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Relevant bibliographies by topics / Supersonic aircraft design

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Academic literature on the topic 'Supersonic aircraft design'

Author: Grafiati

Published: 4 June 2021

Last updated: 17 February 2022

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Journal articles on the topic "Supersonic aircraft design"

1

Chen, Min, Zihao Jia, Hailong Tang, Yi Xiao, Yonghang Yang, and Feijia Yin. "Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept." International Journal of Aerospace Engineering 2019 (January 14, 2019): 1–19. http://dx.doi.org/10.1155/2019/2918646.

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Supersonic civil aircraft is of a promising area in the development of future civil transport, and aircraft propulsion system is one of the key issues which determine the success of the aircraft. To get a good conceptual design and performance investigation of the supersonic civil aircraft engine, in this article, a fast, versatile as well as trust-worthy numerical simulation platform was established to analyze the Mach 4 turbine-based combined cycle (TBCC) engine concept so as to be applied to the supersonic civil aircraft. First, a quick and accurate task requirement analysis module was newly established to analyze the mission requirement of the Mach 4 supersonic civil aircraft. Second, the TBCC engine performance simulation model was briefly presented and the number of engines on the supersonic civil aircraft was analyzed, considering single engine inoperative. Third, the Stone model and the DLR method were investigated to estimate the engine jet noise and the NOx emission of the Mach 4 supersonic civil aircraft. Finally, a multiobjective optimization tool made up of a response surface method and a genetic algorithm was developed to optimize the design parameters and the control law of the TBCC engine, in order to make the Mach 4 supersonic civil aircraft engine with better performance, lower noise, and lower emissions. The uniqueness of the developed analysis tool lies in that it affords a numerical simulation platform capable of investigating the task requirement analysis module of the supersonic civil aircraft, engine jet noise prediction model, and the NOx emission prediction model, as well as a multiobjective performance optimization tool, which is beneficial for the conceptual design and performance research of Mach 4 supersonic civil aircraft’s propulsion system.

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Joiner, Keith F., Jordan Zahra, and Obaid Rehman. "Conceptual sizing of next supersonic passenger aircraft from regression of the limited existing designs." MATEC Web of Conferences 198 (2018): 05001. http://dx.doi.org/10.1051/matecconf/201819805001.

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Despite previous versions, there are no current supersonic passenger transport aircraft. Much aircraft research is focused on hypersonic flight and the new technologies therein and is therefore unlikely to add to commercial versions anytime soon. This study re-examines conceptual sizing of a supersonic transport aircraft based on extant supersonic designs in order to ignite research into whether a commercially-viable design might exist. Key metrics are developed using distances between likely airport network nodes, an assumed number of passengers, and a reduction in transport time to one-third of current journeys. The study uses multiple response regression of known designs to develop key performance formulae, which are then optimized to set performance values so as to estimate an initial aircraft size, including an expected value analysis to guide the next conceptual design iteration. Twenty years ago a NASA Langley Research optimization system was used to examine non-linear regression of supersonic aircraft designs and to optimize such a design around similar performance criteria. In contrast, this work is the first supersonic transport aircraft sizing to use commercially-available Excel add-on software and standard design-for-sixsigma analysis techniques; notably for the sensitivity analyses to guide the next design iteration.

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Schuermann, M., M. Gaffuri, and P. Horst. "Multidisciplinary pre-design of supersonic aircraft." CEAS Aeronautical Journal 6, no. 2 (November 27, 2014): 207–16. http://dx.doi.org/10.1007/s13272-014-0140-1.

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Mabey, D. G. "Design features which influence flow separations on aircraft." Aeronautical Journal 92, no. 920 (December 1988): 409–15. http://dx.doi.org/10.1017/s0001924000016547.

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Summary Features of aircraft which influence flow separations, and hence the onset of buffeting, should be always of interest to an aerodynamicist. The present compilation of such features is based on notes made during a visit to the USAF Aircraft Museum in Dayton, Ohio. Although two low-speed aircraft with high aspect ratio wings are considered, the emphasis is primarily on transonic and supersonic military aircraft, with wings of lower aspect ratio. Some recommendations are made to stimulate research into improved methods to control flow separation, particularly for future transonic and supersonic aircraft.

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Steer, A. J. "Supersonic transport aircraft longitudinal flight control law design." Aeronautical Journal 108, no. 1084 (June 2004): 319–29. http://dx.doi.org/10.1017/s000192400000018x.

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Abstract Modern civil transport aircraft utilise increasingly complex command and stability augmentation systems to restore stability, optimise aerodynamic performance and provide the pilot with the optimum handling qualities. Provided it has sufficient control power a second generation fly-by-wire supersonic transport aircraft should be capable of exhibiting similarly desirable low-speed handling qualities. However, successful flight control law design requires identification of the ideal command response type for a particular phase of flight, a set of valid handling quality design criteria and piloted simulation evaluation tasks and metrics. A non-linear mathematical model of the European supersonic transport aircraft has been synthesized on the final approach to land. Specific handling quality design criteria have been proposed to enable the non-linear dynamic inversion flight control laws to be designed, with piloted simulation used for validation. A pitch rate command system, with dynamics matched to the aircraft’s flight path response, will consistently provide Level 1 handling qualities. Nevertheless, pre-filtering the pilot’s input to provide a second order pitch rate response, using the author’s suggested revised constraints on the control anticipation parameter will generate the best handling qualities during the terminal phase of flight. The resulting pre-filter can be easily applied to non-linear dynamic inversion inner loop controllers and has simple and flight proven sensor requirements.

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Steer, A. J., and M. V. Cook. "Control and handling qualities considerations for an advanced supersonic transport aircraft." Aeronautical Journal 103, no. 1024 (June 1999): 265–72. http://dx.doi.org/10.1017/s0001924000064800.

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Abstract A future advanced supersonic transport aircraft (AST) has fundamental characteristics and problems inherent to supersonic cruise aircraft with corresponding unique control and handling characteristics. In order to optimise the aerodynamic performance across the full flight envelope a fully integrated flight and propulsion control system will be required. However, this will need to be designed from the outset within clearly defined flight control and performance guidelines. Relevant existing and AST specific handling qualities criteria will need to be developed if a successful commercial transport aircraft is to be produced. This paper begins by presenting an overview of existing supersonic transport (SST) aircraft operations and current second generation SST research activities and design considerations. This is followed by an analysis of the principal aerodynamic, dynamic and control characteristics of SST and AST aircraft and their effect on the aircraft’s handling qualities. Finally, some possible solutions to the control and handling issues are investigated, assessed and presented.

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Chudoba, B., G. Coleman, A. Oza, and P. A. Czysz. "What price supersonic speed? A design anatomy of supersonic transportation Part 1." Aeronautical Journal 112, no. 1129 (March 2008): 141–51. http://dx.doi.org/10.1017/s0001924000002074.

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Abstract The first generation of supersonic commercial transportation has seen three serious attempts to arrive at an economically and environmentally viable aircraft. The US B2707-200/300 design was cancelled early before a prototype could emerge; the Russian Tu-144 design succeeded to become the first supersonic transport but spanned only a few years of restricted airline service; the Anglo-French Concorde endured more than 27 glamorous airline service years until the last of its species was retired on 30 August 2003. This first generation was followed by a second generation of supersonic commercial transport projects in the time period between 1986 until about 1999, designs which did not proceed towards the production hardware stage. This study critically examines the anatomy of two generations of supersonic commercial transport design failures and successes in order to arrive at lessons learned free of ‘wishful thinking’. The design conditions leading to the identification of the product ‘solution space’ for an economically and environmentally acceptable supersonic commercial transport are discussed. Having assembled an understanding of the product metrics valid for supersonic commercial transports, the paper then provides an outlook for the first generation of supersonic corporate and cargo jet projects. This first generation of supersonic business jet (SSBJ) and supersonic cargo jet (SSCJ) projects spans a period of nearly two decades of development, starting from 1988 until today. The present study identifies that the product development metrics of this class of aircraft is radically different compared to the metrics valid for supersonic commercial transports. The challenges in VIP transportation and dedicated freight transportation at supersonic speeds are portrayed leading to two principal trains of thought targeting the development of the first supersonic business jet and/or supersonic cargo jet hardware: the development based on a new airframe, and alternatively the development based on an existing airframe.

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Utomo, Muhammad Adnan, and Romie Oktavianus Bura. "Design of Inward-Turning External Compression Supersonic Inlet for Supersonic Transport Aircraft." INSIST 2, no. 2 (January 25, 2019): 104. http://dx.doi.org/10.23960/ins.v2i2.90.

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Inward-turning external compression intake is one of the hybrid intakes that employs both external and internal compression intakes principle. This intake is commonly developed for hypersonic flight due to its efficiency and utilizing fewer shockwaves that generate heat. Since this intake employ less shockwaves, this design can be applied for low supersonic (Mach 1.4 - 2.5) intakes to reduce noise generated from the shockwaves while maintaining the efficiency. Other than developing the design method, a tool is written in MATLAB language to generate the intake shape automatically based on the desired design requirement. To investigate the intake design tool code and the performance of the generated intake shape, some CFD simulation were performed. The intake design tool code can be validated by comparing the shockwave location and the air properties in every intake's stations. The performance parameters that being observed are the intake efficiency, flow distortion level at the engine face, and the noise level generated by the shockwaves. The design tool written in MATLAB is working as intended. Two dimensional axisymmetric CFD simulations validation has been done and the design meets the minimum requirement. As for the 3D inlet geometry, with a little modification on diffuser and equipping vent to release the buildup pressure, the inlet has been successfully met the military standard on inlet performance (MIL-E-5007D). This design method also has feature to fit every possible throat cross sectional shapes and has been proven to work as designed.Keywords— Inward-turning, Supersonic, Engine Intakes, Low- noise, Design Method

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Jasa, John P., Benjamin J. Brelje, Justin S. Gray, Charles A. Mader, and Joaquim R. R. A. Martins. "Large-Scale Path-Dependent Optimization of Supersonic Aircraft." Aerospace 7, no. 10 (October 20, 2020): 152. http://dx.doi.org/10.3390/aerospace7100152.

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Aircraft are multidisciplinary systems that are challenging to design due to interactions between the subsystems. The relevant disciplines, such as aerodynamic, thermal, and propulsion systems, must be considered simultaneously using a path-dependent formulation to assess aircraft performance accurately. In this paper, we construct a coupled aero-thermal-propulsive-mission multidisciplinary model to optimize supersonic aircraft considering their path-dependent performance. This large-scale optimization problem captures non-intuitive design trades that single disciplinary models and path-independent methods cannot resolve. We present optimal flight profiles for a supersonic aircraft with and without thermal constraints. We find that the optimal flight trajectory depends on thermal system performance, showing the need to optimize considering the path-dependent multidisciplinary interactions.

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Vázquez, M., A. Dervieux, and B. Koobus. "Multilevel optimization of a supersonic aircraft." Finite Elements in Analysis and Design 40, no. 15 (September 2004): 2101–24. http://dx.doi.org/10.1016/j.finel.2004.01.010.

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Dissertations / Theses on the topic "Supersonic aircraft design"

1

Bressollette, Aurélle 1977. "Sonic boom considerations in preliminary design of supersonic aircraft." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/82216.

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Locatelli, Davide. "Optimization of Supersonic Aircraft Wing-Box using Curvilinear SpaRibs." Diss., Virginia Tech, 2012. http://hdl.handle.net/10919/26345.

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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 maneuver loads computed using ZESt (ZONA Technology Inc. Steady Euler equations solver), optimized using SpaRibs parameterized with Independent Shape method; (5) a preliminary application of the Linked Shape parameterization to place SpaRibs into a high speed commercial transport aircraft wing-box characterized by high geometry layout complexity; and (6) an optimization of panels subjected to axial and shear loads using curvilinear stiffeners and grids of curvilinear stiffeners. The results for the optimization of the rectangular wing-box show 36.8% weight reduction from the baseline, when the Bounding Box and Base Curves parameterization is applied and the Two-Step framework is implemented. For the same structure the weight reduction amounts to 46.7% when the Linked Shape parameterization and the Two-Step framework are used. Similar results are obtained for the generic fighter wing-box structure. In this case, the weight saving is about 20%. Bounding Box and Base Curves parameterization and Two-Step framework are used. Finally, the weight reduction for the general business jet wing-box structure amounts to 17% of the baseline weight. In this case, the computation is carried out using the Independent Shape parameterization and the Two-Step framework. In general, the Two-Step optimization framework finds better optimal structure configurations as compared to the One-Step optimization framework. However, the computational time required to find to optimum with the Two-Step optimization is larger when a small number of particles are used in the particle swarm optimization method. For larger number of particles, the computational time for the two methods is comparable. Finally for very large number of particles the Two-Step optimization requires less computational time. It is also important to notice how the Two-Step framework consistently leads to a better optimum than the One-Step framework, for the same number of particles.
Ph. D.

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Steer, A. J. "Flight control for advanced supersonic transport aircraft handling quality design." Thesis, Cranfield University, 2001. http://dspace.lib.cranfield.ac.uk/handle/1826/11286.

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Concorde's unique low-speed handling qualities are acceptable when flown in a rigidly procedural manner by experienced pilots. However, to be commercially viable and environmentally acceptable more numerous second generation supersonic transport (SST) aircraft would have increased passenger carrying capacity, range and the flexibility to integrate with sub-sonic air traffic. Their much larger size, weight and inertia compared to Concorde's, combined with increasing levels of relaxed longitudinal stability to improve aerodynamic efficiency, results in unstable dynamics and degraded handling qualities on the final approach, where precise manual flightpath control is required. Modern fly-by-wire command and stability augmentation systems can restore stability, provide task tailored command laws and an associated level of handling qualities. Nonlinear Dynamic Inversion (NDI) enables control law prototyping and analysis for the rapid assessment, of conceptual designs to identify control power and command response requirements using both off-line and real-time simulation. This study has developed and applied NDI, and its realisable form (RNDI), in a novel way to design flight control laws specifically addressing handling quality requirements using selected criteria. Piloted validation has demonstrated that NDI pitch rate command will consistently provide Level 1 low-speed handling qualities in both steady and turbulent conditions. However, the best handling qualities can be achieved through a second order pitch rate response, generated by pre-filters, designed to author-suggested constraints on control anticipation parameter (CAP). The SST pitch rate criterion envelope, modified to ensure positive pitch attitude dropback, can then be applied to verify the time response. The resulting pre-filters are easily applied to RNDI inner loop controllers and would be straightforward to implement with simple and proven sensor requirements. Carefully designed NDI normal acceleration command laws are also capable of generating Level 1 low-speed handling qualities in steady conditions. However, their degraded performance in turbulence was exacerbated, relative to the pitch rate command laws, by the use of a fixed base simulator for pilot evaluation. Further motion based simulation studies would provide, in addition to pitching motion, the normal acceleration response cues necessary for a fair command law comparison to be made.

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Steer, Anthony J. "Flight control for advanced supersonic transport aircraft handling quality design." Thesis, Cranfield University, 2001. http://dspace.lib.cranfield.ac.uk/handle/1826/11286.

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Concorde's unique low-speed handling qualities are acceptable when flown in a rigidly procedural manner by experienced pilots. However, to be commercially viable and environmentally acceptable more numerous second generation supersonic transport (SST) aircraft would have increased passenger carrying capacity, range and the flexibility to integrate with sub-sonic air traffic. Their much larger size, weight and inertia compared to Concorde's, combined with increasing levels of relaxed longitudinal stability to improve aerodynamic efficiency, results in unstable dynamics and degraded handling qualities on the final approach, where precise manual flightpath control is required. Modern fly-by-wire command and stability augmentation systems can restore stability, provide task tailored command laws and an associated level of handling qualities. Nonlinear Dynamic Inversion (NDI) enables control law prototyping and analysis for the rapid assessment, of conceptual designs to identify control power and command response requirements using both off-line and real-time simulation. This study has developed and applied NDI, and its realisable form (RNDI), in a novel way to design flight control laws specifically addressing handling quality requirements using selected criteria. Piloted validation has demonstrated that NDI pitch rate command will consistently provide Level 1 low-speed handling qualities in both steady and turbulent conditions. However, the best handling qualities can be achieved through a second order pitch rate response, generated by pre-filters, designed to author-suggested constraints on control anticipation parameter (CAP). The SST pitch rate criterion envelope, modified to ensure positive pitch attitude dropback, can then be applied to verify the time response. The resulting pre-filters are easily applied to RNDI inner loop controllers and would be straightforward to implement with simple and proven sensor requirements. Carefully designed NDI normal acceleration command laws are also capable of generating Level 1 low-speed handling qualities in steady conditions. However, their degraded performance in turbulence was exacerbated, relative to the pitch rate command laws, by the use of a fixed base simulator for pilot evaluation. Further motion based simulation studies would provide, in addition to pitching motion, the normal acceleration response cues necessary for a fair command law comparison to be made.

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Pergamalis, Nikolaos. "Conceptual design, flying and handling qualities of a supersonic transport aircraft." Thesis, KTH, Flygdynamik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-211167.

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The purpose of this project is the design of a supersonic aircraft that is able to meet the market’s requirements, be economically viable and mitigate the current barriers. The initial requirements of the design have been set according to the understanding obtained from a brief market research, taking into account the market needs, in addition to the economical and environmental restrictions. The conceptual design proposed is a supersonic transport able to execute transatlantic flights carrying 15 passengers. The aerodynamics, propulsion data and weight of the design have been estimated using empirical relations and experimental data found in references. The design has been evaluated regarding its performance, stability, flying and handling qualities. The relevant models have been created using the software Matlab, while the flight testing has been executed at the Merlin MP521 engineering flight simulator. Finally, a discussion is made about the environmental impact of the supersonic transport, focusing on the aerodynamic noise, generated by the sonic boom, and the air pollutants emissions.

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Guillermo-Monedero, Daniel. "A Comparison of Euler Finite Volume and Supersonic Vortex Lattice Methods used during the Conceptual Design Phase of Supersonic Delta Wings." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1576713976622162.

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Buonanno, Michael Alexander. "A Method for Aircraft Concept Exploration using Multicriteria Interactive Genetic Algorithms." Diss., Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/7571.

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The problem of aircraft concept selection has become increasingly difficult in recent years due to changes in the primary evaluation criteria of concepts. In the past, performance was often the primary discriminator whereas modern programs have placed increased emphasis on factors such as environmental impact, economics, supportability, aesthetics, and other metrics. The revolutionary nature of the vehicles required to simultaneously meet these conflicting requirements has prompted a shift from design using historical data regression techniques for metric prediction to the use of sophisticated physics-based analysis tools that are capable of analyzing designs outside of the historical database. The use of optimization methods with these physics-based tools, however, has proven difficult because of the tendency of optimizers to exploit assumptions present in the models and drive the design towards a solution which, while promising to the computer, may be infeasible due to factors not considered by the computer codes. In addition to this difficulty, the number of discrete options available at this stage may be unmanageable due to the combinatorial nature of the concept selection problem, leading the analyst to select a sub-optimum baseline vehicle. Some extremely important concept decisions, such as the type of control surface arrangement to use, are frequently made without sufficient understanding of their impact on the important system metrics due to a lack of historical guidance, computational resources, or analysis tools. This thesis discusses the difficulties associated with revolutionary system design, and introduces several new techniques designed to remedy them. First, an interactive design method has been developed that allows the designer to provide feedback to a numerical optimization algorithm during runtime, thereby preventing the optimizer from exploiting weaknesses in the analytical model. This method can be used to account for subjective criteria, or as a crude measure of un-modeled quantitative criteria. Other contributions of the work include a modified Structured Genetic Algorithm that enables the efficient search of large combinatorial design hierarchies and an improved multi-objective optimization procedure that can effectively optimize several objectives simultaneously. A new conceptual design method has been created by drawing upon each of these new capabilities and aspects of more traditional design methods. The ability of this new technique to assist in the design of revolutionary vehicles has been demonstrated using a problem of contemporary interest: the concept exploration of a supersonic business jet. This problem was found to be a good demonstration case because of its novelty and unique requirements, and the results of this proof of concept exercise indicate that the new method is effective at providing additional insight into the relationship between a vehicle's requirements and its favorable attributes.

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Waddington, Michael Jon. "Development of an Interactive Wave Drag Capability for the OpenVSP Parametric Geometry Tool." DigitalCommons@CalPoly, 2015. https://digitalcommons.calpoly.edu/theses/1435.

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Minimizing wave drag is critical to successful and efficient transonic and supersonic flight. Area-ruling is the process of managing the cross-sectional area of an aircraft to lessen the wave drag experienced in flight. Effectively calculating the necessary areas for a given aircraft can be difficult, and existing tools for conducting a wave drag analysis often carry limitations in both functionality and availability. In this work, the author utilized an existing parametric geometry tool named OpenVSP to create an interactive design tool for approximating zero-lift wave drag. Here, the wave drag calculation methodology used in industry for decades is combined with the powerful geometry engine of OpenVSP, which was recently heavily upgraded at the start of 2015. Various visual aids allow users of this OpenVSP wave drag tool to interact with area and wave drag results and develop intuition for supersonic aircraft design using the area rule approach. OpenVSP allows geometry changes to be made quickly, enabling rapid reanalysis by the wave drag tool for expeditious comparison of results across the design space.

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Combier, Robert. "Risk-informed scenario-based technology and manufacturing evaluation of aircraft systems." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/49046.

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In the last half century, the aerospace industry has seen a dramatic paradigm shift from a focus on performance-at-any-cost to product economics and value. The steady increase in product requirements, complexity and global competition has driven aircraft manufacturers to seek broad portfolios of advanced technologies. The development costs and cycle times of these technologies vary widely, and the resulting design environment is one where decisions must be made under substantial uncertainty. Modeling and simulation have recently become the standard practice for addressing these issues; detailed simulations and explorations of candidate future states of these systems help reduce a complex design problem into a comprehensible, manageable form where decision factors are prioritized. While there are still fundamental criticisms about using modeling and simulation, the emerging challenge becomes ``How do you best configure uncertainty analyses and the information they produce to address real world problems?” One such analysis approach was developed in this thesis by structuring the input, models, and output to answer questions about the risk and economic impact of technology decisions in future aircraft programs. Unlike other methods, this method placed emphasis on the uncertainty in the cumulative cashflow space as the integrator of economic viability. From this perspective, it then focused on exploration of the design and technology space to tailor the business case and its associated risk in the cash flow dimension. The methodology is called CASSANDRA and is intended to be executed by a program manager of a manufacturer working of the development of future concepts. The program manager has the ability to control design elements as well as the new technology allocation on that aircraft. She is also responsible for the elicitation of the uncertainty in those dimensions within control as well as the external scenarios (that are out of program control). The methodology was applied on a future single-aisle 150 passenger aircraft design. The overall methodology is compared to existing approaches and is shown to identify more economically robust design decisions under a set of at-risk program scenarios. Additionally, a set of metrics in the uncertain cumulative cashflow space were developed to assist the methodology user in the identification, evaluation, and selection of design and technology. These metrics are compared to alternate approaches and are shown to better identify risk efficient design and technology selections. At the modeling level, an approach is given to estimate the production quantity based on an enhanced Overall Evaluation Criterion method that captures the competitive advantage of the aircraft design. This model was needed as the assumption of production quantity is highly influential to the business case risk. Finally, the research explored the capacity to generate risk mitigation strategies in to two analysis configurations: when available data and simulation capacity are abundant, and when they are sparse or incomplete. The first configuration leverages structured filtration of Monte Carlo simulation results. The allocation of design and technology risk is then identified on the Pareto Frontier. The second configuration identifies the direction of robust risk mitigation based on the available data and limited simulation ability. It leverages a linearized approximation of the cashflow metrics and identifies the direction of allocation using the Jacobian matrix and its inversion.

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Kincová, Daniela. "Zavedení a provoz supersonického business jetu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232021.

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Tato práce se zabývá problematikou zavedení a provozu nadzvukových business jetů. V dnešní době se v civilní letecké přepravě, po ukončení provozu Concordu, žádná nadzvuková letadla nevyskytují. V dnešní době existuje mnoho projektů a organizací, které se zabývají znovuzavedením nadzvukových letounů do civilního letectví a soustředí se převážně na business jety. Hlavní otázkou je, zda je vůbec vhodné, či rozumné se k tomu typu dopravy znovu vracet. Existuje hodně problémů, které toto komplikují. Tyto letouny způsobují příliš velký hluk, mají obrovskou spotřebu paliva a musí řešit nadměrné emise, létají ve vysokých výškách ve kterých může docházet k problémům s přetlakováním kabiny, navigací, radioaktivním zářením apod. Navíc zákaz supersonických letů nad pevninou letové cesty omezuje a prodlužuje. Současně vznikající projekty navíc nedosahují tak velkého doletu jako klasické moderní bussjety, což způsobuje, že se nadzvukové business jety se na delších tratích stávají neefektivní. I přes tyto problémy, je víceméně jisté, že k zavedení nadzvukových business jetů dojde během následujících 10 - 15 let, i kdyby to měla být jen otázka jisté prestiže velmi bohatých lidí.

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Books on the topic "Supersonic aircraft design"

1

Ramakrishnan, Sekaripuram. Supersonic flow computations for an ASTOVL aircraft configuration. Hampton, Va: Langley Research Center, 1990.

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2

Boles, Michael A. Theoretical evaluation of engine auxiliary inlet design for supersonic V/STOL aircraft. Raleigh, N.C: Dept. of Mechanical and Aerospace Engineering, North Carolina State University, 1988.

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Boles, Michael A. Theoretical evaluation of engine auxiliary inlet design for supersonic V/STOL aircraft. Raleigh, N.C: North Carolina State University, 1991.

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Keidel, Paul. The horizon: A blended wing aircraft configuration design project : NASA/USRA advanced design program, final report 1987-1988. Pomona, Calif: California State Polytechnic University Pomona, Aerospace Engineering Dept., 1988.

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5

Fluid dynamics research on supersonic aircraft =: Les travaux de recherche en dynamique des fluides relatifs aux aéronefs supersoniques. [Neuilly-sur-Seine Cedex, France: North Atlantic Treaty Organization, Research and Technology Organization, 1998.

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Baysal, Oktay. Aerodynamic shape optimization directed toward a supersonic transport using sensitivity analysis: Final report for the period ended August 15, 1995. Norfolk, Va: Dept. of Aerospace Engineering, College of Engineering & Technology, Old Dominion University, 1995.

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Ardema, Mark D. Development of advanced methods of structural and trajectory analysis for transport aircraft: Annual report : October 1, 1995 - September 30, 1996. Santa Clara, CA: Santa Clara University, 1996.

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Torenbeek, Egbert. Essentials of Supersonic Commercial Aircraft Conceptual Design. Wiley & Sons, Incorporated, John, 2020.

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Essentials of Supersonic Commercial Aircraft Conceptual Design. Wiley & Sons, Limited, John, 2020.

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Torenbeek, Egbert. Essentials of Supersonic Commercial Aircraft Conceptual Design. Wiley & Sons, Limited, John, 2020.

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Book chapters on the topic "Supersonic aircraft design"

1

Velden, A. "Supersonic Aircraft Shape Optimization." In New Design Concepts for High Speed Air Transport, 237–50. Vienna: Springer Vienna, 1997. http://dx.doi.org/10.1007/978-3-7091-2658-5_16.

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Zhang, Yidian, Jiangtao Huang, and Zhenghong Gao. "Low Boom Supersonic Aircraft Configuration Optimization Using Inverse Design Method." In Lecture Notes in Electrical Engineering, 1023–41. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_82.

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Seubert, Rainer. "The Preliminary Aircraft Design and Optimization Program for Supersonic Commercial Transport Aircraft PrADO-Sup." In Notes on Numerical Fluid Mechanics (NNFM), 311–18. Wiesbaden: Vieweg+Teubner Verlag, 1997. http://dx.doi.org/10.1007/978-3-322-86573-1_40.

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Seubert, Rainer. "Validation of the Preliminary Aircraft Design and Optimization Program for Supersonic Commercial Transport Aircraft PrADO-Sup." In Notes on Numerical Fluid Mechanics (NNFM), 442–49. Wiesbaden: Vieweg+Teubner Verlag, 1999. http://dx.doi.org/10.1007/978-3-663-10901-3_57.

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Rajkumar, Karthick, Eike Tangermann, Markus Klein, Sebastian Ketterl, and Andreas Winkler. "DES of Weapon Bay in Fighter Aircraft Under High-Subsonic and Supersonic Conditions." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 656–65. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79561-0_62.

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Liu, Jianhui, Lansong Wang, Mingang Zhang, Xiaoli Qin, and Yajie Ge. "Boost and Ascent Trajectory Design and Guidance Approach for Rocket Launched Supersonic Aircraft." In Lecture Notes in Electrical Engineering, 549–57. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-32-9698-5_61.

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Herrmann, U. "Numerical Design of a Low-Noise High-Lift System for a Supersonic Aircraft." In New Results in Numerical and Experimental Fluid Mechanics V, 120–27. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/978-3-540-33287-9_15.

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Behera, Soumyajit, C. Muthuraj, Balmiki Kumar, U. R. Srikanth, Sathish Sunnam, and R. Jolly. "Design of Vortex Flaps for Reducing Approach Speed of a Supersonic Naval Fighter Aircraft." In Lecture Notes in Mechanical Engineering, 109–17. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5432-2_9.

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"Three-Dimensional Viscous Design Methodology of Supersonic Inlet Systems for Advanced Technology Aircraft." In Numerical Methods for Engine-Airframe Integration, 431–80. New York: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/5.9781600865763.0431.0480.

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"Materials Selection in Design of Structures of Subsonic and Supersonic Aircrafts." In Frontiers in Aerospace Science, edited by Zainul Huda, 442–67. BENTHAM SCIENCE PUBLISHERS, 2016. http://dx.doi.org/10.2174/9781681083056116010013.

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Conference papers on the topic "Supersonic aircraft design"

1

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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Long, B. "The Navy Seadart supersonic seaplane." In Aircraft Design, Systems, and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3941.

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NELSON, B. "Design scope for student supersonic projects." In Aircraft Systems, Design and Technology Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-2638.

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Schuermann, Martin, Peter Horst, and Michele Gaffuri. "Extensions to aircraft pre-design for supersonic aircraft." In 52nd Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-0184.

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HAJELA, P., and R. GLOWASKY. "Application of piezoelectric elements in supersonic panel flutter suppression." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3191.

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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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BARNHART, PAUL. "A supersonic through-flow fan engine airframe integration study." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2140.

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BARATECH, MANUEL, JUAN CEVA, JENNIFER CHAKLOS, JOSE MARTINEZ, JOSEPH WINKELMANN, and K. RAVINDRA. "Preliminary design of a ramjet powered supersonic anti-ship missile." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3127.

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HARRIS, JR., ROY. "On the threshold - The outlook for supersonic and hypersonic aircraft." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2071.

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JOHNSON, V. "A computer-assisted process for supersonic aircraft conceptual design." In Aircraft Design Systems and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-4027.

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Reports on the topic "Supersonic aircraft design"

1

Dehua, Liu, and Huang Changyou. Computational Method in Optimal Bending-Twisting Comprehensive Design of Wings of Subsonic and Supersonic Aircraft. Fort Belvoir, VA: Defense Technical Information Center, February 1993. http://dx.doi.org/10.21236/ada262374.

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