Relevant bibliographies by topics / Aircraft conceptual design

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Aircraft conceptual design'

Author: Grafiati
Published: 4 June 2021
Last updated: 12 February 2022

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Journal articles on the topic "Aircraft conceptual design"

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Kwiek, Agnieszka. "Conceptual design of an aircraft for Mars mission." Aircraft Engineering and Aerospace Technology 91, no. 6 (June 10, 2019): 886–92. http://dx.doi.org/10.1108/aeat-08-2018-0231.

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Purpose The purpose of this paper is to present the results of a conceptual design of Martian aircraft. This study focuses on the aerodynamic and longitudinal dynamic stability analysis. The main research questions are as follows: Does a tailless aircraft configuration can be used for Martian aircraft? How to the short period characteristic can be improved by side plates modification? Design/methodology/approach Because of a conceptual design stage of this Martian aircraft, aerodynamic characterises were computed by the Panukl package by using the potential flow model. The longitudinal dynamic stability was computed by MATLAB code, and the derivatives computed by the SDSA software were used as the input data. Different aircraft configurations have been studied, including different wing’s aerofoils and configurations of the side plate. Findings This paper presents results of aerodynamic characteristics computations and longitudinal dynamic stability analysis. This paper shows that tailless aircraft configuration has potential to be used as Martian aircraft. Moreover, the study of the impact of side plates’ configurations on the longitudinal dynamic stability is presented. This investigation reveals that the most effective method to improve the short period damping ratio is to change the height of the bottom plate. Practical implications The presented result might be useful in case of further design of the aircrafts for the Mars mission and designing the aircrafts in a tailless configuration. Social implications It is considered by the human expedition that Mars is the most probable planet to explore. This paper presents the conceptual study of aircraft which can be used to take the high-resolution pictures of the surface of Mars, which can be crucial to find the right place to establish a potential Martian base. Originality/value Most of aircrafts proposed for the Mars mission are designed in a configuration with a classic tail; this paper shows a preliminary calculation of the tailless Martian aircraft. Moreover, this paper shows the results of a dynamic stability analysis, where similar papers about aircrafts for the Mars mission do not show such outcomes, especially in the case of the tailless configuration. Moreover, this paper presents the results of the dynamic stability analysis of tailless aircraft with different configurations of the side plates.
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Fioriti, Marco. "Adaptable conceptual aircraft design model." Advances in aircraft and spacecraft science 1, no. 1 (January 31, 2014): 43–67. http://dx.doi.org/10.12989/aas.2014.1.1.043.

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Al-Ahmed, S., and J. P. Fielding. "Vulnerability prediction method for use in aircraft conceptual design." Aeronautical Journal 103, no. 1024 (June 1999): 309–15. http://dx.doi.org/10.1017/s0001924000064903.

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Abstract A methodology has been developed to integrate the vulnerability discipline into the conceptual/preliminary design process of combat aircraft. An interactive and programmable solid modelling Computer Aided Design (CAD) system is used to generate a CAD solid model of the aircraft’s critical components. The aircraft’s components’ sizes and shapes are pre-defined by a conceptual/preliminary design synthesis computer model. A systematic Child-Parent assembly process is used to model the aircraft vulnerability, by defining the criticality degree of each component in the aircraft assembly. Solid Modelling CAD techniques have been modified to develop techniques to perform the two main standard vulnerability assessments, namely the shotline and vulnerable area methods.
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Smith, H., D. Sziroczák, GE Abbe, and P. Okonkwo. "The GENUS aircraft conceptual design environment." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 8 (July 16, 2018): 2932–47. http://dx.doi.org/10.1177/0954410018788922.

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The design of aircraft has evolved over time from the classical design approach to the more modern computer-based design method utilizing multivariate design optimization. In recent years, aircraft concepts and configurations have become more diverse and complex thus pushing many synthesis packages beyond their capability. Furthermore, many examples of aircraft design software focus on the analysis of one particular concept thus requiring separate packages for each concept. This can lead to complications in comparing concepts and configurations as differences in performance may originate from different prediction toolsets being used. This paper presents the GENUS Aircraft Design Framework developed by Cranfield University’s Aircraft Design Group to address these issues. The paper reviews available aircraft design methodologies and describes the challenges faced in their development and application. Following this, the GENUS aircraft design environment is introduced, along with the theoretical background and practical reasoning behind the program architecture. Particular attention is given to the programming, choice of methodology, and optimization techniques involved. Subsequently, some applications of the developed methodology, implemented in the framework are presented to illustrate the diversity of the approach. Three special classes of aircraft design concept are presented briefly.
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Mieloszyk, Jacek, and Andrzej Tarnowski. "Enhancements in conceptual electric aircraft design." Aircraft Engineering and Aerospace Technology 91, no. 6 (June 10, 2019): 851–56. http://dx.doi.org/10.1108/aeat-07-2018-0192.

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PurposeThis paper aims to describe the enhancement of the numerical method for conceptual phase of electric aircraft design.Design/methodology/approachThe algorithm provides a balance between lift force and weight of the aircraft, together with drag and thrust force equilibrium, while modifying design variables. Wing geometry adjustment, mass correction and performance estimation are performed in an iterative process.FindingsAircraft numerical model, which is most often very simplified, has a number of new improvements. This enables to make more accurate analyses and to show relationships between design parameters and aircraft performance.Practical implicationsThe presented approach can improve design results.Originality/valueThe new methodology, which includes enhanced numerical models for conceptual design, has not been presented before.
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YOSHIZAKI, Shinichi, and Junzo SATO. "Computer Analysis of Aircraft Conceptual Design." Journal of the Japan Society for Aeronautical and Space Sciences 46, no. 531 (1998): 224–29. http://dx.doi.org/10.2322/jjsass1969.46.224.

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UDROIU, Razvan, and Madalina-Ioana BLAJ. "CONCEPTUAL DESIGN OF A VTOL REMOTELY PILOTED AIRCRAFT FOR EMERGENCY MISSIONS." SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 18, no. 1 (June 24, 2016): 207–14. http://dx.doi.org/10.19062/2247-3173.2016.18.1.27.

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Henderson, R. P., J. R. R. A. Martins, and R. E. Perez. "Aircraft conceptual design for optimal environmental performance." Aeronautical Journal 116, no. 1175 (January 2012): 1–22. http://dx.doi.org/10.1017/s000192400000659x.

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Abstract Consideration of the environmental impact of aircraft has become critical in commercial aviation. The continued growth of air traffic has caused increasing demands to reduce aircraft emissions, imposing new constraints on the design and development of future airplane concepts. In this paper, an aircraft design optimisation framework is used to design aircraft that minimise specific environmental metrics. Multidisciplinary design optimisation is used to optimise aircraft by simultaneously considering airframe, engine and mission. The environmental metrics considered in this investigation are CO2 emissions — which are proportional to fuel burn — and landing-takeoff NOx emissions. The results are compared to those of an aircraft with minimum direct operating cost. The design variables considered in the optimisation problems include aircraft geometry, engine parameters, and cruise settings. An augmented Lagrangian particle swarm optimiser and a genetic algorithm are used to solve the single objective and multi-objective optimisation problems, respectively.
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Romli, Fairuz I. "Conceptual Aircraft Design Exploration through Functional Approach." Applied Mechanics and Materials 446-447 (November 2013): 602–5. http://dx.doi.org/10.4028/www.scientific.net/amm.446-447.602.

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In today’s market, it is no longer sufficient to have better designs than the competition. In order to maximize the product’s market potential, it has to be rapidly produced and made available to the market. To reduce their time-to-market period, manufacturers need to shorten their design and development process. It becomes vital that the design architecture solution is derived faster, which can be handful for complex products like an aircraft with the current geometrical-based approaches due to the plethora of physical alternatives to be considered. On the other hand, the search for design architecture solution from functional requirements is theoretically more effective because functional space is comparatively smaller than physical search space. This allows the design efforts to be more focused and this subsequently saves time, efforts and resources. With this notion, there is a driving motivation to adapt functional approaches into the conceptual product design process in order to exploit some of its advertised benefits. In this paper, an example case study of an aircraft conceptual development is presented to highlight possible advantages of approaching architecture solutions from the functional space.
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Pornet, C., and A. T. Isikveren. "Conceptual design of hybrid-electric transport aircraft." Progress in Aerospace Sciences 79 (November 2015): 114–35. http://dx.doi.org/10.1016/j.paerosci.2015.09.002.

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Dissertations / Theses on the topic "Aircraft conceptual design"

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Karlsson, Albin, and Anton Lomaeus. "Transport Aircraft Conceptual Design." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-210778.

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A conceptual design for a transport aircraft has been created, tailored for human-itarian missions along the equator with its home base in the European Union while optimizing for fuel eciency and speed. An initial estimate of the empty weight was made using historical data and Breguet equations, based on a required payload of 60 tonnes and range of 5 500 nautical miles. A constraint diagram consisting of require-ments for stall speed, takeo distance, climb rate and landing distance was used to determine wing loading and thrust to weight ratio, resulting in a main wing area of 387m 2 and thrust to weight ratio of 0:224, for which two Rolls Royce Trent 1000-H engines were selected. A high aspect ratio wing was designed with blended winglets to optimize against lift induced drag. Wing placement and tail volume were decided by iterative calculations, resulting in a centre of lift located aft of the centre of gravity during all stages of the mission. The resulting aircraft model has a high wing with a span of 62 m, length of 49m with a takeo gross weight of 221 tonnes, of which 83 tonnes are fuel.
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Carlson, Jesper, and Diyar Jazrawi. "Conceptual Design of a Transport Aircraft." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-211549.

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When flooding or earthquakes hits a country the population in the area could suffer a lot and are in a big need of help quickly. In these situations heavy transport aircraft are used around the world to help and support the victims in the area by delivering supplies. In our operational mission scenario the country Papa New guinea has been hit by an earthquake and approximately 5000 people have lost their home and are in need of help. The only problem is that there are no heavy transport airplanes available to fly from EU to this country and return without refuelling. The problem here is that the country is in a big need of help and if an airplane needs to land to refuel a lot of time is wasted. Therefore, in this task we have designed a conceptual transport aircraft that is able to fly from EU to Papa New Guinea to deliver supplies in form of food, aid, water etc. Due to the horrific accident the airplane does not have access to a runway and will have to deliver the supplies by airdrop in parachutes. In this report we will generate a requirements specification, which will state the requirements of the aircraft and be vital for the design. There will be precise estimations and calculations presented and it will include important parameters used in the Design of the aircraft.
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Rabizadeh, Nadja, and Bahar Kasbi. "Conceptual Design of a Transport Aircraft." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-211556.

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The mission of this project is to conceptually design a transport aircraft. A typical mission for a transport aircraft is to deliver supplies to countries in need of help. The given requirement is that the aircraft should be able to travel from a place within EU to a place along the equator in Africa, deliver the supplies, and return (to the takeoff location) without refueling. The operational mission will be to provide people in need with supplies such as food, water and tents. The aircraft will be able to carry necessities that will be able to provide 5000 persons during a week. Since a landing runway is not available at the destination, the payload will be airdropped in parachutes. First off, the desired requirements are defined, they are either already given or estimated. An analysis of´the mission and the desired performance of the aircraft is made by creating a mission profile. With the help of this a weight estimation is done, most importantly the takeoff weight of the aircraft is estimated. With the takeoff weight known and by the help of the desired performance requirements, a constraint diagram is made. By a constraint analysis the optimal wing loading and thrust-to-weight ratio is found. This makes it possible to choose an appropriate engine and to design the wings so that they are customized for the desired mission. Other parts of the aircraft such as the tail and fuselage are designed, and the center-of gravity of the aircraft is found. Throughout the project, different aerodynamic parameters are changed in order to optimize the aircraft and its performance to make it as adapted as possible to the desired mission.
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Jackson, David Wayne. "Robust aircraft subsystem conceptual architecting." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50202.

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Aircraft subsystems are key components in modern aircraft, the impact and significance of which have been constantly increasing. Furthermore, the architecture selection of these subsystems has overall system-level effects. Despite the significant effects of architecture selections, existing methods for determining the architecture, especially early in design, are similar to the use of traditional point solutions. Currently, aircraft subsystems are rarely examined during the conceptual design phase, despite the fact that this phase has a significant influence on aircraft cost and performance. For this reason, there is a critical need to examine subsystem architecture trades and investigate the design space during the conceptual design of an aircraft. Traditionally, after the aircraft conceptual design phase, subsystems are developed in a process that begins with the point selection of the architecture, then continues with its development and analysis, and concludes in the detailed development of the subsystems. The choice of the point design of the architecture to be developed can be made using simplified models to explore the design space. This method known as conceptual architecting is explored in this dissertation. This dissertation also focuses on bringing actuation subsystem architecture trades into conceptual design because of the significant cost impact of this design phase and the interdependence of vehicle sizing with the subsystems impact on the aircraft. The extent of these interdependencies is examined and found to be significant. As a result, this coupling must be captured to enable better informed decision making. A methodology to examine the design space of aircraft subsystem architectures during the conceptual design of aircraft, while incorporating this coupling, is presented herein and applied specifically to actuation architectures.
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Gangadharan, Venkata Krishnan. "Conceptual Design Tool for Aircraft Electrical System." Thesis, Linköpings universitet, Fluida och mekatroniska system, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-96162.

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The conceptual design stage of an aircraft involves many uncertainties with regard to prediction of weight of systems. The current trend is that electrical systems increasingly replace hydraulic and pneumatic systems in an aircraft. This leads to greater uncertainty in weight, size and power requirement prediction. This work is an attempt at developing a sizing tool that will allow users to estimate the power requirements and weight of electrical systems for a given size of an aircraft specified either by passenger capacity or by aircraft operating empty weight or by maximum take-off weight. As with all predictive tools, the results of this work are based on currently available data, i.e., the specification of existing aircraft. This collection of specification of existing aircrafts would constitute the data library. The accuracy of the result of this work depends greatly on the variety of aircrafts and the level of detail for which the data is available. The tool is made in Microsoft Excel with some codes made in VBA to perform Excel calculations.
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Raymer, Daniel. "Enhancing Aircraft Conceptual Design using Multidisciplinary Optimization." Doctoral thesis, KTH, Aeronautical Engineering, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3331.

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Research into the improvement of the Aircraft ConceptualDesign process by the application of MultidisciplinaryOptimization (MDO) is presented. Aircraft conceptual designanalysis codes were incorporated into a variety of optimizationmethods including Orthogonal Steepest Descent (full-factorialstepping search), Monte Carlo, a mutation-based EvolutionaryAlgorithm, and three variants of the Genetic Algorithm withnumerous options. These were compared in the optimization offour notional aircraft concepts, namely an advanced multiroleexport fighter, a commercial airliner, a flying-wing UAV, and ageneral aviation twin of novel asymmetric configuration. Tobetter stress the methods, the commercial airliner design wasdeliberately modified for certain case runs to reflect a verypoor initial choice of design parameters including wingloading, sweep, and aspect ratio.

MDO methods were evaluated in terms of their ability to findthe optimal aircraft, as well as total execution time,convergence history, tendencies to get caught in a localoptimum, sensitivity to the actual problem posed, and overallease of programming and operation. In all, more than a millionparametric variations of these aircraft designs were definedand analyzed in the course of this research.

Following this assessment of the optimization methods, theywere used to study the issue of how the computer optimizationroutine modifies the aircraft geometric inputs to the analysismodules as the design is parametrically changed. Since thiswill ultimately drive the final result obtained, this subjectdeserves serious attention. To investigate this subject,procedures for automated redesign which are suitable foraircraft conceptual design MDO were postulated, programmed, andevaluated as to their impact on optimization results for thesample aircraft and on the realism of the computer-defined"optimum" aircraft. (These are sometimes called vehicle scalinglaws, but should not be confused with aircraft sizing, alsocalled scaling in some circles.)

This study produced several key results with application toboth Aircraft Conceptual Design and MultidisciplinaryOptimization, namely:

    MDO techniques truly can improve the weight and cost ofan aircraft design concept in the conceptual design phase.This is accomplished by a relatively small "tweaking" of thekey design variables, and with no additional downstreamcosts.In effect, we get a better airplane for free.

    For a smaller number of variables (<6-8), adeterministic searching method (here represented by thefull-factorial Orthogonal Steepest Descent) provides aslightly better final result with about the same number ofcase evaluations

    For more variables, evolutionary/genetic methods getclose to the best final result with far-fewer caseevaluations. The eight variables studied herein probablyrepresent the practical upper limit on deterministicsearching methods with today’s computer speeds.

    Of the evolutionary methods studied herein, the BreederPool approach (which was devised during this research andappears to be new) seems to provide convergence in the fewestnumber ofcase evaluations, and yields results very close tothe deterministic best result. However, all of the methodsstudied produced similar results and any of them is asuitable candidate for use.

    Hybrid methods, with a stochastic initial optimizationfollowed by a deterministic final "fine tuning", proved lessdesirable than anticipated.

    Not a single case was observed, in over a hundred caseruns totaling over a million parametric design evaluations,of a method returning a local rather than global optimum.Even the modified commercial airliner, with poorly selectedinitial design variables far away from the global solution,was easily "fixed" by all the MDO methods studied.

    The postulated set of automated redesign procedures andgeometric constraints provide a more-realistic final result,preventing attainment of an unrealistic "better" finalresult. Especially useful is a new approach defined herein,Net Design Volume, which can prevent unrealisticallyhigh design densities with relatively little setup andcomputational overhead. Further work in this area issuggested, especially in the unexplored area of automatedredesign procedures for discrete variables.

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Munjulury, Venkata Raghu Chaitanya. "Knowledge Based Integrated Multidisciplinary Aircraft Conceptual Design." Licentiate thesis, Linköpings universitet, Fluida och mekatroniska system, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-106925.

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With the ever growing complexity of aircrafts, new tools and eventually methods to use these tools are needed in aircraft conceptual design. To reduce the development cost, an enhancement in the conceptual design is needed. This thesis presents a knowledge-based aircraft geometry design tool RAPID and the methodology applied in realizing the design. The parameters used to create a geometry need to be exchange between different tools. This is achieved by using a centralized database or onedata concept. One-database will enable creating a less number of cross connections between different tools to exchange data with one another. Different types of aircraft configurations can be obtained with less effort. As RAPID is developed based on relational design, any changes made to the geometric model will update automatically. The geometry model is carefully defined to carry over to the preliminary design. The validation of RAPID is done by implementing it in different aircraft design courses at Linköping University. In the aircraft project course, RAPID was effectively used and new features were added to the obtained desired design. Knowledge-base is used to realize the design performance for the geometry with an integrated database approach for a multidisciplinary aircraft conceptual design.
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Schäfer, Katharina [Verfasser]. "Conceptual Aircraft Design for Sustainability / Katharina Schäfer." Aachen : Shaker, 2018. http://d-nb.info/1161299424/34.

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Kay, Jacob. "Control authority assessment in aircraft conceptual design." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-03242009-040703/.

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Squire, Douglas J. "Afterbody drag prediction for conceptual aircraft design." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-09192009-040348/.

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Books on the topic "Aircraft conceptual design"

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Aircraft conceptual design synthesis. London: Professional Engineering Pub., 2000.

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Howe, Denis. Aircraft Conceptual Design Synthesis. Chichester, UK: John Wiley & Sons, Ltd, 2000. http://dx.doi.org/10.1002/9781118903094.

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Raymer, Daniel P. Aircraft design: A conceptual approach. 5th ed. Reston, VA: American Institute of Aeronautics and Astronautics, 2012.

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Raymer, Daniel P. Aircraft design: A conceptual approach. 2nd ed. Washington, D.C: American Institute of Aeronautics and Astronautics, 1992.

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American Institute of Aeronautics and Astronautics., ed. Aircraft design: A conceptual approach. Washington, D.C: American Institute of Aeronautics and Astronautics, 1989.

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Hollowell, Steven James. Conceptual design optimization study. Hampton, Va: Langley Research Center, 1990.

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Raymer, Daniel P. Enhancing aircraft conceptual design using multidisciplinary optimization. Stockholm: Tekniska högsk., 2002.

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Hollowell, S. J. Conceptual design optimization study. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Albright, Alan E. Modification and validation of conceptual design aerodynamic prediction method HASC95 with VTXCHN. Hampton, Va: Langley Research Center, 1996.

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Tan, Rendell Kheng Wah. Quality functional deployment as a conceptual aircraft design tool. Monterey, Calif: Naval Postgraduate School, 2000.

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Book chapters on the topic "Aircraft conceptual design"

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Howe, Denis. "Aircraft Configuration." In Aircraft Conceptual Design Synthesis, 23–52. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch2.

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Howe, Denis. "The Design Process." In Aircraft Conceptual Design Synthesis, 1–22. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch1.

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Howe, Denis. "Analysis of Concept Design." In Aircraft Conceptual Design Synthesis, 279–92. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch9.

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Baier, H., M. Hornung, B. Mohr, D. Paulus, Ö. Petersson, C. Rößler, F. Stroscher, and T. Salmon. "Conceptual Design." In Modeling and Control for a Blended Wing Body Aircraft, 29–45. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-10792-9_2.

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Howe, Denis. "Configuration of the Wing." In Aircraft Conceptual Design Synthesis, 113–38. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch5.

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Howe, Denis. "Basic Lift, Drag and Mass Representations." In Aircraft Conceptual Design Synthesis, 139–64. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch6.

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Howe, Denis. "Performance Estimation." In Aircraft Conceptual Design Synthesis, 165–222. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch7.

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Howe, Denis. "Parametric Analysis and Optimisation." In Aircraft Conceptual Design Synthesis, 223–78. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch8.

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Howe, Denis. "Flight Regime and Powerplant Considerations." In Aircraft Conceptual Design Synthesis, 53–80. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch3.

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Howe, Denis. "Fuselage Layout." In Aircraft Conceptual Design Synthesis, 81–112. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch4.

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Conference papers on the topic "Aircraft conceptual design"

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HAVEY, C., and MARGARET KLINE. "Propulsion optimization for conceptual STOVL aircraft." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2020.

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GABRIELE, GARY. "Computer-aided conceptual design of rotorcraft." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3099.

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INOUE, TOSHIAKI, JUN-ICHI HIROKAWA, TOSHIO HANAI, and HIKARU TAKAMI. "Conceptual study of supersonic propulsion systems." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3133.

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SNYDER, JAMES. "CFD needs in conceptual design." In Aircraft Design, Systems and Operations Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-3209.

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Locatelli, Davide, Benjamin Riggins, Joseph A. Schetz, Rakesh K. Kapania, Bernard Robic, Clement Leenaert, and Thomas Poquet. "Aircraft Conceptual Design: Tools Evaluation." In 14th AIAA Aviation Technology, Integration, and Operations Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2030.

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BRIDGENS, D. "FAA conceptual changes in minimum equipment list policies." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2055.

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PETEREIN, SR., WAYNE, ALFRED ZALESKI, GEORGE LIND, and MICHAEL BRITTINGHAM. "An Advanced Counter Air System (ACAS) - Conceptual formulation." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2136.

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"Control authority assessment in aircraft conceptual design." In Aircraft Design, Systems, and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3968.

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BROWN, DAVID. "Supersonic STOVL conceptual design of a fighter/attack aircraft." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2112.

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Neufeld, Daniel, and Joon Chung. "Aircraft Conceptual Design Optimization Considering Airworthiness." In 12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-5907.

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