06 Fakultät Luft- und Raumfahrttechnik und Geodäsie
Permanent URI for this collectionhttps://elib.uni-stuttgart.de/handle/11682/7
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Item Open Access Smart ground support equipment : the design and demonstration of robotic ground support equipment for small spacecraft integration and verification(2024) Kottmeier, Sebastian; Wittje, Philipp; Klinkner, Sabine; Essmann, Olaf; Suhr, Birgit; Kirchler, Jan-Luca; Ho, Tra-MiIn order to reduce the costs of integration and verification processes and to optimize the assembly, integration and verification (AIV) flow in the prototype development of small- and medium-sized spacecrafts, an industrial six-axis robot was used as a universal mechanical ground support equipment instead of a tailored prototype specific ground support equipment (GSE). In particular, a robotic platform offers the possibility of embedding verification steps such as mass property determination into the integration process while offering a wider range of ergonomic adaption due to the enhanced number of degrees of freedom compared to a classical static Mechanical GSE (MGSE). This reduces development costs for projects and enhances the flexibility and ergonomics of primarily mechanical AIV operations. In this paper, the robotic MGSE system is described, the operational prospects for in-line verification are elaborated and an example is given showing the possibilities and challenges of its operational use as well as its in-line mass determination capabilities. For this purpose, a method has been developed that allows for the precise measurement of the spacecraft mass using the robot’s existing technology without the need for additional hardware. Subsequent work will extend this to determine the center of gravity and the moments of inertia of the payload on the robotic MGSE.Item Open Access Optimierung eines Hochdruckelektrolysesystems für regenerative Brennstoffzellensysteme(2023) Fremdling, Fabian; Fasoulas, Stefanos (Prof. Dr.-Ing)Diese Dissertation fasst die Entwicklung eines Hochdruckelektrolysesystems mit einem Betriebsdruck von 100 bar als Teil eines regenerativen Brennstoffzellensystems (RFCS) für Luft- und Raumfahrtanwendungen zusammen. Die Entwicklung basiert auf den zuvor durchgeführten Optimierungsmaßnahmen eines alkalischen Wasserelektrolyseurs, dem ein Zelldesign mit immobilem Elektrolyt und direkter Wasserzufuhr in ein Doppeldiaphragma zugrunde liegt. Die Probleme bei diesem Elektrolyseur liegen in der Unterbrechung der ionischen Leitfähigkeit durch Inhomogenitäten in der Elektrolytkonzentration und Gasansammlungen im Elektrolytbereich, die im Betrieb auftreten, sowie in der Versorgung der Kathode mit Wasser. Dies wird experimentell abgebildet und theoretisch beschrieben. Verschiedene Maßnahmen zur Behebung der Probleme werden vorgestellt, jedoch kann kein zufriedenstellender Betrieb erreicht werden, was zu einer Änderung des Zelldesigns führt. Anstatt einer direkten Wasserversorgung ins Doppeldiaphragma wird eine Elektrolytzirkulation durch den Kathodenraum implementiert und ein Diaphragma entfernt. Diese Änderungen bringen eine Separationseinheit für Wasserstoff vom Elektrolyt sowie eine zusätzliche Pumpe mit sich, der Elektrolyt liegt nun mobil vor. Somit erhöht sich die Systemkomplexität, die uneingeschränkte Raumfahrttauglichkeit ist zunächst nicht gegeben. Dieses neue Elektrolysesystem wird anschließend in zahlreichen Testreihen charakterisiert. Erzielt werden auf Zellebene eine maximale Effizienz von 90.4 % bei 0.509 A/cm², ein möglicher Stromdichtebereich bis 0.76 A/cm², ein Betriebsdruck von 100 bar (Wasserstoff und Sauerstoff) und ein Temperaturbereich von 30-90 °C. Die so gewonnenen Versuchsdaten bilden, zusammen mit theoretischen Grundlagen und weiteren experimentellen Daten, die Basis für eine Modellierung des Systems. Diese Modellierung wird in Matlab/Simulink erstellt und bildet das gesamte Elektrolysesystem ab. Mithilfe der Modellierung können Betriebsparameter des Elektrolysesystems optimiert sowie das Verhalten des Systems in bestimmten Betriebspunkten vorhergesagt werden. Das Modell selbst kann in eine RFCS Gesamtsystemmodellierung implementiert werden. Des Weiteren werden in dieser Arbeit Untersuchungen zur Gasreinheit des Elektrolysesystems durchgeführt. Dies beinhaltet theoretische und experimentelle Untersuchungen zur Gasverunreinigung von Elektrolysegasen sowie Konzepte und Untersuchungen zur Reinigung dieser Gase. Für die für regenerative Brennstoffzellensysteme spezifische Anforderung der Passivphase des Elektrolysesystems wird ein Betriebskonzept erarbeitet. Das Elektrolysesystem ist so umfangreich theoretisch abgebildet, was eine akkurate Auslegung und Anpassung zulässt, auch für Anwendungen außerhalb regenerativer Brennstoffzellensysteme.Item Open Access Science planning for the DESTINY+ Dust Analyzer : leveraging the potential of a space exploration instrument(2024) Sommer, Maximilian; Srama, Ralf (Apl. Prof. Dr.-Ing.)The DESTINY+ Dust Analyzer (DDA) is a highly sophisticated planetary science instrument to provide cutting-edge in-situ characterization of individual cosmic dust grains, with respect to their composition, as well as their physical and dynamical properties. As such, it constitutes a critical component of the upcoming JAXA mission DESTINY+, which is scheduled to launch in 2025. After a three-year cruise phase, the spacecraft will perform a flyby of the target asteroid 3200 Phaethon, with the goal of observing the enigmatic Geminids parent body with two camera instruments, and sampling particles released from its surface with the DDA. Until that flyby, DESTINY+ will execute a highly diverse, ion-engine-driven flight plan that allows DDA to extensively study the dust environments of the Earth, Moon, and interplanetary space - a breadth of science opportunities that is unique to this mission and instrument. This dissertation provides a comprehensive study of the dust types and phenomena possibly encountered by DDA during its journey to Phaethon and applies the principles and methods of science planning to prepare for the operational phase of the mission. The work synthesizes technical considerations and scientific analyses of relevant cosmic dust populations, aiming to optimize DDA’s scientific potential. Detailed examinations of spacecraft and instrument factors, such as the dynamic spacecraft attitude during the near-Earth phase or the instrument’s two-axis pointing mechanism, lay the groundwork for the scientific planning. The thorough analysis of known (and lesser known) dust populations in the inner solar system and of previous relevant measurements by other dust instruments form the core of the study. Finally, the findings are consolidated into a draft science activity plan for the entire mission, as well as exemplary pointing timelines to be executed by the instrument for optimal scientific return. The latter is accomplished with the DOPE tool, which aids in intuitive and efficient planning of DDA observations, having been developed in the scope of this project. The presented work builds the foundation for the scientific operations of DDA, setting it up for a successful and scientifically impactful mission. The findings of this study also provide a valuable perspective for other ventures of in-situ dust astronomy to the inner solar system and contribute to the field of cosmic dust as a whole.Item Open Access Merging spacecraft software development and system tests : an agile verification approach(2021) Bucher, Nico; Eickhoff, Jens (Prof. Dr.-Ing.)In this dissertation, the author describes an agile verification approach for spacecraft onboard software that allows for software development guided by system tests performed with the actual spacecraft. The approach was applied for the Flying Laptop small satellite, built and operated by the Institute of Space System (IRS) at the University of Stuttgart, Germany. This work contains examples of practical experience gathered during the system testing campaign of Flying Laptop.Item Open Access Simulating asteroid impacts and meteor events by high-power lasers : from the laboratory to spaceborne missions(2023) Ferus, Martin; Knížek, Antonín; Cassone, Giuseppe; Rimmer, Paul B.; Changela, Hitesh; Chatzitheodoridis, Elias; Uwarova, Inna; Žabka, Ján; Kabáth, Petr; Saija, Franz; Saeidfirozeh, Homa; Lenža, Libor; Krůs, Miroslav; Petera, Lukáš; Nejdl, Lukáš; Kubelík, Petr; Křivková, Anna; Černý, David; Divoký, Martin; Pisařík, Michael; Kohout, Tomáš; Palamakumbure, Lakshika; Drtinová, Barbora; Hlouchová, Klára; Schmidt, Nikola; Martins, Zita; Yáñez, Jorge; Civiš, Svatopoluk; Pořízka, Pavel; Mocek, Tomáš; Petri, Jona; Klinkner, SabineMeteor plasmas and impact events are complex, dynamic natural phenomena. Simulating these processes in the laboratory is, however, a challenge. The technique of laser induced dielectric breakdown was first used for this purpose almost 50 years ago. Since then, laser-based experiments have helped to simulate high energy processes in the Tunguska and Chicxulub impact events, heavy bombardment on the early Earth, prebiotic chemical evolution, space weathering of celestial bodies and meteor plasma. This review summarizes the current level of knowledge and outlines possible paths of future development.Item Open Access Assessment of high enthalpy flow conditions for re-entry aerothermodynamics in the plasma wind tunnel facilities at IRS(2021) Loehle, Stefan; Zander, Fabian; Eberhart, Martin; Hermann, Tobias; Meindl, Arne; Massuti-Ballester, Bartomeu; Leiser, David; Hufgard, Fabian; Pagan, Adam S.; Herdrich, Georg; Fasoulas, StefanosThis article presents the full operational experimental capabilities of the plasma wind tunnel facilities at the Institute of Space Systems at the University of Stuttgart. The simulation of the aerothermodynamic environment experienced by vehicles entering the atmosphere of Earth is attempted using three different facilities. Utilizing the three different facilities, the recent improvements enable a unique range of flow conditions in relation to other known facilities. Recent performance optimisations are highlighted in this article. Based on the experimental conditions demonstrated a corresponding flight scenario is derived using a ground-to-flight extrapolation approach based on local mass-specific enthalpy, total pressure and boundary layer edge velocity gradient. This shows that the three facilities cover the challenging parts of the aerothermodynamics along the entry trajectory from Low Earth Orbit. Furthermore, the more challenging conditions arising during interplanetary return at altitudes above 70 km are as well covered.Item Open Access Untersuchungen zum Einsatzpotential und zur Inkjet-Fertigung von Mischpotential-Elektrolytsystemen(2022) Scherer, Philip; Fasoulas, Stefanos (Prof. Dr.-Ing.)Item Open Access 3-D visualization of transparent fluid flows from snapshot light field data(2021) Eberhart, Martin; Loehle, Stefan; Offenhäuser, PhilippThis paper presents the use of light field data, recorded in a snapshot from a single plenoptic camera, for 3-D visualization of transparent fluid flows. We demonstrate the transfer of light field deconvolution, a method so far used only in microscopy, to macroscopic scales with a photographic setup. This technique is suitable for optically thin media without any additional particles or tracers and allows volumetric investigation of non-stationary flows with a simple single camera setup. An experimental technique for the determination of the shift-variant point spread functions is presented, which is a key for applications using a photographic optical system. The paper shows results from different test cases with increasing complexity. Reconstruction of the 3-D positions of randomly distributed light points demonstrates the achievable high accuracy of the technique. Gas flames and droplets of a fluorescent liquid show the feasibility of the proposed method for the visualization of transparent, luminous flows. The visualizations exhibit high quality and resolution in low-contrast flows, where standard plenoptic software based on computer vision fails. Axial resolution depends on the data and is about an order of magnitude lower than the lateral resolution for simple point objects. The technique also allows the time-resolved analysis of flow structures and the generation of 3D3C-velocity fields from a sequence of exposures.Item Open Access Satellite formation and instrument design for autonomous meteor detection(2022) Petri, Jona; Klinkner, Sabine (Prof. Dr.-Ing.)A meteoroid entering the Earth atmosphere causes a light phenomenon called meteor. Meteoroids origin from comets or asteroids, these small particles are mostly unchanged since the formation of the solar system. Therefore, observing meteors gives insight on how our solar system evolved and from what materials it consists. Additionally, meteor observations are used to improve meteoroid flux models, which are needed to safely plan space activities. Meteor observations from space offer several advantages compared to ground-based meteor observations, such as greater coverage and an unobstructed view to the meteor as well as weather independence. Using two satellites for meteor observations allows to calculate the trajectory of a meteor and determine its parent body. In this thesis two example satellites are used to develop and design a mission and an instrument for the visual observation of meteors. The first mission is called SOURCE (Stuttgart Operated University Research Cubesat for Evaluation and Education), a three unit CubeSat dedicated to technology demonstrations, demise investigation and meteor observation. Here, a visual monochromatic camera is used to observe meteors and qualify the instrument. The second mission is called FACIS (Formation for Analysis of Cosmic Particles), which consists of a formation of two identical small satellites dedicated to meteor observation and dust measurements. Since two satellites are used, meteors are observed stereoscopically to determine meteor trajectories. Two main challenges of spaceborne meteor observation are addressed in this thesis: The first one is the design of the mission and the instrument. This includes analysing the influence of the satellite bus parameters (e.g. attitude knowledge accuracy) and formation parameters (e.g. satellite distance) on the scientific output of a (stereoscopic) meteor observation mission. Furthermore, the instrument parameters must be analysed and optimized depending on the scientific objective of the mission. Thus, different simulations are developed to evaluate the scientific output depending on satellite bus and formation parameters as well as instrument parameters. These simulations were used to develop the mission, including the design of the instrument and deriving requirements for the satellite bus. Furthermore, the ideal formation parameters depending on the scientific objective and instrument design could be determined. The second challenge of a space based meteor observation mission is the limited downlink capacity of a satellite. This requires onboard processing of the image data. An algorithm must be used, to identify images containing a meteor and downlink only these images. Existing detection algorithms can not be used, since the satellite moves during an observation and thus, the background is moving as well. Therefore, a new meteor detection algorithm called SpaceMEDAL (Spaceborne MEteor Detection ALgorithm) based on optical flow calculations is developed. This algorithm is tested by developing and using an artificial meteor simulation called ArtMESS (Artificial Meteorvideo Simulation Software) to generate test data and a test bed to display and image this data. A challenge for the algorithm is the limited processing power. Thus, the developed algorithm is accelerated by moving functions to dedicated hardware of the used on board computer. Finally, the observation concept and scientific output of both missions can be determined, by taking into account the instrument parameters, satellite bus and formation parameters as well as the algorithm performance and operational constraints of the satellite. For both missions a concept resulting in a significant observation of meteors could be developed. All in all, this thesis shows that a space based meteor observation mission using small satellites is possible. The main aspects of the mission design were analysed in order to design two different missions. The main aspects addressed in this thesis are the instrument design, the satellite bus and formation requirements and the algorithm development. All three aspects could be successfully revised and the missions and the instrument could be developed. Furthermore, a demonstrator instrument for the SOURCE mission could be built, including the development of the detection algorithm.Item Open Access Upgrades of a small electrostatic dust accelerator at the University of Stuttgart(2023) Li, Yanwei; Bauer, Marcel; Kelz, Sebastian; Strack, Heiko; Simolka, Jonas; Mazur, Christian; Sommer, Maximilian; Mocker, Anna; Srama, RalfIn this paper, we describe the upgrade of a small electrostatic dust accelerator located at the University of Stuttgart. The newly developed dust source, focusing lens, differential detector and linac stage were successfully installed and tested in the beam line. The input voltage range of the dust source was extended from 0-20 kV to 0-30 kV. A newly developed dust detector with two differential charge sensitive amplifiers is employed to monitor particles with speeds from several m/s to several km/s and with surface charges above 0.028 fC. The post-stage linac provides an additional acceleration ability with a total voltage of up to 120 kV. The entire system of this dust accelerator works without protection gas and without a complex high voltage terminal. The volumes to be pumped down are small and can be quickly evacuated. The new system was used to accelerate micron- and submicron-sized metal particles or coated mineral materials. Improvements in the acceleration system allow for a wider variety of dust materials and new applications.