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Linköping University
1.
Sohaib, Muhammad.
Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis.
Degree: Machine Design, 2011, Linköping University
URL: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264 
► This master thesis work presents the development of a parameterized automated generic model for the structural design of an aircraft wing. Furthermore, in order…
(more)
▼ This master thesis work presents the development of a parameterized automated generic model for the structural design of an aircraft wing. Furthermore, in order to perform finite element analysis on the aircraft wing geometry, the process of finite element mesh generation is automated.
Aircraft conceptual design is inherently a multi-disciplinary design process which involves a large number of disciplines and expertise. In this thesis work, it is investigated how high-end CAD software‟s can be used in the early stages of an aircraft design process, especially for the design of an aircraft wing and its structural entities wing spars and wing ribs.
The generic model that is developed in this regard is able to automate the process of creation and modification of the aircraft wing geometry based on a series of parameters which define the geometrical characteristics of wing panels, wing spars and wing ribs.Two different approaches are used for the creation of the generic model of an aircraft wing which are “Knowledge Pattern” and “PowerCopy with Visual Basic Scripting” using the CATIA V5 software. A performance comparison of the generic wing model based on these two approaches is also performed.
In the early stages of the aircraft design process, an estimate of the structural characteristic of the aircraft wing is desirable for which a surface structural analysis (using 2D mesh elements) is more suitable. In this regard, the process of finite element mesh generation for the generic wing model is automated. The finite element mesh is generated for the wing panels, wing spars and wing ribs. Furthermore, the finite element mesh is updated based on any changes in geometry and the shape of the wing panels, wing spars or wing ribs, and ensure that all the mesh elements are always properly connected at the nodes. The automated FE mesh generated can be used for performing the structural analysis on an aircraft wing.
Subjects/Keywords: aircraft design; aircraft wing; wing spars; wing ribs; FEM; structural mesh; generic wing model; parametric wing model; automation; design; TECHNOLOGY; TEKNIKVETENSKAP
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APA (6th Edition):
Sohaib, M. (2011). Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis. (Thesis). Linköping University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Sohaib, Muhammad. “Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis.” 2011. Thesis, Linköping University. Accessed January 25, 2021.
http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Sohaib, Muhammad. “Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis.” 2011. Web. 25 Jan 2021.
Vancouver:
Sohaib M. Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis. [Internet] [Thesis]. Linköping University; 2011. [cited 2021 Jan 25].
Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Sohaib M. Parameterized Automated Generic Model for Aircraft Wing Structural Design and Mesh Generation for Finite Element Analysis. [Thesis]. Linköping University; 2011. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-71264
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Michigan
2.
Bons, Nicolas.
High-Fidelity Wing Design Exploration with Gradient-Based Optimization.
Degree: PhD, Aerospace Engineering, 2020, University of Michigan
URL: http://hdl.handle.net/2027.42/163242
► Numerical optimization has been applied to wing design problems for over 40 years. Over the decades, the scope and detail of optimization problems have advanced…
(more)
▼ Numerical optimization has been applied to
wing design problems for over 40 years. Over the decades, the scope and detail of optimization problems have advanced considerably. At the present time, the state-of-the-art in
wing design optimization incorporates high-fidelity modeling of the steady-state aeroelastic response of the
wing at both on-
design and off-
design operating conditions. Reynolds-averaged solutions of the Navier–Stokes equations coupled with linear finite element anal- ysis offer the highest fidelity modeling currently tenable in an optimization con- text. However, the complexity of implementing and cost of executing high-fidelity aerostructural optimization have limited the extent of research on the topic. The goal of this dissertation is to examine the general application of these tools to
wing design problems and highlight several factors pertaining to their usefulness and versatility.
Two types of
wing design problems are considered in this dissertation: refin- ing and exploratory. Refining problems are more common in practice, especially for high-fidelity optimization, because they start from a good
design and make small changes to improve it. Exploratory problems are intended to have liberal parametrizations predisposed to have significant differences between the original and final designs. The investigation of exploratory problems yields novel findings regarding multimodality in the
design space and robustness of the framework.
Multimodality in the
design space can impact the usefulness and versatility of gradient-based optimization in
wing design. Both aerodynamic and aerostructural
wing design problems are shown to be amenable to gradient-based optimization despite the existence of multimodality in some cases. For example, a rectangular
wing with constant cross-section is successfully converted, through gradient-based optimization, into a swept-back
wing with transonic airfoils and a minimum-mass structure. These studies introduce new insights into the tradeoff between skin- friction and induced drag and its impact on multimodality and optimization. The results of these studies indicate that multimodality is dependent on model fidelity and geometric parametrization. It is shown that artificial multimodality can be eliminated by improving model fidelity and numerical accuracy of functions and derivatives, whereas physically significant multimodality can be controlled with the application of geometric constraints.
The usefulness of numerical optimization in
wing design hinges on the ability of the optimizer to competently balance fundamental tradeoffs. With comprehensive access to the relevant
design parameters and physics models of the aerostructural system, an optimizer can converge to a better multidisciplinary
design than is pos- sible with a traditional, sequential
design process. This dissertation features the high-fidelity aerostructural optimization of an Embraer regional jet, in which si- multaneous optimization of airfoil shape, planform, and structural sizing variables yields a…
Advisors/Committee Members: Mader, Charles (committee member), Martins, Joaquim R R A (committee member), Young, Yin Lu (committee member), Cesnik, Carlos E (committee member).
Subjects/Keywords: multidisciplinary design optimization; aerostructural optimization; wing design optimization; multimodality in wing design; practical wing design optimization; Aerospace Engineering; Engineering
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APA (6th Edition):
Bons, N. (2020). High-Fidelity Wing Design Exploration with Gradient-Based Optimization. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/163242
Chicago Manual of Style (16th Edition):
Bons, Nicolas. “High-Fidelity Wing Design Exploration with Gradient-Based Optimization.” 2020. Doctoral Dissertation, University of Michigan. Accessed January 25, 2021.
http://hdl.handle.net/2027.42/163242.
MLA Handbook (7th Edition):
Bons, Nicolas. “High-Fidelity Wing Design Exploration with Gradient-Based Optimization.” 2020. Web. 25 Jan 2021.
Vancouver:
Bons N. High-Fidelity Wing Design Exploration with Gradient-Based Optimization. [Internet] [Doctoral dissertation]. University of Michigan; 2020. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/2027.42/163242.
Council of Science Editors:
Bons N. High-Fidelity Wing Design Exploration with Gradient-Based Optimization. [Doctoral Dissertation]. University of Michigan; 2020. Available from: http://hdl.handle.net/2027.42/163242
Delft University of Technology
3.
Sol, M.B. (author).
Conceptual Design of Swept Wing Root Aerofoils.
Degree: 2015, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9
► For modern transonic transport aeroplanes, it is important to produce low drag at high cruise speeds. The root effect, caused by effects of symmetry on…
(more)
▼ For modern transonic transport aeroplanes, it is important to produce low drag at high cruise speeds. The root effect, caused by effects of symmetry on swept wings, decreases the performance of these aeroplanes. During aeroplane
design, root modifications are applied to counteract this decrease in performance. Most conceptual aeroplane
design tools do not have a method for
design of the root aerofoil. However, the
design of the root aerofoil has a significant influence on the properties of the final
design, since it transfers the loads from the
wing to the fuselage. Therefore, having a conceptual method for
design of the
wing root aerofoil will increase the accuracy of a conceptual aeroplane
design. For conceptual
design, computational times are important, to allow the designer to try different approaches and get a feel for the
design. In this report a method is developed to approximate the root aerofoil
design to achieve straight isobars on a
wing of any given shape, within computational times that are suitable for conceptual
design. First a method is developed for estimating the pressure distribution over the root aerofoil of a given
wing. This is done by combining a method for estimation of the root effect due to thickness, a method for estimation of the root effect due to lift, a Vortex Lattice Method (VLM) and a two-dimensional panel method. A full potential method, MATRICS-V, is used to verify the results of the method, because of its proven validity. It is shown that the results of the first part of the method are generally in good agreement with results found by MATRICS-V. The effects of
wing sweep,
wing taper and addition of a
wing kink can be modelled with results that are in good agreement with the verification data. For aft swept wings with positive lift, the pressure near the leading edge is underestimated. For forward swept wings with positive lift, the pressure on the upper surface is overestimated. For wings with a cambered aerofoil an inaccuracy occurs over the forward part of the profile. The general shape of the curve, however, is captured. Secondly, this method is coupled with an optimisation method for the root aerofoil, using Class-Shape function Transformation (CST) parametrisation. The target of the optimisation is set to achieve a similar pressure distribution over the
wing root aerofoil as the pressure distribution over the outboard section of the
wing. For the developed method, it is difficult to show that the results are valid, since there is no method that has a one-to-one match with the method developed. Therefore, the results are compared to the general characteristics observed in actual root aerofoil designs. The method shows the characteristic behaviour in terms of change in camber, change in location of maximumthickness and change in incidence angle. The increase in thickness, however, is not present. This is caused by the fact that the lower surface pressure distribution is also set as a target. In actual aeroplane
design the lower surface is of less importance. In the method…
Advisors/Committee Members: Vos, R. (mentor).
Subjects/Keywords: conceptual; design; swept wing; wing root; aerofoil; straight isobars
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APA (6th Edition):
Sol, M. B. (. (2015). Conceptual Design of Swept Wing Root Aerofoils. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9
Chicago Manual of Style (16th Edition):
Sol, M B (author). “Conceptual Design of Swept Wing Root Aerofoils.” 2015. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9.
MLA Handbook (7th Edition):
Sol, M B (author). “Conceptual Design of Swept Wing Root Aerofoils.” 2015. Web. 25 Jan 2021.
Vancouver:
Sol MB(. Conceptual Design of Swept Wing Root Aerofoils. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9.
Council of Science Editors:
Sol MB(. Conceptual Design of Swept Wing Root Aerofoils. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:5bf482f6-5910-4346-abd5-785748980bc9
University of Kansas
4.
Schueler, Samantha Katelyn.
A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions.
Degree: MS, Aerospace Engineering, 2014, University of Kansas
URL: http://hdl.handle.net/1808/19593
► In 2008, the commercial aerospace industry saw substantial reductions in aircraft operating hours because of the struggling economy and high operating costs. Recurring fuel costs…
(more)
▼ In 2008, the commercial aerospace industry saw substantial reductions in aircraft operating hours because of the struggling economy and high operating costs. Recurring fuel costs range from 10-40% of total operating cost revealing an inherent need for increased fuel efficiency for in-service aircraft. Current methods, such as control system improvements and winglet installments, yield little improvement. Wingtip extensions using a new
design philosophy, however, indicate significant progress in the area through large scale reductions in the span loading of the aircraft thereby dramatically reducing induced drag. The adaptability of the wingtip extension allows for the span limitations set by the aircraft group classification to be met through the inclusion of a folding mechanism. Unlike currently used folding mechanisms, the Prandtl-tailored dynamically aerocompliant wingtip extension, explored herein, maintains the aerodynamic surface on both the upper and lower surface, thereby reducing drag further over the state of the art in active hinge mechanisms. The philosophy behind the Prandtl-tailored dynamically aerocompliant wingtip extensions follows technology commonly used in the helicopter and missile communities along with an approach by Ludwig Prandtl for reductions in induced drag. Strong pitch-flap coupling in the folding region results in reduced flapping tendencies and reduced fatigue while the shaping of the wingtip extension reduces the force increase due to the retrofit. By combining these techniques and adaptive materials, the benefits predicted through the retrofit of in-service aircraft with the wingtip extensions include: fatigue reduction, gust load alleviation, improved fuel burn efficiency, iv improved marketability through an increase in the
design range, and improved safety during adverse flying conditions. This study uses the Boeing 727-200 as an analytical proof of concept aircraft to retrofit with the Prandtl-tailored dynamically aerocompliant wingtip extensions. This aircraft was used due to the abundance of publicly available technical data while the aircraft is still in-service but out of production, therefore the study is applicable while being "non-controversial". The aerodynamic results of this study indicate substantial improvement in the fuel efficiency of the aircraft during the cruise segment of the flight profile. The smallest span wingtip extension which was analyzed resulted in a 2% cruise fuel consumption reduction while the largest span wingtip extension analyzed resulted in a 48% cruise fuel consumption reduction. Although the Boeing 727-200 was used as the basis for this analysis, this wingtip extension
design philosophy can be applied to most commercial aircraft with slight modifications to the layout and
design. By proving the concept with wingtip extensions, the market can become accustomed to adaptive
wing technology in commercial applications which, eventually, could lead to fundamentally new
wing designs.
Advisors/Committee Members: Barrett, Ronald (advisor), Taghavi, Ray (cmtemember), Chao, Haiyang (cmtemember).
Subjects/Keywords: Aerospace engineering; Adaptive structures; Wing design
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APA ·
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APA (6th Edition):
Schueler, S. K. (2014). A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions. (Masters Thesis). University of Kansas. Retrieved from http://hdl.handle.net/1808/19593
Chicago Manual of Style (16th Edition):
Schueler, Samantha Katelyn. “A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions.” 2014. Masters Thesis, University of Kansas. Accessed January 25, 2021.
http://hdl.handle.net/1808/19593.
MLA Handbook (7th Edition):
Schueler, Samantha Katelyn. “A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions.” 2014. Web. 25 Jan 2021.
Vancouver:
Schueler SK. A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions. [Internet] [Masters thesis]. University of Kansas; 2014. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/1808/19593.
Council of Science Editors:
Schueler SK. A Study in Aircraft Efficiency Enhancements via Prandtl-Tailored Dynamically Aerocompliant Wingtip Extensions. [Masters Thesis]. University of Kansas; 2014. Available from: http://hdl.handle.net/1808/19593
Cranfield University
5.
Mohd Saleh, Siti Juita Mastura.
Modelling and analysis of thin-walled structures for optimal design of composite wing.
Degree: PhD, 2017, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/14308
;
https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783253
► At present, the option for composite usage in aircraft components and the associated manufacturing process is largely based on experience, knowledge, benchmarking, and partly market…
(more)
▼ At present, the option for composite usage in aircraft components and the associated manufacturing process is largely based on experience, knowledge, benchmarking, and partly market driven. Consequently, a late realisation involving the design and manufacture, and an inevitable iterative design and validation process has led to high costs. The aim of this research is to develop a Knowledge-Based Optimisation Analysis Tool (K-BOAT) for optimal design of composite structures, subject to multi design constraints. Extensive study has been carried out on composite structure design, modelling, testing and analysis method to optimise a design of a composite wing panel during the preliminary design stage. This approach will allow the maximum knowledge input and interface between users (design engineers) with the design tool, rather than be left to the optimiser to provide a solution. The K-BOAT will build a set of parameters in the initial design, including the ratio of component dimensions, layers of different fibre angles, and bending-torsion coupling of a panel and a wing box. This framework offers a guideline for the design engineers to understand and expect the optimal solution of composite structures at the early design stage. This research focused on the optimal design of aircraft composite wing skin. The first level involved the initial analysis of the composite wing by using a low fidelity model based on thin-walled structural analysis method. The second level focused on the optimal design of the wing skin using the analytical method and validation using the high fidelity finite element (FE) method. In-house computing programs and commercial software are used for this level of study. In the third level, the FE model has been used to present a baseline structure to perform further detailed analysis and optimisation. The study is related to an industrially funded project. A case study of a practical wing structure in the project has indicated an improvement in aircraft aeroelastic stability by 30.5% from the initial design. Validation of the real industrial application proved that K-BOAT is applicable to the conceptual and preliminary phases in aircraft design.
Subjects/Keywords: Composite structure; aircraft wing structure; optimal wing design; knowledge-based; optimisation tool
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APA (6th Edition):
Mohd Saleh, S. J. M. (2017). Modelling and analysis of thin-walled structures for optimal design of composite wing. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/14308 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783253
Chicago Manual of Style (16th Edition):
Mohd Saleh, Siti Juita Mastura. “Modelling and analysis of thin-walled structures for optimal design of composite wing.” 2017. Doctoral Dissertation, Cranfield University. Accessed January 25, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/14308 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783253.
MLA Handbook (7th Edition):
Mohd Saleh, Siti Juita Mastura. “Modelling and analysis of thin-walled structures for optimal design of composite wing.” 2017. Web. 25 Jan 2021.
Vancouver:
Mohd Saleh SJM. Modelling and analysis of thin-walled structures for optimal design of composite wing. [Internet] [Doctoral dissertation]. Cranfield University; 2017. [cited 2021 Jan 25].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14308 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783253.
Council of Science Editors:
Mohd Saleh SJM. Modelling and analysis of thin-walled structures for optimal design of composite wing. [Doctoral Dissertation]. Cranfield University; 2017. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14308 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783253
Virginia Tech
6.
Meadows, Nicholas Andrew.
Multidisciplinary Design Optimization of a Medium Range Transonic Truss-Braced Wing Transport Aircraft.
Degree: MS, Aerospace and Ocean Engineering, 2011, Virginia Tech
URL: http://hdl.handle.net/10919/44022
► This study utilizes Multidisciplinary Design Optimization (MDO) techniques to explore the effectiveness of the truss-braced (TBW) and strut-braced (SBW) wing configurations in enhancing the performance…
(more)
▼ This study utilizes Multidisciplinary
Design Optimization (MDO) techniques to explore the effectiveness of the truss-braced (TBW) and strut-braced (SBW)
wing configurations in enhancing the performance of medium range, transonic transport aircraft. The truss and strut-braced
wing concepts synergize structures and aerodynamics to create a planform with decreased weight and drag. Past studies at Virginia Tech have found that these configurations can achieve significant performance benefits when compared to a cantilever aircraft with a long range, Boeing 777-200ER-like mission. The objective of this study is to explore these benefits when applied to a medium range Boeing 737-800NG-like aircraft with a cruise Mach number of 0.78, a 3,115 nautical mile range, and 162 passengers.
Results demonstrate the significant performance benefits of the SBW and TBW configurations. Both configurations exhibit reduced weight and fuel consumption. Configurations are also optimized for 1990â s or advanced technology aerodynamics. For the 1990â s technology minimum TOGW cases, the SBW and TBW configurations achieve reductions in the TOGW of as much as 6% with 20% less fuel weight than the comparable cantilever configurations. The 1990â s technology minimum fuel cases offer fuel weight reductions of about 13% compared to the 1990â s technology minimum TOGW configurations and 11% when compared to the 1990â s minimum fuel optimized cantilever configurations. The advanced aerodynamics technology minimum TOGW configurations feature an additional 4% weight savings over the comparable 1990â s technology results while the advanced technology minimum fuel cases show fuel savings of 12% over the 1990â s minimum fuel results. This translates to a 15% reduction in TOGW for the advanced technology minimum TOGW cases and a 47% reduction in fuel consumption for the advanced technology minimum fuel cases when compared to the simulated Boeing 737-800NG. It is found that the TBW configurations do not offer significant performance benefits over the comparable SBW designs.
Advisors/Committee Members: Schetz, Joseph A. (committeechair), Kapania, Rakesh K. (committee member), Bhatia, Manav (committee member).
Subjects/Keywords: Transonic Transport Aircraft; Truss-Braced Wing; Multidisciplinary Design Optimization; Strut-Braced Wing
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APA (6th Edition):
Meadows, N. A. (2011). Multidisciplinary Design Optimization of a Medium Range Transonic Truss-Braced Wing Transport Aircraft. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/44022
Chicago Manual of Style (16th Edition):
Meadows, Nicholas Andrew. “Multidisciplinary Design Optimization of a Medium Range Transonic Truss-Braced Wing Transport Aircraft.” 2011. Masters Thesis, Virginia Tech. Accessed January 25, 2021.
http://hdl.handle.net/10919/44022.
MLA Handbook (7th Edition):
Meadows, Nicholas Andrew. “Multidisciplinary Design Optimization of a Medium Range Transonic Truss-Braced Wing Transport Aircraft.” 2011. Web. 25 Jan 2021.
Vancouver:
Meadows NA. Multidisciplinary Design Optimization of a Medium Range Transonic Truss-Braced Wing Transport Aircraft. [Internet] [Masters thesis]. Virginia Tech; 2011. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/10919/44022.
Council of Science Editors:
Meadows NA. Multidisciplinary Design Optimization of a Medium Range Transonic Truss-Braced Wing Transport Aircraft. [Masters Thesis]. Virginia Tech; 2011. Available from: http://hdl.handle.net/10919/44022
University of KwaZulu-Natal
7.
Moore, Neall Neville.
Lightweight structural design of a UAV wing through the use of coreless composite materials employing novel construction techniques.
Degree: 2017, University of KwaZulu-Natal
URL: https://researchspace.ukzn.ac.za/handle/10413/17298
► A new structural layout was designed for an existing UAV wing with the aims of lightening the wing by eliminating the use of cored composite…
(more)
▼ A new structural layout was designed for an existing UAV
wing with the aims of lightening the
wing by eliminating the use of cored composite construction and reducing the manufacturing time of the
wing by making use of waterjet-cut internal frames while satisfying strength and stiffness requirements. Two layouts, a traditional metal
wing layout and a tri-directional rib lattice layout, were selected for consideration based on the literature surveyed. In order to present a valid comparison with the previous
wing design the same composite materials were used in the
design of the new
wing layout and material tests were performed according to ASTM testing standards to obtain the mechanical properties of these materials. Load cases for the
wing in flight were calculated according to FAR-23 standards and the loads on the
wing were found using XFLR5 vortex-lattice methods. An empirical, spreadsheet-based initial sizing tool was developed to obtain initial layups for an iterative FEA-based optimisation process that employed the SolidWorks Simulation Premium software package and made use of the Tsai-Wu composite material failure criterion and empirical buckling equations. The iterative optimisation resulted in the traditional metal
wing layout being selected and predicted a weight saving of 14% over the original
wing design. A full scale prototype
wing was constructed in the CSIR UAS Laboratory using wet layup techniques and laser cut internal frames as it was found that the waterjet cutting of thin composite frames was not practical as a result of the high working pressure of the waterjet cutter. The prototype
wing showed an actual weight saving of 14% but took considerably longer to manufacture due to the necessity of constructing specialised jigs to aid in the bonding and alignment of the internal frames. The prototype
wing was tested using a custom set-up whiffle tree rig up to its maximum limit load of 4.9 g and showed an average of 4% error between measured and predicted deflections thereby validating the FEA models. It was concluded that a UAV
wing can be significantly lightened through a coreless structural
design, but at the expense of an increase in construction time. It is hoped that this study will contribute towards a changed
design philosophy in an industry where cored construction is the norm. It is recommended that the methods developed during this project be applied to the rest of the aircraft components in order to obtain a lighter overall structure.
Advisors/Committee Members: Bemont, Clinton Pierre. (advisor).
Subjects/Keywords: Structural design.; Coreless composite materials.; Construction techniques.; Wing design.
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Manager
APA (6th Edition):
Moore, N. N. (2017). Lightweight structural design of a UAV wing through the use of coreless composite materials employing novel construction techniques. (Thesis). University of KwaZulu-Natal. Retrieved from https://researchspace.ukzn.ac.za/handle/10413/17298
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Moore, Neall Neville. “Lightweight structural design of a UAV wing through the use of coreless composite materials employing novel construction techniques.” 2017. Thesis, University of KwaZulu-Natal. Accessed January 25, 2021.
https://researchspace.ukzn.ac.za/handle/10413/17298.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Moore, Neall Neville. “Lightweight structural design of a UAV wing through the use of coreless composite materials employing novel construction techniques.” 2017. Web. 25 Jan 2021.
Vancouver:
Moore NN. Lightweight structural design of a UAV wing through the use of coreless composite materials employing novel construction techniques. [Internet] [Thesis]. University of KwaZulu-Natal; 2017. [cited 2021 Jan 25].
Available from: https://researchspace.ukzn.ac.za/handle/10413/17298.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Moore NN. Lightweight structural design of a UAV wing through the use of coreless composite materials employing novel construction techniques. [Thesis]. University of KwaZulu-Natal; 2017. Available from: https://researchspace.ukzn.ac.za/handle/10413/17298
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Cranfield University
8.
Cheng, Yun.
Preliminary fuselage structural configuration of a flying-wing type airline.
Degree: MSc by Research, 2012, Cranfield University
URL: http://dspace.lib.cranfield.ac.uk/handle/1826/7419
► The flying-wing is a type of configuration which is a tailless airplane accommodating all of its parts within the outline of a single airfoil. Theoretically,…
(more)
▼ The flying-wing is a type of configuration which is a tailless airplane accommodating all of its parts within the outline of a single airfoil. Theoretically, it has the most aerodynamic efficiency. The fuel consumption can be more efficient than the existed conventional airliner. It seems that this configuration can achieve the above mentioned requirements.
According to these outstanding advantages, many aircraft companies did a great deal of projects on the flying-wing concept. However, the application was only for sport and military use; for airliner, none of them entered production.
FW-11 is a flying-wing configuration airliner which is a design cooperation between Cranfield University and Aviation Industry Corporation of China (AVIC). Aiming the spatial economic and environmental needs, this 200-seat airliner would attract attention from airline companies for cost saving and environmental protection.
Before start, this program is designated for a new generation commercial aircraft to compete with the existing same capability airliner, such as Airbus A320 and Boeing 767. As the first team of this program, the aim is to finish the conceptual design and prepare the relevant document for next two teams that will perform preliminary and detail design.
As a member of FW-11 program and as part of the GDP, the author has been through the four conceptual design stages: engine manufacturers, aircraft family issues, structure design and the establishment of 3-D CAD model.
The aim of IRP study is to focus on the initial fuselage design.
Subjects/Keywords: Preliminary design; Flying-wing; multi-bubble; structure initial design; AVIC program
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APA (6th Edition):
Cheng, Y. (2012). Preliminary fuselage structural configuration of a flying-wing type airline. (Masters Thesis). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/7419
Chicago Manual of Style (16th Edition):
Cheng, Yun. “Preliminary fuselage structural configuration of a flying-wing type airline.” 2012. Masters Thesis, Cranfield University. Accessed January 25, 2021.
http://dspace.lib.cranfield.ac.uk/handle/1826/7419.
MLA Handbook (7th Edition):
Cheng, Yun. “Preliminary fuselage structural configuration of a flying-wing type airline.” 2012. Web. 25 Jan 2021.
Vancouver:
Cheng Y. Preliminary fuselage structural configuration of a flying-wing type airline. [Internet] [Masters thesis]. Cranfield University; 2012. [cited 2021 Jan 25].
Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7419.
Council of Science Editors:
Cheng Y. Preliminary fuselage structural configuration of a flying-wing type airline. [Masters Thesis]. Cranfield University; 2012. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/7419
Brno University of Technology
9.
Křížová, Barbora.
Design plachetnice: Design of Sailing Boat.
Degree: 2019, Brno University of Technology
URL: http://hdl.handle.net/11012/24730
► The topic of this master‘s thesis is design and analysis of a sailing boat in accordance with ergonomic and technological requirements. The goal is to…
(more)
▼ The topic of this master‘s thesis is
design and analysis of a sailing boat in accordance with ergonomic and technological requirements. The goal is to create a sailing boat, which will be modern, visually interesting and which and which will take future development of both
design and technology into account.
Advisors/Committee Members: Křenek, Ladislav (advisor), Řezníček, Svatopluk (referee).
Subjects/Keywords: Plachetnice; loď; plavidlo; jachta; design; křídlo; Sailing boat; sailing ship; vessel; sailing yacht; sail; design; wing; wing-sail
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APA (6th Edition):
Křížová, B. (2019). Design plachetnice: Design of Sailing Boat. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/24730
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Křížová, Barbora. “Design plachetnice: Design of Sailing Boat.” 2019. Thesis, Brno University of Technology. Accessed January 25, 2021.
http://hdl.handle.net/11012/24730.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Křížová, Barbora. “Design plachetnice: Design of Sailing Boat.” 2019. Web. 25 Jan 2021.
Vancouver:
Křížová B. Design plachetnice: Design of Sailing Boat. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/11012/24730.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Křížová B. Design plachetnice: Design of Sailing Boat. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/24730
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Delft University of Technology
10.
Elham, A.
Weight Indexing for Multidisciplinary Design Optimization of Lifting Surfaces.
Degree: 2013, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79
;
urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79
;
urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79
;
http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79
Subjects/Keywords: wing design; multidisciplinary design optimization; wing weight estimation
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Manager
APA (6th Edition):
Elham, A. (2013). Weight Indexing for Multidisciplinary Design Optimization of Lifting Surfaces. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79
Chicago Manual of Style (16th Edition):
Elham, A. “Weight Indexing for Multidisciplinary Design Optimization of Lifting Surfaces.” 2013. Doctoral Dissertation, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79.
MLA Handbook (7th Edition):
Elham, A. “Weight Indexing for Multidisciplinary Design Optimization of Lifting Surfaces.” 2013. Web. 25 Jan 2021.
Vancouver:
Elham A. Weight Indexing for Multidisciplinary Design Optimization of Lifting Surfaces. [Internet] [Doctoral dissertation]. Delft University of Technology; 2013. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79.
Council of Science Editors:
Elham A. Weight Indexing for Multidisciplinary Design Optimization of Lifting Surfaces. [Doctoral Dissertation]. Delft University of Technology; 2013. Available from: http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; urn:NBN:nl:ui:24-uuid:253459bb-e20b-4165-b093-81b1a8cf3a79 ; http://resolver.tudelft.nl/uuid:253459bb-e20b-4165-b093-81b1a8cf3a79
Indian Institute of Science
11.
Pushpangathan, Jinraj V.
Design and Development of 75 mm Fixed-Wing Nano Air Vehicle.
Degree: PhD, Faculty of Engineering, 2018, Indian Institute of Science
URL: http://etd.iisc.ac.in/handle/2005/3689
► This thesis deals with the design and development of a 75 mm fixed-wing nano-air vehicle (NAV). The NAV is designed to fit inside a cube…
(more)
▼ This thesis deals with the
design and development of a 75 mm fixed-
wing nano-air vehicle (NAV). The NAV is designed to fit inside a cube with each side measuring 75 mm. The range and endurance of the NAV are 300 m and 2-3 minutes, respectively. The high-
wing horizontal tailless NAV has a take-off weight of 19.5 g. The battery-powered single propeller NAV has two control surfaces in the form of elevator and rudder.
This thesis contains a detailed account of the airfoil selection, selection of the configuration of NAV and the longitudinal, lateral and directional aerodynamic characterization of the NAV. The development of one of the lightweight autopilot hardware which weighs 1.8 g is also given in detail. The development of non-linear equations of motion of NAV including thrust and coupling effects is also discussed. The effects of the gyroscopic coupling and counter torque on the linear dynamics of the NAV are analyzed by conducting a parametric study about the variation of the eigenstructure attributable to the varying degree of coupling in the system matrix of the linear coupled model.
A robust simultaneously stabilizing output feedback controller is synthesized for stabilizing the plants of the NAV. The synthesizing of the robust simultaneously stabilizing output feedback controller is based on a frequency-shaped central plant. A new procedure is developed to determine the frequency-shaped central plant utilizing the v-gap metric between the plants, the frequency-shaping of the plants with the pre and post compensators and the robust stabilization theory. An optimization problem is formulated to obtain these compensators. A novel iterative algorithm is developed to acquire the compensators by solving the optimization problem. Thereafter, an iterative algorithm is developed to find an output feedback controller for robust simultaneous stabilization by blending the existing features of robust stability condition of right co-prime uncertainty model of the frequency-shaped central plant, the maximum v-gap metric of the frequency-shaped central plant, H∞ loop-shaping and eigenstructure assignment algorithm for output feedback using the genetic algorithm. The six-degree-of-freedom numerical and hardware-in-loop simulations (HILS) of closed-loop non-linear and linear plants of NAV are performed to assess the performance of the controller and to validate the control algorithm implemented in the autopilot.
The airworthiness of the aircraft is tested by conducting flight trials in radio-controlled (RC) mode without including the autopilot. The successful RC flight trial of the NAV indicates airworthiness of the aircraft which aided in freezing the configuration. This is one of the smallest fixed
wing aerial vehicle that was successfully flown till date.
Advisors/Committee Members: Bhat, M Seetharama (advisor).
Subjects/Keywords: Nano Air Vehicle (NAV); Flight Control System Design; Fixed Wing Nano Air Vehicle; 75 mm Fixed-Wing Nano Air Vehicle Design; Fixed-Wing Air Vehicle; Aerospace Engineering
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APA (6th Edition):
Pushpangathan, J. V. (2018). Design and Development of 75 mm Fixed-Wing Nano Air Vehicle. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3689
Chicago Manual of Style (16th Edition):
Pushpangathan, Jinraj V. “Design and Development of 75 mm Fixed-Wing Nano Air Vehicle.” 2018. Doctoral Dissertation, Indian Institute of Science. Accessed January 25, 2021.
http://etd.iisc.ac.in/handle/2005/3689.
MLA Handbook (7th Edition):
Pushpangathan, Jinraj V. “Design and Development of 75 mm Fixed-Wing Nano Air Vehicle.” 2018. Web. 25 Jan 2021.
Vancouver:
Pushpangathan JV. Design and Development of 75 mm Fixed-Wing Nano Air Vehicle. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2018. [cited 2021 Jan 25].
Available from: http://etd.iisc.ac.in/handle/2005/3689.
Council of Science Editors:
Pushpangathan JV. Design and Development of 75 mm Fixed-Wing Nano Air Vehicle. [Doctoral Dissertation]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3689
IUPUI
12.
Gandhi, Viraj D.
Parametric Designs and Weight Optimization using Direct and Indirect Aero-structure Load Transfer Methods.
Degree: 2019, IUPUI
URL: http://hdl.handle.net/1805/19941
► Indiana University-Purdue University Indianapolis (IUPUI)
Within the aerospace design, analysis and optimization community, there is an increasing demand to finalize the preliminary design phase of…
(more)
▼ Indiana University-Purdue University Indianapolis (IUPUI)
Within the aerospace design, analysis and optimization community, there is an increasing demand to finalize the preliminary design phase of the wing as quickly as possible without losing much on accuracy. This includes rapid generation of designs, an early adaption of higher fidelity models and automation in structural analysis of the internal structure of the wing. To perform the structural analysis, the aerodynamic load can be transferred to the wing using many different methods. Generally, for preliminary analysis, indirect load transfer method is used and for detailed analysis, direct load transfer method is used. For the indirect load transfer method, load is discretized using shear-moment-torque (SMT) curve and applied to ribs of the wing. For the direct load transfer method, the load is distributed using one-way Fluid-Structure Interaction (FSI) and applied to the skin of the wing. In this research, structural analysis is performed using both methods and the nodal displacement is compared. Further, to optimize the internal structure, iterative changes are made in the number of structural members. To accommodate these changes in geometry as quickly as possible, the parametric design method is used through Engineering SketchPad (ESP). ESP can also provide attributions the geometric feature and generate multi-fidelity models consistently. ESP can generate the Nastran mesh file (.bdf) with the nodes and the elements grouped according to their geometric attributes. In this research, utilizing the attributions and consistency in multi-fidelity models an API is created between ESP and Nastran to automatize the multi-fidelity structural optimization. This API generates the design with appropriate parameters and mesh file using ESP. Through the attribution in the mesh file, the API works as a pre-processor to apply material properties, boundary condition, and optimization parameters. The API sends the mesh file to Nastran and reads the results file to iterate the number of the structural member in design. The result file is also used to transfer the nodal deformation from lower-order fidelity structural models onto the higher-order ones to have multi-fidelity optimization. Here, static structural optimization on the whole wing serves as lower fidelity model and buckling optimization on each stiffened panel serves as higher fidelity model. To further extend this idea, a parametric model of the whole aircraft is also created.
2021-08-17
Advisors/Committee Members: Dalir, Hamid, Dannenhoffer, John F., III, Larriba-Andaluz, Carlos.
Subjects/Keywords: Multifidelity optimization; Parametric design; Weight optimization of wing
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APA (6th Edition):
Gandhi, V. D. (2019). Parametric Designs and Weight Optimization using Direct and Indirect Aero-structure Load Transfer Methods. (Thesis). IUPUI. Retrieved from http://hdl.handle.net/1805/19941
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Gandhi, Viraj D. “Parametric Designs and Weight Optimization using Direct and Indirect Aero-structure Load Transfer Methods.” 2019. Thesis, IUPUI. Accessed January 25, 2021.
http://hdl.handle.net/1805/19941.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Gandhi, Viraj D. “Parametric Designs and Weight Optimization using Direct and Indirect Aero-structure Load Transfer Methods.” 2019. Web. 25 Jan 2021.
Vancouver:
Gandhi VD. Parametric Designs and Weight Optimization using Direct and Indirect Aero-structure Load Transfer Methods. [Internet] [Thesis]. IUPUI; 2019. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/1805/19941.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Gandhi VD. Parametric Designs and Weight Optimization using Direct and Indirect Aero-structure Load Transfer Methods. [Thesis]. IUPUI; 2019. Available from: http://hdl.handle.net/1805/19941
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Penn State University
13.
Kambampati, Sandilya.
Optimization of Composite Tiltrotor Wings with Extensions and Winglets.
Degree: 2016, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/ns0646000
► Tiltrotors suffer from an aeroelastic instability during forward flight called whirl flutter. Whirl flutter is caused by the whirling motion of the rotor, characterized by…
(more)
▼ Tiltrotors suffer from an aeroelastic instability during forward flight called whirl
flutter. Whirl flutter is caused by the whirling motion of the rotor, characterized
by highly coupled
wing-rotor-pylon modes of vibration. Whirl flutter is a major
obstacle for tiltrotors in achieving high-speed flight. The conventional approach to
assure adequate whirl flutter stability margins for tiltrotors is to
design the wings
with high torsional stiffness, typically using 23% thickness-to-chord ratio wings.
However, the large aerodynamic drag associated with these high thickness-to-chord
ratio wings decreases aerodynamic efficiency and increases fuel consumption. Wingtip
devices such as
wing extensions and winglets have the potential to increase the
whirl flutter characteristics and the aerodynamic efficiency of a tiltrotor. However,
wing-tip devices can add more weight to the aircraft.
In this study, multi-objective parametric and optimization methodologies for
tiltrotor aircraft with
wing extensions and winglets are investigated. The objectives
are to maximize aircraft aerodynamic efficiency while minimizing weight penalty due
to extensions and winglets,
subject to whirl flutter constraints. An aeroelastic model
that predicts the whirl flutter speed and a
wing structural model that computes
strength and weight of a composite
wing are developed. An existing aerodynamic
model (that predicts the aerodynamic efficiency) is merged with the developed
structural and aeroelastic models for the purpose of conducting parametric and
optimization studies. The variables of interest are the
wing thickness and structural
properties, and extension and winglet planform variables. The Bell XV-15 tiltrotor
aircraft the chosen as the parent aircraft for this study.
Parametric studies reveal that a
wing extension of span 25% of the inboard
wing
increases the whirl flutter speed by 10% and also increases the aircraft aerodynamic
efficiency by 8%. Structurally tapering the
wing of a tiltrotor equipped with an
extension and a winglet can increase the whirl flutter speed by 15% while reducing
the
wing weight by 7.5%.
The baseline
design for the optimization is the optimized
wing with no extension
or winglet. The optimization studies reveal that the optimum
design for a cruise speed of 250 knots has an increased aerodynamic efficiency of 7% over the baseline
design for only a weight penalty of 3% – thus a better transport range of 5.5%
more than the baseline. The optimal
design for a cruise speed of 300 knots has
an increased aerodynamic efficiency of 5%, a weight penalty of 2.5%, and a better
transport range of 3.5% more than the baseline.
Advisors/Committee Members: Edward Smith, Dissertation Advisor/Co-Advisor, Edward Smith, Committee Chair/Co-Chair, Jose Palacios, Committee Member, Mark David Maughmer, Committee Member, Christopher Rahn, Outside Member.
Subjects/Keywords: optimization; tiltrotor; winglet; whirl flutter; composite material; wing extensions; aircraft design
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Manager
APA (6th Edition):
Kambampati, S. (2016). Optimization of Composite Tiltrotor Wings with Extensions and Winglets. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/ns0646000
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Kambampati, Sandilya. “Optimization of Composite Tiltrotor Wings with Extensions and Winglets.” 2016. Thesis, Penn State University. Accessed January 25, 2021.
https://submit-etda.libraries.psu.edu/catalog/ns0646000.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Kambampati, Sandilya. “Optimization of Composite Tiltrotor Wings with Extensions and Winglets.” 2016. Web. 25 Jan 2021.
Vancouver:
Kambampati S. Optimization of Composite Tiltrotor Wings with Extensions and Winglets. [Internet] [Thesis]. Penn State University; 2016. [cited 2021 Jan 25].
Available from: https://submit-etda.libraries.psu.edu/catalog/ns0646000.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Kambampati S. Optimization of Composite Tiltrotor Wings with Extensions and Winglets. [Thesis]. Penn State University; 2016. Available from: https://submit-etda.libraries.psu.edu/catalog/ns0646000
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Washington University in St. Louis
14.
Hainline, Kevin.
Vehicle Design Study of a Straight Flying-Wing with Bell-Shaped Spanload.
Degree: MS, Mechanical Engineering & Materials Science, 2020, Washington University in St. Louis
URL: https://openscholarship.wustl.edu/eng_etds/512
► Straight flying-wing configurations, that is flying wings with zero quarter-chord sweep, are key to understanding bird flight, have potential performance improvements, and are suitable for…
(more)
▼ Straight flying-
wing configurations, that is flying wings with zero quarter-chord sweep, are key to understanding bird flight, have potential performance improvements, and are suitable for "survivable" applications. Straight flying-wings are also well suited for morphing geometry, e.g. with variable twist, since changes in lift distribution do not impact longitudinal equilibrium. The straight-flying
wing can adjust its lift distribution to optimize aerodynamic efficiency across a wide range of flight conditions. In this thesis, we conduct the
design study of a flying-
wing with bell-shaped spanload; the study vehicle is called "Biom T1". Biom T1 has a more efficient directional control scheme acheived by employing the same bell-shaped lift-distribution as used by birds which creates a downwash distribution favorable to proverse yaw in the outer portion of the
wing. The flying qualities and control system robustness are demonstrated through linear analysis and it is shown that straight flying-wings are viable in terms of stability and control and are suitable for high-efficiency, low-payload-volume applications.
Advisors/Committee Members: Dr. Ramesh Agarwal, Kevin A. Wise
David A. Peters.
Subjects/Keywords: Aircraft Design Bell-Shaped Birds Flying Wing; Engineering
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APA ·
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MLA ·
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Export
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Manager
APA (6th Edition):
Hainline, K. (2020). Vehicle Design Study of a Straight Flying-Wing with Bell-Shaped Spanload. (Thesis). Washington University in St. Louis. Retrieved from https://openscholarship.wustl.edu/eng_etds/512
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Hainline, Kevin. “Vehicle Design Study of a Straight Flying-Wing with Bell-Shaped Spanload.” 2020. Thesis, Washington University in St. Louis. Accessed January 25, 2021.
https://openscholarship.wustl.edu/eng_etds/512.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Hainline, Kevin. “Vehicle Design Study of a Straight Flying-Wing with Bell-Shaped Spanload.” 2020. Web. 25 Jan 2021.
Vancouver:
Hainline K. Vehicle Design Study of a Straight Flying-Wing with Bell-Shaped Spanload. [Internet] [Thesis]. Washington University in St. Louis; 2020. [cited 2021 Jan 25].
Available from: https://openscholarship.wustl.edu/eng_etds/512.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Hainline K. Vehicle Design Study of a Straight Flying-Wing with Bell-Shaped Spanload. [Thesis]. Washington University in St. Louis; 2020. Available from: https://openscholarship.wustl.edu/eng_etds/512
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Delft University of Technology
15.
Hendrich, T.J.M. (author).
Multidisciplinary Design Optimization in the Conceptual Design Phase: Creating a Conceptual Design of the Blended Wing-Body with the BLISS Optimization Strategy.
Degree: 2011, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:d586ee6e-4815-4561-87d9-6ae00bdb739e
► Traditionally, the aircraft design process is divided into three phases: conceptual, preliminary and detailed design. In each subsequent phase, the fidelity of the analysis tools…
(more)
▼ Traditionally, the aircraft
design process is divided into three phases: conceptual, preliminary and detailed
design. In each subsequent phase, the fidelity of the analysis tools increases and more and more details of the
design geometry are frozen. In each phase a number of
design variants is generated, fully analyzing them with the tools available, and then doing trade studies between important
design variables to finally choose the best variant. In the past, this approach has shown good results for 'Kansas city' type aircraft, which could be decomposed into different airframe parts with distinct functions, such as wings, tail, engines and fuselage. Each part needs to fullfill its own set of requirements and could be designed and optimized relatively independently from the others. For the new generation of large transport aircraft, such as the Blended
Wing Body (BWB), the traditional
design approach is less suited. The Blended
Wing-Body - studied by Boeing and many others as a future long-haul transport aircraft concept - is characterized by an integrated airframe, in which the aforementioned parts can no longer be clearly distinguished. The Blended
Wing-Body features many and strong interactions between the various
design disciplines and airframe subparts. Using the traditional
design doctrine, these interactions greatly increase the required time to
design. Over the past years,Multidisciplinary
Design Optimization (MDO) is being considered as an alternative. Nowadays, in industry the MDO approach is mainly used in the detail
design phase and for isolated, well-defined
design cases. The goal of this project is to create an MDO framework which can aid the designer in optimizing entire aircraft designs in the conceptual phase. This framework is shaped to the Bi-level Integrated System Synthesis (BLISS) strategy. This strategy splits the optimization into two levels: a disciplinary level, and a system one. Before optimization, BLISS performs a sensitivity analysis to obtain linearized global sensitivities of the
design objective and constraints to each of the
design variables. Validation is done using three cases: two sample problems from literature with known solutions, and the optimization of a simplified Boeing 747
wing for maximum aerodynamic efficiency using an aerodynamic and structural model. All three cases were optimized succesfully. Finally, as a proof-of-concept for MDO, the framework is required to find an conceptual
design of the Blended
Wing-Body with minimum structural weight and minimum drag across a given mission. Meanwhile, structural, aerodynamic and performance constraints had to be satisfied. The problem features 5 disciplines, 93 constraints, 110 states and in total 92
design variables. Again, BLISS could converge to a solution, requiring 4 hours per cycle. By tuning the
design variables, BLISS managed to converge to a final
design in 22 cycles. The final
design satisfies all constraints, except for the large local Mach number on the outboard
wing. Similar problems were identified in several…
Advisors/Committee Members: Schroijen, M.J.T. (mentor), Bijl, H. (mentor), Visser, H.G. (mentor), La Rocca, G. (mentor).
Subjects/Keywords: MDO; multidisciplinary; BLISS; Blended Wing Body; design; optimization
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APA (6th Edition):
Hendrich, T. J. M. (. (2011). Multidisciplinary Design Optimization in the Conceptual Design Phase: Creating a Conceptual Design of the Blended Wing-Body with the BLISS Optimization Strategy. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:d586ee6e-4815-4561-87d9-6ae00bdb739e
Chicago Manual of Style (16th Edition):
Hendrich, T J M (author). “Multidisciplinary Design Optimization in the Conceptual Design Phase: Creating a Conceptual Design of the Blended Wing-Body with the BLISS Optimization Strategy.” 2011. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:d586ee6e-4815-4561-87d9-6ae00bdb739e.
MLA Handbook (7th Edition):
Hendrich, T J M (author). “Multidisciplinary Design Optimization in the Conceptual Design Phase: Creating a Conceptual Design of the Blended Wing-Body with the BLISS Optimization Strategy.” 2011. Web. 25 Jan 2021.
Vancouver:
Hendrich TJM(. Multidisciplinary Design Optimization in the Conceptual Design Phase: Creating a Conceptual Design of the Blended Wing-Body with the BLISS Optimization Strategy. [Internet] [Masters thesis]. Delft University of Technology; 2011. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:d586ee6e-4815-4561-87d9-6ae00bdb739e.
Council of Science Editors:
Hendrich TJM(. Multidisciplinary Design Optimization in the Conceptual Design Phase: Creating a Conceptual Design of the Blended Wing-Body with the BLISS Optimization Strategy. [Masters Thesis]. Delft University of Technology; 2011. Available from: http://resolver.tudelft.nl/uuid:d586ee6e-4815-4561-87d9-6ae00bdb739e
Delft University of Technology
16.
Zohlandt, C.N. (author).
Conceptual Design of High Subsonic Prandtl Planes.
Degree: 2016, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:e1f01743-e2eb-4d8b-8b2c-131f50f41a2c
► The increasing airtraffic demands on aircraft capacity, sustainability and profitability, require the investigation of unconventional aircraft configurations with high aerodynamic efficiency, as the commonly applied…
(more)
▼ The increasing airtraffic demands on aircraft capacity, sustainability and profitability, require the investigation of unconventional aircraft configurations with high aerodynamic efficiency, as the commonly applied fuselage-wing-tail configuration shows to reach an optimum in that respect which cannot be further improved using current technology. The application of the box wing system, following from the Best Wing System theory presented by Ludwig Prandtl in 1924, theoretically results in an aircraft configuration generating minimum induced drag, named Prandtl Plane. A balanced performance analysis and comparison is performed in this research, in terms of fuel burn, structural weight and cost benefits, to indicate the types of missions in which the Prandtl Plane could provide a superior alternative to conventional aircraft. For the purpose of this research, the Initiator has been used as the design and analysis environment. Methods applied specifically for the design and analysis of the Prandtl Plane configuration have been implemented in the tool, to compare the performance with respect to conventional aircraft, in the high subsonic transport category. Parametric studies have been performed on the wing design variables to assess the sensitivity of the Prandtl Plane performance. The aspect ratio of the total wing system showed to have the largest influence on the aerodynamic performance, where a large AR results in high aerodynamic efficiency, however at the same time this yields a high wing weight. Three comparison studies have been performed between a PrP and conventional aircraft, designed using the Initiator to perform a single aisle - medium range mission typically covered by an A320-200 (144 pax, range of 4,000 km), a twin aisle - long range mission typically flown by an A340-300 (270 pax, 10,500 km) and finally a high payload - low range mission (514 pax, 2,500 km) for which no conventional aircraft are specifically designed, but large aircraft such as the A380 are exploited. On each of these missions, the PrP design shows lower induced drag during cruise, as expected, and a lower fuselage weight due to distributed bending loads from the double-wing system. An a single aisle – medium range mission this results in 8% savings in fuel burn, on the long range mission in 10% savings in fuel burn and 9% on DOC. Due to a smaller wing span, the capacity of this type of Prandtl Plane can be increased further without exceeding the dimensional constraints on wing span, and could therefore be a competitor of the A380 which currently marks the maximum capabilities of aircraft in terms of maximum range and payload capacity, due to span restrictions imposed by gate dimensions on existing airports. Prandtl planes with a higher passenger capacity could be exploited on existing routes, while meeting identical airport restrictions.
Flight Performance and Propulsion
Flight Performance and Propulsion
Aerospace Engineering
Advisors/Committee Members: La Rocca, G. (mentor).
Subjects/Keywords: Prandtl Plane; box wing; initiator; conceptual aircraft design
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APA (6th Edition):
Zohlandt, C. N. (. (2016). Conceptual Design of High Subsonic Prandtl Planes. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:e1f01743-e2eb-4d8b-8b2c-131f50f41a2c
Chicago Manual of Style (16th Edition):
Zohlandt, C N (author). “Conceptual Design of High Subsonic Prandtl Planes.” 2016. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:e1f01743-e2eb-4d8b-8b2c-131f50f41a2c.
MLA Handbook (7th Edition):
Zohlandt, C N (author). “Conceptual Design of High Subsonic Prandtl Planes.” 2016. Web. 25 Jan 2021.
Vancouver:
Zohlandt CN(. Conceptual Design of High Subsonic Prandtl Planes. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:e1f01743-e2eb-4d8b-8b2c-131f50f41a2c.
Council of Science Editors:
Zohlandt CN(. Conceptual Design of High Subsonic Prandtl Planes. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:e1f01743-e2eb-4d8b-8b2c-131f50f41a2c
17.
Vanneste, Thomas.
Développement d'un outil de modélisation aéroélastique du vol battu de l'insecte appliqué à la conception d'un nano-drone résonant : Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant nano air vehicle.
Degree: Docteur es, Mécanique, 2013, Valenciennes
URL: http://www.theses.fr/2013VALE0021
► Développer, à partir de zéro, un drone imitant le vol battu de l'insecte est une tâche ambitieuse et ardue pour un designer en raison du…
(more)
▼ Développer, à partir de zéro, un drone imitant le vol battu de l'insecte est une tâche ambitieuse et ardue pour un designer en raison du manque de savoir-faire en la matière. Pour en accélérer le développement pendant les phases de design préliminaires, un outil modélisant les phénomènes aéroélastiques du vol de l'insecte est un véritable atout pour le designer et est le sujet de cette thèse. Le cœur de cet outil est un solveur éléments finis 'structure' couplé, en utilisant une approche par tranche, à un modèle aérodynamique quasi-statique du vol de l'insecte prenant en compte la flexibilité de l'aile, à la fois selon l'envergure et la corde, mais aussi ses grands déplacements. L'ensemble est conçu de manière à contenir le coût de calcul tout en étant assez modulaire pour s'adapter à un large panel d'applications. Afin de valider l'intégralité de cet outil, un processus en deux étapes a été entrepris avec d'abord une approche numérique et ensuite une validation expérimentale grâce à un banc de caractérisation dédié. Les résultats du modèle concordent de manière satisfaisante dans les deux cas, capturant l'amortissement dû aux forces aérodynamiques, et ouvrent ainsi la voie à son utilisation pour le design de drones à ailes battantes. Pour démontrer l'intérêt de cette approche lors des phases de design préliminaires, deux applications sur un nano-drone résonant sont réalisées: la définition d'une stratégie d'actionnement efficace et la recherche d'une géométrie d'aile potentiellement intéressante d'un point de vue aérodynamique, en couplant l'outil de modélisation à un algorithme génétique. Les résultats obtenus sont cohérents avec ceux trouvés dans la nature et sont en cours d'implémentation sur le drone.
Developing insect-like flapping-wing drones from scratch is an ambitious and arduous task for designers due to a lack of well-established know-how. To speed up the development of such vehicles through the preliminary design stage, a framework modeling the aeroelastic phenomena encountered in insect flight is an asset and is the subject of this thesis. Its kernel is a FEM based structural solver coupled in a blade-element approach to a quasi-steady aerodynamic model of insect flight accounting for the wing flexibility, both in the spanwise and in the chordwise direction, and for its large displacement. The complete framework is devised so as to maintain the computation load low while being modular enough for a wide range of applications. To validate the overall aeroelastic framework, a two-steps process has been undertaken with in one hand numerical studies and in the other hand experimental ones acquired on a dedicated test bench. The framework computation agrees satisfactorily, capturing the damping due to the aerodynamic force, and thus paves the way for preliminary design applications of a flapping-wing vehicle. To exhibit the capabilities of the framework as a preliminary design tool, two applications on a resonant nano air vehicle are performed: the definition of an efficient actuation strategy and the…
Advisors/Committee Members: Cattan, Eric (thesis director), Grondel, Sébastien (thesis director), Paquet, Jean-Bernard (thesis director).
Subjects/Keywords: Aile battante; Modèle aéroélastique; Aile souple; Optimisation; Outil de dimensionnement; Flapping-wing; Aeroelastic framework; Flexible wing; Optimization; Design tool
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APA (6th Edition):
Vanneste, T. (2013). Développement d'un outil de modélisation aéroélastique du vol battu de l'insecte appliqué à la conception d'un nano-drone résonant : Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant nano air vehicle. (Doctoral Dissertation). Valenciennes. Retrieved from http://www.theses.fr/2013VALE0021
Chicago Manual of Style (16th Edition):
Vanneste, Thomas. “Développement d'un outil de modélisation aéroélastique du vol battu de l'insecte appliqué à la conception d'un nano-drone résonant : Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant nano air vehicle.” 2013. Doctoral Dissertation, Valenciennes. Accessed January 25, 2021.
http://www.theses.fr/2013VALE0021.
MLA Handbook (7th Edition):
Vanneste, Thomas. “Développement d'un outil de modélisation aéroélastique du vol battu de l'insecte appliqué à la conception d'un nano-drone résonant : Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant nano air vehicle.” 2013. Web. 25 Jan 2021.
Vancouver:
Vanneste T. Développement d'un outil de modélisation aéroélastique du vol battu de l'insecte appliqué à la conception d'un nano-drone résonant : Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant nano air vehicle. [Internet] [Doctoral dissertation]. Valenciennes; 2013. [cited 2021 Jan 25].
Available from: http://www.theses.fr/2013VALE0021.
Council of Science Editors:
Vanneste T. Développement d'un outil de modélisation aéroélastique du vol battu de l'insecte appliqué à la conception d'un nano-drone résonant : Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant nano air vehicle. [Doctoral Dissertation]. Valenciennes; 2013. Available from: http://www.theses.fr/2013VALE0021
Delft University of Technology
18.
Brown, M.T.H. (author).
Conceptual Design of Blended Wing Body Airliners Within a Semi-automated Design Framework.
Degree: 2017, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:6f66cd83-673c-4a20-ae5f-c3ea1b7ce3c3
► Blended wing body aircraft represent a paradigm shift in jet transport aircraft design. Stepping away from the conventional tube-and-wing philosophy, they promise benefits over existing…
(more)
▼ Blended
wing body aircraft represent a paradigm shift in jet transport aircraft
design. Stepping away from the conventional tube-and-
wing philosophy, they promise benefits over existing or future conventional aircraft. The most significant challenge with the concept is the increased coupling between aircraft
design disciplines that has necessitated the development and implementation of multidisciplinary
design optimisation routines. A novel conceptual aircraft
design program named the Initiator has been developed that is able to
design conventional and unconventional passenger transport aircraft, enabling comparisons to be made which are based on the same top level requirements and analysis fidelity. It however lacks the ability to
design or analyse the blended
wing body. The aim of this thesis is to make comparative studies between the blended-
wing-body aircraft and its conventional tube-and-
wing counterpart based upon the same
design requirements. To this end the work investigates the methods that are required to implement the blended
wing body aircraft in a semi-automated
design framework such as the Initiator. By developing a novel geometric parametrisation of the blended
wing body, the
design possibilities have been increased while maintaining straightforward shaping manipulation and robustness. All relevant topics of conceptual aircraft layout are considered, making the resulting aircraft feasible in terms of the integration of its components. Furthermore, methods have been implemented or developed which are capable of analysing the mass, aerodynamic performance and longitudinal stability of the aircraft to a fidelity which is suitable for conceptual
design. The mass estimation methods that have been implemented are verified and validated to be within 10% of reference blended
wing bodies with a smaller error of 5% being common. There is however significant scatter in reference results, making conclusive statements about accuracy difficult. Drag estimations perform less accurately with drag being overpredicted by approximately 20%. The cause of this over prediction was largely due to empirical corrections for miscellaneous and unaccounted drag sources as is done for conventional aircraft. Wave drag is considerably higher than reference cases (7 versus 1 counts). Considering the applicability of the implemented method to blended
wing bodies and the limited specific transonic
design that is performed, it is chosen to accept this result as a conservative estimate until higher order validations of the wave drag can be performed. Induced drag was also higher for the test cases but results are inconclusive whether this is an error or a true result of the
design choices. Zero-lift drag has however been accurately estimated by the novel implementation of empirical methods. Test case blended
wing body and tube and
wing aircraft were formed in the 150, 250 and 400 passenger classes. The comparisons of the resulting aircraft show that the blended
wing body is feasible at the fidelity level achieved. They have reduced mass,…
Advisors/Committee Members: Vos, R. (mentor).
Subjects/Keywords: Blended Wing Body; BWB; Hybrid Wing Body; HWB; conceptual; design; MDO; KBE; unconventional; passenger; aircraft; oval fuselage
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APA (6th Edition):
Brown, M. T. H. (. (2017). Conceptual Design of Blended Wing Body Airliners Within a Semi-automated Design Framework. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:6f66cd83-673c-4a20-ae5f-c3ea1b7ce3c3
Chicago Manual of Style (16th Edition):
Brown, M T H (author). “Conceptual Design of Blended Wing Body Airliners Within a Semi-automated Design Framework.” 2017. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:6f66cd83-673c-4a20-ae5f-c3ea1b7ce3c3.
MLA Handbook (7th Edition):
Brown, M T H (author). “Conceptual Design of Blended Wing Body Airliners Within a Semi-automated Design Framework.” 2017. Web. 25 Jan 2021.
Vancouver:
Brown MTH(. Conceptual Design of Blended Wing Body Airliners Within a Semi-automated Design Framework. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:6f66cd83-673c-4a20-ae5f-c3ea1b7ce3c3.
Council of Science Editors:
Brown MTH(. Conceptual Design of Blended Wing Body Airliners Within a Semi-automated Design Framework. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:6f66cd83-673c-4a20-ae5f-c3ea1b7ce3c3
Brno University of Technology
19.
Jurda, Martin.
Návrh křídla soutěžního letounu: Wing design of competition aircraft.
Degree: 2020, Brno University of Technology
URL: http://hdl.handle.net/11012/192570
► This bachelor thesis deals with wing design of the new competition aircraft for the SAE Aero Design East 2020 competition. Introduction of the thesis is…
(more)
▼ This bachelor thesis deals with
wing design of the new competition aircraft for the SAE Aero
Design East 2020 competition. Introduction of the thesis is focused on explanation and analysis of the rules taking into account
wing design with the following analysis of the scoring equation. Following chapter deals with a research study on the concept of
wing and the
design of conceptual
wing possibilities. Thesis continues with computational chapters containing calculations of the characteristics of designed
wing and flight envelope load together with the
wing load. The last part is a chapter including structural
design of the
wing and attachment of the
wing to the aircraft.
Advisors/Committee Members: Katrňák, Tomáš (advisor), Navrátil, Jan (referee).
Subjects/Keywords: Návrh krídla; SAE Aero Design East; bodová analýza; koncepčný návrh; letová obálka; zaťaženie krídla; Wing design; SAE Aero Design East; point analysis; conceptual design; flight envelope; wing load
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APA (6th Edition):
Jurda, M. (2020). Návrh křídla soutěžního letounu: Wing design of competition aircraft. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/192570
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Jurda, Martin. “Návrh křídla soutěžního letounu: Wing design of competition aircraft.” 2020. Thesis, Brno University of Technology. Accessed January 25, 2021.
http://hdl.handle.net/11012/192570.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Jurda, Martin. “Návrh křídla soutěžního letounu: Wing design of competition aircraft.” 2020. Web. 25 Jan 2021.
Vancouver:
Jurda M. Návrh křídla soutěžního letounu: Wing design of competition aircraft. [Internet] [Thesis]. Brno University of Technology; 2020. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/11012/192570.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Jurda M. Návrh křídla soutěžního letounu: Wing design of competition aircraft. [Thesis]. Brno University of Technology; 2020. Available from: http://hdl.handle.net/11012/192570
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Delft University of Technology
20.
Schouten, Tom (author).
Assessment of Conceptual High-Capacity Regional Turbopropeller Aircraft.
Degree: 2018, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:236ad212-eb0b-443d-a40d-602ec6fe64f9
► Designers are motivated to create more a efficient aircraft design following the growth of the market and environmental restrictions. As a result new interest in…
(more)
▼ Designers are motivated to create more a efficient aircraft design following the growth of the market and environmental restrictions. As a result new interest in propeller-powered aircraft as such engines show higher theoretical propulsive efficiency as compared to turbofan engines. The employment of turboprop engines on commercial aircraft has so far been limited on short-range regional aircraft, capable of transporting up to seventy passengers. The thesis shows the feasibility of a 130-passenger commercial turboprop aircraft configuration where propeller forces and slipstream effects are included in the determination of aircraft longitudinal stability and control. For configurations with increased stabilizer dynamic pressure the stability, equilibrium and rotation limits are reduced in restrictiveness, allowing for a decrease of horizontal stabilizer area. However, these limits should still be satisfied in power-out conditions, eliminating the possibility of design an conventional aircraft capable of utilizing the slipstream effect fully in order to reduce the horizontal stabilizer area. The final results present a set of 130-passenger turboprop aircraft where the main influence of the key performance indicators is the engine positioning. The set of configurations is shown to be competitive based on a comparison with existing turboprop aircraft and turbofan aircraft operating on the same mission.
Flight Performance and Propulsion
Advisors/Committee Members: Vos, Roelof (mentor), Delft University of Technology (degree granting institution).
Subjects/Keywords: aircraft design; Initiator; slipstream; longitudinal stability; longitudinal control; propeller wing interaction; conceptual design; feasibility study
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Export
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Manager
APA (6th Edition):
Schouten, T. (. (2018). Assessment of Conceptual High-Capacity Regional Turbopropeller Aircraft. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:236ad212-eb0b-443d-a40d-602ec6fe64f9
Chicago Manual of Style (16th Edition):
Schouten, Tom (author). “Assessment of Conceptual High-Capacity Regional Turbopropeller Aircraft.” 2018. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:236ad212-eb0b-443d-a40d-602ec6fe64f9.
MLA Handbook (7th Edition):
Schouten, Tom (author). “Assessment of Conceptual High-Capacity Regional Turbopropeller Aircraft.” 2018. Web. 25 Jan 2021.
Vancouver:
Schouten T(. Assessment of Conceptual High-Capacity Regional Turbopropeller Aircraft. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:236ad212-eb0b-443d-a40d-602ec6fe64f9.
Council of Science Editors:
Schouten T(. Assessment of Conceptual High-Capacity Regional Turbopropeller Aircraft. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:236ad212-eb0b-443d-a40d-602ec6fe64f9
Virginia Tech
21.
Blaesser, Nathaniel James.
Interference Drag Due to Engine Nacelle Location for a Single-Aisle, Transonic Aircraft.
Degree: PhD, Aerospace Engineering, 2020, Virginia Tech
URL: http://hdl.handle.net/10919/96446
► Engine placement on an aircraft is dependent on multiple disciplines. Engine placement affects the noise of the aircraft because the wing can shield or reflect…
(more)
▼ Engine placement on an aircraft is dependent on multiple disciplines. Engine placement affects the noise of the aircraft because the
wing can shield or reflect the engine noise. Engine placement impacts the structural loads of an aircraft, with some positions requiring more reinforcement that adds to the cost and weight of the aircraft. Aerodynamically, the engine placement impacts the vehicle's drag. Taken together, the only means of trading the different disciplines' needs is through a multidisciplinary
design optimization (MDO) framework. The challenge of MDO frameworks is that they require numerous solutions to effectively explore the trade space. Thus, MDO frameworks employ fast, low-order tools to compute hundreds or thousands of different combinations of features. A common approach to make running MDO analysis feasible is to develop surrogate models of the key considerations. Current aerodynamic drag build-ups for aircraft do not consider the interference drag associated with engine placement. The first goal of this research was to determine the feasibility of generating a surrogate model for inclusion in an MDO framework. In order to collect the data required for the surrogate, appropriate tools to capture the interference drag are required. Building a surrogate requires a large number of samples, thus the aerodynamic solver must be fast, robust, and accurate.
An Euler (inviscid) computational fluid dynamics (CFD) was used do explore the engine placement
design space to test the feasibility of building the surrogate model. The target aircraft was a single-aisle, transonic aircraft with a freestream Mach number of 0.8, flying at an altitude of 35,000 feet and a
design lift coefficient of 0.5. The initial vehicle used a baseline
wing, and the engine placement was varied across the
wing span and fuselage. The results showed that the conventional location, where the engine is forward and beneath the
wing, had the a modestly beneficial interference drag, though positions near the trailing edge and above the
wing also showed neutral interference drag. In general, if the engine overlapped the
wing, the interference drag increased dramatically.
%
A follow-on study used Reynolds Averaged Navier-Stokes (RANS) CFD to investigate seven engine placements above and aft of the
wing. Each of these positions had the
wing tailored such that the
wing performance would be typical of a good transonic
wing. The results showed that with
wing tailoring, a moderate amount of overlap between the
wing and nacelle results in reduced or neutral interference drag. This is in contrast with the baseline
wing results that showed moderate overlap led to large increases in interference drag.
%
The results from this research suggest that building a surrogate model of interference drag for transonic aircraft is not feasible given today's computational resources. In order to accurately model the interference drag, one must use a RANS CFD solver and tailor the
wing. These requirements increase the cost of evaluating an engine position such…
Advisors/Committee Members: Schetz, Joseph A. (committeechair), Kapania, Rakesh K. (committeechair), Raj, Pradeep (committee member), Lowe, Kevin T. (committee member).
Subjects/Keywords: Propulsion-Airframe Integration; Interference Drag; Computational Fluid Dynamics; Transonic Aerodynamics; Wing Design; Aircraft Design
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APA (6th Edition):
Blaesser, N. J. (2020). Interference Drag Due to Engine Nacelle Location for a Single-Aisle, Transonic Aircraft. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/96446
Chicago Manual of Style (16th Edition):
Blaesser, Nathaniel James. “Interference Drag Due to Engine Nacelle Location for a Single-Aisle, Transonic Aircraft.” 2020. Doctoral Dissertation, Virginia Tech. Accessed January 25, 2021.
http://hdl.handle.net/10919/96446.
MLA Handbook (7th Edition):
Blaesser, Nathaniel James. “Interference Drag Due to Engine Nacelle Location for a Single-Aisle, Transonic Aircraft.” 2020. Web. 25 Jan 2021.
Vancouver:
Blaesser NJ. Interference Drag Due to Engine Nacelle Location for a Single-Aisle, Transonic Aircraft. [Internet] [Doctoral dissertation]. Virginia Tech; 2020. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/10919/96446.
Council of Science Editors:
Blaesser NJ. Interference Drag Due to Engine Nacelle Location for a Single-Aisle, Transonic Aircraft. [Doctoral Dissertation]. Virginia Tech; 2020. Available from: http://hdl.handle.net/10919/96446
Virginia Tech
22.
Locatelli, Davide.
Optimization of Supersonic Aircraft Wing-Box using Curvilinear SpaRibs.
Degree: PhD, Engineering Science and Mechanics, 2012, Virginia Tech
URL: http://hdl.handle.net/10919/26345
► This dissertation investigates the advantages of using curvilinear spars and ribs, termed SpaRibs, to design supersonic aircraft wing-box in comparison to the use of classic…
(more)
▼ This dissertation investigates the advantages of using curvilinear spars and ribs, termed SpaRibs, to
design supersonic aircraft
wing-box in comparison to the use of classic
design concepts that employ straight spars and ribs. The intent is to achieve a more efficient load-bearing mechanism and to passively control aeorelastic behavior of the structure under the flight loads. The use of SpaRibs broadens the
design space and allows for the natural frequencies and natural mode shape tailoring.
The SpaRibs concept is implemented in a new MATLAB-based optimization framework referred to as EBF3SSWingOpt. This framework interfaces different analysis software to perform the tasks required. VisualDOC is used as optimizer; the generation of the SpaRibs geometry and of the structure Finite Element Model (FEM) is performed by MD.PATRAN; MD.NASTRAN is utilized to compute the weight of the structure, the linear static stress analysis and the linear buckling analysis required for the calculation of the response functions. EBF3SSWingOpt optimization scheme performs both the sizing and the shaping of the internal structural elements. Two methods are compared while optimizing the
wing-box; a One-Step method in which sizing and topology optimization are carried out simultaneously and a Two-Step method, in which the sizing and topology optimization are carried out separately but in an iterative way. The optimization problem statements for the One-Step and the Two-Step methodologies are presented.
Three methods to define the shape of the SpaRibs parametrically are described: (1) the Bounding Box and Base Curves method defines the shape of the SpaRibs based on the shape of two curves called Base Curves which are positioned into the Bounding Box, a rectangular region defined on the plane z=0 and containing the projection of the
wing plan-form onto the same plane; (2) the Linked Shape method defines the shape of a set of SpaRibs in a one by one square domain of the natural space. The set of curves is subsequently transformed in the physical space for creating the
wing structure geometry layout. The shape of each curve of each set is unique however, mathematical relations link their curvature in an effort to reduce the number of
design variables; and (3) the Independent Shape parameterization is similar to the Linked Shape parameterization however, the shape of each curve is unique.
The framework and parameterization methods described are applied to optimize different types of
wing structures. Following results are presented and discussed: (1) a rectangular
wing-box subjected to a chord-wise linearly varying load, optimized using SpaRibs parameterized with Bounding-Box and Base Curves method; (2) a rectangular
wing-box subjected to a chord-wise linearly varying load, optimized using SpaRibs parameterized with Linked Shape method; (3) a generic fighter
wing subjected to uniform distributed pressure load, optimized using SpaRibs parameterized with Bounding-Box and Base Curves method; (4) a general business jet
wing subjected to pull-up…
Advisors/Committee Members: Kapania, Rakesh K. (committeechair), Singh, Mahendra P. (committee member), Patil, Mayuresh J. (committee member), Thangjitham, Surot (committee member), Schetz, Joseph A. (committee member).
Subjects/Keywords: Structural Optimization; Wing Optimization; SpaRibs; Aircraft Design; Particle Swarm Optimization; Supersonic Aircraft Design
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APA (6th Edition):
Locatelli, D. (2012). Optimization of Supersonic Aircraft Wing-Box using Curvilinear SpaRibs. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/26345
Chicago Manual of Style (16th Edition):
Locatelli, Davide. “Optimization of Supersonic Aircraft Wing-Box using Curvilinear SpaRibs.” 2012. Doctoral Dissertation, Virginia Tech. Accessed January 25, 2021.
http://hdl.handle.net/10919/26345.
MLA Handbook (7th Edition):
Locatelli, Davide. “Optimization of Supersonic Aircraft Wing-Box using Curvilinear SpaRibs.” 2012. Web. 25 Jan 2021.
Vancouver:
Locatelli D. Optimization of Supersonic Aircraft Wing-Box using Curvilinear SpaRibs. [Internet] [Doctoral dissertation]. Virginia Tech; 2012. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/10919/26345.
Council of Science Editors:
Locatelli D. Optimization of Supersonic Aircraft Wing-Box using Curvilinear SpaRibs. [Doctoral Dissertation]. Virginia Tech; 2012. Available from: http://hdl.handle.net/10919/26345
Virginia Tech
23.
Naghshineh-Pour, Amir H.
Structural Optimization and Design of a Strut-Braced Wing Aircraft.
Degree: MS, Aerospace and Ocean Engineering, 1998, Virginia Tech
URL: http://hdl.handle.net/10919/36142
► A significant improvement can be achieved in the performance of transonic transport aircraft using Multidisciplinary Design Optimization (MDO) by implementing truss-braced wing concepts in combination…
(more)
▼ A significant improvement can be achieved in the performance of transonic transport aircraft using Multidisciplinary
Design Optimization (MDO) by implementing truss-braced
wing concepts in combination with other advanced technologies and novel
design innovations. A considerable reduction in drag can be obtained by using a high aspect ratio
wing with thin airfoil sections and tip-mounted engines. However, such
wing structures could suffer from a significant weight penalty. Thus, the use of an external strut or a truss bracing is promising for weight reduction.
Due to the unconventional nature of the proposed concept, commonly available
wing weight equations for transport aircraft will not be sufficiently accurate. Hence, a bending material weight calculation procedure was developed to take into account the influence of the strut upon the
wing weight, and this was coupled to the Flight Optimization System (FLOPS) for total
wing weight estimation. The
wing bending material weight for single-strut configurations is estimated by modeling the
wing structure as an idealized double-plate model using a piecewise linear load method.
Two maneuver load conditions 2.5g and -1.0g factor of safety of 1.5 and a 2.0g taxi bump are considered as the critical load conditions to determine the
wing bending material weight. From preliminary analyses, the buckling of the strut under the -1.0g load condition proved to be the critical structural challenge. To address this issue, an innovative
design strategy introduces a telescoping sleeve mechanism to allow the strut to be inactive during negative g maneuvers and active during positive g maneuvers. Also, more
wing weight reduction is obtained by optimizing the strut force, a strut offset length, and the
wing-strut junction location. The best configuration shows a 9.2% savings in takeoff gross weight, an 18.2% savings in
wing weight and a 15.4% savings in fuel weight compared to a cantilever
wing counterpart.
Advisors/Committee Members: Kapania, Rakesh K. (committeechair), Schetz, Joseph A. (committee member), Mason, William H. (committee member), Johnson, Eric R. (committee member).
Subjects/Keywords: Strut-Braced Wing; Wing Box; Structural Optimization; Multidisciplinary Design Optimization; Aircraft Design
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APA (6th Edition):
Naghshineh-Pour, A. H. (1998). Structural Optimization and Design of a Strut-Braced Wing Aircraft. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/36142
Chicago Manual of Style (16th Edition):
Naghshineh-Pour, Amir H. “Structural Optimization and Design of a Strut-Braced Wing Aircraft.” 1998. Masters Thesis, Virginia Tech. Accessed January 25, 2021.
http://hdl.handle.net/10919/36142.
MLA Handbook (7th Edition):
Naghshineh-Pour, Amir H. “Structural Optimization and Design of a Strut-Braced Wing Aircraft.” 1998. Web. 25 Jan 2021.
Vancouver:
Naghshineh-Pour AH. Structural Optimization and Design of a Strut-Braced Wing Aircraft. [Internet] [Masters thesis]. Virginia Tech; 1998. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/10919/36142.
Council of Science Editors:
Naghshineh-Pour AH. Structural Optimization and Design of a Strut-Braced Wing Aircraft. [Masters Thesis]. Virginia Tech; 1998. Available from: http://hdl.handle.net/10919/36142
Virginia Tech
24.
McDonald, Melea E.
The Effect of Reducing Cruise Altitude on the Topology and Emissions of a Commercial Transport Aircraft.
Degree: MS, Aerospace and Ocean Engineering, 2010, Virginia Tech
URL: http://hdl.handle.net/10919/34124
► In recent years, research has been conducted for alternative commercial transonic aircraft design configurations, such as the strut- braced wing and the truss-braced wing aircraft…
(more)
▼ In recent years, research has been conducted for alternative commercial transonic aircraft
design configurations, such as the strut- braced
wing and the truss-braced
wing aircraft designs,
in order to improve aircraft performance and reduce the impact of aircraft emissions as compared to a typical cantilever
wing design. Research performed by Virginia Tech in conjunction with NASA Langley Research Center shows that these alternative configurations result in 20% or more reduction in fuel consumption, and thus emissions. Another option to reduce the impact of emissions on the environment is to reduce the aircraft cruise altitude, where less nitrous oxides are released into the atmosphere and contrail formation is less likely. The following study was performed using multidisciplinary
design optimization (MDO) in ModelCenterTM for cantilever
wing, strut-braced
wing, and truss-braced
wing designs and optimized for minimum takeoff gross weight at 7730 NM range and minimum fuel weight for 7730 and 4000 NM range at the following cruise altitudes: 25,000; 30,000; and 35,000 ft. For the longer range, both objective functions exhibit a large penalty in fuel weight and takeoff gross weight due to the increased drag from the fixed fuselage when reducing cruise altitude. For the shorter range, there was a slight increase in takeoff gross weight even though there was a large increase in fuel weight for decreased cruise altitudes. Thus, the benefits of reducing cruise altitude were offset by increased fuel weight. Either a two-jury truss-braced
wing or telescopic strut could be studied to reduce the fuel penalty.
Advisors/Committee Members: Schetz, Joseph A. (committeechair), Kapania, Rakesh K. (committee member), Gur, Ohad (committee member).
Subjects/Keywords: Multidisciplinary Design Optimization; Aircraft Design; Strut-Braced Wing; Truss-Braced Wing; Transonic Transport
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APA (6th Edition):
McDonald, M. E. (2010). The Effect of Reducing Cruise Altitude on the Topology and Emissions of a Commercial Transport Aircraft. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/34124
Chicago Manual of Style (16th Edition):
McDonald, Melea E. “The Effect of Reducing Cruise Altitude on the Topology and Emissions of a Commercial Transport Aircraft.” 2010. Masters Thesis, Virginia Tech. Accessed January 25, 2021.
http://hdl.handle.net/10919/34124.
MLA Handbook (7th Edition):
McDonald, Melea E. “The Effect of Reducing Cruise Altitude on the Topology and Emissions of a Commercial Transport Aircraft.” 2010. Web. 25 Jan 2021.
Vancouver:
McDonald ME. The Effect of Reducing Cruise Altitude on the Topology and Emissions of a Commercial Transport Aircraft. [Internet] [Masters thesis]. Virginia Tech; 2010. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/10919/34124.
Council of Science Editors:
McDonald ME. The Effect of Reducing Cruise Altitude on the Topology and Emissions of a Commercial Transport Aircraft. [Masters Thesis]. Virginia Tech; 2010. Available from: http://hdl.handle.net/10919/34124
Ryerson University
25.
Kalaji, Ahmad T.
Design And Experimental Studies Of Flexible Trailing Edge For Variable Camber Morphing Wing.
Degree: 2017, Ryerson University
URL: https://digital.library.ryerson.ca/islandora/object/RULA%3A6844
► This thesis presents a flexible trailing edge mechanism capable of undergoing a change in camber for a wing section. The mechanism takes advantage of a…
(more)
▼ This thesis presents a flexible trailing edge mechanism capable of undergoing a change in camber for a
wing section. The mechanism takes advantage of a rigid constraint between the ends of two flexible carbon fiber panels, which produces a deflection when there is a difference in length between the two panels.
A prototype was designed and built and experimental data was collected for the deformation of the panels for different values of lengths and analyzed to find a function to describe the coefficients which form the polynomials describing the shape for each of the panels, based on the difference in length value. Deflection and deflection angle results were used to develop a controller which will calculate the required change in length based on a deflection or angle and a bottom panel length input.
Advisors/Committee Members: Xi, Jeff (Thesis advisor).
Subjects/Keywords: Wing-warping (Aerodynamics); Airplanes – Wings – Design and construction; Drag (Aerodynamics); Aeronautics – Research
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APA (6th Edition):
Kalaji, A. T. (2017). Design And Experimental Studies Of Flexible Trailing Edge For Variable Camber Morphing Wing. (Thesis). Ryerson University. Retrieved from https://digital.library.ryerson.ca/islandora/object/RULA%3A6844
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Kalaji, Ahmad T. “Design And Experimental Studies Of Flexible Trailing Edge For Variable Camber Morphing Wing.” 2017. Thesis, Ryerson University. Accessed January 25, 2021.
https://digital.library.ryerson.ca/islandora/object/RULA%3A6844.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Kalaji, Ahmad T. “Design And Experimental Studies Of Flexible Trailing Edge For Variable Camber Morphing Wing.” 2017. Web. 25 Jan 2021.
Vancouver:
Kalaji AT. Design And Experimental Studies Of Flexible Trailing Edge For Variable Camber Morphing Wing. [Internet] [Thesis]. Ryerson University; 2017. [cited 2021 Jan 25].
Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A6844.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Kalaji AT. Design And Experimental Studies Of Flexible Trailing Edge For Variable Camber Morphing Wing. [Thesis]. Ryerson University; 2017. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A6844
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Toronto
26.
Galantai, Vlad Paul.
Design and Analysis of Morphing Wing for Unmanned Aerial Vehicles.
Degree: 2012, University of Toronto
URL: http://hdl.handle.net/1807/33722
► This study is concerned with the design and development of a novel wing for UAVs that morphs seamlessly without the use of complex hydraulics, servo…
(more)
▼ This study is concerned with the design and development of a novel wing for UAVs that morphs seamlessly without the use of complex hydraulics, servo motors and controllers. The selected novel design is characterized by a high degree of flight adaptability and improved performance with a limited added weight. These characteristics were attained through the use of shape memory actuators in an antagonistic fashion. Unlike compliant actuators, the antagonistic setup requires the thermal energy to deform the wing but not to maintain its deformed shape. Structural analysis based upon safety factors specified by FAR23 standards and aerodynamic analysis using FLUENT were conducted on the novel design to validate its suitability as a viable wing for UAVs. In addition, thermal conditioning of the shape memory actuators was conducted using a specially designed programmable controller. This thesis does not concern itself with the design of a skin that accommodates the shape changes.
MAST
Advisors/Committee Members: Meguid, Shaker A., Mechanical and Industrial Engineering.
Subjects/Keywords: Morphing Wing; UAV; Shape Adaptation; Smart Materials; Shape Memory Alloy; Conceptual Design; RPV; Biomimetics; 0538
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APA (6th Edition):
Galantai, V. P. (2012). Design and Analysis of Morphing Wing for Unmanned Aerial Vehicles. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/33722
Chicago Manual of Style (16th Edition):
Galantai, Vlad Paul. “Design and Analysis of Morphing Wing for Unmanned Aerial Vehicles.” 2012. Masters Thesis, University of Toronto. Accessed January 25, 2021.
http://hdl.handle.net/1807/33722.
MLA Handbook (7th Edition):
Galantai, Vlad Paul. “Design and Analysis of Morphing Wing for Unmanned Aerial Vehicles.” 2012. Web. 25 Jan 2021.
Vancouver:
Galantai VP. Design and Analysis of Morphing Wing for Unmanned Aerial Vehicles. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/1807/33722.
Council of Science Editors:
Galantai VP. Design and Analysis of Morphing Wing for Unmanned Aerial Vehicles. [Masters Thesis]. University of Toronto; 2012. Available from: http://hdl.handle.net/1807/33722
Delft University of Technology
27.
Lambers, A.C. (author).
Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design.
Degree: 2016, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:a8f151f0-1c47-4a8a-9cef-b9784a1662cd
► Aircraft concepts with high aspect ratio wings have been investigated more extensively in the recent past, as such configurations would reduce the induced drag significantly.…
(more)
▼ Aircraft concepts with high aspect ratio wings have been investigated more extensively in the recent past, as such configurations would reduce the induced drag significantly. At the same time, the high aspect ratio challenges the wing’s aero-structural stability (flutter). Therefore there is a need to perform aero-structural analysis already within the conceptual design phase, preferably in an automated fashion to enable the execution of multidisciplinary design optimization (MDO). This study has investigated methods to directly incorporate flutter speed predictions as constraints in an automated optimization process for conceptual design of aircraft. The computationally expensive flutter calculations have been modelled using different surrogate models (SM) to reduce calculation time in the automated design process. The combination of different surrogate and design of experiments (DOE) methods have been investigated and compared. Each combination of SM and DOE provides an indication of the trade-off between computation time and precision. The MultiFit software tool, developed by the Netherlands Aerospace Centre, was used to set up the different SMs. Artificial neural networks have shown the best capabilities in representing the behaviour of the flutter speed. Furthermore, surrogate-based optimization (SBO) methods have been able to find the same optimum design point at lower computational cost compared to the classical (non-surrogate) multidisciplinary feasible (MDF) MDO architecture. In an attempt to reduce optimization time even further, an adaptive surrogate modelling approach has been incorporated in the surrogate-based optimization method. The proposed method starts with a small DOE to create an initial SM. Then, an SBO is performed on this model. The value of the resulting optimum is recalculated using the complete multidisciplinary analysis and this new design point is then added to the DOE. A new surrogate model is created and an SBO is performed using the earlier found optimum as a starting point. This process is repeated until the process converges. The case study in this research has shown that adaptive surrogate-based optimization can be an efficient method to find the optimum of the objective function at a low computational cost, although more advanced enrichment and convergence criteria are recommended to improve the algorithm.
Aerospace Engineering
Aerodynamics, Wind Energy & Propulsion
Advisors/Committee Members: van Gent, I. (mentor).
Subjects/Keywords: Mutlidisciplinary Design Optimization; MDO; surrogate modelling; SBO; surrogate-based optimization; strut-braced wing; flutter
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APA (6th Edition):
Lambers, A. C. (. (2016). Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:a8f151f0-1c47-4a8a-9cef-b9784a1662cd
Chicago Manual of Style (16th Edition):
Lambers, A C (author). “Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design.” 2016. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:a8f151f0-1c47-4a8a-9cef-b9784a1662cd.
MLA Handbook (7th Edition):
Lambers, A C (author). “Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design.” 2016. Web. 25 Jan 2021.
Vancouver:
Lambers AC(. Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:a8f151f0-1c47-4a8a-9cef-b9784a1662cd.
Council of Science Editors:
Lambers AC(. Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:a8f151f0-1c47-4a8a-9cef-b9784a1662cd
Delft University of Technology
28.
Rubio Pascual, Berta (author).
Engine-Airframe Integration for the Flying-V.
Degree: 2018, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:75be27a7-6fd4-4112-a600-45df2999758f
► The Flying-V is a novel flying wing concept where the main lifting surface has been fully integrated with the passenger cabin. Previous studies have focused…
(more)
▼ The Flying-V is a novel flying
wing concept where the main lifting surface has been fully integrated with the passenger cabin. Previous studies have focused on the aerodynamic and structural
design of the airframe; but, prior to determining which engine-airframe integration alternative is most beneficial (e.g. boundary layer ingestion, distributed propulsion, and alike), an aerodynamic analysis of the engine installation effects needs to be performed. In this sense, engine integration studies require of complex models and a multidisciplinary approach to address the physics involved in the engine-airframe interaction phenomenon. In particular, the location of the engines around the airframe has a major impact on the overall aerodynamics of the aircraft. Hence, this study focuses on determining whether the aerodynamic efficiency benefits expected from this configuration are not offset by negative interferences with the nacelle, weight penalties, or regulation constraints. In order to do so, and initial benchmark for the lift to drag ratio is obtained from a baseline Flying-V configuration, and the influence of the x, y, and z coordinates, as well as engine orientation are analysed afterwards. To carry out the simulations, an Euler pressure-based solver on a three-dimensional-unstructured grid is used to model the flow at cruise condition: M = 0.85, h = 13000 m, α = 2.9 ◦ , and T = 50 kN, and the viscous drag contribution is computed following an empirical approach. A total of forty different engine locations are tested under these conditions to build a preliminary surrogate model that predicts the aircraft’s lift to drag ratio based on the position of the nacelle. The results obtained show that misplacing the engine can lead to significant lift to drag ratio losses going as high as 55% when compared against the ideal integration configuration. Finally, a region behind the airframe’s trailing edge is identified where the interference losses due to the installation are minimized. In light of the results obtained, a location is recommended for the engines where the perturbations observed on the lift to drag ratio are near the 10%, and a good compromise is obtained among the different requirements imposed.
Advisors/Committee Members: Vos, Roelof (mentor), Veldhuis, Leo (graduation committee), van Zuijlen, Alexander (graduation committee), Delft University of Technology (degree granting institution).
Subjects/Keywords: Flying V; Engine; Integration; flying wing; Interference; Aerodynamic; Aircraft design; positioning study
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APA (6th Edition):
Rubio Pascual, B. (. (2018). Engine-Airframe Integration for the Flying-V. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:75be27a7-6fd4-4112-a600-45df2999758f
Chicago Manual of Style (16th Edition):
Rubio Pascual, Berta (author). “Engine-Airframe Integration for the Flying-V.” 2018. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:75be27a7-6fd4-4112-a600-45df2999758f.
MLA Handbook (7th Edition):
Rubio Pascual, Berta (author). “Engine-Airframe Integration for the Flying-V.” 2018. Web. 25 Jan 2021.
Vancouver:
Rubio Pascual B(. Engine-Airframe Integration for the Flying-V. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:75be27a7-6fd4-4112-a600-45df2999758f.
Council of Science Editors:
Rubio Pascual B(. Engine-Airframe Integration for the Flying-V. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:75be27a7-6fd4-4112-a600-45df2999758f
Delft University of Technology
29.
Mangano, Marco (author).
Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes.
Degree: 2019, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:4a40e302-bdf1-4319-81de-a6aad9376d65
► The second-generation of supersonic civil transport has to match ambitious targets in terms of noise reduction and efficiency to become economically and environmentally viable. High-fidelity…
(more)
▼ The second-generation of supersonic civil transport has to match ambitious targets in terms of noise reduction and efficiency to become economically and environmentally viable. High-fidelity numerical optimization offers a powerful approach to address the complex trade-offs intrinsic to this novel configuration. Past and current research however, despite proving the potential of such
design strategy, lacks in deeper insight on final layouts and optimization workflow challenges. Stemming from the necessity to quantify and exploit the potential of modern
design tools applied to supersonic aircraft
design, this work partially fills the gap in previous research by investigating RANS-based aerodynamic optimization for both supersonic, transonic and subsonic conditions. The investigation is carried out with the state-of-the-art, gradient-based MDO framework it{MACH}, developed at University of Michigan's MDO Lab - which hosted the author for the 14-month research stint. Details of the tool and a brief overview of supersonic aircraft
design and modern aerodynamic optimization strategies are reported in the first part of this manuscript. After circumscribing the research niche, I perform single and multi-point optimization to minimize the drag over an ideal supersonic aircraft flight envelope and assess the influence of physical and numerical parameters on optimization accuracy and reliability. Leading and trailing edge morphing capabilities are introduced to improve the efficiency at transonic and subsonic flight speed by relaxing the trade-offs on clean shape optimization. Benefits in terms of drag reduction are quantified and benchmarked with fixed-edges results. It is observed how the optimized airfoils outperform baseline reference shapes from a minimum of 4% up to 86% for different
design cases and flight conditions. The study is then extended to the optimization of a planar, low-aspect-ratio, and low-sweep
wing, using the same schematic approach of 2D analysis. I investigate the influence of
wing twist alone and twist and shape on cruise performance, obtaining a drag reduction of 6% and 25% respectively as the optimizer copes with both viscosity and compressibility effects over the
wing. Results for 3D multi-point optimization suggest that the proposed strategy enables a fast and effective
design of highly-efficient wings, with drag reduction ranging from a minimum of 24% up to 74% for cruise at different speeds and altitudes, including edge deflection. Ultimately, this work provides an extensive and, to the best of author knowledge, unprecedented insight on the optimal
design solutions for this specific aircraft configuration and the challenges of the optimization framework. The benefits of RANS-based aerodynamic shape optimization to capture non-intuitive
design trade-offs and offer deeper physical insight are ultimately discussed and quantified. Given the promising results in terms of performance improvements and
design efficiency, it is hoped that this work will foster the implementation of…
Advisors/Committee Members: la Rocca, Gianfranco (mentor), Martins, Joaquim (mentor), Veldhuis, Leo (graduation committee), Dwight, Richard (graduation committee), Delft University of Technology (degree granting institution).
Subjects/Keywords: Optimization; Aerodynamics; MDO; CFD; Supersonic; wing design; Airfoil; morphing; Gradient-based Optimization
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APA (6th Edition):
Mangano, M. (. (2019). Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:4a40e302-bdf1-4319-81de-a6aad9376d65
Chicago Manual of Style (16th Edition):
Mangano, Marco (author). “Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes.” 2019. Masters Thesis, Delft University of Technology. Accessed January 25, 2021.
http://resolver.tudelft.nl/uuid:4a40e302-bdf1-4319-81de-a6aad9376d65.
MLA Handbook (7th Edition):
Mangano, Marco (author). “Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes.” 2019. Web. 25 Jan 2021.
Vancouver:
Mangano M(. Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2021 Jan 25].
Available from: http://resolver.tudelft.nl/uuid:4a40e302-bdf1-4319-81de-a6aad9376d65.
Council of Science Editors:
Mangano M(. Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:4a40e302-bdf1-4319-81de-a6aad9376d65
Virginia Tech
30.
Mallik, Wrik.
Aeroelastic Analysis of Truss-Braced Wing Aircraft: Applications for Multidisciplinary Design Optimization.
Degree: PhD, Aerospace Engineering, 2016, Virginia Tech
URL: http://hdl.handle.net/10919/71650
► This study highlights the aeroelastic behavior of very flexible truss-braced wing (TBW) aircraft designs obtained through a multidisciplinary design optimization (MDO) framework. Several improvements to…
(more)
▼ This study highlights the aeroelastic behavior of very flexible truss-braced
wing (TBW) aircraft designs obtained through a multidisciplinary
design optimization (MDO) framework. Several improvements to previous analysis methods were developed and validated.
Firstly, a flutter constraint was developed and the effects of the constraint on the MDO of TBW transport aircraft for both medium-range and long-range missions were studied while minimizing the take-off gross weight (TOGW) and the fuel burn as the objective functions. Results show that when the flutter constraint is applied at 1.15 times the dive speed, it imposes a 1.5% penalty on the take-off weight and a 5% penalty on the fuel consumption while minimizing these two objective functions for the medium-range mission. For the long-range mission, the penalties imposed by the similar constraint on the minimum TOGW and minimum fuel burn designs are 3.5% and 7.5%, respectively. Importantly, the resulting TBW designs are still superior to equivalent cantilever designs for both of the missions as they have both lower TOGW and fuel burn. However, a relaxed flutter constraint applied at 1.05 times the dive speed can restrict the penalty on the TOGW to only 0.3% and that on the fuel burn to 2% for minimizing both the objectives, for the medium-range mission. For the long-range mission, a similar relaxed constraint can reduce the penalty on fuel burn to 2.9%. These observations suggest further investigation into active flutter suppression mechanisms for the TBW aircraft to further reduce either the TOGW or the fuel burn.
Secondly, the effects of a variable-geometry raked wingtip (VGRWT) on the maneuverability and aeroelastic behavior of passenger aircraft with very flexible truss-braced wings (TBW) were investigated. These TBW designs obtained from the MDO environment while minimizing fuel burn resemble a Boeing 777-200 Long Range (LR) aircraft both in terms of flight mission and aircraft configuration. The VGRWT can sweep forward and aft relative to the
wing with the aid of a Novel Control Effector (NCE) mechanism. Results show that the VGRWT can be swept judiciously to alter the bending-torsion coupling and the movement of the center of pressure of
wing. Such behavior of the VGRWT is applied to both achieve the required roll control as well as to increase flutter speed, and thus, enable the operation of TBW configurations which have up to 10% lower fuel burn than comparable optimized cantilever
wing designs.
Finally, a transonic aeroelastic analysis tool was developed which can be used for conceptual
design in an MDO environment. Routine transonic aeroelastic analysis require expensive CFD simulations, hence they cannot be performed in an MDO environment. The present approach utilizes the results of a companion study of CFD simulations performed offline for the steady Reynolds Averaged Navier Stokes equations for a variety of airfoil parameters. The CFD results are used to develop a response surface which can be used in the MDO environment to perform a…
Advisors/Committee Members: Kapania, Rakesh K. (committeechair), Schetz, Joseph A. (committee member), Patil, Mayuresh J. (committee member), Roy, Christopher John (committee member).
Subjects/Keywords: Aeroelasticity; Multidisciplinary Design Optimization; Truss-Braced Wing Aircraft; Variable Geometry Raked Wingtip; State-space Aerodynamics
Record Details
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Share »
Record Details
Similar Records
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❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Mallik, W. (2016). Aeroelastic Analysis of Truss-Braced Wing Aircraft: Applications for Multidisciplinary Design Optimization. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/71650
Chicago Manual of Style (16th Edition):
Mallik, Wrik. “Aeroelastic Analysis of Truss-Braced Wing Aircraft: Applications for Multidisciplinary Design Optimization.” 2016. Doctoral Dissertation, Virginia Tech. Accessed January 25, 2021.
http://hdl.handle.net/10919/71650.
MLA Handbook (7th Edition):
Mallik, Wrik. “Aeroelastic Analysis of Truss-Braced Wing Aircraft: Applications for Multidisciplinary Design Optimization.” 2016. Web. 25 Jan 2021.
Vancouver:
Mallik W. Aeroelastic Analysis of Truss-Braced Wing Aircraft: Applications for Multidisciplinary Design Optimization. [Internet] [Doctoral dissertation]. Virginia Tech; 2016. [cited 2021 Jan 25].
Available from: http://hdl.handle.net/10919/71650.
Council of Science Editors:
Mallik W. Aeroelastic Analysis of Truss-Braced Wing Aircraft: Applications for Multidisciplinary Design Optimization. [Doctoral Dissertation]. Virginia Tech; 2016. Available from: http://hdl.handle.net/10919/71650
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Open Access Theses and Dissertations