Download or read book Optimization Techniques in Aircraft Configuration Design written by Brent Silver and published by . This book was released on 1970 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: The application of optimization techniques to aircraft configuration design is discussed. Advantages and disadvantages of automated search methods are compared with those of parametric analysis methods. The formulation of the design problem for direct search methods using a normalization procedure is developed. Various direct methods are briefly described. Operational results using several of these methods are reported for aircraft configuration design problems. Gradient methods are found to give disappointing results when compared with certain non-gradient methods. Reasons are suggested for this behavior. The future promise of 'man-computer interactive design' is briefly described. (Author).
Download or read book Optimization Methods Applied to the preliminary design of innovative non conventional aircraft configurations written by Emanuele Rizzo and published by Emanuele Rizzo. This book was released on 2009 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Technique for Integrating Engine Cycle and Aircraft Configuration Optimization written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11-02 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method for conceptual aircraft design that incorporates the optimization of major engine design variables for a variety of cycle types was developed. The methodology should improve the lengthy screening process currently involved in selecting an appropriate engine cycle for a given application or mission. The new capability will allow environmental concerns such as airport noise and emissions to be addressed early in the design process. The ability to rapidly perform optimization and parametric variations using both engine cycle and aircraft design variables, and to see the impact on the aircraft, should provide insight and guidance for more detailed studies. A brief description of the aircraft performance and mission analysis program and the engine cycle analysis program that were used is given. A new method of predicting propulsion system weight and dimensions using thermodynamic cycle data, preliminary design, and semi-empirical techniques is introduced. Propulsion system performance and weights data generated by the program are compared with industry data and data generated using well established codes. The ability of the optimization techniques to locate an optimum is demonstrated and some of the problems that had to be solved to accomplish this are illustrated. Results from the application of the program to the analysis of three supersonic transport concepts installed with mixed flow turbofans are presented. The results from the application to a Mach 2.4, 5000 n.mi. transport indicate that the optimum bypass ratio is near 0.45 with less than 1 percent variation in minimum gross weight for bypass ratios ranging from 0.3 to 0.6. In the final application of the program, a low sonic boom fix a takeoff gross weight concept that would fly at Mach 2.0 overwater and at Mach 1.6 overland is compared with a baseline concept of the same takeoff gross weight that would fly Mach 2.4 overwater and subsonically overland. The results indicate that for the design mission, th...
Download or read book Advanced Aircraft Design written by Egbert Torenbeek and published by John Wiley & Sons. This book was released on 2013-05-28 with total page 412 pages. Available in PDF, EPUB and Kindle. Book excerpt: Although the overall appearance of modern airliners has not changed a lot since the introduction of jetliners in the 1950s, their safety, efficiency and environmental friendliness have improved considerably. Main contributors to this have been gas turbine engine technology, advanced materials, computational aerodynamics, advanced structural analysis and on-board systems. Since aircraft design became a highly multidisciplinary activity, the development of multidisciplinary optimization (MDO) has become a popular new discipline. Despite this, the application of MDO during the conceptual design phase is not yet widespread. Advanced Aircraft Design: Conceptual Design, Analysis and Optimization of Subsonic Civil Airplanes presents a quasi-analytical optimization approach based on a concise set of sizing equations. Objectives are aerodynamic efficiency, mission fuel, empty weight and maximum takeoff weight. Independent design variables studied include design cruise altitude, wing area and span and thrust or power loading. Principal features of integrated concepts such as the blended wing and body and highly non-planar wings are also covered. The quasi-analytical approach enables designers to compare the results of high-fidelity MDO optimization with lower-fidelity methods which need far less computational effort. Another advantage to this approach is that it can provide answers to “what if” questions rapidly and with little computational cost. Key features: Presents a new fundamental vision on conceptual airplane design optimization Provides an overview of advanced technologies for propulsion and reducing aerodynamic drag Offers insight into the derivation of design sensitivity information Emphasizes design based on first principles Considers pros and cons of innovative configurations Reconsiders optimum cruise performance at transonic Mach numbers Advanced Aircraft Design: Conceptual Design, Analysis and Optimization of Subsonic Civil Airplanes advances understanding of the initial optimization of civil airplanes and is a must-have reference for aerospace engineering students, applied researchers, aircraft design engineers and analysts.
Download or read book Aircraft Design written by Daniel P. Raymer and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 2006 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Winner of the Summerfield Book Award Winner of the Aviation-Space Writers Association Award of Excellence. --Over 30,000 copies sold, consistently the top-selling AIAA textbook title This highly regarded textbook presents the entire process of aircraft conceptual designfrom requirements definition to initial sizing, configuration layout, analysis, sizing, and trade studiesin the same manner seen in industry aircraft design groups. Interesting and easy to read, the book has more than 800 pages of design methods, illustrations, tips, explanations, and equations, and extensive appendices with key data essential to design. It is the required design text at numerous universities around the world, and is a favorite of practicing design engineers.
Download or read book Numerical Aircraft Design Using 3 D Transonic Analysis with Optimization written by Andrew J. Srokowski and published by . This book was released on 1981 with total page 382 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose was to develop and validate a new transonic wing design procedure using the numerical optimization technique. The new procedure was used to design both a transport and a fighter configuration. Because the missions and design requirements of a fighter and transport are so different, the design procedure was developed along parallel lines. Lockheed-Georgia Co. developed the transport design procedure, and Grumman Aerospace Corp. developed the fighter design procedure. This is Part 1 of a two-part volume: Part 1 details the transport development, and Part 2 describes the fighter development. The results of a transport design case study performed to evaluate the transonic aircraft design procedure developed as part of the Advanced Transonic Technology (ATT) program are presented. A derivative of the C141B aircraft was selected as the design configuration. The design procedure was applied to the baseline configuration and the performance of resulting configuration was then compared to the C141 aircraft. Extensive wind tunnel testing of the design configuration was performed to validate the design procedure. The results of the wind tunnel tests are correlated with computational results generated in the design process. In addition, the evolution of the design procedure and its application in the transport design case study is discussed.
Download or read book Numerical Aircraft Design Using 3 D Transonic Analysis with Optimization written by Andrew J. Srokowski and published by . This book was released on 1981 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: This executive summary volume is divided into two parts: Part 1 highlights the transport development, and Part 2 highlights the fighter development. There are two other volumes which make up the final report. Volume 2 is the main volume in the final report. It presents in detail the information that has been highlighted here. Volume 2 is also divided into two parts with part 1 dealing with transport design and part 2 concerned with the fighter design. Volume 3 is a detailed user's guide to the computer programs produced under this contract. Volume 3 is similarly divided into two parts. A detailed summary of the work performed in the Advanced Transonic Technology (ATT) program to incorporate 3-D Transonic computational aerodynamics methods into aircraft design procedures is presented. Existing transonic analysis programs were modified for the design procedure and linked with a numerical optimization program to design wings that are in some sense optimized for a given set of design conditions. The design procedure was validated by applying it in two design case studies. The application of the design procedure in each of these case studies is described in detail. The configurations resulting from these studies were subjected to design verification wind tunnel testing. Comparisons of test data with computed results are presented.
Download or read book Aircraft Aerodynamic Design written by András Sóbester and published by John Wiley & Sons. This book was released on 2014-11-17 with total page 276 pages. Available in PDF, EPUB and Kindle. Book excerpt: Optimal aircraft design is impossible without a parametric representation of the geometry of the airframe. We need a mathematical model equipped with a set of controls, or design variables, which generates different candidate airframe shapes in response to changes in the values of these variables. This model's objectives are to be flexible and concise, and capable of yielding a wide range of shapes with a minimum number of design variables. Moreover, the process of converting these variables into aircraft geometries must be robust. Alas, flexibility, conciseness and robustness can seldom be achieved simultaneously. Aircraft Aerodynamic Design: Geometry and Optimization addresses this problem by navigating the subtle trade-offs between the competing objectives of geometry parameterization. It beginswith the fundamentals of geometry-centred aircraft design, followed by a review of the building blocks of computational geometries, the curve and surface formulations at the heart of aircraft geometry. The authors then cover a range of legacy formulations in the build-up towards a discussion of the most flexible shape models used in aerodynamic design (with a focus on lift generating surfaces). The book takes a practical approach and includes MATLAB®, Python and Rhinoceros® code, as well as ‘real-life’ example case studies. Key features: Covers effective geometry parameterization within the context of design optimization Demonstrates how geometry parameterization is an important element of modern aircraft design Includes code and case studies which enable the reader to apply each theoretical concept either as an aid to understanding or as a building block of their own geometry model Accompanied by a website hosting codes Aircraft Aerodynamic Design: Geometry and Optimization is a practical guide for researchers and practitioners in the aerospace industry, and a reference for graduate and undergraduate students in aircraft design and multidisciplinary design optimization.
Download or read book Multidisciplinary Design Optimization written by Natalia M. Alexandrov and published by SIAM. This book was released on 1997-01-01 with total page 476 pages. Available in PDF, EPUB and Kindle. Book excerpt: Multidisciplinary design optimization (MDO) has recently emerged as a field of research and practice that brings together many previously disjointed disciplines and tools of engineering and mathematics. MDO can be described as a technology, environment, or methodology for the design of complex, coupled engineering systems, such as aircraft, automobiles, and other mechanisms, the behavior of which is determined by interacting subsystems.
Download or read book Accelerating Structural Optimization in the Early Aircraft Design Phases written by Jason Qian and published by . This book was released on 2022 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the search for higher efficiencies, a number of unconventional aircraft planforms have been proposed to replace the conventional tube and wing airliner. With entirely new designs, these new configurations would have to be designed from a clean sheet and makes for a risky proposition. To ensure that such an endeavor would succeed, high-fidelity geometry and analysis would need to be introduced earlier in the aircraft design process to ensure that the configuration is feasible before any component is manufactured. This thesis pursues this idea and presents several methods in which high-fidelity aircraft structures can be generated, analyzed and optimized in a faster manner. Within the design process, bottlenecks can occur in the geometry/mesh generation and the computationally expensive analysis modules. To speed up the generation process, a parametric framework was written which takes a set of inputs and automatically and quickly generates a finite element analysis (FEA) model of a wing structure. Fidelity is maintained by being able to model all primary structural components in both conventional and unconventional aircraft configurations. This ability to rapidly create meshes is then leveraged to generate models of different resolutions, which can be tailored for the various FEA analysis types in terms of computational speed and accuracy. One of the most computationally expensive FEA analysis is finding the buckling eigenvalues. To reduce the cost of local buckling analysis, an iterative method calculates the eigenvalue of an aircraft panel and its surrounding section. This method was found to match the eigenvalues of the same global model to high degree of accuracy at a lower computational cost. To find the global eigenvalues without repeating the local eigenvalues, a displacement constraint method was applied to limit the possible mode shapes. This application guarantees only global mode shapes from the eigenvalue solver, making the extraction of global buckling eigenvalues easier. These methods are applied the optimization of a conventional wingbox and the unconventional structures of a blended wing body and truss-braced wing, where the complete model is generated from scratch and optimized under its aeroelastic loading with stress and buckling constraints. Their demonstration shows that ability design and optimize with high-fidelity geometry and methods can be applied at the start of the aircraft design process and can be applied for unconventional aircraft planforms.
Download or read book Synthesis of Subsonic Airplane Design written by E. Torenbeek and published by Springer Science & Business Media. This book was released on 2013-06-29 with total page 607 pages. Available in PDF, EPUB and Kindle. Book excerpt: Since the education of aeronautical engineers at Delft University of Technology started in 1940 under tae inspiring leadership of Professor H.J. van der Maas, much emphasis has been placed on the design of aircraft as part of the student's curriculum. Not only is aircraft design an optional subject for thesis work, but every aeronautical student has to carry out a preliminary airplane design in the course of his study. The main purpose of this preliminary design work is to enable the student to synthesize the knowledge ob tained separately in courses on aerodynamics, aircraft performances, stability and con trol, aircraft structures, etc. The student's exercises in preliminary design have been directed through the years by a number of staff members of the Department of Aerospace Engineering in Delft. The author of this book, Mr. E. Torenbeek, has made a large contribution to this part of the study programme for many years. Not only has he acquired vast experience in teaching airplane design at university level, but he has also been deeply involved in design-oriented re search, e.g. developing rational design methods and systematizing design information. I am very pleased that this wealth of experience, methods and data is now presented in this book.
Download or read book Aerodynamic Shape Optimization of Complex Aircraft Configurations Via an Adjoint Formulation written by James Reuther and published by . This book was released on 1996 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: "This work describes the implementation of optimization techniques based on control theory for complex aircraft configurations. Here control theory is employed to derive the adjoint differential equations, the solution of which allows for a drastic reduction in computational costs over previous design methods [13, 12, 43, 38]. In our earlier studies [19, 20, 22, 23, 39, 25, 40, 41, 42] it was shown that this method could be used to devise effective optimization procedures for airfoils, wings and wing-bodies subject to either analytic or arbitrary meshes. Design formulations for both potential flows and flows governed by the Euler equations have been demonstrated, showing that such methods can be devised for various governing equations [39, 25]. In our most recent works [40, 42] the method was extended to treat wing-body configurations with a large number of mesh points, verifying that significant computational savings can be gained for practical design problems. In this paper the method is extended for the Euler equations to treat complete aircraft configurations via a new multiblock implementation. New elements include a multiblock-multigrid flow solver, a multiblock-multigrid adjoint solver, and a multiblock mesh perturbation scheme. Two design examples are presented in which the new method is used for the wing redesign of a transonic business jet."
Download or read book Multidisciplinary Optimization of Aircraft Design and Takeoff Operations for Low Noise written by Anya Rachel Jones and published by . This book was released on 2006 with total page 137 pages. Available in PDF, EPUB and Kindle. Book excerpt: (Cont.) A distributed optimization framework was constructed from a problem decomposition into three subspaces: aircraft planform and engine design, aircraft operations, and wing design. In this framework, a system level optimizer is responsible for minimizing the system noise while subspace optimizers control the disciplinary models individually. This setup allowed for the exploration of different areas of the design space. As a result, the distributed optimization converged to a fundamentally different design solution with the same minimum noise value as in the single-level optimization, but with a much lower fuel burn. The key contributions of this thesis are the development and quantitative analysis of a weight and center of gravity model for an unconventional aircraft configuration, a distributed optimization framework, and a low noise aircraft design with competitive fuel burn.
Download or read book Multicriteria Design written by R.B. Statnikov and published by Springer Science & Business Media. This book was released on 2013-03-09 with total page 219 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book is devoted to the PSI method. Its appearance was a reaction to the unsatisfactory situation in applications of optimization methods in engineering. After comprehensive testing of the PSI method in various fields of machine engineering it has become obvious that this method substantially surpasses all other available techniques in many respects. It has now become known that the PSI method is successfully used not only in machine design, at which it was initially aimed, but also in polymer chemistry, pharmacy, nuclear energy, biology, geophysics, and many other fields of human activity. To all appearances this method has become so popular for its potential of taking into account the specific features of applied optimization better than other methods, being, at the same time, comparatively simple and friendly, and because, unlike traditional optimization methods which are intended only for searching for optimal solutions, the PSI method is also aimed at correctly formulating engineering optimization problems. One well-known aircraft designer once said, "To solve an optimization problem in engineering means, first of all, to be able to state this problem properly". In this sense the PSI method has no competitors. Although this method has been presented in Russia in numerous papers and books, Western readers have had the opportunity to familiarize themselves with this method only recently (Ozernoy 1988; Lieberman 1991; Stadler and Dauer 1992; Dyer, Fishburn, Steuer, Wallenius, and Zionts 1992; Steuer and Sun 1995, etc. ).
Download or read book Aerodynamic Shape Optimization of Supersonic Aircraft Configurations Via an Adjoint Formulation on Parallel Computers written by Research Institute for Advanced Computer Science (U.S.) and published by . This book was released on 1996 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: "This work describes the application of a control theory-based aerodynamic shape optimization method to the problem of supersonic aircraft design. The design process is greatly accelerated through the use of both control theory and a parallel implementation on distributed memory computers. Control theory is employed to derive the adjoint differential equations whose solution allows for the evaluation of design gradient information at a fraction of the computational cost required by previous design methods [13, 12, 44, 38]. The resulting problem is then implemented on parallel distributed memory architectures using a domain decomposition approach, an optimized communication schedule, and the MPI (Message Passing Interface) Standard for portability and efficiency. The final result achieves very rapid aerodynamic design based on higher order computational fluid dynamics methods (CFD). In our earlier studies, the serial implementation of this design method [19, 20, 21, 23, 39, 25, 40, 41, 42, 43, 9] was shown to be effective for the optimization of airfoils, wings, wing-bodies, and complex aircraft configurations using both the potential equation and the Euler equations [39, 25]. In our most recent paper, the Euler method was extended to treat complete aircraft configurations via a new multiblock implementation. Furthermore, during the same conference, we also presented preliminary results demonstrating that this basic methodology could be ported to distributed memory parallel computing architectures [24]. In this paper, our concern will be to demonstrate that the combined power of these new technologies can be used routinely in an industrial design environment by applying it to the case study of the design of typical supersonic transport configurations. A particular difficulty of this test case is posed by the propulsion/airframe integration."
Download or read book Aircraft Design Projects written by Lloyd R. Jenkinson and published by Elsevier. This book was released on 2003-04-28 with total page 393 pages. Available in PDF, EPUB and Kindle. Book excerpt: Written with students of aerospace or aeronautical engineering firmly in mind, this is a practical and wide-ranging book that draws together the various theoretical elements of aircraft design - structures, aerodynamics, propulsion, control and others - and guides the reader in applying them in practice. Based on a range of detailed real-life aircraft design projects, including military training, commercial and concept aircraft, the experienced UK and US based authors present engineering students with an essential toolkit and reference to support their own project work.All aircraft projects are unique and it is impossible to provide a template for the work involved in the design process. However, with the knowledge of the steps in the initial design process and of previous experience from similar projects, students will be freer to concentrate on the innovative and analytical aspects of their course project. The authors bring a unique combination of perspectives and experience to this text. It reflects both British and American academic practices in teaching aircraft design. Lloyd Jenkinson has taught aircraft design at both Loughborough and Southampton universities in the UK and Jim Marchman has taught both aircraft and spacecraft design at Virginia Tech in the US. * Demonstrates how basic aircraft design processes can be successfully applied in reality* Case studies allow both student and instructor to examine particular design challenges * Covers commercial and successful student design projects, and includes over 200 high quality illustrations
Download or read book General Aviation Aircraft Design written by Snorri Gudmundsson and published by Butterworth-Heinemann. This book was released on 2021-10-31 with total page 1146 pages. Available in PDF, EPUB and Kindle. Book excerpt: General Aviation Aircraft Design, Second Edition, continues to be the engineer’s best source for answers to realistic aircraft design questions. The book has been expanded to provide design guidance for additional classes of aircraft, including seaplanes, biplanes, UAS, high-speed business jets, and electric airplanes. In addition to conventional powerplants, design guidance for battery systems, electric motors, and complete electric powertrains is offered. The second edition contains new chapters: Thrust Modeling for Gas Turbines Longitudinal Stability and Control Lateral and Directional Stability and Control These new chapters offer multiple practical methods to simplify the estimation of stability derivatives and introduce hinge moments and basic control system design. Furthermore, all chapters have been reorganized and feature updated material with additional analysis methods. This edition also provides an introduction to design optimization using a wing optimization as an example for the beginner. Written by an engineer with more than 25 years of design experience, professional engineers, aircraft designers, aerodynamicists, structural analysts, performance analysts, researchers, and aerospace engineering students will value the book as the classic go-to for aircraft design. The printed book is now in color, with 1011 figures and illustrations! Presents the most common methods for conceptual aircraft design Clear presentation splits text into shaded regions, separating engineering topics from mathematical derivations and examples Design topics range from the "new" 14 CFR Part 23 to analysis of ducted fans. All chapters feature updated material with additional analysis methods. Many chapters have been reorganized for further help. Introduction to design optimization is provided using a wing optimization as an example for the beginner Three new chapters are offered, two of which focus on stability and control. These offer multiple practical methods to simplify the estimation of stability derivatives. The chapters introduce hinge moments and basic control system design Real-world examples using aircraft such as the Cirrus SR-22 and Learjet 45
