2019
Budelmann, Dennis; Reichert, Lisa; Schmidt, Carsten; Meiners, Dieter
Design und Herstellung unkonventionell versteifter Flugzeugstrukturen Artikel
In: Sonderprojekte ATZ/MTZ, Bd. 24, Nr. 2, S. 46-48, 2019, ISSN: 2509-4610.
Abstract | Links | BibTeX | Schlagwörter: Continuous Wet Draping, Design Optimization, Light Weight Construction
@article{Budelmann2019b,
title = {Design und Herstellung unkonventionell versteifter Flugzeugstrukturen},
author = {Dennis Budelmann and Lisa Reichert and Carsten Schmidt and Dieter Meiners},
doi = {10.1007/s41491-019-0045-8},
issn = { 2509-4610},
year = {2019},
date = {2019-12-18},
journal = {Sonderprojekte ATZ/MTZ},
volume = {24},
number = {2},
pages = {46-48},
abstract = {Am gemeinsamen Forschungsstandort in Stade entwickeln die TU Clausthal, die TU Braunschweig und die Leibniz Universität Hannover eine Fertigungstechnologie zur Herstellung komplex gekrümmter Faserverbundbauteile. Als individuelle Versteifungsstrukturen im Flugzeugrumpf ermöglichen diese Bauteile die notwendige Gewichtsreduktion im Flugzeugbau.},
keywords = {Continuous Wet Draping, Design Optimization, Light Weight Construction},
pubstate = {published},
tppubtype = {article}
}
2018
Deniz, Onur
Production-Based Multi-Criteria Design Optimisation of Stiffened Composite Fuselage Structures Buch
2018, ISBN: 978-3-947623-06-8.
Abstract | BibTeX | Schlagwörter: Design Method, Design Optimization
@book{Deniz2018,
title = {Production-Based Multi-Criteria Design Optimisation of Stiffened Composite Fuselage Structures},
author = {Onur Deniz},
isbn = {978-3-947623-06-8},
year = {2018},
date = {2018-03-08},
abstract = {The current applications of the composite materials in the commercial aviation are carried out only on the material level by slight adjustments while maintaining the traditional design topology, due to the fact that the composite materials are prone to each manufacturing step leading to formidable challenges particularly in seeking innovative concepts. Therefore, multi-disciplinary criteria must be addressed in the design of innovative composite air-frames such as structural failure, weight savings, economic efficiency, manufacturability, production deviations and defects leading to reoccurring manual phases between the design engineers and manufacturers. Existing design methodologies lack in the comprehensive con-sideration of such aspects. Hence, the realisation of cutting-edge composite designs aiming to reduce structural weight as well as the direct operating costs, becomes inefficient and time-consuming by the current design methodologies. The aim of the dissertation is to develop and demonstrate a multi-criteria design method-ology for the production-oriented design of innovative stiffened airframes. The methodology is composed based on the interdisciplinary interaction between the structural design and the production during the product development covering the above addressed issues in the com-posite design. For the implementation of the methodology, a multi-disciplinary design envi-ronment was built by the interdisciplinary parametric representations of structures and pro-cesses in an interactive framework consisting of several modules. The structural modules carry out automated Finite Element (FE) modelling for the stability and material failure cal-culations of a wide variety of stiffened panel designs whereas the process modules conduct manufacturing and cost analysis of arbitrary components. This includes, in particular, manu-facturability analysis of an automated fibre placement process, including the tow-gap esti-mation which is validated by an experimental setup as well as the drapability analysis of fabrics with the identification of fibre misalignments which is coupled with the FE models. Moreover, the economic aspects of the structural design are addressed by estimating the production costs through the process models belonging to a user-defined production chain. The framework composes interdisciplinary criteria into a fitness value by an evaluation model for the ranking and the development of structures (individuals) by a coupled evolu-tionary optimisation environment. The applicability of the developed methodology is first demonstrated by the cost-weight optimisations of conventionally stiffened panel concepts with varying stiffener topologies under the influences of associated process histories. Consequently, the framework is em-ployed for the cost-weight optimisation of a newly developed unconventionally stiffened Lattice-Grid panel under the influences of newly developed manufacturing systems. The developed framework generates a set of process-oriented (defect-free) designs with realistic cost-weight trade-offs as well as their production chain for the preference of the user. The obtained solutions satisfy the multi-disciplinary criteria such as structural integrity, manu-facturability and economical requirements based on a user defined business model.},
keywords = {Design Method, Design Optimization},
pubstate = {published},
tppubtype = {book}
}
Deniz, Onur
Multi-Criteria Methodology for the Production-Oriented Optimisation of Composite Aircraft Structures Promotionsarbeit
Technische Universität Braunschweig, 2018, ISBN: 978-3-947623-06-8.
Abstract | BibTeX | Schlagwörter: Design Optimization, Light Weight Construction
@phdthesis{Deniz2018b,
title = {Multi-Criteria Methodology for the Production-Oriented Optimisation of Composite Aircraft Structures},
author = {Onur Deniz},
isbn = {978-3-947623-06-8},
year = {2018},
date = {2018-03-08},
school = {Technische Universität Braunschweig},
abstract = {The current applications of the composite materials in the commercial aviation are carried out only on the material level by slight adjustments while maintaining the traditional design topology, due to the fact that the composite materials are prone to each manufacturing step leading to formidable challenges particularly in seeking innovative concepts. Therefore, multi-disciplinary criteria must be addressed in the design of innovative composite air-frames such as structural failure, weight savings, economic efficiency, manufacturability, production deviations and defects leading to reoccurring manual phases between the design engineers and manufacturers. Existing design methodologies lack in the comprehensive con-sideration of such aspects. Hence, the realisation of cutting-edge composite designs aiming to reduce structural weight as well as the direct operating costs, becomes inefficient and time-consuming by the current design methodologies. The aim of the dissertation is to develop and demonstrate a multi-criteria design method-ology for the production-oriented design of innovative stiffened airframes. The methodology is composed based on the interdisciplinary interaction between the structural design and the production during the product development covering the above addressed issues in the com-posite design. For the implementation of the methodology, a multi-disciplinary design envi-ronment was built by the interdisciplinary parametric representations of structures and pro-cesses in an interactive framework consisting of several modules. The structural modules carry out automated Finite Element (FE) modelling for the stability and material failure cal-culations of a wide variety of stiffened panel designs whereas the process modules conduct manufacturing and cost analysis of arbitrary components. This includes, in particular, manu-facturability analysis of an automated fibre placement process, including the tow-gap esti-mation which is validated by an experimental setup as well as the drapability analysis of fabrics with the identification of fibre misalignments which is coupled with the FE models. Moreover, the economic aspects of the structural design are addressed by estimating the production costs through the process models belonging to a user-defined production chain. The framework composes interdisciplinary criteria into a fitness value by an evaluation model for the ranking and the development of structures (individuals) by a coupled evolu-tionary optimisation environment. The applicability of the developed methodology is first demonstrated by the cost-weight optimisations of conventionally stiffened panel concepts with varying stiffener topologies under the influences of associated process histories. Consequently, the framework is em-ployed for the cost-weight optimisation of a newly developed unconventionally stiffened Lattice-Grid panel under the influences of newly developed manufacturing systems. The developed framework generates a set of process-oriented (defect-free) designs with realistic cost-weight trade-offs as well as their production chain for the preference of the user. The obtained solutions satisfy the multi-disciplinary criteria such as structural integrity, manu-facturability and economical requirements based on a user defined business model.},
keywords = {Design Optimization, Light Weight Construction},
pubstate = {published},
tppubtype = {phdthesis}
}
2014
Deniz, Onur; Horst, Peter; Weber, Patricc; Schmidt, Carsten; Denkena, Berend
Design optimization of an unconventinal cfrp aircraft panel stiffner based on manufacturability criteria of integrated fiber placement processes Konferenzbeitrag
In: 16th European Conference on Composite Materials, Seville, 2014.
Abstract | BibTeX | Schlagwörter: Automated Fiber Placement, Composite Structures, Design Optimization
@inproceedings{Deniz2014,
title = {Design optimization of an unconventinal cfrp aircraft panel stiffner based on manufacturability criteria of integrated fiber placement processes},
author = {Onur Deniz and Peter Horst and Patricc Weber and Carsten Schmidt and Berend Denkena},
year = {2014},
date = {2014-06-22},
booktitle = {16th European Conference on Composite Materials},
address = {Seville},
abstract = {This paper introduces a global optimization methodology that comprises structural analysis in conjunction with manufacturability examination of the aircraft components based on in-house developed automated fiber placement (AFP) system. Target point of the investigation is an unconventional grid stiffened carbon fiber reinforced plastic (CFRP) fuselage panel with additional multi-curved local stabilizers (stiffener peaks) that are located between diagonal grid stiffeners. The optimization task is formulated to reach global minimum weight of the panel under combined loading scenarios with respect to composite material failures, stability and manufacturability of stiffener peaks based on AFP system. Presented methodology solves the multi-disciplinary problem and offers producible unconventional configurations with adequate mechanical performance and weight savings based on production limits and objectives.},
keywords = {Automated Fiber Placement, Composite Structures, Design Optimization},
pubstate = {published},
tppubtype = {inproceedings}
}
2013
Deniz, Onur; Biel, Andreas; Horst, Peter; Ziegmann, Gerhard; Schmidt, Carsten
Simulation Based Design Optimization of a Cfrp Fuselage Panel According to Draping Process of Carbon Fibre Textiles Using Evolutionary Algorithms and Response Surface Methods Konferenzbeitrag
In: Sampe, 2013.
Abstract | BibTeX | Schlagwörter: Composite Structures, Design Optimization, Draping Simulation, Fuselage
@inproceedings{Deniz2013,
title = {Simulation Based Design Optimization of a Cfrp Fuselage Panel According to Draping Process of Carbon Fibre Textiles Using Evolutionary Algorithms and Response Surface Methods},
author = {Onur Deniz and Andreas Biel and Peter Horst and Gerhard Ziegmann and Carsten Schmidt},
year = {2013},
date = {2013-05-03},
booktitle = {Sampe},
journal = {Sampe},
abstract = {Design optimization plays a vital role in Aerospace Industry due to its challenging requirements that are not only based on mechanical aspects but also in manufacturing processes. Besides, manufacturing processes cause imperfections and variations on the structure which could be estimated by advanced simulations that result in expensive computations. On the other hand, it has been an issue to obtain global optima of the objective function of structures such as CFRP stiffened fuselage panels whose mechanical system responses are generally evaluated by Finite Element calculations.
This paper proposes a global optimization process on an innovative CFRP fuselage panel which simultaneously covers stability criterion and draping simulation of fiber textiles that is considered as a manufacturing effect. Genetic algorithms were chosen as an optimization technique to reach global optima. During the optimization process, a modified Response Surface Method that is based on artificial neural networks (RBF-ANN) [1] is carried out in order to reduce the computational effort and to couple the simulation inputs and outputs in the optimization frame.
A parametric FEM model generator was developed under periodic boundary conditions in order to obtain buckling modes and corresponding failure criterions during the parameter variation. The shear angles of the fibers arising due to draping process were considered as production constraint and represented with the surrogate model by RBF-ANN in the optimization loop.
This method presents an optimization frame that covers the production failures of draping process and its influence on structural design. Furthermore this optimization process can be modified with other undetermined production constraints that are predicted by simulation.
REFERENCES
[1] K.Lindhorst, M. C. Haupt, P. Horst, “ Usage of time domain surrogate model approaches for transient, nonlinear aerodynamics within aero-structural coupling schemes” presented in"30th AIAA Applied Aerodynamics Conference", 25-28th June 2012, New Orleans, USA
},
keywords = {Composite Structures, Design Optimization, Draping Simulation, Fuselage},
pubstate = {published},
tppubtype = {inproceedings}
}
This paper proposes a global optimization process on an innovative CFRP fuselage panel which simultaneously covers stability criterion and draping simulation of fiber textiles that is considered as a manufacturing effect. Genetic algorithms were chosen as an optimization technique to reach global optima. During the optimization process, a modified Response Surface Method that is based on artificial neural networks (RBF-ANN) [1] is carried out in order to reduce the computational effort and to couple the simulation inputs and outputs in the optimization frame.
A parametric FEM model generator was developed under periodic boundary conditions in order to obtain buckling modes and corresponding failure criterions during the parameter variation. The shear angles of the fibers arising due to draping process were considered as production constraint and represented with the surrogate model by RBF-ANN in the optimization loop.
This method presents an optimization frame that covers the production failures of draping process and its influence on structural design. Furthermore this optimization process can be modified with other undetermined production constraints that are predicted by simulation.
REFERENCES
[1] K.Lindhorst, M. C. Haupt, P. Horst, “ Usage of time domain surrogate model approaches for transient, nonlinear aerodynamics within aero-structural coupling schemes” presented in"30th AIAA Applied Aerodynamics Conference", 25-28th June 2012, New Orleans, USA