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Item type:Publication, Access status: without files , Early model-based functional integration testing for aircraft systems architectures demonstrated on a hydrogen-powered propulsion unit(2025-10-25); ; ; ; Developing complex, hydrogen-powered aircraft and their on-board systems is challenging due to a vast design space, limited knowledge, and high uncertainties. Hence, the risk of undetected errors introduced during conceptual design increases. To address this, a method for early model-based functional integration testing as an integrated part of systems architecting is proposed. It includes simulation-based testing of functional behavior under nominal and off-nominal conditions based on executable architecture models, enabling the discovery of design errors and the down-selection of large design spaces. The method is demonstrated on a fuel cell-powered propulsion unit of a novel hydrogen-powered concept aircraft, showing its value for complex, novel systems in off-design conditions.Publicationtype: Conference Paper82 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: with files , TechMAPS: technology management for the architecting process of aircraft on-board systemsDue to climate change, low-emission aircraft with novel technologies, such as hydrogen-powered fuel cells, are being investigated. However, navigating the technology knowledge is challenging due to the vast number of existing and emerging technologies. Hence, supporting the engineer during the complex task of exploring, comparing, and selecting technologies from the extensive design space as part of the aircraft conceptual design phase is crucial. To address this challenge, the Technology Management for the Architecting Process of aircraft on-board Systems (TechMAPS) method is proposed. TechMAPS is used to navigate and manage available and emerging technologies. Moreover, the method supports the conservation and provision of technology knowledge in a standardized and formalized way. To this end, TechMAPS consists of three parts: a technology radar to identify technologies, a formalized ontology-driven database to conserve knowledge in a machine-readable, queryable way, and standardized technology fact sheets to provide concise data to the engineer. TechMAPS is exemplarily applied to different technologies of a hybrid-electric power train, i.e., a fuel cell, an existing electric motor, and battery technologies, to demonstrate the method’s capabilities to present the landscape of technologies for different systems and abstraction levels. The study highlights the effectiveness of TechMAPS for technology management but also outlines aspects that need further research, such as creating an automated and standardized interface to and from the database.Publicationtype: Journal Article47 60 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: with files , Integration of a model-based systems engineering framework with safety assessment for early design phases: a case study for hydrogen-based aircraft fuel system architectingNovel hydrogen-based aircraft concepts pose significant challenges for the system development process. This paper proposes a generic, adaptable, and multidisciplinary framework for integrated model-based systems engineering (MBSE) and model-based safety assessment (MBSA) for the conceptual design of complex systems. The framework employs a multi-granularity, model-centric approach, whereby the architectural specification is utilized for design as well as query purposes as part of a qualitative and quantitative, graph-based preliminary safety assessment. For the qualitative assessment, design and safety rules based on existing standards and best practices are formalized in the model and applied to a graph-based architecture representation. Consequently, the remaining architectures are quantitatively assessed using automated fault trees. This safety-integrated approach is applied to the conceptual design of a liquid hydrogen fuel system architecture as a novel, uncertain, and complex system with many unknown system interrelations. This paper illustrates the potential of a combined MBSE-MBSA framework to streamline complex, early-stage system design and demonstrates that all qualitatively down-selected hydrogen system architecture variants also satisfy quantitative assessment. Furthermore, it is shown that the design space of novel systems is also constrained by safety and certification requirements, significantly reducing the number of actual feasible solutions.Publicationtype: Journal Article59 57 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , Conceptual Design of IMA Platforms with Distributed A653-P4 Computing Modules for Next-Generation AircraftThe desire to further extend system functions on Integrated Modular Avionics (IMA) platforms necessitates advances in terms of module and network technology. The introduction of distributed computing concepts, such as passively cooled ARINC 653 Part 4 modules, is intended to enable fast local control loops for safety-critical systems on IMA, for which a central computing platform with an ARINC 664 backbone network would not meet timing requirements. Moreover, by mapping low-computing software applications close to their corresponding peripherals, a reduction of network load can be achieved. However, challenges persist during the conceptual design phase of IMA platforms, as peripheral localization and installation constraints induced by the aircraft geometry are difficult to consider due to high uncertainties. An approach that leverages parametric architecture design pattern within a model-based conceptual design framework is proposed. A use case study was conducted to identify conceptual variants of both state-of-the-Art Distributed IMA and next-generation architectures that feature distributed computing for a Virtual Research Aircraft (ViRAC). The study demonstrated that a fully model-based, formalised approach that integrates different disciplinary tools during early design iterations can lead to a reasonable platform draft in fewer design iterations.Publicationtype: Conference Paper61 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: with files , Assessment of an auto-routing method for topology generation of aircraft power supply systemsDuring early phases of aircraft development, overall systems design is performed to estimate relevant system design parameters such as mass, power consumption, and compliance with architectural requirements (redundancy). The GeneSys software framework has been developed for parametric modeling of aircraft on-board systems for overall systems design. To this end, model-based architecture definition, topology generation (components positioning and connections routing), and system sizing are conducted. The topology generation is currently performed using design templates containing knowledge-based heuristics derived from systems topologies of existing aircraft. However, using such design templates limits their generic application to novel aircraft models because exceptions for geometric differences between these models need to be implemented. This especially applies to the topology generation of power supply systems (electric, hydraulic) due to their high number of interfaces to consumer systems. To overcome these limitations, an automated routing method is presented in this paper as a generic approach for topology generation. With this method, the system topology is generated based on a defined routing network, which comprises areas of the aircraft for allowed components positioning and connections routing. Using Dijkstra’s algorithm, the shortest path connections are found within the established routing network. Furthermore, boundary conditions for routing, for instance adding a cost function for power segregation, can be defined. An assessment of the automated routing method applied on the electric power supply system is performed using qualitative parameters such as the capability to adapt the routing network. Quantitative parameters like cable length and system mass are assessed as well.Publicationtype: Journal Article53 65 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , Techmaps – Technology Management for the architecting process of aircraft on-board systems(International Council of the Aeronautical Sciences, 2024); ; ; Due to the noticeable effects of climate change and defined emission reduction targets, such as FlightPath 2050, efforts are being made to achieve low-emission aircraft in the near future. Therefore, many propulsion and on-board systems technologies, such as hydrogen-powered fuel cells, are being investigated. However, due to the vast number of existing and emerging technologies, it is challenging to navigate and manage technology knowledge. Hence, during the aircraft conceptual design phase, providing support to the engineers is crucial as they explore this vast design space of technologies and need to choose among many different technology variants. To handle this complex problem and to navigate the technology variants, this paper presents the Technology Management for Architecting Process of on-board Systems (TechMAPS) method. It is used to navigate and manage available and emerging technologies. Moreover, the method supports the conservation and provision of technology knowledge in a standardized and formalized way. To this end, TechMAPS consists of three parts: a technology radar to identify emerging technologies, a database to enable knowledge conservation and query capabilities, and an automated report generation with so-called technology fact sheets to provide the data to the engineer. In addition, intellectual property and confidential data handling are included.TechMAPS is exemplarily applied to a fuel cell, an existing electric motor, and battery technologies to demonstrate the method’s capabilities for different systems and different technology abstraction levels. The study highlights the effectiveness of TechMAPS for technology management but also outlines aspects, which need further research, such as creating an automated and standardized interface to and from the database.Publicationtype: Conference Paper33 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , Evaluation metrics for systems architecting demonstrated on cooling system of hydrogen-powered concept aircraft(American Institute of Aeronautics and Astronautics (AIAA), 2024-01); ; ; Climate change presents a global challenge, with aviation significantly contributing to greenhouse gas emissions. To reduce the environmental impact of aviation, novel aircraft concepts incorporating renewable energy sources, such as green hydrogen, are being explored during the aircraft conceptual design phase. Low temperature proton exchange membrane fuel cells are currently being investigated as one possible technology for supplying power to the aircraft power train and on-board systems. However, the design of a cooling system for these fuel cells is challenging due to the small available temperature difference between fuel cell operation and ambient temperatures in hot day on-ground scenarios. Therefore, the development of novel cooling system architecture concepts is necessary. For this design problem, many conceivable architecture variants need to be investigated, resulting in a complex and large design space during systems architecting. To assist the engineer during systems architecting and to reduce the design space to promising architecture variants, the Systems Architecting Assistant (SArA) methodology is used. In this work, SArA is extended by a method for evaluating architecture performance based on the metrics complexity and risk, including a knowledge-based and a model-based approach. This helps engineers quantitatively compare system architecture alternatives, thereby simplifying the down-selection process. The developed metrics are applied to eight different cooling system architecture variants of a hydrogen-powered concept aircraft, enabling a rapid and partially automated approach for architecture evaluation. While the use of a combined knowledge-based and model-based approach proved beneficial, it became apparent that complexity and risk as high-level metrics provide limited insights and value in the decision-making process. To enhance the value of the evaluation method and to gain a deeper understanding of the architectures, a comprehensive investigation of the selected technologies becomes imperative.Publicationtype: Conference Paper44 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , Seamless transitions from logical to physical avionics architecture models for preliminary aircraft system designThe transition of federated aviation electronics (avionics) systems to Integrated Modular Avionics (IMA) concepts leads to a higher integration of functions, which reduces the amount of equipment and therefore system mass. However, these benefits are accompanied by a strong increase in system complexity and more interdependencies. Moreover, further digitalization and automation of aircraft functions lead to a higher impact of avionics in terms of equipment number and energy consumption. One challenge arises from the fact that the IMA platform design starts in parallel to the design of other aircraft on-board systems, for which the platform shall provide resources like computing power. This leads to a high uncertainty during early design phases on the one hand and to a complex design process including many data and tool interfaces on the other hand. In order to meet these challenges, seamless model-based design approaches are being broadly investigated. For this purpose, standardized and automated interfaces between different design steps, tools, and stakeholders are needed. In this work, a formalized avionics architecture design process is proposed to support a seamless model-based tool chain from systems architecting to detailed system design. Methods to handle uncertainties, to provide standardized model interfaces, and to automate transitions between model abstraction levels are included. Overall, this reduces manual effort and the introduction of errors that would lead to high costs during system implementation.Publicationtype: Conference Presentation101 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , Model-based framework for data and knowledge-driven systems architecting demonstrated on a hydrogen-powered concept aircraftAircraft development is a protracted process over many years. Novel concept aircraft with new energy sources and disruptive systems technologies are investigated during the aircraft conceptual design phase with the goal to achieve sustainable aviation. Current development cycles need to be accelerated to reduce time to market and development costs of novel aircraft, while still handling complexity and uncertainty of systems technologies. Therefore, a holistic framework for knowledge-based systems architecting using a model-based systems engineering approach is presented. This framework has the purpose to conserve and provide knowledge, i.e., information, data, and experiences about existing systems architectures, to the engineer. The developed framework consists of a database concept, a method for model-based systems architecting, and an interface to the overall systems design software tool GeneSys. Based on evaluating different modeling languages and tools, MathWorks System Composer is selected as most suitable tool for knowledge-based systems architecting. The developed framework is then demonstrated by conserving and reusing formalized knowledge for the design of a novel hydrogen-powered concept aircraft. On-board systems architecture models are saved in a database and automatically recreated reducing development time. The complete graphical representation could not yet be stored in a formalized manner partly reducing the advantage of a clear representation of model-based systems architecting. However, this did not reduce automatic recreation and evaluation capabilities.Publicationtype: Conference Presentation42 - Some of the metrics are blocked by yourconsent settings
Item type:Publication, Access status: without files , Overall parametric design and integration of on-board systems for a hydrogen-powered concept aircraftTo reach climate neutrality in aviation, new technologies and concepts for aircraft power supply have to be considered. For regional and short-range aircraft, hybrid fuel cell systems (fuel cells and batteries) are proposed as a promising solution for aircraft power supply. However, the integration of hybrid fuel cell systems and the electrification of the powertrain also affects the power supply for aircraft on-board systems, i.e. normal and emergency secondary power supply. In this context, concept studies need to be performed during the aircraft conceptual design phase to assess systems architectures and power supply strategies for hydrogen-powered concept aircraft. In this paper, such concept studies are performed during the conceptual design phase of the aircraft, proposing a systems architecture for a hydrogen-powered concept aircraft with an estimated entry into service in 2040. The in-house GeneSys software framework is being developed for overall systems design during the conceptual design phase to support system engineers by conducting such studies and evaluating the results. To this end, relevant system sizing laws need to be adjusted and verified to perform and assess concept studies for secondary power supply for hydrogen-powered concept aircraft. In this context, the considered aircraft is the ESBEF-Concept Plane 1 (CP1) which is derived from an ATR 72-like aircraft model. The following steps are performed to adapt and verify the system sizing laws of GeneSys accordingly. First, the systems architecture of the existing ATR 72 aircraft is evaluated. The implemented system sizing laws are adjusted based on known system parameters (e.g. mass and power consumption). Second, the systems architecture of the ATR 72 is updated to a state-of-the-art systems architecture. Last, this systems architecture is fully electrified for the integration in the ESBEF-CP1 and projected to an entry into service in 2040, adding technology factors to estimate improvements of relevant technologies. To identify and select a suitable systems architecture for the ESBEF-CP1, architecture variants are generated and evaluated. The evaluation is performed based on safety and reliability, system masses, and power requirements. The selected systems architecture presented in this paper is the baseline for more detailed analyses, conducting, for example, time-dependent studies for energy management of the aircraft.Publicationtype: Conference Paper125