Journal articles: 'Hypersonic aircraft design'

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Alkaya, Can, Ashish Alex Sam, and Apostolos Pesyridis. "Conceptual Advanced Transport Aircraft Design Configuration for Sustained Hypersonic Flight." Aerospace 5, no. 3 (September 1, 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 to generate enough thrust to sustain hypersonic cruise at an altitude of 30 km.

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Dai, Yalin, Yu Wang, Xiaoyu Xu, and Xiongqing Yu. "An Improved Method for Initial Sizing of Airbreathing Hypersonic Aircraft." Aerospace 10, no. 2 (February 18, 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 hypersonic aircraft is used to describe the detailed procedure of the method. The weight and size of the aircraft are estimated through the simultaneous solution of the weight equation and the volume equation. Constraint analysis is applied to determine the solution space of the thrust-to-weight ratio and the wing loading. A thrust trade is conducted to find the minimum takeoff gross weight of the aircraft. The impacts of technology parameters on the weight, size, and thrust are investigated by sensitivity analyses. The presented method is based on rational derivation. It can be expected that the initial sizing results from the method are reasonable and satisfactory for conceptual design of the airbreathing hypersonic aircraft.

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Koptev, A. ""THEORETICAL ASPECTS OF STRENGTH AND THERMAL CONTROL OF HYPERSONIC AIRCRAFT"." National Association of Scientists 1, no. 66 (May 14, 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, taking into account the thermophysical characteristics of materials from thermal parameters.

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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 show the simpleness and effective of this method.

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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-disciplinary, closely coupled optimisation suite for hypersonic aircraft. An overview of the setup and structure of the optimization suite is given and the integration between the Tranair solver, used to determine the aerodynamic loads and temperatures, and MSC/NASTRAN, used for the structural sizing and design, will be given.

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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 (November 17, 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 numerical simulation of the external flow field and structure coupling of the aerodynamic heat problem is performed. The dynamic parameters of temperature and pressure are obtained, and the thermal protection basis of the internal equipment is obtained. Numerical results indicate that the average temperature and maximum temperature of the optical dome for inner and outer walls exhibit an “M” shape with time, with two high-temperature cusps and one low-temperature cusp. The time of average temperature coincides with that of maximum wall temperature. During the flight, the wall pressure changes with time, exhibiting the characteristics of higher temperature at both ends of the flight and lower temperature in the middle. The structural temperature of the hypersonic aircraft is higher than that of the external flow behind the shock wave after 310 s. Therefore, this study provides a reliable reference for the preliminary design and parameter research of optical domes of hypersonic aircraft.

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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 approximation performance of the response surface models are analyzed.

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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 (April 1, 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 reliability and failure results for the wing spar, and the strength degradation cannot be neglected. Furthermore, the obtained results will provide an important reference for the structural safety of hypersonic aircraft. Research limitations/implications The proposed reliability analysis scheme has not implemented in actual flight, as all the simulations are conducted according to the actual experiment data. Practical implications The proposed reliability analysis scheme can solve the structural life problem of the wing spar for hypersonic aircraft and meet engineering practice requirements, and it also provides an important reference to guarantee the flight safety and structural reliability for hypersonic aircraft. Originality/value To describe the damage evolution more accurately, with consideration of strength degradation, flight dynamics and material characteristics of the hypersonic aircraft, the stress-strength interference method is first applied to analyze the structural reliability of the wing spar for the hypersonic aircraft. The proposed analysis scheme is implemented on the dynamic model of the hypersonic aircraft, and the simulation demonstrates that a more reasonable reliability result can be achieved.

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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 reference trajectory. The navigation algorithm presented in this paper is based on an augmented state EKF data fusion algorithm exploiting inertial measurements provided by gyroscopes and accelerometers, heading estimates provided by a magnetometer and satellite-based measurements provided by a spaceborne GNSS receiver, considering GPS, GLONASS and GALILEO constellations.

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Jiao, Xin, and Ju Jiang. "Design of adaptive switching control for hypersonic aircraft." Advances in Mechanical Engineering 7, no. 10 (October 21, 2015): 168781401561046. http://dx.doi.org/10.1177/1687814015610465.

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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-disciplinary, closely coupled optimization suite that is suitable for preliminary design in the hypersonic regime. The time varying temperature distribution is applied through an equilibrium analysis, and is coupled to the aerodynamics through the Tranair® solver. An analysis of the effect that the aerothermodynamic coupling has on the sizing of the aircraft is given, along with the effect of skin buckling. It is shown that the coupling of the aerothermodynamics drives the sizing of the structure and therefore must be considered for hypersonic applications.

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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 (December 10, 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 to the different operating conditions and was able to retain its performance throughout the altitude simulated. The expansion ramp shape, angle, exit area, and cowl shape influenced the thrust substantially. The internal nozzle expansion and expansion ramp had a significant effect on the lift and moment performance. An optimized SERN was assembled into a scramjet and was subject to various nozzle inflow conditions, to which combustion flow from twin strut injectors produced the best thrust performance. Side fence studies observed longer and diverging side fences to produce extra thrust compared to small and straight fences.

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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 (January 1998): 58–63. http://dx.doi.org/10.2514/2.4197.

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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 (April 17, 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, and recommendations are arrived at by constructing and evaluating a hypersonic technology demonstrator design matrix. This multi-disciplinary parametric sizing investigation of hypersonic vehicle demonstrators focuses on the evaluation of the combined carrier platform, booster, and hypersonic cruiser solution space topography. Promising baseline configurations are evaluated against operational requirements by trading fuel type, endurance cruise time, and payload weight. The multi-disciplinary study results are constrained with carrier payload mass and geometry limitations. The multi-disciplinary results provide physical insights into near-term hypersonic demonstrator payload and cruise time requirements that will stretch the capability of existing carrier aircraft. Any growth in hypersonic research aircraft size or capability will require new carrier vehicle investments.

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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 performance of the vehicle. This article investigates the effect of two different structural concepts: a conventional rib-spar configuration and a pillow tank. A number of different structural options in terms of number of ribs / spars will be investigated. The structure will be optimised based on critical loading conditions. Results for various temperature distributions will be investigated, while looking at change on structural strength, in-flight static deformation and dynamic response. Keywords: Aeroelasticity, Hypersonics, Design.

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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 (January 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 air-breathing engines to the above-mentioned waverider vehicle concepts and missions. In particular, the cruise mission is discussed in detail and attempts are made to compare and contrast it with the accelerator mission. Past criticisms levied against waveriders alleging low volumetric efficiency, lack of engine/airframe integration studies, poor off-design performance, poor take-off and landing capability, have been shown by ongoing research to be unfounded. A discussion is presented of some of the technical challenges and ongoing research aimed at realizing such vehicles: from turboramjet and scramjet technology development, propulsion-airframe integration effects on vehicle performance, aeroservothermoelastic systems analysis, hypersonic stability and control with aeroservothermoelastic and propulsion effects, etc. A unique and very strong aspect of hypersonic vehicle design is the integration and interaction of the propulsion system, aerodynamics, aerodynamic heating, stability and control, and materials and structures. This first-order multidisciplinary situation demands the ability to integrate highly coupled and interacting elements in a fundamental and optimal fashion to achieve the desired performance. Some crucial technology needs are found in propulsion-airframe integration and its role in configuration definition, hypersonic boundary-layer transition and its impact on vehicle gross-weight and mission success, scramjet combustor mixing length and its impact on engine weight and, CFD (turbulence modeling, transition modeling, etc) as a principal tool for the design of hypersonic vehicles. Key technology implications in thermal management, structures, materials, and flight control systems will also be briefly discussed. It is concluded that most of the technology requirements in the Mach 4–7 regime are relatively conventional, making cited applications near-term, yet offering very significant advancements in aircraft technology.

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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 (January 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 and describes the computer program used for the propulsion system performance simulation, including all relevant integration aspects. Furthermore, some results of propulsion system performance for a generic hypersonic aircraft and a typical ascent profile will be compared to indicate the special characteristics of the engines. Finally, some thoughts concerning the suitability and relevant technological requirements of the two engine types—seen from an aircraft manufacturer’s view—are included. The paper includes the results of two diploma theses, written by W. Sterr [1] and B. Zellner [2] at the Technical University of Munich, supervised by Prof. H. Rick (LFA) and O. Herrmann (MBB).

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

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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 (November 1994): 1260–66. http://dx.doi.org/10.2514/3.21342.

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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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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 (October 14, 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. Firstly, a parameterized model of a hypersonic vehicle is obtained as a basis, then the optimal cruise point is obtained by the optimization method, and the influence of a single aircraft parameter on the optimal point is investigated. In order to model the relationship between the aircraft parameters and the optimal cruise point, a neural network is employed. Finally, the model is used to optimize the aircraft parameters under multiple constraints. The results show that, after aircraft parameters optimization, the optimal cruise point is located at the predetermined position and the fuel consumption is lower, which provides a new perspective for the design of aircraft.

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Navó, Àlex, and Josep M. Bergada. "Aerodynamic Study of the NASA’s X-43A Hypersonic Aircraft." Applied Sciences 10, no. 22 (November 19, 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 different angles of attack. Evaluations are made for an incident Mach number of 7 and an altitude of 30 km. For both methodologies, the required angles of attack to achieve a Vertical Force Balance (VFB) and a completely zero pitching moment conditions are considered. In addition, an analysis to optimise the nose configuration of the aircraft is performed. The mass flow rate throughout the scramjet as a function of the angle of attack is also presented in the CFD model in addition to the pressure, density, temperature and Mach fields. Before presenting the corresponding results, a comparison between the aerodynamic coefficients in terms of the angle of attack of both models is carried out in order to properly validate the CFD model. The paper clarifies the requirements needed to make sure that both oblique shock waves originating from the leading edge meet just at the scramjet inlet clarifying the advantages of fulfilling such condition.

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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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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 (March 27, 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 calibration center of traditional external box-balance and the gravity center of the aircraft test model, innovatively designing a convex structure in the joint part of the force measuring system. Furthermore, the AFMS effectively overcomes the time-varying stiffness of joints caused by test model vibration in hypersonic wind tunnel testing, which eventually leads to test errors. Compared with the traditional box-balance, the AFMS proposed in this study has sufficient design space. This ensures more thorough aerodynamic decomposition of the AFMS and less interference between channels, whilst also having the advantages of the large support stiffness of traditional box-balance. Thus, the AFMS provides a new technical path for airframe/propulsion integrated aerodynamic testing of air-breathing hypersonic vehicles in a hypersonic wind tunnel.

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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 (December 17, 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 combustion system design. The analysis from this study can be used for future research to successfully reach a sustainable design and operation of a Dual-Mode Free-Jet combustion chamber. The 53% size reduction in the combustion system represents significant progress which encourages future research regarding in the design of combustion systems for hypersonic propulsion systems.

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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 (August 23, 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 to material characteristic change and thermal stress was studied. After structural finite element analysis was completed, flutter of the present vehicle was investigated. Aero-servo-elastic analysis was then started from the definition of an aero-servo-elastic closed-loop system. In this system, the present aircraft is treated as flexible structure, in which the control sensor on the aircraft received not only rigid motion signal but also elastic vibration signal, and this signal can translate into the deflection signal to form aerodynamic control force through this aero-servo control system, and this force can continually influence aerodynamic force. One of the most important steps for this analysis was computation of unsteady aerodynamic force of the present structure, and the related process was developed based on an effective fitting method. Finally, bode diagrams of pitching, rolling and yawing were investigated, form which the law of aero-servo stability of the X-43A vehicle can be observed and analyzed. It can be found from the results of this paper that effective investigation of aero-servo-elastic characteristics of a complex hypersonic aircraft should be based on accurate structural finite element modeling, modal analysis and flutter analysis. The proposed method in this paper can provide effective analysis process for the design of controller for hypersonic aircraft.

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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 STRATOFLY aircraft consists of combination of two different type of engines: an array of air turbo rockets and a dualmode ramjet/scramjet. In the present study, 1D transient thermodynamic simulations for this combined cycle propulsion plant have been conducted between Mach 0 to 8 by utilizing 1D inviscid flow transport relations, numerical tools availablein EcosimPro software platform and the European Space Propulsion System Simulation libraries. The optimized engine parameters are achieved by coupling EcosimPro software with Computer Aided Design Optimization which is a differential evolution algorithm developed at the von Karman Institute.

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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 researched, an interactive engineering software had been developed. The software improves the calculation accuracy and calculation efficiency of TPS thickness optimization, and it is suitable for rapid design in the conceptual design stage of the aircraft. Finally, by an example, the function of the software is verified.

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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 demonstrate the good performance of the controller. Nonlinear six-degree-of-freedom (6-DOF) numerical simulation results for a HSA model are presented to demonstrate the effectiveness of the proposed method.

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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 (July 2005): 663–71. http://dx.doi.org/10.2514/1.8782.

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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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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 (August 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 (July 12, 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 flight process, simulate the real steering process of the aircraft. By changing spring with different springs, the speed of the rudder surface can be changed. The dual optical path and image acquisition technology can capture the motion picture before and after the deflection of the rudder surface from two angles. After the image is matched by model matching, the six degrees of freedom parameter of the model can be changed with the time curve before and after the deflection of the rudder surface, and the area of the six freedom degree curve of the different state model is compared. In other words, the specific influence of dynamic rudder rotation on the motion of the model is known. The wind tunnel test of the model in the hypersonic wind tunnel of the 500 mm is carried out using this platform. The test results are highly repeatable, and the test platform technology is mature and reliable.

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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 (February 14, 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 paper makes benefit of the connection between the propellant storage and distribution subsystems of the aircraft to exploit hydrogen vapors and liquid flow as the means to drive a thermodynamic cycle able, on one hand, to ensure engine feed and thermal control of the cabin environment, while providing, on the other hand, the necessary power for other on-board systems and utilities, especially during the operation of high-speed propulsion plants, which cannot host traditional generators. The system layout, inspired by concepts studied within precursor EU-funded projects, is detailed and modified in order to suggest an operable solution that can be installed on-board the reference aircraft, with focus on those interfaces impacting its performance requirements and integration features as part of the overall systems architecture of the plane. Analysis and modeling of the system is performed, and the main results in terms of performance along the reference mission profile are discussed.

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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 (April 24, 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, maximum take-off weight, and wing surface since the very beginning of the design process. Although the tool was originally developed for conventional aircraft, several extensions and updates of the mathematical models have been proposed over the years to widen its application to innovative configurations. Following this trend, this paper presents a further evolution of the MC model to support the conceptual design of high-speed transportation systems, encompassing supersonic and hypersonic flight vehicles. At this purpose, this paper reports and discusses the updates of the methodology laying behind the generation of the MC for high-speed transportation. Eventually, the results of the validation of the updated methodology and tool are reported, using as case study, the STRATOFLY MR3 vehicle configuration, a Mach 8 antipodal civil transportation system, currently under development within the H2020 STRATOFLY project.

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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 (July 1, 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 nozzle performance a detailed two-dimensional analysis from transonic to hypersonic flight Mach numbers has been performed. A direct optimization method has been used to investigate the influence of the lower nozzle flap shape on the thrust vector.

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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 (October 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 was modified by the Sivells-Payne method. Then, the numerical simulation was carried out, and the simulation results prove that the nozzle profile thus calculated meets the design requirements of the Mach number. For its structural design, a three-section design method is adopted to ensure the continuity and smoothness of the inner surface so as to better calibrate the flow field. Standard model tests were also carried out. The test results show that the velocity field of the Mach 4.5 nozzle we developed meets technical requirements. The standard model test data provide data reliable support for the development of aircraft.

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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 (August 28, 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 operational effectiveness when applied to remotely piloted aircraft that are not constrained by direct requirements. The research concludes with suggestions for improved designs and further work that may enable higher altitudes with low speeds.

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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 proved to be uniform convergence. Finally, the flight control system of the hypersonic vehicle is designed based on the proposed method and the simulation results demonstrate the excellent performance and robustness of the controllers.

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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 (June 15, 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, knowledge of the sensor and process noises at the speeds and heights where the aircraft will be flying is limited. The simulation shows that the Luenberger estimator significantly filters the noise. This is an advantage for the HST as prior knowledge of the noises is not necessary when designing the Luenberger estimator.

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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 concern, a 3D finite element model coupled with progressive damage analysis is carried out to predict high temperature tensile properties and failure behavior of single-lap, double-bolt CMC/superalloy joints assembled by two serial protruding-head bolts. In the implementation of progressive damage analysis of 2D plain-woven C/SiC composites, a user-defined subroutine UMAT including a nonlinear constitutive model, 3D Alvaro failure criterion and Tan’s material degradation rule were embedded into the general package ABAQUS® through Fortran program interface. A parametric study considering geometries of joints was performed to evaluate their resultant influence on high temperature tensile behavior and the associated damage mechanisms for the CMC/superalloy double-bolt joint. New findings were provided for full exploitation of high performance through geometric design of ceramic matrix composite hot structure for hypersonic aircraft.

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Miao, Shuangxi, Chengqi Cheng, Weixin Zhai, Fuhu Ren, Bo Zhang, Shuang Li, Junxiao Zhang, and Huangchuang Zhang. "A Low-Altitude Flight Conflict Detection Algorithm Based on a Multilevel Grid Spatiotemporal Index." ISPRS International Journal of Geo-Information 8, no. 6 (June 21, 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 solutions required quickly enough. In this paper, we present a novel, low-altitude flight conflict detection algorithm, based on the multi-level grid spatiotemporal index, that transforms the traditional trajectory-traversing multivariate conflict computation into a grid conflict state query of distributed grid databases. Essentially, this is a method of exchanging "storage space" for "computational time". First, we build the spatiotemporal subdivision and encoding model based on the airspace. The model describes the geometries of the trajectories, low-altitude obstacles, or dangerous fields and identifies the grid with grid codes. Next, we design a database table structure of the grid and create a grid database. Finally, we establish a multilevel grid spatiotemporal index, design a query optimization scheme, and examine the flight conflict detection results from the grid database. Experimental verification confirms that the computation efficiency of our algorithm is one order of magnitude higher than those of traditional methods. Our algorithm can perform real-time (dynamic/static) conflict detection on both individual aircraft and aircraft flying in formation with more efficient trajectory planning and airspace utilization.

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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 (June 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 control design solutions early during the flight vehicle definition phase. In particular, the conceptual design of integrated control effectors for advanced aircraft is far from being trivial. Never before have we been presented with such tremendous wealth of specialised data and information suitable for detail design of controls. In contrast, never before has it been necessary to approach any one of the primary design disciplines still as entirely ad hoc and inconsistent as in the case of designing controls during the conceptual design phase. This need initiated the development of a configuration independent (generic) stability and control methodology capable of sizing primary control effectors of fixed wing subsonic to hypersonic designs of conventional and unconventional, symmetric and asymmetric configuration layouts. This paper summarises the methodology concept and demonstrates its versatility and validity by analyzing selected stability and control characteristics of the Northrop YB-49 flying wing.

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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 (September 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 laws and Varignon’s theory, a mathematical model for hypersonic vehicle with centroid shift is built up to research the influence of centroid on the motion of hypersonic vehicle. The zero-input response tests are conducted from the different aircraft body axes of the coordinate. Simulation results show that such influence is coupling, abrupt, irregular, and time-variant. In order to inhibit the bad influence of unexpected centroid shift, terminal sliding mode controller combined with radial basis function neural networks and just terminal sliding mode controller alone are adopted to handle such problems in view of robust control itself and auxiliary compensation. Simulation results show that such influence can be inhibited and compensated in a certain region, and the further research is still needed.

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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 (February 21, 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 various using types of thermal protection system are compared and the necessity to develop a new type of it using the effect of thermionic emission of electrons is proved. The scheme and the possible material composition of thermionic power cell with a reversed geometry of the electrodes are given. The problem of the choice of material for emission surface of the system with external electron emission and its manufacturing technology are discussed. Using cesium intercalated graphite as one of the possible coating materials is reviewed. A sequence of forthcoming studies is formulated at the stage of transition to the design basis for the operation of thermal protection of this type.

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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 (February 8, 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 proved completely using the piecewise Lyapunov analysis. Then, the NESO-assisted backstepping variable structure attitude controller employs the reduced-order modeling idea to decompose the whole system design problem into two first-order subsystem design problem, and classifies the nonlinear dynamic changes caused by the large-scale changes of the aircraft parameters into the aggregated uncertain terms of the two subsystems. The simulation results show that the backstepping attitude controller based on NESO can realize the stable and accurate tracking of the flight attitude when the aircraft parameters change in a large range.

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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 (March 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, liquid hydrogen fuelled, 30 minute duration Mach 6 demonstrator (with 10 min Mach 8 capability) provides the largest feasible solution space of the trades examined (i.e. largest design margins, lowest technical risk) when compared to a kerosene-powered equivalent.

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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. Compute unified device architecture (CUDA) is used as a parallel computing platform and programming model for GPUs, which reduces the complexity of programming. The main purpose of this paper is to design an extremely efficient multi-GPU parallel algorithm based on MPI+CUDA to study the hypersonic flow characteristics. Solutions of hypersonic flow over an aerospace plane model are provided at different Mach numbers. The agreement between numerical computations and experimental measurements is favourable. Acceleration performance of the parallel platform is studied with single GPU, two GPUs, and four GPUs. For single GPU implementation, the speedup reaches 63 for the coarser mesh and 78 for the finest mesh. GPUs are better suited for compute-intensive tasks than traditional CPUs. For multi-GPU parallelization, the speedup of four GPUs reaches 77 for the coarser mesh and 147 for the finest mesh; this is far greater than the acceleration achieved by single GPU and two GPUs. It is prospective to apply the multi-GPU parallel algorithm to hypersonic flow computations.

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Journal articles on the topic 'Hypersonic aircraft design'

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