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Journal articles on the topic 'Hypersonic aircraft design'

Author: Grafiati

Published: 14 March 2023

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1

Alkaya, Can, Ashish Alex Sam, and Apostolos Pesyridis. "Conceptual Advanced Transport Aircraft Design Configuration for Sustained Hypersonic Flight." Aerospace 5, no. 3 (2018): 91. http://dx.doi.org/10.3390/aerospace5030091.

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The conceptual aircraft design and its integration with a combined cycle engine for hypersonic cruise at Mach 8 is documented in this paper. The paper describes the process taken to develop a hypersonic aircraft from a conceptual approach. The discussion also includes the design and CFD analysis of the integrated combined cycle engine. A final conceptual hypersonic transport aircraft with an integrated combined cycle engine was achieved through this study. According to the analysis carried out, the aircraft is able to take-off and land at the airports it is intended to be used and will be able

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2

Dai, Yalin, Yu Wang, Xiaoyu Xu, and Xiongqing Yu. "An Improved Method for Initial Sizing of Airbreathing Hypersonic Aircraft." Aerospace 10, no. 2 (2023): 199. http://dx.doi.org/10.3390/aerospace10020199.

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One essential problem in aircraft conceptual design is initial sizing in which the aircraft primary parameters such as weight, size, and thrust are estimated for given design requirements. The airbreathing hypersonic aircraft is a type of novel aircraft and has significant differences from conventional aircraft in terms of its flight speed and propulsion system. Traditional initial sizing methods are not suitable for this type of novel aircraft. This paper presents an improved initial sizing method for the conceptual design of airbreathing hypersonic aircraft. An illustrative airbreathing hype

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3

Koptev, A. ""THEORETICAL ASPECTS OF STRENGTH AND THERMAL CONTROL OF HYPERSONIC AIRCRAFT"." National Association of Scientists 1, no. 66 (2021): 54–60. http://dx.doi.org/10.31618/nas.2413-5291.2021.1.66.403.

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This article analyzes the theoretical aspects of controlling the strength and thermal modes of hypersonic aircraft. The conditions for the functioning of hypersonic aircraft were also investigated, and problematic situations for their design were identified.  The parameters of aerodynamic heating of surfaces and heating of thermal protection of hypersonic aircraft were estimated with an assessment of the parameters of thermal protection of hypersonic aircraft and the magnitude of the heat flux supplied to the surface, with the determination of the parameters of their thermal protection,

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4

Chen, Jie, Yan Lin, and Chang Peng Pan. "Hypersonic Aircraft Nonlinear Fault-Tolerant Controller Design." Applied Mechanics and Materials 494-495 (February 2014): 1056–59. http://dx.doi.org/10.4028/www.scientific.net/amm.494-495.1056.

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One hypersonic aircraft nonlinear observer and controller are designed synthetically to solve the part of actuator failure problem. The research model is developed based on a SISO output feedback nonlinear unobservered minimum phase system. filter is adopted to reconstruct state vectors, adaptive control law is designed to guarantee the system boundedness. Dynamic surface control is employed strategy to eliminate the explosion of terms by introducing a series of first order filters to obtain the differentiation of the virtual control inputs. Both theory analysis and simulation verification sho

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5

Morrell, Benjamin J., David J. Munk, Gareth A. Vio, and Dries Verstraete. "Development of a Hypersonic Aircraft Design Optimization Tool." Applied Mechanics and Materials 553 (May 2014): 847–52. http://dx.doi.org/10.4028/www.scientific.net/amm.553.847.

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The design and optimization of hypersonic aircraft is severely impacted by the high temperatures encountered during flight as they can lead to high thermal stresses and a significant reduction in material strength and stiffness. This reduction in rigidity of the structure requires innovative structural concepts and a stronger focus on aeroelastic deformations in the early design and optimisation of the aircraft structure. This imposes the need for a closer coupling of the aerodynamic and structural design tools than is current practice. The paper presents the development of a multi-disciplinar

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6

Wang, Zhiqiang, Anjing Zhang, Jia Pan, Weiguo Lu, and Yubiao Sun. "Fluid-Thermal Interaction Simulation of a Hypersonic Aircraft Optical Dome." Energies 15, no. 22 (2022): 8619. http://dx.doi.org/10.3390/en15228619.

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Hypersonic aircraft design is an enabling technology. However, many problems are encountered, including the design of the hood. The aircraft optical dome can become heated due to aerodynamic effects. Since the optical dome of a hypersonic aircraft should satisfy optical imaging requirements, a conventional ablative coating cannot be adopted. The aerodynamic heating characteristics during the whole flight must be studied. In this study, a numerical simulation method for the aerodynamic heat of hypersonic aircraft under long-term variable working conditions is proposed. In addition, the numerica

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Yang, Jie, Song Ping Wu, and Wen Xin Hou. "A Method for Aerodynamic Characteristic Analysis of Hypersonic Aircraft Based on Response Surface Model." Applied Mechanics and Materials 477-478 (December 2013): 277–80. http://dx.doi.org/10.4028/www.scientific.net/amm.477-478.277.

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Aerodynamic characteristic analysis of hypersonic cruise aircraft is more difficult than that of conventional aircraft, for the complex flow field simulation and inadequate amount of results under limited flight conditions. In this paper, numerical schemes applicable for hypersonic flow field are adopted to acquire a set of aerodynamic characteristics of a typical hypersonic cruise aircraft as sample data, based on which response surface models (RSM) are constructed to provide approximation of aerodynamic characteristics under any flight conditions within the design domain, finally the overall

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8

Wang, Yuhui, Peng Shao, Qingxian Wu, and Mou Chen. "Reliability analysis for a hypersonic aircraft’s wing spar." Aircraft Engineering and Aerospace Technology 91, no. 4 (2019): 549–57. http://dx.doi.org/10.1108/aeat-11-2017-0242.

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Purpose This paper aims to present a novel structural reliability analysis scheme with considering the structural strength degradation for the wing spar of a generic hypersonic aircraft to guarantee flight safety and structural reliability. Design/methodology/approach A logarithmic model with strength degradation for the wing spar is constructed, and a reliability model of the wing spar is established based on stress-strength interference theory and total probability theorem. Findings It is demonstrated that the proposed reliability analysis scheme can obtain more accurate structural reliabili

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9

Castigliola, Luca, Flavia Causa, and Michele Grassi. "Navigation architecture for hypersonic aircraft." MATEC Web of Conferences 304 (2019): 04008. http://dx.doi.org/10.1051/matecconf/201930404008.

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This paper aims at presenting an integrated navigation algorithm designed for estimating the navigation state of the STRATOFLY vehicle (LAPCAT–MR3). STRATOFLY project has been funded by the European Commission, under the framework of Horizon 2020 plan, with the aim of assessing the potential of high–speed transport vehicle. The complex interaction between elements of an air-breathing hypersonic vehicle represents a new paradigm in aircraft design. In particular, one of the needs for early GNC analysis in the case of LAPCAT–MR3 vehicle is the assessment of navigation performance over the refere

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10

Jiao, Xin, and Ju Jiang. "Design of adaptive switching control for hypersonic aircraft." Advances in Mechanical Engineering 7, no. 10 (2015): 168781401561046. http://dx.doi.org/10.1177/1687814015610465.

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11

Munk, David J., Gareth A. Vio, and Dries Verstraete. "A Hypersonic Aircraft Optimization Tool with Strong Aerothermoelastic Coupling." Applied Mechanics and Materials 846 (July 2016): 494–99. http://dx.doi.org/10.4028/www.scientific.net/amm.846.494.

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The design and optimization of hypersonic aircraft is severely impacted by the high temperatures encountered during flight as they can lead to high thermal stresses and a significant reduction in material strength and stiffness. This reduction in rigidity of the structure requires innovative structural concepts and a stronger focus on aerothermoelastic deformations in the early design and optimization phase of the design cycle. This imposes the need for a closer coupling of the aerodynamic, thermal and structural design tools than is currently in practice. The paper presents a multi-disciplina

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12

Ridgway, Andrew, Ashish Sam, and Apostolos Pesyridis. "Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies." Energies 11, no. 12 (2018): 3449. http://dx.doi.org/10.3390/en11123449.

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This paper aims to contribute to developing a potential combined cycle air-breathing engine integrated into an aircraft design, capable of performing flight profiles on a commercial scale. This study specifically focuses on the single expansion ramp nozzle (SERN) and aircraft-engine integration with an emphasis on the combined cycle engine integration into the conceptual aircraft design. A parametric study using computational fluid dynamics (CFD) have been employed to analyze the sensitivity of the SERN’s performance parameters with changing geometry and operating conditions. The SERN adapted

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13

Marrison, Christopher I., and Robert F. Stengel. "Design of Robust Control Systems for a Hypersonic Aircraft." Journal of Guidance, Control, and Dynamics 21, no. 1 (1998): 58–63. http://dx.doi.org/10.2514/2.4197.

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14

Haley, J. G., T. P. McCall, I. W. Maynard, and B. Chudoba. "A sizing-based approach to evaluate hypersonic demonstrators: demonstrator-carrier constraints." Aeronautical Journal 124, no. 1279 (2020): 1318–49. http://dx.doi.org/10.1017/aer.2020.30.

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ABSTRACTThe objective of this study is to identify, evaluate, and provide recommendations towards the realisation of near-term hypersonic flight hardware through the consideration of carrier vehicle constraints. The current rush of available funds for hypersonic research cannot cause a program to ignore growth potential for future missions. The prior NB-52 carrier vehicles, famous for the X-15 and X-43A missions, are retired. Next generation hypersonic demonstrator requirements will necessitate a substitution of carrier vehicle capability. Flight vehicle configuration, technology requirements,

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Giannelis, Nicholas F., Gareth A. Vio, Dries Verstraete, and Johan Steelant. "Temperature Effect on the Structural Design of a Mach 8 Vehicle." Applied Mechanics and Materials 553 (May 2014): 249–54. http://dx.doi.org/10.4028/www.scientific.net/amm.553.249.

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Hypersonic aircraft design is a pressing area of research. The motivation to create aircraft that can cross the globe in only a few hours is driving this forward but there are a number of challenges that need to be overcome. One of the principle challenges is the effect that temperature has on the structure. Temperature changes cause heating of the structure as well as changing the material properties of the affected structure. This has a compound effect in that the structures gets geometrically deformed, stiffness is reduced, and this will have an impact on the aerodynamic and structural perf

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16

Blankson, I. M. "Air-Breathing Hypersonic Cruise: Prospects for Mach 4–7 Waverider Aircraft." Journal of Engineering for Gas Turbines and Power 116, no. 1 (1994): 104–15. http://dx.doi.org/10.1115/1.2906779.

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There is currently a renewal of world-wide interest in hypersonic flight. Vehicle concepts being considered range from cruise missiles to SSTO and TSTO vehicles. The new characteristics of these vehicles are that they will be powered by air-breathing engines and have long residence times in the air-breathing corridor. In the Mach 4–7 regime, waverider aircraft are being considered as candidates for both long-range and short-range cruise missions, as hypersonic missiles, and as high-L/D highly maneuverable vehicles. This paper will discuss the potential for near-term and far-term application of

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17

Zellner, B., W. Sterr, and O. Herrmann. "Integration of Turbo-Expander and Turbo-Ramjet Engines in Hypersonic Vehicles." Journal of Engineering for Gas Turbines and Power 116, no. 1 (1994): 90–97. http://dx.doi.org/10.1115/1.2906815.

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Turbo-expander-ramjet and turbo-ramjet are two engine concepts considered for hypersonic aircraft designs with a flight regime between Mach 0 and 7. To establish any performance or integration aspects for these two combined-cycle engine types, an extended study of a variety of influence parameters is necessary, because the interaction between aircraft and propulsion system is even stronger than on conventional aircraft. In fact, the propulsion system is very sensitive to intake and nozzle/afterbody design at these high speeds. This paper presents the engine configurations chosen for comparison

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18

Gainutdinov, V. G. "Computer-aided design analysis of hypersonic aircraft air intake geometry." Russian Aeronautics (Iz VUZ) 56, no. 3 (2013): 274–79. http://dx.doi.org/10.3103/s1068799813030094.

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19

Vu, Phuong, and Daniel J. Biezad. "Direct-lift design strategy for longitudinal control of hypersonic aircraft." Journal of Guidance, Control, and Dynamics 17, no. 6 (1994): 1260–66. http://dx.doi.org/10.2514/3.21342.

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20

MATSUNO, Yoshinori, Takeshi TSUCHIYA, Shunsuke IMAMURA, and Hideyuki TAGUCHI. "Multidisciplinary Design Optimization of Long or Short Range Hypersonic Aircraft." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 57, no. 3 (2014): 143–52. http://dx.doi.org/10.2322/tjsass.57.143.

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21

Li, Hesong, Yunfan Zhou, Yi Wang, Sha Du, and Shangcheng Xu. "Optimal Cruise Characteristic Analysis and Parameter Optimization Method for Air-Breathing Hypersonic Vehicle." Applied Sciences 11, no. 20 (2021): 9565. http://dx.doi.org/10.3390/app11209565.

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There is an optimal cruise point with the lowest fuel consumption when a hypersonic vehicle performs steady-state cruise. The optimal cruise point is composed of the optimal cruise altitude and the optimal cruise Mach number, and its position is closely related to the aircraft parameters. This article aims to explore the relationship between the optimal cruise point and relevant aircraft parameters and establish a model to describe it, then an aircraft parameter optimization method of adjusting the optimal cruise point to the target position is explored with validation by numerical simulation.

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22

Navó, Àlex, and Josep M. Bergada. "Aerodynamic Study of the NASA’s X-43A Hypersonic Aircraft." Applied Sciences 10, no. 22 (2020): 8211. http://dx.doi.org/10.3390/app10228211.

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A 2D aerodynamic study of the NASA’s X-43A hypersonic aircraft is developed using two different approaches. The first one is analytical and based on the resolution of the oblique shock wave and Prandtl–Meyer expansion wave theories supported by an in-house program and considering a simplified aircraft’s design. The second approach involves the use of a Computational Fluid Dynamics (CFD) package, OpenFOAM and the real shape of the aircraft. The aerodynamic characteristics defined as the lift and drag coefficients, the aerodynamic efficiency and the pitching moment coefficient are calculated for

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23

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

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24

Li, Shichao, Zihao Liu, Fan Zhao, and Hongli Gao. "A New Hypersonic Wind Tunnel Force Measurement System to Reduce Additional Bending Moment and Avoid Time-Varying Stiffness." Sensors 22, no. 7 (2022): 2572. http://dx.doi.org/10.3390/s22072572.

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In order to improve traditional hypersonic wind tunnel airframe/propulsion integrated aerodynamic testing technology for hypersonic vehicles, a new force measurement system called the aerodynamic force measuring support (AFMS) was designed. The AFMS effectively overcomes the defect that the traditional internal box-balance occupies a large amount of internal space in the aircraft test model, which makes the airframe/propulsion integrated aerodynamic test more difficult. The AFMS also alleviates the interference of the additional bending moment caused by the non-coincidence between the calibrat

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Cooper, Maxim, Ashish Alex Sam, and Apostolos Pesyridis. "Modelling of a Dual-Fuel-Mode Free-Jet Combustion System." Aerospace 6, no. 12 (2019): 135. http://dx.doi.org/10.3390/aerospace6120135.

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The focus of this study is to design a combustion system able to sustain hypersonic flight at Mach 8. A Dual-Mode Free-Jet combustion chamber design, first tested in 2010 by NASA, is being adapted to run on hydrogen fuel instead of ethylene while addressing the excessive thermal heat load. This study is part of the FAME (Flight at Mach Eight) project, with the primary objective to design and analyse the engine configuration for a hypersonic commercial aircraft. This CFD analysis and validation study, the first to replicate this combustion chamber design, provides detailed instructions on the c

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Qian, Wei, Yuguang Bai, Xiangyan Chen, and Taojun Lu. "Aero-servo-elastic analysis of a hypersonic aircraft." Journal of Low Frequency Noise, Vibration and Active Control 37, no. 3 (2017): 534–53. http://dx.doi.org/10.1177/1461348417725956.

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Aero-servo-elastic analysis of a complex hypersonic aircraft is presented in this paper. A structure geometry was designed and built based on the X-43A vehicle. First, a three-dimensional structural finite element model was proposed with effective two-dimensional elements, which can obtain effective modal analysis results without useless local modes. Second, computational fluid dynamic (CFD) simulation was adopted to find aero-heating distribution of thermal mode via this structure. Aero-heating effect was included to study thermal-modal characteristics of the present structure. Influence due

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27

Ispir, Ali Can, Pedro Miguel Gonçalves, and Bayindir H. Saracoglu. "Analysis of a combined cycle propulsion system for STRATOFLY hypersonic vehicle over an extended trajectory." MATEC Web of Conferences 304 (2019): 03001. http://dx.doi.org/10.1051/matecconf/201930403001.

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Hypersonic civil aviation is an important enabler for extremely shorter flight durations for long-haul routes and using unexploited flight altitudes. Combined cycle engine concepts providing extended flight capabilities, i.e. propelling the aircraft from take-off to hypersonic speeds, are proposed to achieve high-speed civil air transportation. STRATOFLY project is a continuation of former European efforts in hypersonic research and aims at developing a commercial reusablevehicle for cruise speed of Mach 8 at stratospheric altitudes as high as 35 km above ground level. The propulsion plant of

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Wang, Zhijin, Tao Cheng, and Yu Zhou. "Software Development for Thickness Optimization of Tile-Type Thermal Protection System." International Journal of Aerospace Engineering 2022 (October 14, 2022): 1–24. http://dx.doi.org/10.1155/2022/3663567.

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During the flight mission of hypersonic aircraft, severe aerodynamic heating will occur on the surface, so thermal protection system (TPS) is required to protect the load-bearing structure of the aircraft. The present paper develops an engineering software for automatic optimization of the thickness of tile-type TPS for reusable aircraft. For requirements on TPS of reusable aircraft in the reentry stage, the method of heat flow-time curve enveloping, automatic material selection, and one-dimensional unsteady heat transfer calculation for multilayer plates under thermal load conditions had been

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Chen, Jie, Yan Lin, and Chang Peng Pan. "One Near Space Hypersonic Aircraft Neural Networks Dynamic Surface Backstepping Control Design." Applied Mechanics and Materials 494-495 (February 2014): 1068–71. http://dx.doi.org/10.4028/www.scientific.net/amm.494-495.1068.

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By using multilayer neural networks and dynamic surface backstepping,one new robust adaptive control design method is proposed for one hypersonic aircraft (HSA) uncertain MIMO nonaffine block control system. We adopt dynamic surface control strategy to eliminate the explosion of terms by introducing a series of first order filters to obtain the differentiation of the virtual control inputs. multi-layers nerual network adjust function to compensate the influence from the uncertain, and design the robust terms to solve the problem from approach error. The stability analysis and simulations demon

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Javaid, Kashif H., and Varnavas C. Serghides. "Airframe-Propulsion Integration Methodology for Waverider-Derived Hypersonic Cruise Aircraft Design Concepts." Journal of Spacecraft and Rockets 42, no. 4 (2005): 663–71. http://dx.doi.org/10.2514/1.8782.

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31

Jiao, Xin, and Ju Jiang. "Design of Interval Type-2 Fuzzy Sliding Mode Controller for Hypersonic Aircraft." Journal of Automation and Control Engineering 4, no. 2 (2016): 123–26. http://dx.doi.org/10.12720/joace.4.2.123-126.

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32

WANG, Jifei, Jinsheng CAI, Chuanzhen LIU, Yanhui DUAN, and Yaojie YU. "Aerodynamic configuration integration design of hypersonic cruise aircraft with inward-turning inlets." Chinese Journal of Aeronautics 30, no. 4 (2017): 1349–62. http://dx.doi.org/10.1016/j.cja.2017.05.002.

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Xue, Fei, Yuchao Wang, Zenghui Jiang, and Yinong Yang. "Hypersonic Free Flight Investigation on Rudder Reflection of Aircraft." Proceedings 2, no. 8 (2018): 542. http://dx.doi.org/10.3390/icem18-05434.

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In order to study the control effect of the rudder surface of the hypersonic vehicle and the coupling dynamic characteristics of the rudder surface deflection and the flight attitude, a technical platform for the deflection and motion coupling of the aircraft rudder surface was designed. The platform ejection mechanism can launch the model into the wind tunnel flow field according to the preset attitude, and model can free flight without support interference. The innovative design of the model internal rudder partial system can guarantee the model to deflect the rudder surface in the free flig

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Ferretto, Davide, and Nicole Viola. "Preliminary Design and Simulation of a Thermal Management System with Integrated Secondary Power Generation Capability for a Mach 8 Aircraft Concept Exploiting Liquid Hydrogen." Aerospace 10, no. 2 (2023): 180. http://dx.doi.org/10.3390/aerospace10020180.

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This paper introduces the concept of a thermal management system (TMS) with integrated on-board power generation capabilities for a Mach 8 hypersonic aircraft powered by liquid hydrogen (LH2). This work, developed within the EU-funded STRATOFLY Project, aims to demonstrate an opportunity for facing the challenges of hypersonic flight for civil applications, mainly dealing with thermal and environmental control, as well as propellant distribution and on-board power generation, adopting a highly integrated plant characterized by a multi-functional architecture. The TMS concept described in this

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Ferretto, Davide, Roberta Fusaro, and Nicole Viola. "Innovative Multiple Matching Charts approach to support the conceptual design of hypersonic vehicles." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 12 (2020): 1893–912. http://dx.doi.org/10.1177/0954410020920037.

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Several well-established best practices and reliable tools have been developed along the years to support aircraft conceptual and preliminary design. In this context, one of the most widely used tool is the Matching Chart (MC), a graphical representation of the different performance requirements (curves representing the thrust-to-weight ratio (T/W) requirement as function of the wing loading (W/S)) for each mission phase. The exploitation of this tool allows the identification of a feasible design space as well as the definition of a reference vehicle configuration in terms of maximum thrust,

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Esch, T., and M. Giehrl. "Numerical Analysis of Nozzle and Afterbody Flow of Hypersonic Transport Systems." Journal of Engineering for Gas Turbines and Power 117, no. 3 (1995): 389–93. http://dx.doi.org/10.1115/1.2814107.

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Using an implicit Finite-Volume Navier–Stokes code, the flow field in a Single Expansion Ramp Nozzle (SERN) for a hypersonic aircraft is studied. Comparisons between experimental data and CFD calculations for certain components of the integrated exhaust system (cold two-dimensional nozzle flow, high temperature reacting three-dimensional combustion chamber flow, and two-dimensional nozzle flow with external flow) are presented. To show the sensitivity of the considered components to off-design operating conditions, comprehensive numerical studies have been carried out. For the determination of

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HUANG, Ju, Yongneng YANG, Qi LIU, Haibin YANG, and Wei ZHANG. "Developing and applying Mach 4.5 nozzle in hypersonic wind tunnel." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 39, no. 5 (2021): 1064–69. http://dx.doi.org/10.1051/jnwpu/20213951064.

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Mach 4.5 tests in a conventional trans-supersonic wind tunnel are often accompanied by the air liquefaction phenomenon, resulting in the low reliability of test data. The Mach 4.5 nozzle developed in a hypersonic wind tunnel is able to heat airflow and provide more accurate test data. At present, China does not have the capability to test the Mach 4.5 nozzle in the 0.5-meter hypersonic wind tunnel. This gap may be filled by developing the Mach 4.5 nozzle in the hypersonic wind tunnel. The axisymmetric nozzle profile was calculated by the inviscid flow calculation method, and the boundary layer

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Lu, Qiugang, Lixian Zhang, Peng Shi, and Hamid Reza Karimi. "Control design for a hypersonic aircraft using a switched linear parameter-varying system approach." Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 227, no. 1 (2012): 85–95. http://dx.doi.org/10.1177/0959651812455897.

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Witcher, Kenneth, Ian McAndrew, and Elena Vishnevskaya. "Aerodynamic Analysis of Low Speed Wing Design using Taguchi L9 Orthogonal Array." MATEC Web of Conferences 151 (2018): 04005. http://dx.doi.org/10.1051/matecconf/201815104005.

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The study of aerodynamics has been preoccupied with understanding flight at increasing speeds and ultimately supersonic. Today, this pursuit has advanced the science for both Hypersonic and Transonic flight to near Mach 1 supporting economical commercial flight operations. This research presents the data from a Taguchi array on low speed with twin wing designs to establish the design parameters for their use in low speed and high altitude. Also presented is how aerodynamic advantages can be achieved through understanding the interactions of parameters and their use. This is compared to operati

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Yao, Cong Chao, Xin Min Wang, and Xiao Chen Zhang. "Design of Robust Adaptive Inverse Controller for a Hypersonic Aircraft Based on CMAC Neural Network." Applied Mechanics and Materials 325-326 (June 2013): 1135–39. http://dx.doi.org/10.4028/www.scientific.net/amm.325-326.1135.

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A new control structure based on dynamic inversion (DI) and neural network technology for a class of nonlinear uncertain system is proposed. DI is an effective nonlinear tracking and decoupling control method. However, the performance of the current DI may significantly degrade when internal unmodeled dynamics and external disturbances exist. In this paper, a Cerebellar Model Articulation Controller (CMAC) neural network is used to improve overall system performance of robust tracking control. The algorithm convergence condition is shown. Based on Lyapunov stability theory, all signals are pro

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Sun, Guo, and Yuan Gui Sun. "Thermal-Structural Analysis of Ni-Based Alloy Panel with Active Cooling Thermal Protection System." Applied Mechanics and Materials 644-650 (September 2014): 4718–21. http://dx.doi.org/10.4028/www.scientific.net/amm.644-650.4718.

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In hypersonic environments, the development of aircraft engine presents the mitigation of the extreme thermal environment inside the combustion chamber. This paper establishes the capabilities for combustor panel design. By given the key loading and boundary conditions of the panel structure, the thermal structural analysis determines temperatures and stresses and the optimization improves panel’s robustness subject to thermal mechanical loads. A parametric sweep analysis is carried and the results give the optimal value of the panel face thickness.

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Zaludin, Zairil A. "Sensor and Process Noises Reduction using a Luenberger State Estimator with a Stability Augmentation System for a Hypersonic Transport Aircraft." Asian Review of Mechanical Engineering 11, no. 1 (2022): 40–52. http://dx.doi.org/10.51983/arme-2022.11.1.3346.

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This paper firstly, presents an autopilot strategy for a Hypersonic Transport Aircraft (HST) using a Stability Augmentation System (SAS) with a Luenberger estimator. The SAS is designed using Linear Quadratic Regulator (LQR) theory which, for HST, benefits the guaranteed robust dynamic stability provided three theoretical requirements are met. The Luenberger estimator is incorporated into the autopilot design to estimate the state variables of the aircraft for the SAS. In the dynamic response simulation, sensor and process noises are inserted into the mathematical model. However, to date, know

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Zhao, Shuyuan, Qian Sun, Yumin Zhang, and Jin Jia. "Parametric Influences of Geometric Dimensions on High Temperature Mechanical Behaviors and Damage Mechanisms of Ceramic Matrix Composite and Superalloy Double Bolted Joints." International Journal of Aerospace Engineering 2022 (August 31, 2022): 1–16. http://dx.doi.org/10.1155/2022/7169123.

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Given multiple material performance advantages, ceramic matrix composite (CMC) material has become one of the most promising hot structural materials used for thermal protection system in hypersonic vehicles. Under harsh thermal exposure of vehicles in flight, the design of connection structure would be a critical issue in improving load-carrying efficiency and ensuring service safety of aircraft structures in service environments. However, little attention was paid on mechanical behavior and its factors affecting the mechanical property of CMC joining at elevated temperature. To address this

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Miao, Shuangxi, Chengqi Cheng, Weixin Zhai, et al. "A Low-Altitude Flight Conflict Detection Algorithm Based on a Multilevel Grid Spatiotemporal Index." ISPRS International Journal of Geo-Information 8, no. 6 (2019): 289. http://dx.doi.org/10.3390/ijgi8060289.

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Flight conflict detection is fundamental to flight dispatch, trajectory planning, and flight safety control. An ever-increasing aircraft population and higher speeds, particularly the emergence of hypersonic/supersonic aircrafts, are challenging the timeliness and accuracy of flight conflict detection. Traditional trajectory conflict detection algorithms rely on traversing multivariate equations of every two trajectories, in order to yield the conflict result and involve extensive computation and high algorithmic complexity; these algorithms are often unable to provide the flight conflict solu

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Chudoba, B., G. Coleman, H. Smith, and M. V. Cook. "Generic stability and control for aerospace flight vehicle conceptual design." Aeronautical Journal 112, no. 1132 (2008): 293–306. http://dx.doi.org/10.1017/s000192400000227x.

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Abstract The recent period has been filled with exceptionally interesting developments and advances, resulting in high-performance conventional and non-conventional manned and unmanned aircraft. Although those vehicles seem to comply well with specific mission performance requirements, one is still confronted with an apparent weakness to reliably stabilise and control throughout the flight envelope. Since the provision of satisfactory stability and control characteristics invariably compromises flight performance, it becomes essential to identify and integrate performance-optimal stability and

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Meng, Yizhen, Bin Jiang, and Ruiyun Qi. "Modeling and control of hypersonic vehicle dynamic under centroid shift." Advances in Mechanical Engineering 10, no. 9 (2018): 168781401879912. http://dx.doi.org/10.1177/1687814018799123.

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Due to the huge flight scale and the fast speed of hypersonic vehicle, the system must be of strong nonlinearity, coupling, and fast time variability, which give rise to the huge challenge for the design of controller. The good control performance must be based on the elaborately designed controller, which is established in the carefully designed center of mass. Once the center of mass moves unexpectedly, it is bound to affect the ability of existing flight controller to maintain the stability of hypersonic vehicle, resulting in serious consequences, even loss of control. Based on Newton’s law

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Khrapko, V. Yu. "The Concept of the Combined Thermal Protection System for Leading Edges of Hypersonic Vehicles with Use of Thermionic Emission." KnE Engineering 3, no. 3 (2018): 465. http://dx.doi.org/10.18502/keg.v3i3.1647.

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This work represents a conceptual stage of the project on development of technology of the combined thermal protection system for hypersonic vehicles heat-stressed surfaces with use of technology of the thermionic power cell and thermal protection system with an external emission of electrons. The relevance of this work is to develop thermal protection system technology for aircraft, enabling prolonged controlled flight at hypersonic speeds, while providing low aerodynamic resistance and relative weight, the consistency of the geometric shape of the hypersonic vehicles leading edge. The variou

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Le, Wenxin, Hanyu Liu, Ruiyuan Zhao, and Jian Chen. "Attitude Control of a Hypersonic Glide Vehicle Based on Reduced-Order Modeling and NESO-Assisted Backstepping Variable Structure Control." Drones 7, no. 2 (2023): 119. http://dx.doi.org/10.3390/drones7020119.

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Aiming at solving the control problem caused by the large-scale change of the Hypersonic Glide Vehicle (HGV) parameters, this paper proposes a design method of backstepping variable structure attitude controller based on Nonlinear Extended State Observer (NESO), with the characteristics of HGV model and the idea of uncertainty estimation and compensation associated. Firstly, the design of the second-order NESO is studied. Due to the large number of NESO parameters, a systematic method for determining the second-order NESO parameters is given in this paper, and the stability of the observer is

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Chudoba, B., G. Coleman, A. Oza, L. Gonzalez, and P. A. Czysz. "Technology and operational sensitivity assessment for hypersonic endurance flight vehicles." Aeronautical Journal 119, no. 1213 (2015): 365–87. http://dx.doi.org/10.1017/s0001924000010514.

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AbstractIn an effort to increase the air-breathing endurance capability of current hypersonic research aircraft (i.e. X-43, 7 seconds; X-51, 5 minutes), the authors have explored the technical and operational solution space for a 30 minute cruise endurance demonstrator operating in the Mach 6 to Mach 8 speed regime. The focus of this activity has been on exploration of the available solution space through a unique screening process to assess the implication and interplay between the (a) mission, (b) baseline vehicle, and (c) operational scenarios. This study concludes that an air-launched, liq

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Lai, Jianqi, Hua Li, Zhengyu Tian, and Ye Zhang. "A Multi-GPU Parallel Algorithm in Hypersonic Flow Computations." Mathematical Problems in Engineering 2019 (March 17, 2019): 1–15. http://dx.doi.org/10.1155/2019/2053156.

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Computational fluid dynamics (CFD) plays an important role in the optimal design of aircraft and the analysis of complex flow mechanisms in the aerospace domain. The graphics processing unit (GPU) has a strong floating-point operation capability and a high memory bandwidth in data parallelism, which brings great opportunities for CFD. A cell-centred finite volume method is applied to solve three-dimensional compressible Navier–Stokes equations on structured meshes with an upwind AUSM+UP numerical scheme for space discretization, and four-stage Runge–Kutta method is used for time discretization

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