Refine
Year of publication
Institute
- Fachbereich Luft- und Raumfahrttechnik (767) (remove)
Has Fulltext
- no (767) (remove)
Document Type
- Article (367)
- Conference Proceeding (197)
- Book (107)
- Part of a Book (43)
- Patent (19)
- Doctoral Thesis (10)
- Report (8)
- Conference: Meeting Abstract (6)
- Other (3)
- Conference Poster (2)
Keywords
- avalanche (6)
- solar sail (5)
- hydrogen (4)
- snow (4)
- GOSSAMER-1 (3)
- Hydrogen (3)
- MASCOT (3)
- Wind Tunnel (3)
- Drinfeld modules (2)
- Flight Test (2)
- Mars (2)
- Micromix (2)
- NOx emissions (2)
- PCM (2)
- Pitching Moment (2)
- Solar sail (2)
- Spacecraft (2)
- Trajectory Optimization (2)
- Transcendence (2)
- Wave Drag (2)
- combustor development (2)
- fuels (2)
- industrial gas turbine (2)
- multiple NEA rendezvous (2)
- small spacecraft (2)
- t-modules (2)
- 1P hub loads (1)
- Active humidity control (1)
- Aerodynamic Drag (1)
- Aeroelasticity (1)
- Aircraft design (1)
- Analogue Environments (1)
- Antarctic Glaciology (1)
- Antarctica (1)
- Asteroid Deflection (1)
- Atmospheres (1)
- Attitude dynamics (1)
- Automated Optimization (1)
- Avalanche (1)
- Bumblebees (1)
- CO2 emission reduction targets (1)
- Capacity Building Higher Education (1)
- Carsharing (1)
- Certification Rule (1)
- Combustion (1)
- Commercial Vehicle (1)
- Common Rail Injection System (1)
- Correlations (1)
- Cost function (1)
- Cryobot (1)
- DLR-ESTEC GOSSAMER roadmap for solar sailing (1)
- Design rules (1)
- Diesel Engine (1)
- Direkteinblasung (1)
- Drag (1)
- Drag Reduction (1)
- Driving cycle recognition (1)
- Dry-low-NOx (DLN) combustion (1)
- Dynamic modeling (1)
- ECMS (1)
- ESATAN (1)
- ESATAN-TMS (1)
- Electrical Flight (1)
- Electrical vehicle (1)
- Electrochemical impedance spectroscopy (1)
- Emissions (1)
- Energy management strategies (1)
- Engine Efficiency (1)
- Epistemische Neugier (1)
- Erasmus+ United (1)
- European Framework and South East Asia (1)
- European Transient Cycle (1)
- Evacuation Rule (1)
- Evolutionary Neurocontrol (1)
- Exoplanet (1)
- Extraterrestrial Glaciology (1)
- Fault detection (1)
- Flame residence time (1)
- Flame temperature (1)
- Flight Mechanics (1)
- Flight Tests (1)
- Flight control (1)
- Flutter (1)
- Friction Drag (1)
- Fuel cell (1)
- Fuel-flexibility (1)
- GEO (1)
- Gas turbine combustion (1)
- Geometry (1)
- Glaciological instruments and methods (1)
- Gossamer (1)
- Gossamer structures (1)
- Green aircraft (1)
- Guide Tube (1)
- Health management system (1)
- High hydrogen combustion (1)
- Higher derivations (1)
- Human factors (1)
- Hybrid Propellants (1)
- Hybrid-electric aircraft (1)
- Hydrogen combustion (1)
- Hydrogen gas turbine (1)
- Hyperdifferentials (1)
- ITS (1)
- Ice Melting (1)
- Ice melting probe (1)
- Ice penetration (1)
- Icy Moons (1)
- Icy moons (1)
- Impedance analysis (1)
- Inflight Regeneration, Recuperation (1)
- Infused Thermal Solutions (1)
- Interplanetary flight (1)
- Interstellar objects (1)
- Jupiter (1)
- Kalman filter (1)
- LEO (1)
- Ladungswechsel (1)
- Leading Edge Vortex (1)
- Low NOx (1)
- Low emission (1)
- Low-Thrust Propulsion (1)
- Low-field NMR (1)
- Lunar Surface (1)
- MAV (1)
- Mach Number (1)
- Malaysian Automotive Industry (1)
- Malaysian automotive industry (1)
- Melting Efficiency (1)
- Melting Performance (1)
- Melting Probe (1)
- Micromix combustion (1)
- Missions (1)
- Multi-objective optimization (1)
- Multidisciplinary Design Optimization (1)
- Multiphase (1)
- NMR exchange relaxometry (1)
- NOx (1)
- Noise Exposure (1)
- Non-model-based Evaluation (1)
- Nozzle (1)
- Obstacle avoidance (1)
- Ocean Worlds (1)
- Ocean worlds (1)
- Online diagnostic (1)
- Orbital dynamics (1)
- PEM fuel cell (1)
- PEM fuel cells (1)
- PHILAE (1)
- Parabolized Stability Equation (1)
- Passenger compartment (1)
- Path planning (1)
- Payload (1)
- Periods (1)
- Planetary Protection (1)
- Planetary exploration (1)
- Predictive battery discharge (1)
- Propeller Aerodynamics (1)
- Propeller whirl flutter (1)
- RAMMS (1)
- Relative air humidity (1)
- Reusable Rocket Engines (1)
- Selbstwirksamkeit (1)
- Selective Catalytic Reduction (1)
- Sequence-Search (1)
- Severe Accident (1)
- Small Solar System Body Lander (1)
- Small Spacecraft (1)
- Small spacecraft (1)
- Snow (1)
- Solar Power Sail (1)
- Solar Sail (1)
- Sonic Boom (1)
- Spacecraft Trajectory Optimization (1)
- Specific Fuel Consumption (1)
- Spectroscopy (1)
- Statistics (1)
- Subclacial exploration (1)
- Subglacial lakes (1)
- Suction (1)
- Supersonic Flow (1)
- Supersonic Wind Tunnel (1)
- TICTOP (1)
- Technology Challenge (1)
- Technology Transfer (1)
- Thermal Fatigue Testing (1)
- Thermal Model (1)
- Thermal analysis (1)
- Thermal comfort (1)
- Thermal management (1)
- Trajectories (1)
- Transit (1)
- UAV (1)
- UTeM Engineering Knowledge Transfer Unit (1)
- Unmanned Air Vehicle (1)
- Unsteady aerodynamics (1)
- Variable Geometry (1)
- Verbrennungsmotor (1)
- Wasserstoff (1)
- adaptive systems (1)
- aircraft engine (1)
- artificial intelligence (1)
- assistance system (1)
- asteroid lander (1)
- asteroid sample return (1)
- attitude dynamics (1)
- aviation application (1)
- combustion (1)
- combustor (1)
- control system (1)
- debris flow (1)
- electrically driven compressors (1)
- electro mobility (1)
- emission (1)
- emission index (1)
- engine demonstration (1)
- flotilla missions (1)
- fuel cell (1)
- fuel cell systems (1)
- fuel cell vehicle (1)
- gamification (1)
- gas turbine (1)
- habitability (1)
- health management systems (1)
- heliosphere (1)
- ice moons (1)
- icy moons (1)
- intelligent control (1)
- intelligent energy management (1)
- internal combustion engine (1)
- intrinsische Motivation (1)
- ion propulsion (1)
- latent heat (1)
- lattice (1)
- life detection (1)
- low-thrust (1)
- low-thrust trajectory optimization (1)
- machine learning (1)
- manufacturing (1)
- near-Earth asteroid (1)
- nitric oxides (1)
- optimization system (1)
- orbit control (1)
- orbital dynamics (1)
- passive thermal control (1)
- planetary defence (1)
- responsive space (1)
- sailcraft (1)
- sample return (1)
- small solar system body characterisation (1)
- small spacecraft asteroid lander (1)
- small spacecraft solar sail (1)
- solar sails (1)
- solar system (1)
- space missions (1)
- star tracker (1)
- subroutine (1)
- system engineering (1)
- technology transfer (1)
- thermo-physical (1)
- underwater vehicle (1)
- vollvariabler Ventilbetrieb (1)
Optical Instruments require an extremely stable thermal surrounding to prevent loss of data quality by misalignments of the instrument components resulting from material deformation due to temperature f luctuations (e.g. from solar intrusion). Phase Change Material (PCM) can be applied as a thermal damper to achieve a more uniform temperature distribution. The challenge of this method is, among others, the integration of PCM into affected areas. If correctly designed, incoming heat is latently absorbed during phase change of the PCM, i.e. the temperature of a structure remains almost constant. In a cold phase, the heat during phase change is released again latently until the PCM returns to its original state of aggregation. Thus, the structure is thermally stabilized. At FH Aachen– University of Applied Sciences research is conducted to apply PCM directly into the structures of affected components (baffles, optical benches, electronic boxes, etc.). Through the application of Additive Manufacturing, the necessary voids are directly printed into these structures and filled later with PCM. Additive Manufacturing enables complex structures that would not have been possible with conservative manufacturing methods. A corresponding Breadboard was developed and manufactured by Selective Laser Melting (SLM). The current state of research includes the handling and analysis of the Breadboard, tests and a correlation of the thermal model. The results have shown analytically and practically that it is possible to use PCM as an integral part of the structure as a thermal damper. The results serve as a basis for the further development of the technology, which should maximize performance and enable the integration of PCM into much more complex structures.
In the last decades, several hundred exoplanets could be detected thanks to space-based observatories, namely CNES’ COROT and NASA’s Kepler. To expand this quest ESA plans to launch CHEOPS as the f irst small class mission in the cosmic visions program (S1) and PLATO as the 3rd medium class mission, so called M3 . PLATO’s primary objective is the detection of Earth like Exoplanets orbiting solar type stars in the habitable zone and characterisation of their bulk properties. This is possible by precise lightcurve measurement via 34 cameras. That said it becomes obvious that accurate pointing is key to achieve the required signal to noise ratio for positive transit detection. The paper will start with a comprehensive overview of PLATO’s mission objectives and mission architecture. Hereafter, special focus will be devoted to PLATO’s pointing requirements. Understanding the very nature of PLATO’s pointing requirements is essential to derive a design baseline to achieve the required performance. The PLATO frequency domain is of particular interest, ranging from 40 mHz to 3 Hz. Due to the very different time-scales involved, the spectral pointing requirement is decomposed into a high frequency part dominated by the attitude control system and the low frequency part dominated by the thermo-elastic properties of the spacecraft’s configuration. Both pose stringent constraints on the overall design as well as technology properties to comply with the derived requirements and thus assure a successful mission.
Electric flight has the potential for a more sustainable and energy-saving way of aviation compared to fossil fuel aviation. The electric motor can be used as a generator inflight to regenerate energy during descent. Three different approaches to regenerating with electric propeller powertrains are proposed in this paper. The powertrain is to be set up in a wind tunnel to determine the propeller efficiency in both working modes as well as the noise emissions. Furthermore, the planned flight tests are discussed. In preparation for these tests, a yaw stability analysis is performed with the result that the aeroplane is controllable during flight and in the most critical failure case. The paper shows the potential for inflight regeneration and addresses the research gaps in the dual role of electric powertrains for propulsion and regeneration of general aviation aircraft.
This paper discusses a new way of inflight power regeneration for electric or hybrid-electric driven general aviation aircraft with one powertrain for both configurations. Three different approaches for the shift from propulsion to regeneration mode are analyzed. Numerical cal-culation and wind tunnel results are compared and show the highest regeneration potential for the "Windmill" approach, where the propeller blades are flipped, and rotation is reversed. A combination of all regeneration approaches for a realistic flight mission is discussed.
The development and operation of hybrid or purely electrically powered aircraft in regional air mobility is a significant challenge for the entire aviation sector. This technology is expected to lead to substantial advances in flight performance, energy efficiency, reliability, safety, noise reduction, and exhaust emissions. Nevertheless, any consumed energy results in heat or carbon dioxide emissions and limited electric energy storage capabilities suppress commercial use. Therefore, the significant challenges to achieving eco-efficient aviation are increased aircraft efficiency, the development of new energy storage technologies, and the optimization of flight operations. Two major approaches for higher eco-efficiency are identified: The first one, is to take horizontal and vertical atmospheric motion phenomena into account. Where, in particular, atmospheric waves hold exciting potential. The second one is the use of the regeneration ability of electric aircraft. The fusion of both strategies is expected to improve efficiency. The objective is to reduce energy consumption during flight while not neglecting commercial usability and convenient flight characteristics. Therefore, an optimized control problem based on a general aviation class aircraft has to be developed and validated by flight experiments. The formulated approach enables a development of detailed knowledge of the potential and limitations of optimizing flight missions, considering the capability of regeneration and atmospheric influences to increase efficiency and range.
Das Diskussionspapier beschreibt einen Prozess an der FH Aachen zur Entwicklung und Implementierung eines Self-Assessment-Tools für Studiengänge. Dieser Prozess zielte darauf ab, die Relevanz der Themen Digitalisierung, Internationalisierung und Nachhaltigkeit in Studiengängen zu stärken. Durch Workshops und kollaborative Entwicklung mit Studiendekan:innen entstand ein Fragebogen, der zur Reflexion und strategischen Weiterentwicklung der Studiengänge dient.
This work presents the Multi-Bees-Tracker (MBT3D) algorithm, a Python framework implementing a deep association tracker for Tracking-By-Detection, to address the challenging task of tracking flight paths of bumblebees in a social group. While tracking algorithms for bumblebees exist, they often come with intensive restrictions, such as the need for sufficient lighting, high contrast between the animal and background, absence of occlusion, significant user input, etc. Tracking flight paths of bumblebees in a social group is challenging. They suddenly adjust movements and change their appearance during different wing beat states while exhibiting significant similarities in their individual appearance. The MBT3D tracker, developed in this research, is an adaptation of an existing ant tracking algorithm for bumblebee tracking. It incorporates an offline trained appearance descriptor along with a Kalman Filter for appearance and motion matching. Different detector architectures for upstream detections (You Only Look Once (YOLOv5), Faster Region Proposal Convolutional Neural Network (Faster R-CNN), and RetinaNet) are investigated in a comparative study to optimize performance. The detection models were trained on a dataset containing 11359 labeled bumblebee images. YOLOv5 reaches an Average Precision of AP = 53, 8%, Faster R-CNN achieves AP = 45, 3% and RetinaNet AP = 38, 4% on the bumblebee validation dataset, which consists of 1323 labeled bumblebee images. The tracker’s appearance model is trained on 144 samples. The tracker (with Faster R-CNN detections) reaches a Multiple Object Tracking Accuracy MOTA = 93, 5% and a Multiple Object Tracking Precision MOTP = 75, 6% on a validation dataset containing 2000 images, competing with state-of-the-art computer vision methods. The framework allows reliable tracking of different bumblebees in the same video stream with rarely occurring identity switches (IDS). MBT3D has much lower IDS than other commonly used algorithms, with one of the lowest false positive rates, competing with state-of-the-art animal tracking algorithms. The developed framework reconstructs the 3-dimensional (3D) flight paths of the bumblebees by triangulation. It also handles and compares two alternative stereo camera pairs if desired.
Next-generation aircraft designs often incorporate multiple large propellers attached along the wingspan (distributed electric propulsion), leading to highly flexible dynamic systems that can exhibit aeroelastic instabilities. This paper introduces a validated methodology to investigate the aeroelastic instabilities of wing–propeller systems and to understand the dynamic mechanism leading to wing and whirl flutter and transition from one to the other. Factors such as nacelle positions along the wing span and chord and its propulsion system mounting stiffness are considered. Additionally, preliminary design guidelines are proposed for flutter-free wing–propeller systems applicable to novel aircraft designs. The study demonstrates how the critical speed of the wing–propeller systems is influenced by the mounting stiffness and propeller position. Weak mounting stiffnesses result in whirl flutter, while hard mounting stiffnesses lead to wing flutter. For the latter, the position of the propeller along the wing span may change the wing mode shapes and thus the flutter mechanism. Propeller positions closer to the wing tip enhance stability, but pusher configurations are more critical due to the mass distribution behind the elastic axis.
The so-called "compound solar sail", also known as "Solar Photon Thruster" (SPT), is a solar sail design concept, for which the two basic functions of the solar sail, namely light collection and thrust direction, are uncoupled. In this paper, we introduce a novel SPT concept, termed the Advanced Solar Photon Thruster (ASPT). This model does not suffer from the simplified assumptions that have been made for the analysis of compound solar sails in previous studies. We present the equations that describe the force, which acts on the ASPT. After a detailed design analysis, the performance of the ASPT with respect to the conventional flat solar sail (FSS) is investigated for three interplanetary mission scenarios: An Earth-Venus rendezvous, where the solar sail has to spiral towards the Sun, an Earth-Mars rendezvous, where the solar sail has to spiral away from the Sun, and an Earth-NEA rendezvous (to near-Earth asteroid 1996FG3), where a large orbital eccentricity change is required. The investigated solar sails have realistic near-term characteristic accelerations between 0.1 and 0.2mm/s2. Our results show that a SPT is not superior to the flat solar sail unless very idealistic assumptions are made.