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Relevant bibliographies by topics / Hypersonic aircraft design

Academic literature on the topic 'Hypersonic aircraft design'

Author: Grafiati

Published: 14 March 2023

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Journal articles on the topic "Hypersonic aircraft design"

1

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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Dissertations / Theses on the topic "Hypersonic aircraft design"

1

Javiad, Kashif Hussan. "Development of conceptual and preliminary design methodologies for hypersonic military aircraft." Thesis, Imperial College London, 2005. http://hdl.handle.net/10044/1/7150.

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Fiorentini, Lisa. "Nonlinear Adaptive Controller Design For Air-breathing Hypersonic Vehicles." The Ohio State University, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=osu1274986563.

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Dicara, Daniel L. "Development of an aerodynamic/RCS framework for the preliminary design of a hypersonic aircraft." Thesis, Massachusetts Institute of Technology, 2006. http://hdl.handle.net/1721.1/46570.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2006.
Includes bibliographical references (p. 59-60).
The design of hypersonic airbreathing aircraft pushes the envelope of current state-ofthe-art aerospace propulsion and materials technology. Therefore, these aircraft are highly integrated to produce adequate thrust, reduce drag, and limit surface heating. Consequently, every aircraft component (e.g., wings, fuselage, propulsion system) is sensitive to changes in every other component. Including Radar Cross Section (RCS) considerations further complicates matters. During preliminary design, this requires the rapid analysis of different aircraft configurations to investigate component interactions and determine performance trends. This thesis presents a framework and accompanying software for performing such an analysis. The intent is to optimize a hypersonic airbreathing aircraft design in terms of aerodynamic performance and RCS. Computational Fluid Dynamics (CFD) and Computational Electromagnetics (CEM) are the two main framework software components. CFD simulates airflow around the aircraft to analyze its aerodynamic performance. Alternately, CEM simulates the electromagnetic signature of the aircraft to predict its RCS. The framework begins with the generation of a three-dimensional computer aided design aircraft model. Next, a grid generator discretizes this model. The flow simulation is performed on this grid and the aircraft's aerodynamic characteristics are determined. Flow visualization aids this determination. Then, aircraft geometry refinements are made to improve aerodynamic performance. Afterward, CEM is performed on aerodynamically favorable designs at various aspect angles and frequencies. RCS values are determined and used to rank the different configurations. Also, inverse synthetic aperture radar images are generated to locate major scattering centers and aid the design refinement. The design loop continues in this fashion until an acceptable aircraft design is achieved. The NASA X-43A test vehicle was used to validate this preliminary design framework.
by Daniel L. DiCara.
S.M.

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Sharifzadeh, Shayan. "Design Optimization and Analysis of Long-Range Hydrogen-Fuelled Hypersonic Cruise Vehicles." Thesis, The University of Sydney, 2017. http://hdl.handle.net/2123/19127.

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Aviation industry is continuously growing especially for very long distance flights due to the globalisation of local economies around the world and the explosive economic growth in Asia. Reducing the time of intercontinental flights from 16-20 hours to 4 hours or less would therefore make the, already booming, ultra-long distance aviation sector even more attractive. To accomplish this drastic travel time reduction for civil transport, hypersonic cruise aircraft are considered as a potential cost-effective solution. Such vehicles should also be fuelled by liquid hydrogen, which is identified as the only viable propellant to achieve antipodal hypersonic flight with low environmental impact. Despite considerable research on hypersonic aircraft and hydrogen fuel, several major challenges should still be addressed before such airliner becomes reality. The current thesis is therefore motivated by the potential benefit of hydrogen-fuelled hypersonic cruise vehicles associated with their limited state-of-the-art. Hypersonic cruise aircraft require innovative structural configurations and thermal management solutions due to the extremely harsh flight environment, while the uncommon physical properties of liquid hydrogen, combined with high and long-term heat fluxes, introduce complex design and technological storage issues. Achieving hypersonic cruise vehicles is also complicated by the multidisciplinary nature of their design. In the scope of the present research, appropriate methodologies are developed to assess, design and optimize the thermo-structural model and the cryogenic fuel tanks of long-range hydrogen-fuelled hypersonic civil aircraft. Two notional vehicles, cruising at Mach 5 and Mach 8, are then investigated with the implemented methodologies. The design analysis of light yet highly insulated liquid hydrogen tanks for hypersonic cruise vehicles indicates an optimal gravimetric efficiency of 70-75% depending on insulation system, tank wall material, tank diameter, and flight profile. A combination of foam and load-bearing aerogel blanket leads to the lightest cryogenic tank for both the Mach 5 and the Mach 8 aircraft. If the aerogel blanket cannot be strengthened sufficiently so that it can bear the full load, then a combination of foam and fibrous insulation materials gives the best solution for both vehicles. The aero-thermal and structural design analysis of the Mach 5 cruiser shows that the lightest hot-structure is a titanium alloy construction made of honeycomb sandwich panels. This concept leads to a wing-body weight of 143.9 t, of which 36% accounts for the wing, 32% for the fuselage, and 32% for the cryogenic tanks. As expected, hypersonic thermal loads lead to important weight penalties (of more than 35 %). The design of the insulated cold structure, however, demonstrates that the long-term high-speed flight of the airliner requires a substantial thermal protection system, such that the best configuration (obtained by load-bearing aerogel blanket) leads to a titanium cold design of only 4% lighter than the hot structure. Using aluminium 7075 rather than titanium offers a further weight saving of about 2 %, resulting in a 135.4 t wing-body weight (with a contribution of 23 %, 25 %, 18%and 34%from the TPS, the wing, the fuselage, and the cryogenic tanks respectively). Given the design hypotheses, the difference in weight is not significant enough to make a decisive choice between hot and cold concepts. This requires the current methodologies to be further elaborated by relaxing the simplifications. Investigation of the thermal protection must be extended from one single point to different regions of the vehicle, and the TPS thickness and weight should be considered in the structural sizing of the cold design. More generally, the design process should be matured by including additional (static, dynamic and transient) loads, special structural concepts, multi-material configurations and other parameters such as cost and safety aspects.

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Sharifzadeh, Shayan. "Design Optimization and Analysis of Long-Range Hydrogen-Fuelled Hypersonic Cruise Vehicles." Doctoral thesis, Universite Libre de Bruxelles, 2017. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/255764.

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Aviation industry is continuously growing especially for very long distance flights due to the globalisation of local economies around the world and the explosive economic growth in Asia. Reducing the time of intercontinental flights from 16-20 hours to 4 hours or less would therefore make the, already booming, ultra-long distance aviation sector even more attractive. To accomplish this drastic travel time reduction for civil transport, hypersonic cruise aircraft are considered as a potential cost-effective solution. Such vehicles should also be fuelled by liquid hydrogen, which is identified as the only viable propellant to achieve antipodal hypersonic flight with low environmental impact. Despite considerable research on hypersonic aircraft and hydrogen fuel, several major challenges should still be addressed before such airliner becomes reality. The current thesis is therefore motivated by the potential benefit of hydrogen-fuelled hypersonic cruise vehicles associated with their limited state-of-the-art.Hypersonic cruise aircraft require innovative structural configurations and thermal management solutions due to the extremely harsh flight environment, while the uncommon physical properties of liquid hydrogen, combined with high and long-term heat fluxes, introduce complex design and technological storage issues. Achieving hypersonic cruise vehicles is also complicated by the multidisciplinary nature of their design. In the scope of the present research, appropriate methodologies are developed to assess, design and optimize the thermo-structural model and the cryogenic fuel tanks of long-range hydrogen-fuelled hypersonic civil aircraft. Two notional vehicles, cruising at Mach 5 and Mach 8, are then investigated with the implemented methodologies. The design analysis of light yet highly insulated liquid hydrogen tanks for hypersonic cruise vehicles indicates an optimal gravimetric efficiency of 70-75% depending on insulation system, tank wall material, tank diameter, and flight profile. A combination of foam and load-bearing aerogel blanket leads to the lightest cryogenic tank for both the Mach 5 and the Mach 8 aircraft. If the aerogel blanket cannot be strengthened sufficiently so that it can bear the full load, then a combination of foam and fibrous insulation materials gives the best solution for both vehicles. The aero-thermal and structural design analysis of the Mach 5 cruiser shows that the lightest hot-structure is a titanium alloy construction made of honeycomb sandwich panels. This concept leads to a wing-body weight of 143.9 t, of which 36% accounts for the wing, 32% for the fuselage, and 32% for the cryogenic tanks. As expected, hypersonic thermal loads lead to important weight penalties (of more than 35%). The design of the insulated cold structure, however, demonstrates that the long-term high-speed flight of the airliner requires a substantial thermal protection system, such that the best configuration (obtained by load-bearing aerogel blanket) leads to a titanium cold design of only 4% lighter than the hot structure. Using aluminium 7075 rather than titanium offers a further weight saving of about 2%, resulting in a 135.4 t wing-body weight (with a contribution of 23%, 25%, 18% and 34% from the TPS, the wing, the fuselage, and the cryogenic tanks respectively). Given the design hypotheses, the difference in weight is not significant enough to make a decisive choice between hot and cold concepts. This requires the current methodologies to be further elaborated by relaxing the simplifications. Investigation of the thermal protection must be extended from one single point to different regions of the vehicle, and the TPS thickness and weight should be considered in the structural sizing of the cold design. More generally, the design process should be matured by including additional (static, dynamic and transient) loads, special structural concepts, multi-material configurations and other parameters such as cost and safety aspects.
Doctorat en Sciences de l'ingénieur et technologie
This thesis was conducted in co-tutelle between University of Sydney and Université Libre de Bruxelles.Professor Dries Verstraete was my supervisor at the University of Sydney (so as a member of SydneyUni), but is automatically registered here as a member of ULB because he worked at ULB almost ten years ago.Ben Thornber is also a member of the University of Sydney but the application does not save it for an unknown reason.
info:eu-repo/semantics/nonPublished

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Chalker, Jack Randolph. "Design and Manipulation of a Power-Generating System with High-Temperature Fuel Cells for Hypersonic Applications." Wright State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=wright1567169603256774.

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Tancred, James Anderson. "Aerodynamic Database Generation for a Complex Hypersonic Vehicle Configuration Utilizing Variable-Fidelity Kriging." University of Dayton / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1543801033672049.

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Books on the topic "Hypersonic aircraft design"

1

Hani, Alkamhawi, and United States. National Aeronautics and Space Administration., eds. Hypersonic aircraft design. [Columbus, Ohio]: Ohio State University, 1990.

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Ardema, Mark D. Body weight of hypersonic aircraft. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

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A, Mackley Ernest, and Langley Research Center, eds. NASA's hypersonic research engine project: A review. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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J, Chattot J., Lawrence S. L, and United States. National Aeronautics and Space Administration., eds. Parallelization of a parabolized Navier-Stokes solver with a design optimizer: 34th AIAA Aerospace Sciences Meeting and Exhibit. [Washington, DC: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. Low-speed, high-lift aerodynamic characteristics of slender, hypersonic accelerator-type configurations. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

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Gatlin, Gregory M. Low-speed, high-lift aerodynamic characteristics of slender, hypersonic accelerator-type configurations. Hampton, Va: Langley Research Center, 1989.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. Low-speed, high-lift aerodynamic characteristics of slender, hypersonic accelerator-type configurations. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. Aeropropulsion '91: Proceedings of a conference held at NASA Lewis Research Center, Cleveland, Ohio, March 20-21, 1991. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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Advanced hypersonic aircraft design. [Columbus, Ohio]: Ohio State University, Aeronautical and Astronautical Engineering, 1992.

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Aeropropulsion '91: Proceedings of a conference held at NASA Lewis Research Center, Cleveland, Ohio, March 20-21, 1991. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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Book chapters on the topic "Hypersonic aircraft design"

1

Merlen, A. "From the analytical theory to hypersonic aircraft design." In Asymptotic Modelling in Fluid Mechanics, 221–28. Berlin, Heidelberg: Springer Berlin Heidelberg, 1994. http://dx.doi.org/10.1007/3-540-59414-0_69.

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Yang, Zhiling, and Hongfei Sun. "Nonlinear Control Design of a Hypersonic Aircraft Using Sum-of-Squares Method." In Informatics in Control, Automation and Robotics, 333–42. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-25992-0_48.

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Martin, Katharina, Dennis Daub, Burkard Esser, Ali Gülhan, and Stefanie Reese. "Numerical Modelling of Fluid-Structure Interaction for Thermal Buckling in Hypersonic Flow." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 341–55. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_22.

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Abstract Experiments have shown that a high-enthalpy flow field might lead under certain mechanical constraints to buckling effects and plastic deformation. The panel buckling into the flow changes the flow field causing locally increased heating which in turn affects the panel deformation. The temperature increase due to aerothermal heating in the hypersonic flow causes the metallic panel to buckle into the flow. To investigate these phenomena numerically, a thermomechanical simulation of a fluid-structure interaction (FSI) model for thermal buckling is presented. The FSI simulation is set up in a staggered scheme and split into a thermal solid, a mechanical solid and a fluid computation. The structural solver Abaqus and the fluid solver TAU from the German Aerospace Center (DLR) are coupled within the FSI code ifls developed at the Institute of Aircraft Design and Lightweight Structures (IFL) at TU Braunschweig. The FSI setup focuses on the choice of an equilibrium iteration method, the time integration and the data transfer between grids. To model the complex material behaviour of the structure, a viscoplastic material model with linear isotropic hardening and thermal expansion including material parameters, which are nonlinearly dependent on temperature, is used.

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Kossira, H., A. Bardenhagen, and W. Heinze. "An Integrated Computer-Program-System for the Preliminary Design of Advanced Hypersonic Aircraft (PrADO-Hy)." In Orbital Transport, 129–47. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-45720-3_9.

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Guo, Yixiang, Lifang Chen, and Yuhang Zhou. "A Review of the Development of Sealing Materials and Measurement and Control Simulation Technology for Typical Hypersonic Vehicle Positions." In Proceedings of the 2022 International Conference on Smart Manufacturing and Material Processing (SMMP2022). IOS Press, 2022. http://dx.doi.org/10.3233/atde220826.

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Hypersonic vehicles are an important development direction in aerospace, and their development will have a significant impact on world security, the development of cosmic space resources and related disciplines. Along with the rapid development of modern aircraft, landing gear is commonly used with retractable technology, which brings a series of problems, such as the design of landing gear hatch retraction heat sealing mechanism and the evaluation of air tightness. This paper takes the thermal sealing structure of the front main landing gear hatch of a vehicle as an example, reviews the progress of the analysis techniques of sealing material properties and sealing structure design for hypersonic vehicles at home and abroad, discusses the current status of the development and limitations of hatch thermal sealing technology, outlines and discusses the key technologies for design and analysis of hatch thermal sealing structure and the future development trend, and summarizes the test equipment and methods for identifying the performance of seals and sealing systems.

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Conference papers on the topic "Hypersonic aircraft design"

1

JOHNSON, REUBEN. "Soviet applications for hypersonic vehicles." In Aircraft Design, Systems and Operations Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4507.

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COONS, L. "Propulsion challenges for hypersonic flight." In Aircraft Systems, Design and Technology Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-2620.

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TRIKHA, ARUN, and THOMAS CREIGHTON. "Crew escape system design for hypersonic vehicles." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2025.

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ARDEMA, MARK, ERIC TERJESEN, and CATHY ROBERTS. "Body weight of advanced concept hypersonic aircraft." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3180.

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WARD, RICHARD, MARK LEAGUE, and EDDIE MOORE. "Assessment of a Soviet hypersonic transport." In Aircraft Design, Systems and Operations Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4506.

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CHAPUT, ARMAND. "Preliminary sizing methodology for hypersonic vehicles." In Aircraft Design, Systems and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2954.

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ARMENGAUD, F., R. DECHER, B. LAFOSSE, and A. KOOPMAN. "One-dimensional modeling of hypersonic flight propulsion engines." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2026.

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CASSIDY, P., and S. M. HALLEY. "Airframe/engine mechanical integration for hypersonic airbreathing aircraft." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3177.

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Czysz, Paul. "For hypersonic design propulsion sharpens the focus." In Aircraft Design, Systems, and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-4012.

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

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