities for detachable and specialized systems. Specifically the touchdown and landing on the surface is a very risky maneuver, but enables unprecedented high resolution in-situ investigations. However, non-propelled landing systems were designed so far to land on very small objects only with mean diameters of < 4 km (e.g. Near-Earth objects). The general interest has shifted only recently to larger bodies with mean diameters of > 10 km (e.g. Main-Belt and Trojan objects). But with increasing size and density of the target the gravitational attraction on a separated lander increases significantly, which results in much higher touchdown velocities and potential harmful impact loads. For these types of landers, however, no adequate protection system currently exists! For this reason, this thesis reviews existing methods of impact and crush mechanics, which were recombined and partially extended for the defined scope of application, to formulate a new system context and a coherent design and verification methodology for such a new technology. More specifically, this dissertation investigated the concept to enhance deployable non-propelled small body landers with a crushable and expendable exo-shell, with the main objective to sustain higher landing velocities in the range of 1 – 5 m/s by simultaneously lowering impact loads to < 100G. Furthermore, the work aimed at creating a comprehensive and applicable guide from the first concept idea to a verified innovative system design. It therefore performed the entire processing chain, including concept analysis and evaluation, system design and functional demonstration as well as empirical investigations using laboratory experiments and numerical simulations in the to be expected low gravity environment. Hereby providing fundamental details and the required tools to be applied by system and project engineers in the future to effectively design and verify small body landers with increased system performance and reliability as well as reduced overall development costs.Dissertation213 151