Journal articles: 'Hypersonic'

1

Tuttle, S. L. "An Experiment for Teaching Hypersonic Aerodynamics to Undergraduate Mechanical Engineering Students." International Journal of Mechanical Engineering Education 28, no. 2 (April 2000): 151–62. http://dx.doi.org/10.7227/ijmee.28.2.4.

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An experiment designed to enhance the teaching of hypersonics to undergraduate mechanical engineering students is described. A small shock tunnel is used to demonstrate principles learned in the classroom. The pressures measured on two models at hypersonic Mach numbers are compared with suitable theoretical estimates. Typical results are shown and the success and relevance of the experiment is reported. Consideration is given to the teaching of such a highly specialized subject as hypersonic aerodynamics at the undergraduate level.

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2

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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Seguin, Jory, Song Gao, Wagdi George Habashi, Dario Isola, and Guido Baruzzi. "A finite element solver for hypersonic flows in thermo-chemical non-equilibrium, Part I." International Journal of Numerical Methods for Heat & Fluid Flow 29, no. 7 (July 1, 2019): 2352–88. http://dx.doi.org/10.1108/hff-09-2018-0498.

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Purpose This paper aims to describe the physical and numerical modeling of a new computational fluid dynamics solver for hypersonic flows in thermo-chemical non-equilibrium. The code uses a blend of numerical techniques to ensure accuracy and robustness and to provide scalability for advanced hypersonic physics and complex three-dimensional (3D) flows. Design/methodology/approach The solver is based on an edge-based stabilized finite element method (FEM). The chemical and thermal non-equilibrium systems are loosely-coupled to provide flexibility and ease of implementation. Chemical non-equilibrium is modeled using a laminar finite-rate chemical kinetics model while a two-temperature model is used to account for thermodynamic non-equilibrium. The systems are solved implicitly in time to relax numerical stiffness. Investigations are performed on various canonical hypersonic geometries in two-dimensional and 3D. Findings The comparisons with numerical and experimental results demonstrate the suitability of the code for hypersonic non-equilibrium flows. Although convergence is shown to suffer to some extent from the loosely-coupled implementation, trading a fully-coupled system for a number of smaller ones improves computational time. Furthermore, the specialized numerical discretization offers a great deal of flexibility in the implementation of numerical flux functions and boundary conditions. Originality/value The FEM is often disregarded in hypersonics. This paper demonstrates that this method can be used successfully for these types of flows. The present findings will be built upon in a later paper to demonstrate the powerful numerical ability of this type of solver, particularly with respect to robustness on highly stretched unstructured anisotropic grids.

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Pletzer, Johannes, Didier Hauglustaine, Yann Cohen, Patrick Jöckel, and Volker Grewe. "The climate impact of hydrogen-powered hypersonic transport." Atmospheric Chemistry and Physics 22, no. 21 (November 8, 2022): 14323–54. http://dx.doi.org/10.5194/acp-22-14323-2022.

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Abstract. Hypersonic aircraft flying at Mach 5 to 8 are a means for traveling very long distances in extremely short times and are even significantly faster than supersonic transport (Mach 1.5 to 2.5). Fueled with liquid hydrogen (LH2), their emissions consist of water vapor (H2O), nitrogen oxides (NOx), and unburned hydrogen. If LH2 is produced in a climate- and carbon-neutral manner, carbon dioxide does not have to be included when calculating the climate footprint. H2O that is emitted near the surface has a very short residence time (hours) and thereby no considerable climate impact. Super- and hypersonic aviation emit at very high altitudes (15 to 35 km), and H2O residence times increase with altitude from months to several years, with large latitudinal variations. Therefore, emitted H2O has a substantial impact on climate via high altitude H2O changes. Since the (photo-)chemical lifetime of H2O largely decreases at altitudes above 30 km via the reaction with O(1D) and via photolysis, the question is whether the H2O climate impact from hypersonics flying above 30 km becomes smaller with higher cruise altitude. Here, we use two state-of-the-art chemistry–climate models and a climate response model to investigate atmospheric changes and respective climate impacts as a result of two potential hypersonic fleets flying at 26 and 35 km, respectively. We show, for the first time, that the (photo-)chemical H2O depletion of H2O emissions at these altitudes is overcompensated by a recombination of hydroxyl radicals to H2O and an enhanced methane and nitric acid depletion. These processes lead to an increase in H2O concentrations compared to a case with no emissions from hypersonic aircraft. This results in a steady increase with altitude of the H2O perturbation lifetime of up to 4.4±0.2 years at 35 km. We find a 18.2±2.8 and 36.9±3.4 mW m−2 increase in stratosphere-adjusted radiative forcing due to the two hypersonic fleets flying at 26 and 35 km, respectively. On average, ozone changes contribute 8 %–22 %, and water vapor changes contribute 78 %–92 % to the warming. Our calculations show that the climate impact, i.e., mean surface temperature change derived from the stratosphere-adjusted radiative forcing, of hypersonic transport is estimated to be roughly 8–20 times larger than a subsonic reference aircraft with the same transport volume (revenue passenger kilometers) and that the main contribution stems from H2O.

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5

Fan, Y., J. Chang, W. Bao, and D. Yu. "Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets." Aeronautical Journal 114, no. 1157 (July 2010): 445–50. http://dx.doi.org/10.1017/s0001924000003924.

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Abstract The unsteady flowfield of a series of mixed-compression hypersonic inlets with different bleeding rates were numerically simulated. Firstly unstart oscillatory flow of hypersonic inlets caused by downstream massflow choking was discussed. Then the effects of boundary layer bleeding on the averaged performance parameter of hypersonic inlets, and on the dominant amplitude and frequency of unstart oscillatory flow of hypersonic inlets were presented. The reasons why the boundary-layer bleeding can suppress unstart oscillatory flow of hypersonic inlets were analysed. In conclusion, the averaged performance parameter of hypersonic inlets during a big buzz is improved greatly, and the dominant frequency of unstart oscillatory flow of hypersonic inlets is reduced in contrast with no bleeding, and all these are benefit to the design and operation of hypersonic inlets.

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Chang, J., D. Yu, W. Bao, Y. Fan, and Y. Shen. "Effects of boundary-layers bleeding on unstart/restart characteristics of hypersonic inlets." Aeronautical Journal 113, no. 1143 (May 2009): 319–27. http://dx.doi.org/10.1017/s0001924000002992.

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Abstract A series of mixed-compression hypersonic inlets at different bleeding rates were simulated at different freestream conditions in this paper. The unstart/restart characteristics of hypersonic inlets were analysed and the reasons why the unstart/restart phenomenon is in existence is presented. The unstart/restart characteristics of hypersonic inlets at different bleeding rates were given. The effects of boundary-layer bleeding on the performance parameter (mass-captured coefficient, total-pressure recovery coefficient), starting and restarting Mach number of hypersonic inlets were discussed. In conclusion, boundary-layer bleeding can improve the performance parameter of hypersonic inlets, and can reduce the starting and restarting Mach number, and can broad the operation range of the hypersonic inlet.

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7

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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8

Chekov, A., and S. Babkina. "Hypersonic Weapons: Evolution or Revolution?" International Trends / Mezhdunarodnye protsessy 21, no. 2 (December 7, 2023): 83–102. http://dx.doi.org/10.17994/it.2023.21.2.73.5.

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Hypersonic strike systems have become a driving force in the development of offensive weapons. Academic literature offers two perspectives on the prospects of their impact on the military-strategic situation. One approach tends to position hypersonic weapons as a revolutionary technology, while the other proceeds from the premise that hypersonic strike systems represent an evolutionary development of offensive systems. The objective of this article is to establish the specifics and limits of the hypersonic weapons impact on the existing military-strategic balance. The paper analyzes the problem of hypersonic weapons classification, their role and place in military strategy, as well as the evolution and prospects of the Russian, U.S. and Chinese programs on hypersonic weapons. The authors conclude that the advantages of hypersonic weapons cannot automatically be transformed into a guaranteed success amid a full-scale military conflict and are largely available to other strike systems based on less advanced technological solutions. The key scenario, where the benefits of hypersonic weapons can be realized the most, is a limited conflict, in which they are used for the surprise defeat of highly-protected priority targets and the establishment of theater domination. This is evidenced by the hypersonic development programs of the leading military powers – Russia, the United States, and China, – each of which is more or less committed to developing medium- and short-range systems. The implications of the unfolding hypersonic arms race for strategic stability are ambiguous. On the one hand, forward deployment of such systems increases the risks of escalation; reduced flight time to enemy strategic infrastructure facilities encourages the adversary to adopt more aggressive retaliation postures based on the principle of launch-on-warning rather than post-attack. On the other hand, the possession of hypersonic weapons by both sides in the same theater increases their mutual vulnerability and can thus play a stabilizing role.

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9

LEES, LESTER. "Hypersonic Flow." Journal of Spacecraft and Rockets 40, no. 5 (September 2003): 700–735. http://dx.doi.org/10.2514/2.6897.

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10

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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11

NISHIDA, Michio. "Hypersonic Flows." Journal of the Society of Mechanical Engineers 92, no. 852 (1989): 982–86. http://dx.doi.org/10.1299/jsmemag.92.852_982.

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12

Guizzo, E. "Hypersonic Flight." IEEE Spectrum 41, no. 1 (January 2004): 58. http://dx.doi.org/10.1109/mspec.2004.1259370.

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13

Anastasia Kostina. "HYPERSONIC MESSAGE." Current Digest of the Russian Press, The 76, no. 001-003 (January 21, 2024): 22–23. http://dx.doi.org/10.21557/dsp.95519844.

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14

Su, Linfeng, Jinbo Wang, and Hongbo Chen. "A Real-Time and Optimal Hypersonic Entry Guidance Method Using Inverse Reinforcement Learning." Aerospace 10, no. 11 (November 7, 2023): 948. http://dx.doi.org/10.3390/aerospace10110948.

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The mission of hypersonic vehicles faces the problem of highly nonlinear dynamics and complex environments, which presents challenges to the intelligent level and real-time performance of onboard guidance algorithms. In this paper, inverse reinforcement learning is used to address the hypersonic entry guidance problem. The state-control sample pairs and state-rewards sample pairs obtained by interacting with hypersonic entry dynamics are used to train the neural network by applying the distributed proximal policy optimization method. To overcome the sparse reward problem in the hypersonic entry problem, a novel reward function combined with a sophisticated discriminator network is designed to generate dense optimal rewards continuously, which is the main contribution of this paper. The optimized guidance methodology can achieve good terminal accuracy and high success rates with a small number of trajectories as datasets while satisfying heating rate, overload, and dynamic pressure constraints. The proposed guidance method is employed for two typical hypersonic entry vehicles (Common Aero Vehicle-Hypersonic and Reusable Launch Vehicle) to demonstrate the feasibility and potential. Numerical simulation results validate the real-time performance and optimality of the proposed method and indicate its suitability for onboard applications in the hypersonic entry flight.

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15

Cheng, H. K. "Book Review Advances in Hypersonics, Vol. 1: Defining the Hypersonic Environment." AIAA Journal 32, no. 10 (October 1994): 2137–39. http://dx.doi.org/10.2514/3.48309.

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16

Liu, Yanbin, Yanhui Tong, and Feiteng Jin. "Control law design of hypersonic vehicles using the elastic surrogate model." Journal of Low Frequency Noise, Vibration and Active Control 39, no. 1 (March 11, 2019): 216–29. http://dx.doi.org/10.1177/1461348419835131.

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This paper presents a novel control design strategy for the hypersonic vehicle using the elastic surrogate model. First, the parametric model is established for the rigid mode of the hypersonic vehicle based on the engineering estimation and panel methods. Then, the beam surrogate model is applied to identify the elastic mode of the hypersonic vehicle, and the complete parametric model including the rigid and elastic modes is obtained accordingly. Afterward, the control-relevant model is acquired based on the Morris sensitivity analysis method. Furthermore, the control system using the surrogate model is proposed for the hypersonic vehicle to suppress elastic disturbances and maintain system stability. Finally, an illustrative example of the hypersonic vehicle is provided to verify the effectiveness of the presented methods.

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Wang, Jiang-Feng, Jia-Wei Li, Fa-Ming Zhao, and Xiao-Feng Fan. "Numerical method of carbon-based material ablation effects on aero-heating for half-sphere." Modern Physics Letters B 32, no. 12n13 (May 10, 2018): 1840011. http://dx.doi.org/10.1142/s0217984918400110.

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A numerical method of aerodynamic heating with material thermal ablation effects for hypersonic half-sphere is presented. A surface material ablation model is provided to analyze the ablation effects on aero-thermal properties and structural heat conduction for thermal protection system (TPS) of hypersonic vehicles. To demonstrate its capability, applications for thermal analysis of hypersonic vehicles using carbonaceous ceramic ablators are performed and discussed. The numerical results show the high efficiency and validation of the method developed in thermal characteristics analysis of hypersonic aerodynamic heating.

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Rogers, Jacob A., Nathaniel Bass, Paul T. Mead, Aniket Mote, Gavin D. Lukasik, Matthew Intardonato, Khari Harrison, et al. "The Texas A&M University Hypervelocity Impact Laboratory: A modern aeroballistic range facility." Review of Scientific Instruments 93, no. 8 (August 1, 2022): 085106. http://dx.doi.org/10.1063/5.0088994.

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Novel engineering materials and structures are increasingly designed for use in severe environments involving extreme transient variations in temperature and loading rates, chemically reactive flows, and other conditions. The Texas A&M University Hypervelocity Impact Laboratory (HVIL) enables unique ultrahigh-rate materials characterization, testing, and modeling capabilities by tightly integrating expertise in high-rate materials behavior, computational and polymer chemistry, and multi-physics multiscale numerical algorithm development, validation, and implementation. The HVIL provides a high-throughput test bed for development and tailoring of novel materials and structures to mitigate hypervelocity impacts (HVIs). A conventional, 12.7 mm, smooth bore, two-stage light gas gun (2SLGG) is being used as the aeroballistic range launcher to accelerate single and simultaneously launched projectiles to velocities in the range 1.5–7.0 km/s. The aeroballistic range is combined with conventional and innovative experimental, diagnostic, and modeling capabilities to create a unique HVI and hypersonic test bed. Ultrahigh-speed imaging (10M fps), ultrahigh-speed schlieren imaging, multi-angle imaging, digital particle tracking, flash x-ray radiography, nondestructive/destructive inspection, optical and scanning electron microscopy, and other techniques are being used to characterize HVIs and study interactions between hypersonic projectiles and suspended aerosolized particles. Additionally, an overview of 65 2SLGG facilities operational worldwide since 1990 is provided, which is the most comprehensive survey published to date. The HVIL aims to ( i) couple recent theoretical developments in shock physics with advances in numerical methods to perform HVI risk assessments of materials and structures, ( ii) characterize environmental effects (water, ice, dust, etc.) on hypersonic vehicles, and ( iii) address key high-rate materials and hypersonics research problems.

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Zhu, Sheng, Bin Shi Xu, and Jiu Kun Yao. "High Quality Ceramic Coatings Sprayed by High Efficiency Hypersonic Plasma Spraying Gun." Materials Science Forum 475-479 (January 2005): 3981–84. http://dx.doi.org/10.4028/www.scientific.net/msf.475-479.3981.

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This paper introduced the structure of the high efficiency hypersonic plasma spraying gun and the effects of hypersonic plasma jet on the sprayed particles. The optimised spraying process parameters for several ceramic powders such as Al2O3, Cr2O3, ZrO2, Cr3C2 and Co-WC were listed. The properties and microstructure of the sprayed ceramic coatings were investigated. Nano Al2O3-TiO2 ceramic coating sprayed by using the high efficiency hypersonic plasma spraying was also studied. Compared with the conventional air plasma spraying, high efficiency hypersonic plasma spraying improves greatly the ceramic coatings quality but at low cost.

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20

YAN, Binbin, Zehuai LIN, Shuangxi LIU, and Jie YAN. "Research on integrated aircraft-engine control method of hypersonic vehicle based on dynamic inversion control." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 41, no. 5 (October 2023): 878–86. http://dx.doi.org/10.1051/jnwpu/20234150878.

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In order to reduce the influence of the coupling characteristics between the aircraft and engine of hypersonic vehicle, an integrated aircraft-engine control method of hypersonic vehicle is studied in this paper. Firstly, the control-oriented aircraft-engine integrated mathematical model of the hypersonic vehicle is established. Then, by using the nonlinear dynamic inversion (NDI) and the incremental nonlinear dynamic inversion (INDI), the outer loop control algorithm with slow attitude change and the inner loop control algorithm with fast angular rate change are respectively designed. Moreover, based on the online ontology model including aircraft-engine coupling characteristics of the hypersonic vehicle, the coupling control scheme of flight posture and engine of the hypersonic vehicle is designed in the form of control linkage. Finally, the reference model, error control, online estimation and other modules are introduced into the NDI controller to ensure the flight quality and robustness requirements of the hypersonic vehicle. The simulation results show that the aircraft-engine coupling control scheme based on the NDI achieves the expected control performance.

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Song, Lihao, Bowen Bai, Xiaoping Li, Gezhao Niu, Yanming Liu, Liang Zhao, and Hui Zhou. "Analysis of Hypersonic Platform-Borne SAR Imaging: A Physical Perspective." Remote Sensing 13, no. 23 (December 5, 2021): 4943. http://dx.doi.org/10.3390/rs13234943.

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The usage of a hypersonic platform for remote sensing application has promising prospects, especially for hypersonic platform-borne synthetic aperture radar (SAR) imaging. However, the high-speed of hypersonic platform will lead to extreme friction between the platform and air, which will cause the ionization of air. The ionized gas forms the plasma sheath wrapped around the hypersonic platform. The plasma sheath will severely affect the propagation of SAR signal and further affect the SAR imaging. Therefore, hypersonic platform-borne SAR imaging should be studied from a physical perspective. In this paper, hypersonic platform-borne SAR imaging under plasma sheath is analyzed. The SAR signal propagation in plasma sheath is computed using scatter matrix method. The proposed SAR signal model is verified by using a ground experiment system. Moreover, the effect of attenuation caused by plasma sheath on SAR imaging is studied under different SAR parameters and plasma sheath. The result shows that attenuation caused by plasma sheath will degrade the SAR imaging quality and even cause the point and area targets to be submerged into the noise. The real SAR images under plasma sheath also illustrate this phenomenon. Furthermore, by studying imaging results under different SAR and plasma parameters, it can be concluded that the severe degradation of SAR imaging quality appears at condition of high plasma sheath electron density and low SAR carrier frequency. The work in this paper will be beneficial for the study of hypersonic platform-borne SAR imaging and design of hypersonic SAR imaging systems in the future.

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Li, Jingpeng, KeDeng, Gang Wang, Guangming Zhang, Zhiqing Bai, and Xiaodong Lv. "An IPID Control Method for Aerodynamic Heating Ground Simulation of Hypersonic Vehicles." Journal of Physics: Conference Series 2527, no. 1 (June 1, 2023): 012059. http://dx.doi.org/10.1088/1742-6596/2527/1/012059.

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Abstract In order to accurately predict the thermal environment of hypersonic vehicles, many scholars have devoted themselves to the research related to the aerodynamic heating characteristics of hypersonic vehicles, which provides important solutions for the design of thermal protection systems. An IPID controller is designed for the aerothermal ground simulation system of hypersonic vehicles to complete the target tracking.

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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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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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Xiao, Song, Xian Si Tan, Hong Wang, and Zhi Fang Zuo. "Detection Performance Analysis of Space-Based Radar to near Space Hypersonic Target." Advanced Materials Research 981 (July 2014): 730–34. http://dx.doi.org/10.4028/www.scientific.net/amr.981.730.

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Aimed at the problem that it is hard to detect near space hypersonic target for conventional radar because of its high flight speed, flight height, and flight distance and so on, the detection performance of space-based radar to near space hypersonic target was analyzed. The characteristics of near space hypersonic target and the advantages of space-based radar was introducted, and then, the detection performances of space-based radar to near space hypersonic target from detection range, searching and tracking mode were studied. It has certain guiding significance for space-based radar development and perfection of near space detection system.

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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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Balakin, V. L., and M. M. Krikunov. "Disturbed motion of the hypersonic first stage of an aerospace system in climb." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 3 (October 31, 2019): 16–28. http://dx.doi.org/10.18287/2541-7533-2019-18-3-16-28.

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Disturbed motion of the hypersonic first stage of an aerospace system in climb is analyzed. Deviations of atmospheric density from standard values and deviations of aerodynamic force coefficients from reference values are taken as disturbances. Disturbance motion of the hypersonic first stage of a hypersonic vehicle with the optimal angle-of-attack schedule obtained for reference atmosphere and nominal aerodynamic characteristics is modeled. Deviations of terminal conditions of disturbed motion from the target values of velocity, altitude and flight path inclination are determined. The problem of minimum propellant mass consumed in the climb with acceleration to hypersonic velocity is solved for disturbed motion by the method of Pontryagin’s maximum principle. Optimal angle-of-attack schedules, optimal flight paths and finite values of the mass of the hypersonic first stage are determined. Comparative analysis of optimal control programs and flight paths for disturbed and undisturbed motion is made.

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Li, Zhaoying, and Shuai Shi. "\({\mathcal{L}_1}\) Adaptive Loss Fault Tolerance Control of Unmanned Hypersonic Aircraft with Elasticity." Aerospace 8, no. 7 (June 29, 2021): 176. http://dx.doi.org/10.3390/aerospace8070176.

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This paper investigates the fault tolerance control of hypersonic aircrafts with L1 adaptive control method in the presence of loss of actuator effectiveness fault. The hypersonic model considers the uncertainties caused by the features of nonlinearities and couplings. Elasticity is taken into account in hypersonic vehicle modeling which makes the model more accurate. A velocity L1 adaptive controller and an altitude L1 adaptive controller are designed to control flexible hypersonic vehicle model with actuator loss fault. A PID controller is designed as well for comparison. Finally, the simulation results are used to analyze the effectiveness of the controller. Compared to the results of PID controller, L1 controllers have better performance.

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Pajcin, Miroslav, Aleksandar Simonovic, Toni Ivanov, Dragan Komarov, and Slobodan Stupar. "Numerical analysis of a hypersonic turbulent and laminar flow using a commercial CFD solver." Thermal Science 21, suppl. 3 (2017): 795–807. http://dx.doi.org/10.2298/tsci160518198p.

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Computational fluid dynamics computations for two hypersonic flow cases using the commercial ANSYS FLUENT 16.2 CFD software were done. In this paper, an internal and external hypersonic flow cases were considered and analysis of the hypersonic flow using different turbulence viscosity models available in ANSYS FLUENT 16.2 as well as the laminar viscosity model were done. The obtained results were after compared and commented upon.

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Hu, Jichao, Juntao Chang, Lei Wang, Shibin Cao, and Wen Bao. "Unstart Coupling Mechanism Analysis of Multiple-Modules Hypersonic Inlet." Scientific World Journal 2013 (2013): 1–10. http://dx.doi.org/10.1155/2013/254376.

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The combination of multiplemodules in parallel manner is an important way to achieve the much higher thrust of scramjet engine. For the multiple-modules scramjet engine, when inlet unstarted oscillatory flow appears in a single-module engine due to high backpressure, how to interact with each module by massflow spillage, and whether inlet unstart occurs in other modules are important issues. The unstarted flowfield and coupling characteristic for a three-module hypersonic inlet caused by center module II and side module III were, conducted respectively. The results indicate that the other two hypersonic inlets are forced into unstarted flow when unstarted phenomenon appears on a single-module hypersonic inlet due to high backpressure, and the reversed flow in the isolator dominates the formation, expansion, shrinkage, and disappearance of the vortexes, and thus, it is the major factor of unstart coupling of multiple-modules hypersonic inlet. The coupling effect among multiple modules makes hypersonic inlet be more likely unstarted.

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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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Huang, Dedong, Xiaoxiang Hu, and Xunliang Yan. "Adaptive variable structure control of input delay non-minimum phase hypersonic flight vehicles." International Journal of Advanced Robotic Systems 14, no. 1 (January 1, 2017): 172988141668561. http://dx.doi.org/10.1177/1729881416685614.

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An adaptive variable structure control strategy is proposed for the output tracking control of input delay non-minimum hypersonic flight vehicles. The problem is challenging because of the complex nonlinearity of hypersonic flight vehicles and the existence of input delay. The nonlinear model of hypersonic flight vehicles is partially linearized, and a state tracking model is constructed based on the ideal internal dynamics of hypersonic flight vehicles. A filtered tracking error is introduced to handle the input delay. A variable structure control strategy is proposed for the stability of filtered tracking error system, and an adaptive law is established for the unknown perturbations. Finally, the effectiveness of the proposed control method is shown by the simulation results.

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Raza, Imran, and Nasir Mehmood. "HYPERSONIC WEAPON SYSTEMS – A NEW WAVE OF ARMS RACE IN THE INDIAN OCEAN REGION." Margalla Papers 27, no. 1 (June 30, 2023): 28–39. http://dx.doi.org/10.54690/margallapapers.27.1.149.

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Technological advancements and tactical applications have always played a significant role in determining the outcomes of military conflicts. The emergence of Hypersonic Weapon Systems is considered a game-changer in contemporary and future warfare, as it can potentially dominate the early stages of conflict. Major powers like the US, China and Russia are pursuing technological superiority by developing hypersonic weapons, which could undermine conventional strategic capabilities and render even the most advanced air and missile defences obsolete. However, there has been limited discussion on the impact of deploying hypersonic weapons in the Indian Ocean region and its implications on strategic stability in the Pakistan-India military matrix. This paper examines the induction of hypersonic weapons by the Indian Navy, utilising insights from security dilemma and conventional deterrence theories to navigate the complex strategic landscape in the region. It contributes to the ongoing debate on the relationship between the arms race and conventional deterrence in Pakistan and India, highlighting the risks of an arms race in the Indian Ocean region. Without strategic dialogue on regulating hypersonic weapons systems, the chances of escalation and conflict could increase significantly. Bibliography Entry Raza, Imran and Nasir Mehmood. 2023. "Hypersonic Weapon Systems – A New Wave of Arms Race in the Indian Ocean Region." Margalla Papers 27 (1): 28-39.

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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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Kocian, Travis S., Alexander J. Moyes, Helen L. Reed, Stuart A. Craig, William S. Saric, Steven P. Schneider, and Joshua B. Edelman. "Hypersonic Crossflow Instability." Journal of Spacecraft and Rockets 56, no. 2 (March 2019): 432–46. http://dx.doi.org/10.2514/1.a34289.

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36

Yang, R. J. "Hypersonic fin aerodynamics." Journal of Spacecraft and Rockets 31, no. 2 (March 1994): 339–41. http://dx.doi.org/10.2514/3.26443.

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Biegelsen, David K. "Focused Hypersonic Communication." Journal of the Acoustical Society of America 129, no. 1 (2011): 536. http://dx.doi.org/10.1121/1.3554776.

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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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Gorishnyy, Taras, Chaitanya K. Ullal, Martin Maldovan, Edwin L. Thomas, and Ji‐Hyun Jang. "Hypersonic phononic crystals." Journal of the Acoustical Society of America 120, no. 5 (November 2006): 3035. http://dx.doi.org/10.1121/1.4787173.

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CHIRIAC, Cătălin. "COUNTERING HYPERSONIC THREAT." BULLETIN OF "CAROL I" NATIONAL DEFENCE UNIVERSITY 11, no. 3 (October 20, 2022): 38–45. http://dx.doi.org/10.53477/2284-9378-22-80.

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Hypersonic missiles represent the new class of threats, capable declaratively and in a way that has not been proven in a theater of operations, to annihilate air and anti-missile defences that exist at this time. The sum of the new threat’s characteristics, high speed, increased maneuverability, and low flight altitude, get major concerns for air and missile defence, as effective detection and combat are reduced by compressing available time. Rethinking how to combat the new threats thus represents the main concern of military specialists in countries that want to complete their arsenals with new weapons.

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Williamson, Justin, and James J. Wirtz. "Hypersonic or just hype? Assessing the Russian hypersonic weapons program." Comparative Strategy 40, no. 5 (September 3, 2021): 468–81. http://dx.doi.org/10.1080/01495933.2021.1962198.

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42

Xiao, Song, Xian Si Tan, and Hong Wang. "Interacting Multiple Mode Tracking Algorithm Based on Modified Coordinate Turn Model." Applied Mechanics and Materials 610 (August 2014): 534–39. http://dx.doi.org/10.4028/www.scientific.net/amm.610.534.

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The continuing success of near space hypersonic aircraft flight test has become a real threat to China's space attack-defense system, In view of the problem that the single model cannot track such target effectively, an interacting multiple model (IMM) tracking algorithm based on modified cornering model (MCT) was proposed. First the characteristics of near space hypersonic target were analyzed, and then the target real-time angular velocity according to the target motion equation was estimated, finally the near space hypersonic target tracking through the IMM was carried out. The Monte Carlo simulation results show that the IMM tracking algorithm can effectively track near space hypersonic target, and the tracking accuracy and stability are superior to single model, it has certain practical significance.

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Balakin, V. L., and M. M. Krikunov. "Disturbed motion of a hypersonic vehicle in climb." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 2 (July 2, 2019): 7–20. http://dx.doi.org/10.18287/2541-7533-2019-18-2-7-20.

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Disturbed motion of a hypersonic vehicle in climb is analyzed. Deviations of atmospheric density from standard values and deviations of aerodynamic force coefficients from nominal values are taken as disturbances. Disturbed motion of a hypersonic vehicle with the optimum angle-of-attack schedule and nominal flight characteristics is modeled. Deviations of terminal conditions of disturbed motion from the target values of velocity, altitude and path inclination are determined. Using the method of Pontryagin’s maximum principle the problem of fuel mass minimum consumed in hypersonic acceleration climb is solved for disturbed motion. Optimal angle-of-attack schedules, optimal flight paths and finite values of the hypersonic vehicle’s mass are determined. Comparative analysis of optimal control programs and flight paths obtained for disturbed and undisturbed motion is carried out.

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Bao, Cunyu, Peng Wang, and Guojian Tang. "Integrated Guidance and Control for Hypersonic Morphing Missile Based on Variable Span Auxiliary Control." International Journal of Aerospace Engineering 2019 (May 5, 2019): 1–20. http://dx.doi.org/10.1155/2019/6413410.

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The morphing aircraft can improve the flight performance of hypersonic vehicles by satisfying the flight requirements of large airspace and large velocity field. In this paper, for the hypersonic variable span missile, the dynamic model and aerodynamic model are established on the variable span characteristic. The adaptive dynamic surface control back-stepping method is used to establish the integrated guidance and control (IGC) with terminal angular constraint in the dive phase of the hypersonic variable span missile. The span variety is used to assist the lift control to achieve fast and stable control for the centroid motion. The simulation results demonstrate that the feasibility and robustness of the IGC method of the hypersonic variable span missile is better than the invariable span.

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Huang, Bing, Aijun Li, and Bin Xu. "Adaptive fault tolerant control for hypersonic vehicle with external disturbance." International Journal of Advanced Robotic Systems 14, no. 1 (January 1, 2017): 172988141668713. http://dx.doi.org/10.1177/1729881416687136.

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In this article, an adaptive fault tolerant control strategy is proposed to solve the trajectory tracking problem of a generic hypersonic vehicle subjected to actuator fault, external disturbance, and input saturation. The longitudinal model of generic hypersonic vehicle is divided into velocity subsystem and altitude subsystem, in which dynamic inversion and backstepping are applied, respectively, to track the desired trajectories. For the unknown maximum disturbance upper bound, actuator fault, and input saturation constraint, adaptive laws are proposed to estimate these information online. Finally, numeric simulation is conducted in the cruise phase for generic hypersonic vehicle. Simulation results show that the controllers designed in this article can make generic hypersonic vehicle track the desired trajectories in the presence of actuator fault, external disturbance, and input saturation.

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Zheng, Hua, Junhao Liu, and Shiqiang Duan. "Novel Nonstationarity Assessment Method for Hypersonic Flutter Flight Tests." Mathematical Problems in Engineering 2018 (October 25, 2018): 1–12. http://dx.doi.org/10.1155/2018/9742591.

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Hypersonic aircraft have been rapidly developed in recent years both theoretically and experimentally. Aerothermoelastic simulation is very challenging due to its inherent complexity, but physical tests are a workable approach. Flutter tests with variable speed are a popular alternative to hypersonic tests which provide nonstationary structural response data. This paper proposes a nonstationarity assessment method based on energy distribution in the time-frequency domain. The proposed method reveals the nonstationarity level corresponding to the appropriate modal identification algorithm or flutter boundary prediction (FBP) method. Several classic flutter criteria are utilized to build a hypersonic aircraft FBP framework. Numerical simulation and experimental applications demonstrate the effectiveness and feasibility of the proposed method, which facilitates accurate flutter predictions for the subcritical turbulence response during hypersonic flutter flight.

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CERNAT, Romică. "Impactul tehnologiilor emergente și disruptive asupra domeniului militar." Gândirea Militară Românească 2021, no. 4 (November 2021): 230–45. http://dx.doi.org/10.55535/gmr.2021.4.13.

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Hypersonic missiles are a new category of weapons that have sparked intense debate among security experts. The hypersonic weapons, this combination of speed, accuracy, surprise, and maneuverability makes the defense against them more difficult than against standard ballistic or cruise missiles and therefore makes them more destabilizing. Capable of traveling over five times the speed of sound (Mach 5), and of performing evasive maneuvers mid-flight, they are considered practically impossible to intercept using conventional missile defense systems. Innovative nuclear and conventional weapon delivery systems are impressive and developing. These are grouped into three categories: intercontinental ballistic missiles, hypersonic delivery systems and new advanced strategic weapon delivery capabilities. These and other technological advances being made simultaneously may also impact arms control and strategic stability. Other characteristics of hypersonic systems, however, are potentially advantageous compared with ballistic missiles. Of particular interest are the ability to fly at low altitude, making detection by earth-based sensors difficult; the ability to maneuver during flight to avoid detection and interception; and the unpredictability of targets, since hypersonic vehicles do not follow a ballistic trajectory.

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CERNAT, Romică. "The Potential of Hypersonic Weapons and the Great Military Powers Strategy regarding their Production. Case Study." Romanian Military Thinking 2021, no. 4 (November 2021): 230–45. http://dx.doi.org/10.55535/rmt.2021.4.13.

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Hypersonic missiles are a new category of weapons that have sparked intense debate among security experts. The hypersonic weapons, this combination of speed, accuracy, surprise, and maneuverability makes the defense against them more difficult than against standard ballistic or cruise missiles and therefore makes them more destabilizing. Capable of traveling over five times the speed of sound (Mach 5), and of performing evasive maneuvers mid-flight, they are considered practically impossible to intercept using conventional missile defense systems. Innovative nuclear and conventional weapon delivery systems are impressive and developing. These are grouped into three categories: intercontinental ballistic missiles, hypersonic delivery systems and new advanced strategic weapon delivery capabilities. These and other technological advances being made simultaneously may also impact arms control and strategic stability. Other characteristics of hypersonic systems, however, are potentially advantageous compared with ballistic missiles. Of particular interest are the ability to fly at low altitude, making detection by earth-based sensors difficult; the ability to maneuver during flight to avoid detection and interception; and the unpredictability of targets, since hypersonic vehicles do not follow a ballistic trajectory.

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Law, Yee Wei, John Joshua Gliponeo, Dilpreet Singh, John McGuire, Jiajun Liang, Sook-Ying Ho, and Jill Slay. "Detecting and tracking hypersonic glide vehicles: A cybersecurity-engineering analysis of academic literature." International Conference on Cyber Warfare and Security 18, no. 1 (February 28, 2023): 189–98. http://dx.doi.org/10.34190/iccws.18.1.950.

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Hypersonic vehicles are vehicles travelling faster than Mach 5 (five times the speed of sound). Hypersonic technologies have existed since the end of the 1950s, but recent developments of defence applications have led to their resurgence. Hypersonic weapons can be hypersonic (powered) cruise missiles or hypersonic glide vehicles (HGVs). The near-space trajectories of HGV, combined with their superior manoeuvrability, enable HGVs to evade existing space and terrestrial sensors used to track ballistic missiles, posing an immediate threat to today’s radar networks and making HGVs well-suited for intercontinental (> 5500 km) targets. Securing HGV detection and tracking systems is of great interest to at-risk nations and cybersecurity researchers alike. However, like hypersonic flight technologies, HGV defence technologies are heavily guarded secrets. The shortage of public-domain information did not stop academia from proposing various detection and tracking schemes, but a reasonable question is: “How credible and useful is current public-domain information, including academic publications, on HGV detection and tracking for academic researchers to base their cybersecurity research on?” To answer this question, we scanned and critically reviewed public-domain literature on HGV detection and tracking. We then identified ambiguities and knowledge gaps in the literature. In this paper, we provide a concise version of our multivocal literature review and an analysis of the identified ambiguities and knowledge gaps in our attempt to answer our earlier question.

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Yang, Shaohua, and Xia Li. "Nonlinearly Parametrized Modeling and Adaptive Control for a Generic Hypersonic Vehicle." Processes 11, no. 1 (January 13, 2023): 263. http://dx.doi.org/10.3390/pr11010263.

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This paper constructs a nonlinearly parametrized hypersonic cruise vehicle model on the basis of the existing on-orbit flight data using a curve-fitting technique. The hypersonic cruise vehicle system is separated into two interconnected subsystem: an attitude subsystem with rotational dynamics and a velocity subsystem with engine dynamics. The continuous adaptive controllers are designed for two subsystems using a novel function bounding technique and appropriate coordinate transformations, respectively, which ensure the global boundedness of all signals and achieve the non-zero equilibrium point regulation of nonlinearly parametrized hypersonic vehicle systems. One of the implications of this result is that growing nonlinearities in the uncertain model of the hypersonic vehicle system may be allowed for global stabilization. A simulation result verifies the effectiveness of the proposed adaptive control scheme.

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Journal articles on the topic 'Hypersonic'

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