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Journal articles on the topic 'Hypersonic propulsion and hypersonic aerothermodynamics'

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Published: 10 December 2022

Last updated: 29 January 2023

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1

de Araujo Martos, João Felipe, Israel da Silveira Rêgo, Sergio Nicholas Pachon Laiton, Bruno Coelho Lima, Felipe Jean Costa, and Paulo Gilberto de Paula Toro. "Experimental Investigation of Brazilian 14-X B Hypersonic Scramjet Aerospace Vehicle." International Journal of Aerospace Engineering 2017 (2017): 1–10. http://dx.doi.org/10.1155/2017/5496527.

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The Brazilian hypersonic scramjet aerospace vehicle 14-X B is a technological demonstrator of a hypersonic airbreathing propulsion system based on the supersonic combustion (scramjet) to be tested in flight into the Earth’s atmosphere at an altitude of 30 km and Mach number 7. The 14-X B has been designed at the Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics, Institute for Advanced Studies (IEAv), Brazil. The IEAv T3 Hypersonic Shock Tunnel is a ground-test facility able to produce high Mach number and high enthalpy flows in the test section close to those encountered during the flight of the 14-X B into the Earth’s atmosphere at hypersonic flight speeds. A 1 m long stainless steel 14-X B model was experimentally investigated at T3 Hypersonic Shock Tunnel, for freestream Mach numbers ranging from 7 to 8. Static pressure measurements along the lower surface of the 14-X B, as well as high-speed Schlieren photographs taken from the 5.5° leading edge and the 14.5° deflection compression ramp, provided experimental data. Experimental data was compared to the analytical theoretical solutions and the computational fluid dynamics (CFD) simulations, showing good qualitative agreement and in consequence demonstrating the importance of these methods in the project of the 14-X B hypersonic scramjet aerospace vehicle.

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2

Sarosh, Ali, Dong Yun Feng, and Muhammad Adnan. "An Aerothermodynamic Design Approach for Scramjet Combustors and Comparative Performance of Low-Efficiency Systems." Applied Mechanics and Materials 110-116 (October 2011): 4652–60. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.4652.

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This paper is aimed at development of an integrated approach based on analytical and computational aerothermodynamics for the special case of design of a 75% (low process-efficiency), hydrogen-fuelled, constant area combustor of a hypersonic airbreathing propulsion (HAP) system thereafter undertaking study of two types of HAP systems. The results of configurational aerothermodynamics implied that the most appropriate constant area configuration had a 30 degrees downstream wall-mounted fuel injector with a single acoustically stable cavity placed downstream of the fuel injection point. Moreover for identical flow inlet parameters and system configurations at lower levels of thermodynamic process efficiencies, the constant combustor-area (i.e. Scramjet 1) engine is superior in its performance to the constant combustor-pressure (i.e. Scramjet 2) engine for all values of fuel-air ratios.

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3

Park, Chul, and Wayland Griffith. "Nonequilibrium Hypersonic Aerothermodynamics." Physics Today 44, no. 2 (February 1991): 98. http://dx.doi.org/10.1063/1.2809999.

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4

Cheng, Sin-I. "Hypersonic propulsion." Progress in Energy and Combustion Science 15, no. 3 (January 1989): 183–202. http://dx.doi.org/10.1016/0360-1285(89)90008-7.

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5

Treanor, Charles E. "Book Review: Nonequilibrium Hypersonic Aerothermodynamics." AIAA Journal 29, no. 5 (May 1991): 857–58. http://dx.doi.org/10.2514/3.59940.

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6

Chapman, Gary T. "An overview of hypersonic aerothermodynamics." Communications in Applied Numerical Methods 4, no. 3 (May 1988): 319–25. http://dx.doi.org/10.1002/cnm.1630040305.

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7

Park, Chul. "Hypersonic Aerothermodynamics: Past, Present and Future." International Journal of Aeronautical and Space Sciences 14, no. 1 (March 30, 2013): 1–10. http://dx.doi.org/10.5139/ijass.2013.14.1.1.

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8

Sinha, Krishnendu. "Computational Fluid Dynamics in Hypersonic Aerothermodynamics." Defence Science Journal 60, no. 6 (November 20, 2010): 663–71. http://dx.doi.org/10.14429/dsj.60.604.

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9

Bose, Deepak, James L. Brown, Dinesh K. Prabhu, Peter Gnoffo, Christopher O. Johnston, and Brian Hollis. "Uncertainty Assessment of Hypersonic Aerothermodynamics Prediction Capability." Journal of Spacecraft and Rockets 50, no. 1 (January 2013): 12–18. http://dx.doi.org/10.2514/1.a32268.

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10

Lofthouse, Andrew J., Iain D. Boyd, and Michael J. Wright. "Effects of continuum breakdown on hypersonic aerothermodynamics." Physics of Fluids 19, no. 2 (February 2007): 027105. http://dx.doi.org/10.1063/1.2710289.

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11

Gochberg, Lawrence A. "Electron beam fluorescence methods in hypersonic aerothermodynamics." Progress in Aerospace Sciences 33, no. 7-8 (July 1997): 431–80. http://dx.doi.org/10.1016/s0376-0421(97)00002-x.

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12

Lo, Ming-Chung, Cheng-Chin Su, Jong-Shinn Wu, and Kun-Chang Tseng. "Modelling Rarefied Hypersonic Reactive Flows Using the Direct Simulation Monte Carlo Method." Communications in Computational Physics 18, no. 4 (October 2015): 1095–121. http://dx.doi.org/10.4208/cicp.080115.010515s.

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AbstractThis paper presents the implementation, validation and application of TCE (total collision energy) model for simulating hypersonic reactive flows in a parallel direct simulation Monte Carlo code, named PDSC++, using an unstructured grid. A series of benchmarking test cases, which include reproduction of theoretical rate constants in a single cell, 2D hypersonic flow past a cylinder and 2D-axisymmetric hypersonic flow past a sphere, were performed to validate the implementation. Finally, detailed aerothermodynamics of the flown reentry Apollo 6 Command Module at 105 km is simulated to demonstrate the powerful capability of the PDSC++in treating realistic hypersonic reactive flow at high altitude.

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13

Crowell, Andrew R., and Jack J. McNamara. "Model Reduction of Computational Aerothermodynamics for Hypersonic Aerothermoelasticity." AIAA Journal 50, no. 1 (January 2012): 74–84. http://dx.doi.org/10.2514/1.j051094.

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14

Lofthouse, Andrew J., Leonardo C. Scalabrin, and Iain D. Boyd. "Velocity Slip and Temperature Jump in Hypersonic Aerothermodynamics." Journal of Thermophysics and Heat Transfer 22, no. 1 (January 2008): 38–49. http://dx.doi.org/10.2514/1.31280.

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15

Rosato, Daniel A., Mason Thornton, Jonathan Sosa, Christian Bachman, Gabriel B. Goodwin, and Kareem A. Ahmed. "Stabilized detonation for hypersonic propulsion." Proceedings of the National Academy of Sciences 118, no. 20 (May 10, 2021): e2102244118. http://dx.doi.org/10.1073/pnas.2102244118.

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Future terrestrial and interplanetary travel will require high-speed flight and reentry in planetary atmospheres by way of robust, controllable means. This, in large part, hinges on having reliable propulsion systems for hypersonic and supersonic flight. Given the availability of fuels as propellants, we likely will rely on some form of chemical or nuclear propulsion, which means using various forms of exothermic reactions and therefore combustion waves. Such waves may be deflagrations, which are subsonic reaction waves, or detonations, which are ultrahigh-speed supersonic reaction waves. Detonations are an extremely efficient, highly energetic mode of reaction generally associated with intense blast explosions and supernovas. Detonation-based propulsion systems are now of considerable interest because of their potential use for greater propulsion power compared to deflagration-based systems. An understanding of the ignition, propagation, and stability of detonation waves is critical to harnessing their propulsive potential and depends on our ability to study them in a laboratory setting. Here we present a unique experimental configuration, a hypersonic high-enthalpy reaction facility that produces a detonation that is fixed in space, which is crucial for controlling and harnessing the reaction power. A standing oblique detonation wave, stabilized on a ramp, is created in a hypersonic flow of hydrogen and air. Flow diagnostics, such as high-speed shadowgraph and chemiluminescence imaging, show detonation initiation and stabilization and are corroborated through comparison to simulations. This breakthrough in experimental analysis allows for a possible pathway to develop and integrate ultra-high-speed detonation technology enabling hypersonic propulsion and advanced power systems.

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16

Guizzo, E. "Hypersonic flight [scramjet aircraft propulsion]." IEEE Spectrum 41, no. 1 (January 2004): 66. http://dx.doi.org/10.1109/mspec.2004.1317885.

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17

Weidner, J. P. "Hypersonic Propulsion-breaking the Thermal Barrier." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 207, no. 1 (January 1993): 47–59. http://dx.doi.org/10.1243/pime_proc_1993_207_246_02.

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The challenges of hypersonic propulsion impose unique features on the hypersonic vehicle—from large volume requirements to contain cryogenic fuel to airframe-integrated propulsion required to process sufficient quantities of air. Additional challenges exist in the design of the propulsion module that must be capable of efficiently processing air at very high enthalpies, adding and mixing fuel at supersonic speeds and expanding the exhaust products to generate thrust greater than drag. The paper explores the unique challenges of the integrated hypersonic propulsion system, addresses propulsion cycle selection to cope with the severe thermal environment and reviews the direction of propulsion research at hypervelocity speeds.

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18

Votta, R., A. Schettino, G. Ranuzzi, and S. Borrelli. "Hypersonic Low-Density Aerothermodynamics of Orion-Like Exploration Vehicle." Journal of Spacecraft and Rockets 46, no. 4 (July 2009): 781–87. http://dx.doi.org/10.2514/1.42663.

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19

Ahmed, M. Y. M., and N. Qin. "Recent advances in the aerothermodynamics of spiked hypersonic vehicles." Progress in Aerospace Sciences 47, no. 6 (August 2011): 425–49. http://dx.doi.org/10.1016/j.paerosci.2011.06.001.

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20

Xiaoxuan, Yan, Han Jinglong, Zhang Bing, and Yuan Haiwei. "Model reduction of aerothermodynamic for hypersonic aerothermoelasticity based on POD and Chebyshev method." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 10 (November 13, 2018): 3734–48. http://dx.doi.org/10.1177/0954410018808634.

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Accurate modeling of aerothermodynamics with low computational cost takes on a crucial role for the optimization and control of hypersonic vehicles. This study examines three reduced-order models (ROMs) to provide a reliable and efficient alternative approach for obtaining the aerothermodynamics of a hypersonic control surface. Coupled computational fluid dynamics (CFD) and computational thermostructural dynamics (CTSD) approaches are used to generate the snapshots for ROMs considering the interactions between aerothermodynamics, structural dynamics and heat transfer. One ROM adopts a surrogate approach named Kriging. The second ROM is constructed by the combination of Proper Orthogonal Decomposition (POD) and Kriging, namely, POD-Kriging. The accuracy of Kriging-based ROM is higher than that of POD-Kriging-based ROM, but the efficiency is lower. Therefore, to address the shortcomings of the above two approaches, a new ROM is developed that is composed of POD and modified Chebyshev polynomials, namely, POD-Chebyshev. The ROM based on POD-Chebyshev has the best precision and efficiency among the three ROMs and generally has less than 2% average maximum error for the studied problem.

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21

Bruno, Claudio, and Antonella Ingenito. "Some Key Issues in Hypersonic Propulsion." Energies 14, no. 12 (June 21, 2021): 3690. http://dx.doi.org/10.3390/en14123690.

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This paper summarizes and discusses some critical aspects of flying hypersonically. The first is the L/D (lift over drag) ratio determining thrust and that in turn depends on the slenderness Küchemann’s τ parameter. This second parameter is found to depend on the relative importance of wave versus friction drag. Ultimately, all engineering drag is argued to depend on vorticity formed at the expense of the vehicle kinetic energy, thus requiring work by thrust. Different mixing strategies are discussed and shown to depend also on mechanisms forming vorticity when the regime is compressible. Supersonic combustion is briefly analyzed and found, at sufficiently high combustor Mach, to take place locally at constant volume, unlike conventional Brayton cycles.

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22

Kobayashi, Hiroaki, Tetsuya Sato, and Nobuhiro Tanatsugu. "Optimum Design of Hypersonic Airbreathing Propulsion." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 50, no. 583 (2002): 335–42. http://dx.doi.org/10.2322/jjsass.50.335.

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23

Zeutzius, Michael, Toshiaki Setoguchi, Kunio Terao, and Hideo Miyanishi. "Propulsion System for Hypersonic Space Planes." Journal of Propulsion and Power 16, no. 2 (March 2000): 243–50. http://dx.doi.org/10.2514/2.5562.

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24

Kors, David L. "Combined cycle propulsion for hypersonic flight." Acta Astronautica 18 (January 1988): 191–200. http://dx.doi.org/10.1016/0094-5765(88)90099-9.

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25

Holman, Timothy D., and Iain D. Boyd. "Effects of continuum breakdown on hypersonic aerothermodynamics for reacting flow." Physics of Fluids 23, no. 2 (February 2011): 027101. http://dx.doi.org/10.1063/1.3541816.

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26

Yadav, R., and U. Guven. "Aerothermodynamics of a hypersonic projectile with a double-disk aerospike." Aeronautical Journal 117, no. 1195 (September 2013): 913–28. http://dx.doi.org/10.1017/s0001924000008587.

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AbstractThe use of aerospikes at the nose of a hypersonic vehicle can substantially reduce its drag; however, the associated heat flux at the reattachment point is very high for turbulent flows. In this paper, the aerothermodynamics of a generic projectile model represented by a hemisphere- cylinder, fitted axisymmetrically with an aerospike at the nose is investigated numerically with a commercially available Navier Stokes Solver. The base model is a hemisphere-cylinder with a diameter of 40mm and an overall length of 70mm. An aerospike protrudes axisymmetrically at the nose of the base model and has a hemispherical cap from which another aerospike protrudes which again has a hemispherical cap, thus forming a double-disk aerospike. Compressible, axisymmetric Navier-Stokes Equations are solved for turbulent hypersonic flow of thermally perfect air with free stream conditions of Mach No 6·2 at standard sea level atmospheric conditions. The results for the model with double-disk aerospikes are compared with those of hemisphere-cylinder without aerospike. The results suggest that the use of double-disk aerospike can favourably reduce the turbulent reattachment heat flux along with suitable drag reduction of the main body.

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27

Bhutta, Bilal A., and Clark H. Lewis. "Comparison of Hypersonic Experiments and PNS Predictions Part I: Aerothermodynamics." Journal of Spacecraft and Rockets 28, no. 4 (July 1991): 376–86. http://dx.doi.org/10.2514/3.55626.

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28

Votta, Raffaele, Antonio Schettino, and Aldo Bonfiglioli. "Hypersonic high altitude aerothermodynamics of a space re-entry vehicle." Aerospace Science and Technology 25, no. 1 (March 2013): 253–65. http://dx.doi.org/10.1016/j.ast.2012.02.001.

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29

Zhu, Jianwen, Luhua Liu, Guojian Tang, and Weimin Bao. "Robust adaptive gliding guidance for hypersonic vehicles." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 7 (February 9, 2017): 1272–82. http://dx.doi.org/10.1177/0954410017690547.

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A novel robust adaptive gliding guidance strategy based on multi-constrained analytical optimal guidance and online identification of aerodynamic coefficients for hypersonic vehicles is proposed. The guidance models are constructed in both longitudinal and lateral directions and optimal guidance law, namely required load factor, is designed with minimum energy consumption to satisfy terminal position, altitude and flight-path angle constraints. Considering aerodynamic coefficients are the core factors in the angle-of-attack calculation, it constructs the aerodynamic models in the form of quadratic polynomial function and employs extended Kalman filter to estimate the unknown parameters. Using the optimal guidance law based on current flight states and terminal constraints and the identified outputs to calculate angle-of-attack, then the gliding guidance mission can be achieved adaptively and robustly. Finally, the simulation experiments of high performance of the common aerothermodynamics-shell vehicle (CAV-H) are carried out to validate the guidance performance.

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30

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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31

Bhutta, Bilal A., and Clark H. Lewis. "Comparison of hypersonic experiments and PNS predictions. I - Aerothermodynamics. II - Aerodynamics." Journal of Spacecraft and Rockets 28, no. 4 (July 1991): 387–93. http://dx.doi.org/10.2514/3.26257.

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32

Dogra, V. K., R. G. Wilmoth, and J. N. Moss. "Aerothermodynamics of a 1.6-meter-diameter sphere in hypersonic rarefied flow." AIAA Journal 30, no. 7 (July 1992): 1789–94. http://dx.doi.org/10.2514/3.11137.

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33

Ren, Xiang, Junya Yuan, Bijiao He, Mingxing Zhang, and Guobiao Cai. "Grid criteria for numerical simulation of hypersonic aerothermodynamics in transition regime." Journal of Fluid Mechanics 881 (October 24, 2019): 585–601. http://dx.doi.org/10.1017/jfm.2019.756.

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Grid is an important factor in numerical simulation of hypersonic aerothermodynamics. This paper introduces three criteria for determining grid size in the transition flow regime when using the computational fluid dynamics (CFD) method or the direct simulation Monte Carlo (DSMC) method. The numerical relationship between these three criteria sizes is deduced according to the one-dimensional fluid theory. Then, the relationship is verified using the CFD method to simulate the flow around a two-dimensional cylinder. At the same time, the dependence of simulation accuracy on grid size in the CFD and DSMC methods is studied and the mechanism is given. The result shows that the simulation accuracy of heat flux especially depends on the normal grid size next to surfaces, where the $Re_{\mathit{cell},w}$ criterion and the $\unicode[STIX]{x1D706}_{w}$ criterion based on local parameters are applicable and equivalent, while the $Re_{\mathit{cell},\infty }$ criterion based on the free-stream parameter is only applicable under the assumption of constant viscosity coefficient and constant temperature wall conditions. On the other hand, the trend of the heat flux changing with grid size obtained by CFD and DSMC is exactly the opposite. Therefore, the grid size must be strictly satisfied with the grid criteria when comparing CFD with DSMC and even the hybrid DSMC with Navier–Stokes method.

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34

East, R. A. "Nonequilibrium Hypersonic Aerothermodynamics. By C. PARK. Wiley, 1990. 358 pp. £47.50." Journal of Fluid Mechanics 233 (December 1991): 692–93. http://dx.doi.org/10.1017/s0022112091230657.

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35

Brykina, I. G., B. V. Rogov, and G. A. Tirskiy. "Continuum models of rarefied gas flows in problems of hypersonic aerothermodynamics." Journal of Applied Mathematics and Mechanics 70, no. 6 (January 2006): 888–911. http://dx.doi.org/10.1016/j.jappmathmech.2007.01.013.

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36

Bugel, Mathilde, Philippe Reynier, and Arthur Smith. "Survey of European and Major ISC Facilities for Supporting Mars and Sample Return Mission Aerothermodynamics and Tests Required for Thermal Protection System and Dynamic Stability." International Journal of Aerospace Engineering 2011 (2011): 1–18. http://dx.doi.org/10.1155/2011/937629.

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In the frame of future sample return missions to Mars, asteroids, and comets, investigated by the European Space Agency, a review of the actual aerodynamics and aerothermodynamics capabilities in Europe for Mars entry of large vehicles and high-speed Earth reentry of sample return capsule has been undertaken. Additionally, capabilities in Canada and Australia for the assessment of dynamic stability, as well as major facilities for hypersonic flows available in ISC, have been included. This paper provides an overview of European current capabilities for aerothermodynamics and testing of thermal protection systems. This assessment has allowed the identification of the needs in new facilities or upgrade of existing ground tests for covering experimentally Mars entries and Earth high-speed reentries as far as aerodynamics, aerothermodynamics, and thermal protection system testing are concerned.

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37

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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38

Wang, Yuan, Jian Wang, Chuansheng Liu, and Ju Tian. "Research on Key Technologies of Hypersonic Vehicle." Journal of Physics: Conference Series 2183, no. 1 (January 1, 2022): 012011. http://dx.doi.org/10.1088/1742-6596/2183/1/012011.

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Abstract Hypersonic technology is an interdisciplinary research field, which has become the commanding point of new technology in the current aerospace field. Hypersonic vehicle is an important weapon to deal with future war and break through the missile defense system. It has great strategic deterrence significance in the military. This paper introduces the key technologies of hypersonic vehicle, such as integrated aerodynamic configuration, propulsion technology, thermal protection technology, navigation and control technology. The research status, main problems and development trends of various key technologies are summarized.

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39

Georgiadis, Nicholas J., Dennis A. Yoder, Manan A. Vyas, and William A. Engblom. "Status of turbulence modeling for hypersonic propulsion flowpaths." Theoretical and Computational Fluid Dynamics 28, no. 3 (January 16, 2014): 295–318. http://dx.doi.org/10.1007/s00162-013-0316-z.

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40

Liu, Qili, Damiano Baccarella, and Tonghun Lee. "Review of combustion stabilization for hypersonic airbreathing propulsion." Progress in Aerospace Sciences 119 (November 2020): 100636. http://dx.doi.org/10.1016/j.paerosci.2020.100636.

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41

JANISZEWSKI, Jacek, and Ryszard WOŹNIAK. "HYPERSONIC PROPULSION SYSTEMS – A REVIEW OF DESIGN SOLUTIONS." PROBLEMY TECHNIKI UZBROJENIA 161, no. 3 (November 29, 2022): 7–35. http://dx.doi.org/10.5604/01.3001.0016.1105.

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Abstract: The development of space rocket technology in the mid-twentieth century intensified research in the field of engineering materials used both for rockets and protection of space vehicles against damage, e.g., by meteorites. This development, in turn, forced the development of laboratory propulsion systems with hypersonic velocities, enabling the study and modelling of phenomena occurring at high impact velocities. Currently, to accelerate projectiles to hypersonic velocities, launching systems are applied that use the energy of the explosion of explosives or the combustion of liquid fuels, plasma, the energy of the electromagnetic field or light gases expanding. The work presents a review of the design solutions of various accelerators that enable the projectile to reach muzzle velocities above 3000 m/s. Particular attention has been paid to two-stage gas system, which uses light gases such as hydrogen and helium. The paper also presents the history and design of the first, and so far the only, Polish two-stage light gas gun developed at the Military University of Technology, with the help of which in 1973 a projectile weighing 0.5 g was fired at a speed of 4500 m/s. The paper ends with a description of the two-stage propellant system currently under construction at the Institute of Armament Technology, Faculty of Mechatronics, Armaments and Aviation, the Military University of Technology - with the considerable help of the HSW S.A. company from Stalowa Wola.

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42

Yang, Rui Guang, Jian Qiao Yu, and Yuan Chuan Shen. "Flight Dynamic Characteristic Analysis of a Generic Airbreathing Hypersonic Vehicle." Applied Mechanics and Materials 716-717 (December 2014): 724–29. http://dx.doi.org/10.4028/www.scientific.net/amm.716-717.724.

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Because of the high speed, strong coupling between aerodynamics and propulsion system, complex environmental conditions and new propulsion system, the airbreathing hypersonic vehicles have a complex dynamics characteristic. This paper use the generic hypersonic vehicle model (CSULA-GHV) to research this issue. The nonlinear longitudinal equations of motion are linearized based on the assumption of little perturbation. Analyze the dynamic characteristic on a feature point selected. The results show that, the stability of this model is poor. It has to design an efficient controller to adjust the poor stability.

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43

Zhai, Jian, Chen-An Zhang, Fa-Min Wang, and Wei-Wei Zhang. "Alleviation of lateral spillage of two-dimensional hypersonic inlet using waverider-configuration chines." International Journal of Modern Physics B 34, no. 14n16 (June 4, 2020): 2040074. http://dx.doi.org/10.1142/s0217979220400743.

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Hypersonic inlet is an important part of the propulsion system of hypersonic air-breathing vehicles. However, the performance of the two-dimensional hypersonic inlet, a major type of hypersonic inlets, is considerably deteriorated for lateral spillage. In this study, waverider-configuration chines mounted on the lateral sides of a two-dimensional three-staged external-compression hypersonic inlet for a Mach number of 6.0 are investigated to determine their ability to alleviate the lateral spillage. The chines are built by using a waverider design method. The numerical results suggest that a severe flow spillage induced by three-dimensional effect shows up near the lateral edge of the inlet without chines, which degrades the mass-flow ratio and flow uniformity. In contrast, the waverider-configuration chines effectively alleviate the lateral spillage. Consequently, the mass-flow ratio and the flow uniformity are both improved significantly.

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44

Moss, James N. "Direct Simulation Monte Carlo Simulations of Ballute Aerothermodynamics Under Hypersonic Rarefied Conditions." Journal of Spacecraft and Rockets 44, no. 2 (March 2007): 289–98. http://dx.doi.org/10.2514/1.22706.

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45

Sourgen, Frédéric, Joëlle Fontaine, François Garçon, J. L. Verant, C. Pelissier, Jean Pierre Tribot, Pierre Van Hauwaert, Martin Spel, and Jan Vos. "Effect of steps and gaps on aerothermodynamics for the IXV hypersonic vehicle." International Journal of Aerodynamics 2, no. 2/3/4 (2012): 130. http://dx.doi.org/10.1504/ijad.2012.049132.

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Yang, Xiaofeng, Yewei Gui, Wei Tang, Yanxia Du, Lei Liu, Guangming Xiao, and Dong Wei. "Surface thermochemical effects on TPS-coupled aerothermodynamics in hypersonic Martian gas flow." Acta Astronautica 147 (June 2018): 445–53. http://dx.doi.org/10.1016/j.actaastro.2018.03.055.

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47

Zhang, Xi-bin, and Qun Zong. "Modeling and Analysis of an Air-Breathing Flexible Hypersonic Vehicle." Mathematical Problems in Engineering 2014 (2014): 1–9. http://dx.doi.org/10.1155/2014/264247.

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By using light-weighted material in hypersonic vehicle, the vehicle body can be easily deformed. The mutual couplings in aerodynamics, flexible structure, and propulsion system will bring great challenges for vehicle modeling. In this work, engineering estimated method is used to calculate the aerodynamic forces, moments, and flexible modes to get the physics-based model of an air-breathing flexible hypersonic vehicle. The model, which contains flexible effects and viscous effects, can capture the physical characteristics of high-speed flight. To overcome the analytical intractability of the model, a simplified control-oriented model of the hypersonic vehicle is presented with curve fitting approximations. The control-oriented model can not only reduce the complexity of the model, but also retain aero-flexible structure-propulsion interactions of the physics-based model and can be applied for nonlinear control.

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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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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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Sura, J., V. Menezes, A. Kirthyvasan, and V. Kulkarni. "Estimation of Skin Friction Drag on a Model in Hypersonic Shock Tunnel." Applied Mechanics and Materials 232 (November 2012): 234–39. http://dx.doi.org/10.4028/www.scientific.net/amm.232.234.

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Viscous drag on the internal surfaces of a notional scramjet engine model has been estimated through Reynolds analogy, using measured wall heat transfer rates, in a shock tunnel at a hypersonic Mach number of 8. The study has been carried out without fuel injection and at zero degree angle of incidence of the model with the freestream. The heat transfer rate measurements were carried out on the upper and lower internal surfaces of the engine employing fast response E-type thermocouples. Application of Reynolds analogy to the wall heat transfer rates yielded the skin friction coefficient, through which the viscous drag on the surfaces could be determined. The measurements predict the salient features of the flow field of the model and are a novel reference on the data to the researchers working in the area of slender-body, hypersonic aerothermodynamics.

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