Resultado final
T42 Developing MDO framework for aircraft design optimization M818In this task an MDO framework for aircraft design optimization will be developed by TUBS and SOTON The framework is based on the aircraft design tool SUAVE which is under development by the Stanford University and TU Braunschweig The models developed in T41 will be integrated with SUAVE energy network A crosscheck with the aircraft designs from T22 an T32 is necessary to identify differences between SUAVE and TU Delft Aircraft Initiator designs The nonintrusive univariate reduced quadrature URQ method will be used to propagate the uncertainties through the analysis disciplines of SUAVE The design credibility will be formulated based on the probability of the technologies to be realised in a similar way to the reliability constraint The SUAVE design framework will be connected to the open source Surrogate Model Toolbox SMT from the University of Michigan Using the SMT computationally inexpensive models will be generated to be used for credibility based optimization T43 Credibilitybased MDO M1824The framework developed in T42 will be used for credibilitybased optimization of the reference aircraft initially designed in T32 The optimization will be performed by TUBS and SOTON to fine tune the design variables including the aircraft geometry as well as energy network Only continuous design variables such as wing geometry or battery energy density will be considered The optimization will be performed to eg minimize the total energy consumption of the aircraft subject to constraints on TLAR Besides a constraint on credibility will be defined Different values for minimum credibility will be used for optimization Both gradient based and gradient free optimization algorithms will be used The optimization will start with a gradient free such as Genetic Algorithms to find a good starting point for gradient based optimization such as Sequential Quadratic Programming Then the gradient based method will be executed to fine tune the optimum design The optimizations will be executed on the Phoenix computer cluster of TU Braunschweig T44 Assessment of the optimization results M2127The outcomes of the MDO in T43 will be used to investigate the potentials of the target technologies in realizing hybrid electric aircraft The KPIs defined in T23 together with the credibility criteria resulted from MDO in T43 will be used to identify the critical points the switching points for technologies for different categories of hybrid electric aircraft Critical points are considered hierarchically starting from the highest system level down to cross over points that can occur in the drive topology design Therefore analysis of significant system changes with regard to machine cooling behaviour material selection and topology variants implementation of superconductivity gear coupled high speed drives are identified and assessed Assessment will be performed by both SOTON TUD and TUBS A workshop with AB as well as other invitees from industries and academia will be arranged to discuss the final resultsResponsible SOTON contribution TUD and TUBS
Report on opportunities for cross-vehicle class and technology synergiesT34 Opportunities for crossvehicle class scaling and technology synergies M2130Based on the assessment of initial designs and the development of new design rules and physicsbased methods for novel powertrains an overview can be made of any synergies between technologies or vehicle platforms Additionally the results from the credibilitybased MDO from WP4 T44 will further feed this analysis as well as the operational safety and economics assessments from WP5 This task concludes the scalability assessment stage 4 This task will be performed by TUDFPP and SOTON with consultancy from experts from all other involved institutes Responsible TUD contribution SOTON and TUBS
Report on ground architecture requirements for the different solutionsT51 Complementary requirements for ground architecture and ground support M1221Requirements for airport ground architecture and ground support shall be established Focal point shall be on the turnaround process To enable acceptable turnaround times requirements for battery charging and storage facilities and other ground support as well as refuelling facilities shall be established Alternate means like rapid replacement of battery packs shall be investigated The assessment will be conducted by means of simulating the turnaround process An existing simulation environment will be enhanced for the purpose of this proposal The turnaround simulation currently developed within the SE2A cluster follows a flowbased modeling approach where socalled entities move as commodities through a network from node to node Entities in this case a particular aircraft can be assigned with attributes which can be manipulated during the course of the entity throughout the network of the turnaround thus affecting its proceeding within the process The part of the ground simulation provides hierarchical modelling and stochastic functionalities to provide easy adaption to requirements Furthermore the infrastructure adapted to a new charging process could by modeled as well Since the entity based modeling approach allows for an unlimited number of entities within a model as well as an unlimited number of attributes to be assigned to them the level of detail can be adapted gradually This for example applies to the specifications of such vehicles as well as infrastructure or topological aspects Responsible TUBS contribution TUD
Midterm overview and update of dissemination activitiesMidterm overview and update of dissemination activities Responsible TUD contribution TUBS
Report on economic and operational viability of the different solutionsT52 Assessing the economic and operational viability M1228Assess the economic and operational viability of the radical hybridelectric aircraft concept for the vehicle classes Commuter Regional Aircraft and Short and Medium Range large commercial aircraft Use the assumption made for the opportunities and limitations of the upscaling development and the requirements and limitations derived To perform this assessment an airline network development model will be used considering the allocation of the hybridelectric aircraft to routes from the airline network An estimation of the operational costs the demand and the subsequent revenue generated will be used to assess the economic viability of the solutions produced Furthermore supported on this airline network development model and following the experts consultation from T53 a Monte Carlo simulation model will be develop to quantitatively estimate the operational reliability and safety risks of the credibilitybased MDO final designs This operational risk analysis will be based on the risk hazards identified by the experts and on the qualitative prescription of the level of risk associated with these hazards This task will be performed by TUD
Baseline for airport infrastructure, certification requirements and economic/operational viabilityThis task establishes the baseline ie reference for the various activities in workpackage 5 As such it provides a description of the current status on airport infrastructure operationseconomics and certification requirements These will be used as the baseline for all following activities Responsible TUD contribution TUBS
White-paper on Requirements, Certification Specifications and Risks EstimationT53 Requirements and Certification Specifications analysis M1826 An assessment of the current certifications shall be performed These certifications will be analysed following the different airline business models under consideration and the preliminary results obtained from T51 and T52 Experts consultation will be performed to map the certification needs to adopt the hybridelectric aircraft under different context and to identify risk hazards associated with the design and operability of the MDO final solutions The group of experts will involve aircraft designers airline and airport operators and regulatory agencies such as EASA and local civil aviation authorities This should specifically contain considerations on how to achieve large transport aircraft safety for regional and commuter aircraft with potential different certification frameworks Finally this task will also include the elaboration and discussion of a white paper discussing not only the certification needs but also the requirements and the operational feasibility and risk assessment of the hybridelectric solutions studied Responsible TUD contribution TUBS
Report on design of reference vehiclesT31 Design of reference vehicles M16Conceptual design of reference vehicles on the basis of the TLAR defined in T21 and the identified KPIs in T23 TUDFPP will perform the design and analysis of the reference aircraft using its conceptual aircraft design software Aircraft Design Initiator This design will cover typical Class1 Class2 and Class25 design methods for wingpowerloading diagrams constraint analysis including aeropropulsive interaction effects weight estimation finiteelement based beam method of fuselage and lifting surfaces aerodynamics vortex lattice semiempirical corrections for nonlift induced effects empty weight estimation of nonstructural components and mission analysis This software generates converged designs including discipline interactions however does not try to optimize the aircraft for the specified top level requirements Review will be performed together with TUBS The initial hypothesis for TLAR in D21 will be based on current classleading representative aircraft for each of the five vehicle classes Examples of these include Tecnam P2010 or Pipistrell Panthera GA King Air P180 Avanti Citation or EMB Legacy commuter ATR42ATR72 regional A320A321Neo narrow body A350 wide body Especially for the smaller categories GAcommuter the selection of reference aircraft will be critical and may result in more than 5 reference aircraft in total to cover the broadness of these classes Designs of reference vehicles will be compared to the data found in open literature for validation purposes Responsible TUD review contribution TUBS
Report on initial design of aircraft with radical technologies incl. initial assessment of technology limitations and cross-over pointsT32 Initial design of vehicles with radical technologies M318In this WP initial design of radical aircraft with the novel technologies identified in T22 is considered A deterministic design approach will be used in this task using the mean values of the uncertain parameters identified in T22 The architecture of the energy network will be defined together with the power electric experts from TUBSIMAB The design will be performed by TUDFPP with the conceptual design tool Initiator to provide a feasible starting point for the credibilitybased MDO of T43 This will use the same software as for T31 however in this case a hybrid electric power train analysis is included in the constraint analysis and mission analysis This software has been developed and used in the past and will be extended to cover all radical technologies covered in CHYLA fuel cell alternative combustible fuels and enhancement of methods for electric drivesmotors Similarly as for T31 only converged nonoptimal designs are generated that should provide suitable starting points for the MDO Top level requirements will be the same as for the reference aircraftT33 Preliminary analysis of target technologies identification of limitations switching points and crosscheck with certification specifications M1518The initial designs from T32 will serve as a baseline for the identification of crossover points between technologies and as a basis for the assessment of the applicability of current regulations The assumptions that form the basis for these designs will be assessed in the MDO of T43 for their credibility resulting in a potential feedback for redesign of the starting point This preliminary assessment should support the MDO approach and identify focal areas for the final assessment of optimization results and will be performed by TUDFPP TUBSIFL and SOTON with consultancy from experts from all other involved institutes This task performs stage 2 of the scalability assessment Responsible TUD contribution TUBS and SOTON
Report on energy network modelT41 Developing energy network model for hybrid electric propulsion M610A reduced order model ROM will be developed to describe the hybrid electric drive train including LH2 and fuel cell technologies The system model will be developed using the Pseudo BondGraph Theory based on physical descriptors of energy capacities and fluxes Specific subsystem performance behaviour will be implemented using performance maps The reduced order model will allow modelling rubberband fuel cell stacks and systems compressor humidification system waste heat management and allowing the identification of nonlinear system behaviour as well as unsteady system behaviour The ROM shall be implemented into the SUAVE framework in T42Due to the electromagnetic design of electric drives investigations on the scaled drive behaviour of electric drives are done using FEM calculation methods In particular the machine topology and the associated sensitivities with respect to the total weight of the drive are taken into account The cooling system of the electric machine and power electronics is described with regard to evaluation parameters which show the influence on the type and weight of the cooling structures The precalculations and the modelling are done to determine important design criteria winding setup electromagnetic material mechanical tolerances To fulfil the demands of T42 and T43 uncertainties are identified and represented in the physical system descriptionBatteries and fuels cells need power electronics converters to connect these sources to the HVDC board grid The main load is the propulsion system with the drive consisting in electrical machine and a power electronics inverter Both inverters and converters have to be cooled Losses and power densities of the power electronic devices depend on several factors like cooling temperature HVDC voltage altitude electrical operation points For the optimisation sufficient precise power density and loss models for the power electronics will be derived Uncertainties and nonlinearities can occur due to differences in power electronic circuit topologies in rated voltage of the semiconductors clearance and creepage distances or cooling systems This task will be done completely by TUBS
Advancements of state-of-the-art and exploitation planAdvancements of stateoftheart and exploitation plan Includes a summary of activities and an overview of the project results Responsible TUD contribution SOTON and TUBS
Report on KPIs, and reference case for the economic and operational viability studyT23 Definition of KPIs and reference case for economic and operational viability study M4 8In this project the strategy to an optimal aircraft design from mechanical construction to energy supply system with batteries and fuel cells as sources and the propulsion machines as main load plus the most important additional heavy loads shall be described for reference vehicles of different size Identification of KPIs like HVDC voltage level cooling capability of electric systems and peakcont power ratios of drives is a task of this working package For instance the power density of power electronics and drives can be evaluated with regard to the defined KPIs Reference cases for the economic and operational viability study will be done together with all partners such KPIs could include BELF breakeven load factor aircraft utilisation or operating cost The task will be done collaboratively by both partners Responsible TUBS contribution TUD
Report on TLAR and matrix of technologies to be used in CHYLA including the selection of the uncertain parameters/ variablesT21 Definition of TLAR and operations M12In this task the TLAR used for designing the five reference aircraft will be defined by both partners as well as the AB The outcomes will be used to design optimise and assess the aircraft configurations in the WP3 WP4 and WP5 as well as the reference aircraft design and validation in WP3 The initial hypothesis for TLAR will be based on current classleading representative aircraft for each of the five vehicle classes Examples of these include Tecnam P2010 or Pipistrell Panthera GA King Air P180 Avanti Citation or EMB Legacy commuter ATR42ATR72 regional A320A321Neo narrow body A350 wide body Especially for the smaller categories GAcommuter the selection of reference aircraft will be critical and may result in more than 5 reference aircraft in total to cover the broadness of these classes Responsible TUD contribution of TUBST22 Establish matrix of technologies and uncertain parameters M24In this WP the matrix of technologies including airframe propulsion and energy network technologies and propulsive technologies as described in section 131 will be established Besides it will be decided which of these technology parameters will be used as uncertain parametersvariables The decision will be made based on the importance and sensitivity of the technologies on aircraft design and scalability The technologies listed in this table will be implemented at small aircraft level GA then to be developed by upscaling as well as an overview of other radical technologies that may only be applicable in specific classes This provides the basis of T32 T41 and T42 This task will be done collaboratively by both partners and the AB as well as the invitees of the CHYLA first workshop This task involves stage 1 of the scalability assessment ruling out initial options based on existing research and expert judgement Responsible TUBS contribution TUD
Dissemination, communication and exploitation planProject dissemination and exploitation plan Also a consolidated qualitative and quantitative assessment of the project expected impacts and related baseline will be performed at the beginning of the project and included in the Dissemination communication and exploitation plan Similarly the reference vehicles will be summarized in this deliverable and further described in D21 Responsible TUD contribution TUBS
Added according to art 293 defines data management plan for the project Responsible TUD contribution TUBS
Publicaciones
Autores:
V.O. Bonnin, M.F.M. Hoogreef
Publicado en:
33rd Congress of the International Council of the Aeronautical Sciences, 2022
Editor:
DGLR
Autores:
Hoogreef, Maurice Frederik Maria; Elham, Ali; Santos, Bruno F; Henke, Markus; Mallwitz, Regine; Steen, Meiko; Friedrichs, Jens
Publicado en:
EASN 2021, 2021
Editor:
Zenodo
DOI:
10.5281/zenodo.5824660
Autores:
Morlupo, Federico; Santos, Bruno; Förster, Peter Horst; Hoogreef, Maurice
Publicado en:
2023
Editor:
Zenodo
DOI:
10.5281/zenodo.7875829
Autores:
Maurice Hoogreef, Noa Zuijderwijk, Elise Scheers, Pieter-Jan Proesmans and Bruno F. Santos
Publicado en:
AIAA AVIATION FORUM 2023, 2023
Editor:
AIAA
DOI:
10.2514/6.2023-3869
Autores:
Maurice Hoogreef; Pieter-Jan Proesmans
Publicado en:
AIAA SCITECH 2023 Forum, 2023
Editor:
Zenodo
DOI:
10.5281/zenodo.7584077
Autores:
N.F.M. Wahler, L. Radomsky, L.V. Hanisch, R. Mallwitz, M. Henke, A. Elham
Publicado en:
33rd Congress of the International Council of the Aeronautical Sciences, 2022
Editor:
DGLR
Autores:
Nicolas F. Wahler, Lukas Radomsky, Lucas Vincent Hanisch, Jan Göing, Patrick Meyer, Regine Mallwitz, Jens Friedrichs, Markus Henke, Ali Elham
Publicado en:
AIAA AVIATION 2022 Forum, Edición June 27-July 1, 2022, 2022
Editor:
AIAA
DOI:
10.2514/6.2022-3741
Autores:
Bonnin, Vincent; Hoogreef, Maurice
Publicado en:
2023
Editor:
Zenodo
DOI:
10.5281/zenodo.7875784
Autores:
Pieter-Jan Proesmans, Federico Morlupo, Bruno F. Santos and Roelof Vos
Publicado en:
AIAA AVIATION FORUM 2023, 2023
Editor:
AIAA
DOI:
10.2514/6.2023-4300
Autores:
Vincent Bonnin, Maurice Hoogreef, Reynard de Vries
Publicado en:
AIAA SCITECH 2023 Forum, 2023
Editor:
AIAA
DOI:
10.2514/6.2023-2098
Autores:
M.F.M. Hoogreef, V.O. Bonnin
Publicado en:
33rd Congress of the International Council of the Aeronautical Sciences, 2022
Editor:
DGLR
Autores:
Hoogreef, Maurice
Publicado en:
2023
Editor:
Zenodo
DOI:
10.5281/zenodo.7875748
Autores:
Bonnin, Vincent; Hoogreef, Maurice Frederik Maria; Wahler, Nicolas; Elham, Ali; Hanisch, Lucas Vincent; Radomsky, Lukas; Henke, Markus; Mallwitz, Regine; Steen , Meiko; Santos, Bruno F.; Friedrichs, Jens
Publicado en:
EASN 2022, Edición 1, 2022
Editor:
Zenodo
DOI:
10.5281/zenodo.7276640
Autores:
Wahler, Nicolas; Elham, Ali
Publicado en:
2023
Editor:
Zenodo
DOI:
10.5281/zenodo.7875820
Autores:
Nicolas F. Wahler, Daigo Maruyama, Ali Elham
Publicado en:
AIAA SCITECH 2023 Forum, 2023
Editor:
AIAA
DOI:
10.2514/6.2023-1847
Autores:
Maurice F. M. Hoogreef, Vincent O. Bonnin, Bruno F. Santos, Federico Morlupo, Nicolas F. M. Wahler, Ali Elham
Publicado en:
EUCASS 2023 / CEAS 2023, 2023
Editor:
EUCASS
DOI:
10.13009/eucass2023-260
Autores:
Wahler, Nicolas; Elham, Ali
Publicado en:
2023
Editor:
Zenodo
DOI:
10.5281/zenodo.7875752
Autores:
Onorato, G.; Proesmans, P.; Hoogreef, M. F. M.
Publicado en:
CEAS Aeronautical Journal, 2022, ISSN 1869-5590
Editor:
Springer
DOI:
10.1007/s13272-022-00601-6
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