Journal articles: 'Supersonic aircraft design'

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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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Chudoba, B., G. Coleman, P. A. Czysz, and C. M. Butler. "Feasibility study of a supersonic business jet based on the Learjet airframe." Aeronautical Journal 113, no. 1146 (August 2009): 517–31. http://dx.doi.org/10.1017/s0001924000003171.

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Abstract Since the dawn of the jet age, passengers on all jet transports, except Concorde, have traveled at about the same speed — a standard Mach 0 83-0 87 range as a practical compromise. After 27 years of supersonic commercial travel, British Airways and Air France retired their fleet of Concorde aircraft at the end of 2003 because it was considered no longer profitable. Clearly, with the retirement of Concorde, the world has lost the only aircraft offering passenger transportation at supersonic speeds. Over the past several years manufacturers have proposed new aircraft designs that promise an increase in transportation speeds. In particular, the business jet market appears to present a business case for an exclusive supersonic business jet (SSBJ). However, there is a key-hurdle which has, until now, prevented the successful launch of a SSBJ hardware program: the development cost for an all-new aircraft quickly eradicates the soughtafter business case. This paper presents the results of a parametric sizing study which aims to answer the following question: is it possible to drastically reduce the development effort of a supersonic business jet design by converting an existing Learjet airframe into a supersonic vehicle while sustaining FAA interest and approval? This paper discusses selected aircraft sizing trades and operations related constraints. The feasibility study indicates some level of technical plausibility for the case of converting an existing airframe into a certifiable lower-cost supersonic aircraft. Acknowledging the range of actual complications related to the task of economically modifying and certifying a legacy airframe towards a SSBJ, it appears that a larger size SSBJ offers significant technical and economical advantages which outweigh the ‘off-the-shelf’ Learjet case.

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van der Velden, Alexander J. M., and Egbert Torenbeek. "Design of a small supersonic oblique-wing transport aircraft." Journal of Aircraft 26, no. 3 (March 1989): 193–97. http://dx.doi.org/10.2514/3.45745.

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Dovi, A. R., G. A. Wrenn, J. F. M. Barthelemy, P. G. Coen, and L. E. Hall. "Multidisciplinary design integration methodology for a supersonic transport aircraft." Journal of Aircraft 32, no. 2 (March 1995): 290–96. http://dx.doi.org/10.2514/3.46715.

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NINOMIYA, Tetsujiro, Hirokazu SUZUKI, and Jun’ichiro KAWAGUCHI. "Dynamic Inversion Controller Design for Balloon-Launched Supersonic Aircraft." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 61, no. 6 (2018): 248–57. http://dx.doi.org/10.2322/tjsass.61.248.

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Tang, Hong, Guo Guang Chen, and Hui Zhu He. "An Aero-Thermo-Elasticity Method Applied on the Supersonic Aircraft Model." Applied Mechanics and Materials 215-216 (November 2012): 438–42. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.438.

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Coupling between the vibration frequencies and the unsteady aerodynamic will reduce the flutter speed and ride quality through the aerodynamic heat transfer. As the flight speed improved, the aeroelastic analysis has become an essential means of aircraft design. The method of aero-thermo-elastic (ATE) analysis is coupled with aircraft aeroelastic analysis and thermal deformation, and is more realistic reflection of the actual flight of the aircraft. In this paper, an ATE analysis of aircraft adopted by computational fluid dynamics/computational structural dynamics (CFD/CSD) methods, and compared with the traditional analysis, to provide analytical tools for the supersonic aircraft design.

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Lewis, W. J. "Propulsion Systems for Supersonic V/STOL Aircraft." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 206–11. http://dx.doi.org/10.1115/1.2906163.

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A number of different powerplant systems have been and are being considered for supersonic V/STOL aircraft. Some of the main features of these different powerplants are described. As a result of studying the results of operation of successful and unsuccessful V/STOL aircraft in the powered lift condition, a number of real requirements for practical and flexible operation can be identified. These requirements may have a profound impact on the design and configuration of the powered lift powerplant. Some of these are discussed and conclusions reached.

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Jenista, J. E., and D. S. Bodden. "Configuration E-7 Supersonic Fighter/Attack Technology Program." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 212–16. http://dx.doi.org/10.1115/1.2906164.

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The program covering the design and early technology development of Configuration E-7, a supersonic STOVL Fighter/Attack aircraft, is described. This aircraft uses the ejector principle to augment engine fan air for vertical lift. The initial design objectives selected in 1980 are listed and discussed. Some design considerations applicable to the propulsion concept and the chosen configuration are mentioned. The test program accomplished thus far, including wind tunnel models plus other test articles and activities, is outlined. The program has proceeded without major technological obstacles and a full-scale engine-powered model will soon be ready for testing.

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Steer, A. J. "Design criteria for conceptual sizing of primary flight controls." Aeronautical Journal 108, no. 1090 (December 2004): 629–41. http://dx.doi.org/10.1017/s0001924000000464.

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Abstract The European Supersonic Commercial Transport’s control surface configuration is based largely on Concorde’s and has been scaled to provide comparable un-augmented stability and manoeuvre performance. Hence, optimising the surface size could provide significant performance benefits in terms of reduced drag, noise, structural and actuator power requirements. Adequate control power will be required to meet current civil aviation regulations whose primary aim is to ensure the aircraft can be flown safely during both normal and emergency operation. Additional design criteria, combined with the optimum longitudinal control laws, are required to ensure desirable handling qualities with minimum pilot workload. Two critical low-speed flight conditions, normal and emergency, together with associated aircraft configurations for control surface sizing have been identified. The rudder must provide sufficient control power to achieve positive heading changes subsequent to a double asymmetric engine failure during normal operation. The fin should be sized to satisfy Dutch roll stability criteria with the un-augmented aircraft in its emergency configuration. The dual functionality of the elevons require that they are sized using both pitch and roll performance and handling quality criteria. The bank angle capture requirement provides the most critical elevon design case, the satisfaction of which also ensures adequate pitch control power. Validation using ‘pilot-in-the-loop’ simulation will be required whilst more explicit control surface size optimisation would require the definition of limiting airspeeds and operating conditions applicable to the European Supersonic Commercial Transport. Additional studies of control power requirements during transonic and supersonic cruise may also be required.

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Rallabhandi, Sriram K., and Dimitri N. Mavris. "Simultaneous Airframe and Propulsion Cycle Optimization for Supersonic Aircraft Design." Journal of Aircraft 45, no. 1 (January 2008): 38–55. http://dx.doi.org/10.2514/1.33183.

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Li, Wu, Elwood Shields, and Karl Geiselhart. "Mixed-Fidelity Approach for Design of Low-Boom Supersonic Aircraft." Journal of Aircraft 48, no. 4 (July 2011): 1131–35. http://dx.doi.org/10.2514/1.c000228.

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Morris, Craig C., Darcy L. Allison, Joseph A. Schetz, Rakesh K. Kapania, and Cornel Sultan. "Parametric Geometry Model for Design Studies of Tailless Supersonic Aircraft." Journal of Aircraft 51, no. 5 (September 2014): 1455–66. http://dx.doi.org/10.2514/1.c032340.

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Feng, Xiaoqiang, Zhanke Li, and Bifeng Song. "Research of low boom and low drag supersonic aircraft design." Chinese Journal of Aeronautics 27, no. 3 (June 2014): 531–41. http://dx.doi.org/10.1016/j.cja.2014.04.004.

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Herrmann, U. "EPISTLE: High lift system design for low-noise applied to a supersonic aircraft." Aeronautical Journal 110, no. 1107 (May 2006): 327–31. http://dx.doi.org/10.1017/s0001924000013191.

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Abstract A new approach for low-drag high-lift system design based on the application of viscous flow solvers was developed in the EC research project EPISTLE. Two high-lift systems for a supersonic commercial transport aircraft (SCT) wing were designed, manufactured and wind-tunnel tested. The predicted large drag reductions were fully confirmed by tests at high Reynolds numbers. These drag reductions significantly reduce the low-speed noise of future SCT configurations. This was estimated by preliminary aircraft design tools. Low-speed noise reduction by aerodynamic means is obtained, as effective high-lift systems enable these aircraft to climb faster.

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Long, Hao, and Yi-Nung Chung. "Design of the Nonlinear Structure Adaptive Model Inversion Flight Control System." Journal of Robotics and Mechatronics 28, no. 6 (December 20, 2016): 928–35. http://dx.doi.org/10.20965/jrm.2016.p0928.

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[abstFig src='/00280006/17.jpg' width='300' text='Design of the nonlinear SAMI flight control system' ] The advanced aircraft has those technological characteristics: stealth, supersonic cruise, super maneuverability, multi-target attack, multi-role, high load, long range cruise, integrated avionics, short takeoffs and vertical landings. These characteristics need multi-subsystem integration in the advanced aircraft. In order to meet the need of advance aircraft, the nonlinear control system is necessary. In this paper, the nonlinear structure adaptive model inversion system was first used for the nonlinear control problem of super-maneuver aircraft. The sufficient and necessary condition of the control law was analyzed. Finally the results of the height-angle maneuver simulation show that the designed control system has good performance.

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Li, Wu, and Karl Geiselhart. "Multidisciplinary Design Optimization of Low-Boom Supersonic Aircraft with Mission Constraints." AIAA Journal 59, no. 1 (January 2021): 165–79. http://dx.doi.org/10.2514/1.j059237.

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Coen, Peter, and David Richwine. "Status and plans for NASA’s Quiet SuperSonic Technology (QueSST) aircraft design." Journal of the Acoustical Society of America 141, no. 5 (May 2017): 3461. http://dx.doi.org/10.1121/1.4987181.

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Crichton, Daniel, Liping Xu, and Cesare A. Hall. "Preliminary Fan Design for a Silent Aircraft." Journal of Turbomachinery 129, no. 1 (February 1, 2006): 184–91. http://dx.doi.org/10.1115/1.2372779.

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Preliminary fan design for a functionally silent aircraft has been performed with noise reduction as the primary goal. For such an aircraft the fan design must, in addition to delivering low cruise fuel burn, enable low jet and fan source noise during takeoff. This requires the fan to be operating at low pressure ratio and high efficiency during takeoff and, for conditions where the relative tip Mach number onto the fan is supersonic, ensuring the primary shock structure is ingested into the blade passage. To meet these requirements, flyover and cruise flow coefficients are matched using a variable area nozzle at the same time as delivering low takeoff FPR. This places the sideline operating point near the shoulder of the characteristic and fixes the top of climb and cruise fan pressure ratios. For a 4-engine, 250pax, 4000nm silent aircraft this approach leads to a top of climb FPR of 1.45, requiring a 39% increase in nozzle area at takeoff. A fan rotor has been designed for this cycle with 20 blades, low tip loading during takeoff, and a 350m∕s top of climb tip speed.

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Koff, B. L. "Aircraft Gas Turbine Emissions Challenge." Journal of Engineering for Gas Turbines and Power 116, no. 3 (July 1, 1994): 474–77. http://dx.doi.org/10.1115/1.2906845.

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The new generation of jet powered aircraft faces a significant challenge to reduce pollutant emissions while increasing fuel efficiency. Carbon monoxide (CO) and unburned hydrocarbon (HC) emissions are already very low and continued control of these pollutants is expected as engine temperatures and pressure ratios are increased. In contrast, significant system design improvements are needed to reduce oxides of nitrogen (NOx) emissions because of their harmful effect on the earth’s ozone layer. This paper discusses the prospects and technical approaches for significant NOx reductions in current and future subsonic and supersonic aircraft.

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Grewe, V., A. Stenke, M. Plohr, and V. D. Korovkin. "Climate functions for the use in multi-disciplinary optimisation in the pre-design of supersonic business jet." Aeronautical Journal 114, no. 1154 (April 2010): 259–69. http://dx.doi.org/10.1017/s0001924000003705.

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Abstract Mitigation of climate change is a challenge to science and society. Here, we establish a methodology, applicable in multi-disciplinary optimisation (MDO) during aircraft pre-design, allowing a minimisation of the aircraft’s potential climate impact. In this first step we consider supersonic aircraft flying at a cruise altitude between 45kfeet (~13·5km, 150hPa) and 67kfeet (~20·5km, 50hPa). The methodology is based on climate functions, which give a relationship between 4 parameters representing an aircraft/engine configuration and an expected impact on global mean near surface temperature as an indicator for the impact on climate via changes in the greenhouse gases carbon dioxide, water vapour, ozone and methane. These input parameters are cruise altitude pressure, fuel consumption, fuel flow and Mach number. The climate functions for water vapour and carbon dioxide are independent from the chosen engine, whereas the climate functions for ozone and methane depend on engine parameters describing the nitrogen oxide emissions. Ten engine configurations are taken into account, which were considered in the framework of the EU-project HISAC. An analysis of the reliability of the climate functions with respect to the simplified climate-chemistry model AirClim and a detailed analysis of the climate functions is given.

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Herrmann, U. "Multiple Discipline Optimization and Aerodynamic Off-Design Analysis of Supersonic Transport Aircraft." Journal of Aircraft 45, no. 5 (September 2008): 1474–80. http://dx.doi.org/10.2514/1.32673.

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Ordaz, Irian, and Wu Li. "Integration of Off-Track Sonic Boom Analysis for Supersonic Aircraft Conceptual Design." Journal of Aircraft 51, no. 1 (January 2014): 23–28. http://dx.doi.org/10.2514/1.c031511.

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Rallabhandi, Sriram K. "Application of Adjoint Methodology to Supersonic Aircraft Design Using Reversed Equivalent Areas." Journal of Aircraft 51, no. 6 (November 2014): 1873–82. http://dx.doi.org/10.2514/1.c032518.

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Li, Li, Junqiang Bai, Tongbiao Guo, Xiaolong He, and Ziyuan Fu. "Aerodynamic Design of the Supersonic Aircraft Wing-Shape and Wing-Twist Optimization." International Journal of Aeronautical and Space Sciences 19, no. 2 (June 2018): 340–53. http://dx.doi.org/10.1007/s42405-018-0046-y.

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Athani, V. V., and S. Agarwal. "Design of a robust controller for a supersonic aircraft using H∞ approach." Control Engineering Practice 2, no. 6 (December 1994): 1051–61. http://dx.doi.org/10.1016/0967-0661(94)91627-6.

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Latif, A., J. Masud, S. R. Sheikh, and K. Pervez. "Robust Design of an Aerodynamic Compensation Pitot-Static Tube for Supersonic Aircraft." Journal of Aircraft 44, no. 1 (January 2007): 163–69. http://dx.doi.org/10.2514/1.22775.

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Kaemming, T. "Integrated Vehicle Comparison of Turbo-Ramjet Engine and Pulsed Detonation Engine." Journal of Engineering for Gas Turbines and Power 125, no. 1 (December 27, 2002): 257–62. http://dx.doi.org/10.1115/1.1496116.

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The pulsed detonation engine (PDE) is a unique propulsion system that uses the pressure rise associated with detonations to efficiently provide thrust. A study was conducted under the direction of the NASA Langley Research Center to identify the flight applications that provide the greatest potential benefits when incorporating a PDE propulsion system. The study was conducted in three phases. The first two phases progressively screened a large matrix of possible applications down to three applications for a more in-depth, advanced design analysis. The three applications best suited to the PDE were (1) a supersonic tactical aircraft, (2) a supersonic strike missile, and (3) a hypersonic single-stage-to-orbit (SSTO) vehicle. The supersonic tactical aircraft is the focus of this paper. The supersonic, tactical aircraft is envisioned as a Mach 3.5 high-altitude reconnaissance aircraft with possible strike capability. The high speed was selected based on the perceived high-speed fuel efficiency benefits of the PDE. Relative to a turbo-ramjet powered vehicle, the study identified an 11% to 21% takeoff gross weight (TOGW) benefit to the PDE on the baseline 700 n.mi. radius mission depending on the assumptions used for PDE performance and mission requirements. The TOGW benefits predicted were a result of the PDE lower cruise specific fuel consumption (SFC) and lower vehicle supersonic drag. The lower vehicle drag resulted from better aft vehicle shaping, which was a result of better distribution of the PDE cross-sectional area. The reduction in TOGW and fuel usage produced an estimated 4% reduction in life cycle cost for the PDE vehicle. The study also showed that the simplicity of the PDE enables concurrent engineering development of the vehicle and engine.

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Nuckolls, W. E., and W. F. Ng. "Fan Noise Reduction From a Supersonic Inlet During Simulated Aircraft Approach." Journal of Engineering for Gas Turbines and Power 117, no. 2 (April 1, 1995): 237–44. http://dx.doi.org/10.1115/1.2814086.

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A series of experiments was conducted to investigate the radiation of fan noise from a supersonic inlet during a simulated aircraft approach. A scaled-down model of an axisymmetric, mixed-compression, supersonic inlet (P-inlet) was used in conjunction with a 10.4 cm (4.1 in) diameter turbofan engine simulator as the noise source. The tests were conducted at an outdoor facility under static conditions. The main goal of the experiment was to reduce the forward radiating fan noise by modifying the auxiliary inlet doors. The modified doors are designed to reduce the inlet distortion to the fan face. In addition, the new door design also uses a converging flow passage in order to take advantage of the noise attenuation due to the choking effect at the auxiliary door. The simulator was tested at 60 percent design speed in an attempt to match the simulator noise source to that of a real aircraft engine on approach. Both aerodynamic and acoustic measurements were taken in the experiments. The results show that when compared to the original design, the modified auxiliary inlet doors reduced the circumferential inlet distortion to the fan face by a factor of two. The key result is that the blade passing frequency tone has been decreased by an average of 6 dB in the forward sector for the modified door design. Results from the closed auxiliary inlet door case are also presented to provide additional comparisons.

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Gong, Cheng, and Bao-Feng Ma. "Aerodynamic evaluation of an unmanned aerial vehicle with variable sweep and span." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 13 (March 19, 2019): 4980–97. http://dx.doi.org/10.1177/0954410019836907.

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Morphing aircraft can achieve optimum performances at multiple flight conditions through large geometry deformations. However, to obtain the optimum configurations, optimization design studies are required. A study on aerodynamic optimization of a morphing aircraft was conducted to obtain corresponding optimal configurations at various flight speeds. Firstly, an optimization framework being suitable to a morphing aircraft with larger deformations was established by integrating existing codes, in which aerodynamic forces for the optimization are calculated by an Euler-based solver and friction/form drag estimation code. The solver is based on a Cartesian method in which configurations are modeled in terms of components of aircraft, hence large deformations of morphing aircraft can be performed during the optimization. A surrogate-based model was employed for fitting aerodynamic forces, thus reducing computational cost in a global optimization. A generic morphing aircraft with variable sweep and span was investigated at subsonic, transonic, and supersonic conditions through the optimization process. The target of optimization is to obtain maximum lift-to-drag ratios subject to lift, trim, and static stability constrains at each flight condition. The movement of center-of-gravity of the aircraft was also considered in optimization. The results indicate that the center-of-gravity has an important effect on the optimum configurations obtained, and the aerodynamic performance will be enhanced significantly if the center-of-gravity is moved backward at transonic and supersonic cases. In the case of movable center-of-gravity, the optimum sweep angles increase with the increase in flight speeds, and the optimum spans at transonic and supersonic speeds are smaller than the subsonic case.

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Marinov, Assen. "Comparison of oblique shock wave angle in analytical and numerical solution." Aerospace Research in Bulgaria 31 (2019): 137–42. http://dx.doi.org/10.3897/arb.v31.e12.

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The drag of the subsonic aircraft is largely formed by the skin friction drag and lift-induced drag. At transonic flight occurs shock wave. Determination of shock wave angle is important part of design of every aircraft, which working in supersonic airflow regimes. Formation of shock waves cause formation the wave drag. The wave drag could account about 35% from total drag of aircraft. Shock wave angle is directly linked with the intensity of itself. This work compares shock wave angle calculations using analytical and numerical solving methods.

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Li, Zhanke, Yang Liu, Yulin Ding, Zhijin Lei, and Boping Ma. "Influence of Quiet Spike on Supersonic Transport for Low Boom Effect." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 37, no. 1 (February 2019): 203–10. http://dx.doi.org/10.1051/jnwpu/20193710203.

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One of the biggest technical challenges of supersonic flight is the mitigation of sonic boom. To deal with this problem, the Gulfstream Aerospace Corporation came up with the spike concept, and it showed to be efficient. However, there also remain several problems, the first one is that installing the spike makes it harder to balance for supersonic transport and the another one is that the movement equipment is complex. In this paper, a new concept by replacing the multi-stage of the normal spike with smooth transistion cones is proposed. The concept simultaneously uses the CFD solver HUNS3D based on the Reynolds average (RANS) equation and the far-field FL-BOOM sound explosion propagation program based on Thomas waveform parameter method. The effectiveness of the present scheme to suppress supersonic aircraft sound explosion is verified according to the concept. It is proved that the increased length is good for low blast and the main factor affecting the blast reduction effect of multistage mute cone is length rather than series by the analysis. The results have important reference value for the silent cone design of supersonic aircraft.

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Mo¨nig, R., W. Elmendorf, and H. E. Gallus. "Design and Rotor Performance of a 5:1 Mixed-Flow Supersonic Compressor." Journal of Turbomachinery 115, no. 3 (July 1, 1993): 565–72. http://dx.doi.org/10.1115/1.2929291.

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In consideration of further jet-engine developments required by applications for supersonic travel aircraft, airbreathing propulsion of space vehicles, or only the improvement of conventional high-performance turbo-engines, highly loaded supersonic compressors seem to meet the future demands. Particularly mixed-flow compressor stages with moderate supersonic rotor and stator inlet flow reveal the potential of high pressure rise and mass flow as well as favorable performance characteristics and efficiency. The first part of this paper presents analytical considerations for mixed-flow supersonic compressors with strong shock waves. This theoretical approach proves to be essential besides established design tools in order to ensure safe rotor and stage operation in accordance with the design objectives. In this context, the conditions for shock wave stabilization within a diagonal rotor passage are discussed in detail for design and off-design rotational speeds. The main part of this paper, however, presents the results and flow analysis obtained by extensive experimental investigations of the designed mixed-flow compressor rotor. The investigations were restricted to operation without stator in order to strictly separate rotor performance from rotor-stator interactions. The results reveal the design goals to be met in general. Mass flow, total pressure rise, and efficiency in particular show a good agreement with the design properties for near-surge operation at design and off-design conditions.

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Nangia, R. K. "‘Greener’ civil aviation using air-to-air refuelling – relating aircraft design efficiency and tanker offload efficiency." Aeronautical Journal 111, no. 1123 (September 2007): 589–92. http://dx.doi.org/10.1017/s0001924000001858.

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The aircraft industry, as a whole, is striving to limit its impact on the environment. Improved engine design and operation may offer a reduction in emissions of a few percent. More efficient air traffic control (ATC) may offer a limited reduction in overall fuel burn. Improvements in aerodynamic design and materials available (e.g. on A350XWB, B787) might achieve a few percent increases in efficiencies. The use of alternative fuels is some way off. The ACARE objectives present a stiff challenge. Our recent studies have shown that air-to-air-refuelling (AAR), well established in military circles, introduced to civil aircraft operations would provide fuel savings of the order of 30% – 40%. AAR will allow smaller (3,000nm range), more efficient (greener) aircraft, operating from shorter runways, to fulfil long-range route requirements. In addition, the ‘safety-net’ afforded by the availability of AAR will enable a host of hitherto borderline technologies to be accepted and utilised in future aircraft designs. Laminar flow will provide fuel savings and increased efficiency in its own right provided it is enabled within a civil AAR environment. Similarly, supersonic transport becomes an acceptable economic option.

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Schwabacher, Mark, and Andrew Gelsey. "Intelligent gradient-based search of incompletely defined design spaces." Artificial Intelligence for Engineering Design, Analysis and Manufacturing 11, no. 3 (June 1997): 199–210. http://dx.doi.org/10.1017/s0890060400003127.

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AbstractGradient-based numerical optimization of complex engineering designs offers the promise of rapidly producing better designs. However, such methods generally assume that the objective function and constraint functions are continuous, smooth, and defined everywhere. Unfortunately, realistic simulators tend to violate these assumptions. We present a rule-based technique for intelligently computing gradients in the presence of such pathologies in the simulators, and show how this gradient computation method can be used as part of a gradient-based numerical optimization system. We tested the resulting system in the domain of conceptual design of supersonic transport aircraft, and found that using rule-based gradients can decrease the cost of design space search by one or more orders of magnitude.

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Kazula, Stefan, Mark Wöllner, and Klaus Höschler. "Identification of efficient geometries for variable pitot inlets for supersonic transport." Aircraft Engineering and Aerospace Technology 92, no. 7 (June 1, 2020): 981–92. http://dx.doi.org/10.1108/aeat-11-2019-0228.

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Purpose This paper aims to reveal the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation. Design/methodology/approach The trade-off in inlet design and aerodynamic evaluation parameters is presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced. Findings The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to Mach 1.6 are identified. Although entailing additional weight, the inlet length represents the parameter with the highest potential for drag reduction by up to 50% in the selected design space. Ideal geometries for variable pitot inlets are determined. After considering weight, their potential range benefit nearly disappears for subsonic applications, but remains above 20% for supersonic flight at Mach 1.6. Originality/value Hence, the technology of circular variable pitot inlets for supersonic transport aircraft could be a way to achieve the ambitious ecological, safety and economic goals for future civil aviation.

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Smith, H. "A review of supersonic business jet design Issues." Aeronautical Journal 111, no. 1126 (December 2007): 761–76. http://dx.doi.org/10.1017/s0001924000001883.

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Abstract Key issues relating to the Supersonic Business Jet (SBJ) concept are reviewed with the intent to assess the readiness of enabling technologies and hence the concept itself. The multidisciplinary nature of aircraft design precludes an in-depth analysis of each specific aspect, which could individually be the subject of a separate discipline review, hence an overview is presented. The review looks at the market, environmental issues, with particular reference to the sonic boom phenomenon & solutions, technological issues, including prediction methods, flight testing, systems, certification and interested aerospace companies and design organisations. It is apparent that the need to reduce the sonic boom signature is vital if the vehicle is to be permitted to operate over land and hence be economically viable. It is clear that sonic boom acceptability requirements must be set if resources are to be effectively focused and designs are to converge. Despite this challenge, considerable investment is aimed at de-risking many of the enabling technologies and raising readiness levels. Many technologies are moving beyond theoretical and numerical analysis into the experimental and flight test domains. Collaboration between the civil and military sectors is increasing. Clearly, supersonic air travel is not an efficient means of personal conveyance; however, concerns for the environment are difficult to balance against the ‘value of time’ benefits offered by the SBJ concept. Air travel, of which this is a specialised form, is important to the global economy. Continued effort in the areas of human factors, customer demand and certification & requirements would be beneficial.

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Нартова, Лидия, Lidiya Nartova, Валерий Бодрышев, and Valeriy Bodryshev. "ENGINEERING SURFACE GEOMETRICAL MODELING OF CHOSEN CLASSES." Bulletin of Bryansk state technical university 2018, no. 8 (October 25, 2018): 4–13. http://dx.doi.org/10.30987/article_5bb5e68582adf3.47757069.

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In the work there is offered a generalized method for complex surface geometrical modeling with regard to a wide class of problems with an engineering direction. This method is based on the investigation of the applicability of frame, surface or solid-state models. The investigations were based on the analysis of the practical application of frame, surface and solidstate models and their images on the basis of presentday software tools. By the example of deciphering a problem of a cylindrical object flow with a gas supersonic flow according to an intensity parameter of a frame image the 3D image of the “image intensity” function with the use of MatLab and SolidWorks programs is formed. The results of a geometrical solution are compared and an optimum surface image is chosen. The investigation for a specific version provides a visualization of a supersonic gas flow motion and finally offers recommendations for an optimum design of a product. The method described may be used in the course of designing objects having a gas or liquid flow, complex surfaces in the products of aircraft industry. It is approbated at lecturing subjects “Engineering and Computer Graphics”, “Descriptive Geometry”, and also in scientific and diploma works of students with specialties “Aircraft and Helicopter Manufacturing”, “Aircraft Engines”, “Computer design in Aircraft Manufacturing”.

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MARX, WILLIAM J., DIMITRI N. MAVRIS, and DANIEL P. SCHRAGE. "A knowledge-based system integrated with numerical analysis tools for aircraft life-cycle design." Artificial Intelligence for Engineering Design, Analysis and Manufacturing 12, no. 3 (June 1998): 211–29. http://dx.doi.org/10.1017/s0890060498123016.

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An integrated design and manufacturing approach allows economic decisions to be made that reflect an entire system design as a whole. To achieve this objective, we have developed and utilized integrated cost and engineering models within a focused design perspective. A framework for the integrated design of an aircraft system with a combined performance and economic perspective is described in this article. This framework is based on the concept of Design Justification using a Design-for-Economics approach. We have developed a knowledge-based system that can be used to evaluate aircraft structural concept material and process selections. The framework consists of the knowledge-based system, integrated with numerical analysis tools including an aircraft performance/sizing code and a life-cycle cost analysis code. Production cost estimates are applied for evaluation of process trades at the subcomponent level of design. Life-cycle cost estimates are used for evaluation of process trades at the system level. Results of a case study are presented for several advanced wing structural concepts for a future supersonic commercial transport aircraft. Cost versus performance studies indicate that a high-speed civil transport aircraft with a hybrid wing structural concept, though more expensive to manufacture than some homogeneous concepts, can have lower direct operating costs due to a lower take-off gross weight and less mission fuel required.

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Brinkworth, B. J. "On the aerodynamics of the Miles M.52 (E.24/43) – a historical perspective." Aeronautical Journal 114, no. 1153 (March 2010): 125–56. http://dx.doi.org/10.1017/s0001924000003602.

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AbstractThe aerodynamic design of the Miles M.52 experimental supersonic aircraft is reviewed relative to the state of knowledge at its time of 1943 – 1946. Drawing on widely-ranging material, much not previously published, this study enlarges upon, and in places amends, previous accounts of the project.Based on advice collated from the fields of aerodynamics and ballistics, Miles conceived an original and forward-looking design, backed by an extensive test programme. Novel solutions to new requirements in the areas of structures and systems provided a robust airframe, showing fair prospects of being stable and controllable throughout the specified flight envelope. An equally innovative power plant was devised for it by Whittle’s company, Power Jets Ltd.Contradictory predictions of its performance were made by Miles and the RAE, through differences in their estimations of fuselage drag. A new evaluation suggests that the available information would have shown the aircraft to be capable of providing vital aerodynamic data for the transonic and early supersonic regimes at a time when no other sources were available, though further engine development would be needed for it to reach its full potential.

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Krupa, G. P. "Application of Agile Model-Based Systems Engineering in aircraft conceptual design." Aeronautical Journal 123, no. 1268 (August 1, 2019): 1561–601. http://dx.doi.org/10.1017/aer.2019.53.

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ABSTRACTOne of the challenges of modern engineering design is the amount of data that designers must keep track while performing system analysis and synthesis. This task is particularly important in the design process of complex systems such as novel aerospace systems where Modeling and Simulation play an essential role. The Agile philosophy stems from the field of Software Engineering and describes an approach to development in which requirements and solutions gradually develop through collaboration between self-organising cross-functional teams and end users. Agile Model-Based System Engineering (AMBSE) is the application of the Agile philosophy to Model-Based System Engineering. In this paper, AMBSE is accomplished through the application of the Object-Oriented System Engineering Method (OOSEM). OOSEM employs a top-down scenario-driven process that adopts System Modeling Language (SysML) and leverages the object-oriented paradigm to support the analysis, specification, design, and verification of systems. AMBSE assisted by mathematical modelling and safety assessment techniques is applied to the first design iterations of the main aircraft systems, allowing a comprehensive design exploration. The flight control system was chosen to illustrate the procedure in detail, emphasising the synthesis of a six-degrees-of-freedom model augmented by dynamic inversion control for a hypothetical supersonic transport aircraft satisfying class II MIL-F-8785C handling qualities. It is concluded that AMBSE presents promising properties to support future aircraft development within the current regulatory framework for aircraft design, while enabling a smooth transition from conceptual to preliminary design.

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Mao, Yu-Feng, Yun-Ze Li, Ji-Xiang Wang, Kai Xiong, and Jia-Xin Li. "Cooling Ability/Capacity and Exergy Penalty Analysis of Each Heat Sink of Modern Supersonic Aircraft." Entropy 21, no. 3 (February 26, 2019): 223. http://dx.doi.org/10.3390/e21030223.

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The aerospace-based heat sink is defined as a substance used for dissipating heat generated by onboard heat loads. They are becoming increasingly scarce in the thermal management system (TMS) of advanced aircraft, especially for supersonic aircraft. In the modern aircraft there are many types of heat sinks whose cooling abilities and performance penalties are usually obviously different from each other. Besides, the cooling ability and performance penalty of a single heat sink is even different under different flight conditions—flight altitude, Mach number, etc. In this study, the typical heat sinks which are the fuel mass, ram air, engine fan air, skin heat exchanger, and expendable heat sink will be studied. Their cooling abilities/capacities, and exergy penalties under different flight conditions have been systematically estimated and compared with each other. The exergy penalty presented in this paper refers to the exergy loss of aircraft caused by the extra weight, drag and energy extraction of various heat sinks. The estimation models, as well as the results and discussion have been elaborated in this paper, which can be can be used to further optimize the TMS of modern advanced aircraft, for example, the layout design of various heat sinks and the improvement the control algorithm.

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Journal articles on the topic 'Supersonic aircraft design'

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