Relevant bibliographies by topics / Hypersonic Vehicles

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Hypersonic Vehicles'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Hypersonic Vehicles"

1

Gao, Mengjing, Tian Yan, Quancheng Li, Wenxing Fu, and Jin Zhang. "Intelligent Pursuit–Evasion Game Based on Deep Reinforcement Learning for Hypersonic Vehicles." Aerospace 10, no. 1 (January 15, 2023): 86. http://dx.doi.org/10.3390/aerospace10010086.

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As defense technology develops, it is essential to study the pursuit–evasion (PE) game problem in hypersonic vehicles, especially in the situation where a head-on scenario is created. Under a head-on situation, the hypersonic vehicle’s speed advantage is offset. This paper, therefore, establishes the scenario and model for the two sides of attack and defense, using the twin delayed deep deterministic (TD3) gradient strategy, which has a faster convergence speed and reduces over-estimation. In view of the flight state–action value function, the decision framework for escape control based on the actor–critic method is constructed, and the solution method for a deep reinforcement learning model based on the TD3 gradient network is presented. Simulation results show that the proposed strategy enables the hypersonic vehicle to evade successfully, even under an adverse head-on scene. Moreover, the programmed maneuver strategy of the hypersonic vehicle is improved, transforming it into an intelligent maneuver strategy.
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Huo, Lin, and Tao Yang. "The Rapid Engineering Aero-Heating Calculation Method for Hypersonic Vehicles." Applied Mechanics and Materials 775 (July 2015): 59–67. http://dx.doi.org/10.4028/www.scientific.net/amm.775.59.

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The rapid engineering aero-heating calculation method for hypersonic vehicles is established for the question of computational efficiency during conceptual design stage. First the pressure distribution along vehicle’s surface is calculated by modified Newtonian theory. Secondly, the streamline along the surface is calculated with Newtonian steepest decent concept. Then by using reference enthalpy method, the heat flux on the surface is given. Finally, the heat flux on the surfaces of blunted cone, lifting body and wave-rider vehicle is calculated The analysis result shows the method used in this paper is fit for hypersonic vehicles, and can satisfies the aero-heating calculation during conceptual design stage in both efficiency and accuracy.
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Jia, Shengwei, Xiao Wang, Fugui Li, and Yulin Wang. "Distributed Analytical Formation Control and Cooperative Guidance for Gliding Vehicles." International Journal of Aerospace Engineering 2020 (November 17, 2020): 1–14. http://dx.doi.org/10.1155/2020/8826968.

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This paper addresses the analytical formation control and cooperative guidance problem for multiple hypersonic gliding vehicles under distributed communication. The gliding flight of the hypersonic gliding vehicle is divided into formation control phase and time coordination phase. In formation control phase, based on the idea of path tracking, the formation controller is designed using the second-order consensus protocol with normal positions as the coordination variables. In time coordination phase, based on the quasi-equilibrium gliding condition and the assumption of uniform deceleration motion, the analytical expression of time to go is derived. Then, the cooperative guidance method is developed using the first-order consensus protocol with time to go as the coordination variable. The proposed method takes full consideration of the characteristics of hypersonic gliding vehicle, such as complex nonlinear dynamics, no thrust, and quasi-equilibrium gliding condition, and no online numerical iteration is needed, which is well applicable for hypersonic gliding vehicles. Simulation results demonstrate the effectiveness of the formation control and cooperative guidance method.
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Zhao, Ziyang, Bo Bai, Kai Yuan, Rongxin Tang, Jiawei Xiong, and Kaili Wang. "Effect of Terahertz Antenna Radiation in Hypersonic Plasma Sheaths with Different Vehicle Shapes." Applied Sciences 12, no. 4 (February 10, 2022): 1811. http://dx.doi.org/10.3390/app12041811.

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Communication blackout caused by the plasma sheath surrounding hypersonic vehicles is a serious threat to the safety of hypersonic vehicles. Terahertz (THz) communication is considered to be a potential solution to the blackout problem. However, hypersonic plasma sheaths can affect not only electromagnetic wave propagation, but also the radiation performance of onboard antennae. Therefore, it is necessary to investigate the radiation performance of THz antennae in hypersonic plasma sheaths. In the present study, the impact of vehicle shapes (blunt-coned and sharp-coned vehicles) on plasma sheaths was investigated numerically. The antenna involved in the present study was a 0.14 THz array antenna. The antenna performance was compared with the aspects of mainlobe gain, mainlobe direction, and mainlobe width. The present study shows that both sharp-coned and blunt-coned plasma sheaths are inhomogeneous. Nevertheless, their structures are obviously different. Such differences yield different antenna performance in sharp-coned and blunt-coned plasma sheaths. Compared with sharp-coned plasma sheaths, blunt-coned plasma sheaths can refract antenna radiation direction, which can result in worsened communication quality in the expected direction. In addition, the phenomena are discussed in detail. Suggestions of vehicle shape design to guarantee communication quality in hypersonic flight missions are proposed.
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Cheng, Yunpeng, Xiaodong Yan, and Feng Cheng. "Trajectory Estimation of Hypersonic Glide Vehicle Based on Analysis of Aerodynamic Performance." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 37, no. 6 (December 2019): 1102–10. http://dx.doi.org/10.1051/jnwpu/20193761102.

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Due to high speed and high maneuverability of hypersonic glide vehicles (HGVs), the state estimation of such targets has always been a research hotspot. In order to improve accuracy of the trajectory estimation, a nonlinear aerodynamic parameter model for target estimation based on aerodynamic performance analysis is proposed. Firstly, the dynamic characteristics of the hypersonic glide vehicle during the hypersonic gliding stage was analyzed. Then, aiming at HTV-2-liked vehicle, the engineering calculation method was used to form the reference aerodynamic model for the target estimation. Secondly, a deviation model described by first-order Markov process was introduced to compensate the uncertainties of the unknown maneuver information from the target. Finally, extended Kalman filter was utilized to estimate the state of the target. The simulation results show that the proposed model is able to improve the accuracy of acceleration estimation for the HTV-2-liked hypersonic gliding vehicles.
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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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Yi, Yang, Lubing Xu, Hong Shen, and Xiangxiang Fan. "Disturbance observer-based L1 robust tracking control for hypersonic vehicles with T-S disturbance modeling." International Journal of Advanced Robotic Systems 13, no. 6 (November 16, 2016): 172988141667111. http://dx.doi.org/10.1177/1729881416671117.

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This article concerns a disturbance observer-based L1 robust anti-disturbance tracking algorithm for the longitudinal models of hypersonic flight vehicles with different kinds of unknown disturbances. On one hand, by applying T-S fuzzy models to represent those modeled disturbances, a disturbance observer relying on T-S disturbance models can be constructed to track the dynamics of exogenous disturbances. On the other hand, L1 index is introduced to analyze the attenuation performance of disturbance for those unmodeled disturbances. By utilizing the existing convex optimization algorithm, a disturbance observer-based proportional-integral-controlled input is proposed such that the stability of hypersonic flight vehicles can be ensured and the tracking error for velocity and altitude in hypersonic flight vehicle models can converge to equilibrium point. Furthermore, the satisfactory disturbance rejection and attenuation with L1 index can be obtained simultaneously. Simulation results on hypersonic flight vehicle models can reflect the feasibility and effectiveness of the proposed control algorithm.
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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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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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Tian, Xian Ke, Shuo Tang, and Qiang Jun Zhu. "Flight Dynamics Modeling and Analysis of Flexible Hypersonic Flight Vehicles." Applied Mechanics and Materials 275-277 (January 2013): 513–17. http://dx.doi.org/10.4028/www.scientific.net/amm.275-277.513.

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Facing the difficulty of flight dynamics modeling about flexible hypersonic flight vehicles, from view on the Lagrange’s equations based on dynamic first principle, this paper firstly developed kinetic energy and flexibility potential energy of the vehicle, then achieved concise flight dynamics equations by quasi-coordinates which could fully include coupling characteristics of flight dynamics, and lastly made necessary analysis about the equations. The result of study illustrates that flight dynamics equations of flexible hypersonic flight vehicles based on quasi-coordinates can satisfy the research of dynamics, stability, control,couplings and so on.
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Dissertations / Theses on the topic "Hypersonic Vehicles"

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Gibson, Travis Eli. "Adaptive control of hypersonic vehicles." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/46635.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2008.
Includes bibliographical references (p. 105-109).
The guidance, navigation and control of hypersonic vehicles are highly challenging tasks due to the fact that the dynamics of the airframe, propulsion system and structure are integrated and highly interactive. Such a coupling makes it difficult to model various components with a requisite degree of accuracy. This in turn makes various control tasks including altitude and velocity command tracking in the cruise phase of the flight extremely difficult. This work proposes an adaptive controller for a hypersonic cruise vehicle subject to: aerodynamic uncertainties, center-of-gravity movements, actuator saturation, failures, and time-delays. The adaptive control architecture is based on a linearized model of the underlying rigid body dynamics and explicitly accommodates for all uncertainties. Within the control structure is a baseline Proportional Integral Filter commonly used in optimal control designs. The control design is validated using a highfidelity HSV model that incorporates various effects including coupling between structural modes and aerodynamics, and thrust pitch coupling. Analysis of the Adaptive Robust Controller for Hypersonic Vehicles (ARCH) is carried out using a control verification methodology. This methodology illustrates the resilience of the controller to the uncertainties mentioned above for a set of closed-loop requirements that prevent excessive structural loading, poor tracking performance, and engine stalls. This analysis enables the quantification of the improvements that result from using and adaptive controller for a typical maneuver in the V-h space under cruise conditions.
by Travis Eli Gibson.
S.M.
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Chamitoff, Gregory Errol. "Robust intelligent flight control for hypersonic vehicles." Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/44275.

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Ahmed, Mahmoud Y. M. "Aerothermodynamic design optimization of spiked hypersonic vehicles." Thesis, University of Sheffield, 2010. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.531198.

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Singh, Amarjit. "Experimental study of slender vehicles at hypersonic speeds." Thesis, Cranfield University, 1996. http://hdl.handle.net/1826/4257.

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An experimental investigation of the hypersonic flow over (i) a wing-body configuration, (ii) a hemi-spherically blunted cone-cylinder body and (iii) a one-half- power-law body has been conducted for M,, = 8.2 and Re,, = 9.35x104 per cm. The tests were performed at model incidences, a=0,5 and 10° for flap deflection angles, (3 = 0,5,15, and 25° for the wing-body. The incidence ranged from -3 to 10° for the cone- cylinder and -5 to 15° for the power-law body. (i) The schlieren pictures showing top and side views of the model indicate that the body nose shock does not intersect the wing throughout the range of a under investigation. Detailed pressure measurements on the lower surface of the wing and flap along with the liquid crystal pictures suggest that the body nose shock does not strike the flap surfaces either. The wing leading edge shock is found to be attached at a=0 and 5° but detached at a= 10°. The liquid crystal pictures and surface pressure measurements indicated attached flow on the lower surface of the wing and flap for 13 =0 and 5° at all values of a under test. However at a= 0°, as the flap angle is increased to 15° the flow separates ahead of the hinge line. As incidence is increased the boundary layer becomes transitional giving rise to complex separation patterns around the flap hinge line. The spherically blunted body nose causes strong entropy layer effects over the wing and the trailing edge flap. A Navier-Stokes solution indicated a thick entropy layer of approximately constant thickness all around the cylindrical section of the body at zero incidence. However, at an incidence of 10° the layer tapers and becomes thinner under the body. The surface pressure over the wing and the plateau pressure for separated flow was found to increase from the root to the tip. This is partly because of the decrease in local Reynolds number across the span, however in the present case, entropy layer effects also affected separation. The entropy layer effects were found to reduce the peak pressures obtainable on the flap. The peak pressures, over the portion of the flap unaffected by entropy layer effects, could be estimated assuming quasi two dimensional flow. (ii) Force measurements were made for the blunted cone-cylinder alone as well as with the delta wing, with trailing-edge flap, attached to it. The lift, drag, and pitching moment characteristics for the cone-cylinder agree reasonably well with the modified Newtonian theory and the N-S results. The addition of a wing to the cone-cylinder body increases the lift as weil as the drag coefficient but there is an overall increase in the lift/drag ratio. The deflection of a flap from 0° to 25° increases the lift and drag coefficients at all the incidences tested. However, the lift/drag ratio is reduced showing the affects of separation over the wing. The experimental results on the wing-body are compared with the theoretical estimates based upon two-dimensional shock-expansion theory. (iii) The lift, and drag characteristics of a one-half-power-law body are compared with other existing results. The addition of strakes to the power-law body are found to improve its aerodynamic efficiency without any significant change in its pitching moment characteristics.
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Kang, Bryan H. (Bryan Heejin). "Air-data estimation for air-breathing hypersonic vehicles." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/47394.

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Kang, Bryan H. (Bryan Heejin). "Air data and surface pressure measurement for hypersonic vehicles." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/40135.

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

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Wilson, Althea Grace. "Numerical study of energy utilization in nozzle/plume flow-fields of high-speed air-breathing vehicles." Diss., Rolla, Mo. : Missouri University of Science and Technology, 2008. http://scholarsmine.mst.edu/thesis/pdf/Wilson_09007dcc804d881b.pdf.

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Thesis (M.S.)--Missouri University of Science and Technology, 2008.
Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed April 25, 2008) Includes bibliographical references (p. 57).
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Somanath, Amith. "Adaptive control of hypersonic vehicles in presence of actuation uncertainties." Thesis, Massachusetts Institute of Technology, 2010. http://hdl.handle.net/1721.1/59699.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2010.
Cataloged from PDF version of thesis.
Includes bibliographical references (p. 73-75).
The thesis develops a new class of adaptive controllers that guarantee global stability in presence of actuation uncertainties. Actuation uncertainties culminate to linear plants with a partially known input matrix B. Currently available multivariable adaptive controllers yield global stability only when the input matrix B is completely known. It is shown in this work that when additional information regarding the structure of B is available, this difficulty can be overcome using the proposed class of controllers. In addition, a nonlinear damping term is added to the adaptive law to further improve the stability characteristics. It is shown here that the adaptive controllers developed above are well suited for command tracking in hypersonic vehicles (HSV) in the presence of aerodynamic and center of gravity (CG) uncertainties. A model that accurately captures the effect of CG shifts on the longitudinal dynamics of the HSV is derived from first principles. Linearization of these nonlinear equations about an operating point indicate that a constant gain controller does not guarantee vehicle stability, thereby motivating the use of an adaptive controller. Performance improvements are shown using simulation studies carried out on a full scale nonlinear model of the HSV. It is shown that the tolerable CG shifts can be almost doubled by using an adaptive controller as compared to a linear controller while tracking reference commands in velocity and altitude.
by Amith Somanath.
S.M.
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Vick, Tyler J. "Geometry Modeling and Adaptive Control of Air-Breathing Hypersonic Vehicles." University of Cincinnati / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1397468045.

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Books on the topic "Hypersonic Vehicles"

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Aerodynamics of Hypersonic Lifting Vehicles. S.l: s.n, 1987.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Flight testing of airbreathing hypersonic vehicles. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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Gerard, Laruelle, Wagner Alain, and United States. National Aeronautics and Space Administration., eds. Systems challenges for hypersonic vehicles: [AGARD] paper C37. [Washington, D.C: National Aeronautics and Space Administration, 1997.

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United States. National Aeronautics and Space Administration., ed. Robust intelligent flight control for hypersonic vehicles. Cambridge, Mass: Draper Laboratory, 1992.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Special course on aerothermodynamics of hypersonic vehicles. Neuilly sur Seine, France: AGARD, 1989.

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United States. National Aeronautics and Space Administration., ed. Robust intelligent flight control for hypersonic vehicles. Cambridge, Mass: Draper Laboratory, 1992.

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United States. National Aeronautics and Space Administration., ed. Shock-tunnel combustor testing for hypersonic vehicles. San Jose, Calif: MCAT Institute, 1994.

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United States. National Aeronautics and Space Administration., ed. Shock-tunnel combustor testing for hypersonic vehicles. San Jose, Calif: MCAT Institute, 1994.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Hypersonic combined cycle propulsion. Neuilly sur Seine, France: AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Hypersonic combined cycle propulsion. Neuilly sur Seine, France: AGARD, 1990.

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Book chapters on the topic "Hypersonic Vehicles"

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Ingenito, Antonella. "Design of Supersonic/Hypersonic Vehicles." In Subsonic Combustion Ramjet Design, 9–17. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-66881-5_3.

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Perrier, P. "Industrial Methodologies for the Design of Hypersonic Vehicles." In Hypersonics, 93–124. Boston, MA: Birkhäuser Boston, 1989. http://dx.doi.org/10.1007/978-1-4684-9187-6_3.

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Pratap Singh, Amritansh, Vini Choudhary, and Devender Sharma. "Design and Development of Hypersonic Aerial Vehicles." In Lecture Notes in Mechanical Engineering, 457–67. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-9956-9_47.

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Zhang, Yuqing, Jianglong Yu, Xiwang Dong, Qingdong Li, and Zhang Ren. "Formation Optimization Method of Multiple Hypersonic Vehicles." In Lecture Notes in Electrical Engineering, 4702–12. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-6613-2_456.

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Viviani, Antonio, and Giuseppe Pezzella. "Basics of Hypersonic Aerodynamics and Aerothermodynamics." In Aerodynamic and Aerothermodynamic Analysis of Space Mission Vehicles, 1–125. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-13927-2_1.

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Sacher, P. W. "Hypersonic Technology Experimental Vehicles (The Need for Flight Testing at Hypersonic Speed)." In Orbital Transport, 65–81. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-45720-3_6.

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Scott, Carl D. "Effects of Thermochemistry, Nonequilibrium, and Surface Catalysis on the Design of Hypersonic Vehicles." In Hypersonics, 355–427. Boston, MA: Birkhäuser Boston, 1989. http://dx.doi.org/10.1007/978-1-4684-9187-6_8.

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Zhu, Wenbiao. "Robust Control for Air-Breathing Hypersonic Cruise Vehicles." In Lecture Notes in Electrical Engineering, 191–98. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-38460-8_22.

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Wu, Ligang, Xiaojie Su, and Peng Shi. "Fuzzy Control of Nonlinear Air-Breathing Hypersonic Vehicles." In Fuzzy Control Systems with Time-Delay and Stochastic Perturbation, 309–32. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-11316-6_14.

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Hirschel, Ernst Heinrich, and Claus Weiland. "Aerothermodynamic Design Problems of Winged Airbreathing Vehicles." In Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles, 129–209. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-89974-7_4.

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Conference papers on the topic "Hypersonic Vehicles"

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Kremer, Frans G. J. "Balance of Moments for Hypersonic Vehicles." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-251.

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Ramjet engines propelling hypersonic flight vehicles will be highly integrated into the vehicle, resulting in strong interactions between the vehicle and the engine. An assessment of these interactions in relation to the flight mission is made by simple but adequate modeling of the flight vehicle aerodynamics and the engine performance. Especially moments associated with the propulsion system are of interest. This paper deals with the pitch moments introduced by the ramjet related forces, which are evaluated by one-dimensional engine performance and by modeling of the inlet and nozzle flow. Furthermore, it discusses the balance of moments for the first stage of a two stage transportation system for an ascent trajectory.
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LARUELLE, GERARD, and PHILIPPE RAMETTE. "Potential hypersonic vehicles applications." In 3rd International Aerospace Planes Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-5086.

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Blankson, Isaiah M. "Air-Breathing Hypersonic Cruise: Prospects for Mach 4-7 Waverider Aircraft." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-437.

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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 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 alleged low volumetric efficiency, lack of engine/airframe integration studies, poor off-design performance, poor take-off and landing capability, have been shown by on-going research to be unfounded. A discussion is presented of some of the technical challenges and on-going 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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Maxwell, Jesse R. "Shapeable Hypersonic Waverider Entry Vehicles." In 53rd AIAA/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4880.

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Schmidt, David. "Integrated control of hypersonic vehicles." In 5th International Aerospace Planes and Hypersonics Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-5091.

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Wang, Yongzhi, and Xu Zhang. "Static Aerothermoelasticity of Hypersonic Vehicles." In 21st AIAA International Space Planes and Hypersonics Technologies Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-2367.

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

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BUSSING, THOMAS, and SCOTT EBERHARDT. "Chemistry associated with hypersonic vehicles." In 19th AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1292.

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ORTWERTH, P., A. MATHUR, and C. BROWN. "Flowpath optimization for hypersonic vehicles." In 3rd International Aerospace Planes Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-5043.

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Pulok, Mohammad Khairul Habib, and Uttam K. Chakravarty. "Aerodynamic and Vibration Analysis of the Morphing Wings of a Hypersonic Vehicle." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-23663.

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Abstract Hypersonic vehicles are receiving great attention in recent years due to their high speed and long-range capabilities. The shock waves come into consideration as a propagating disturbance for any aircraft when it exceeds the speed of sound. Complex environment and flight requirements of the hypersonic vehicles are leading the researchers to focus on several design considerations. Adaptive shape deformation is one of the prospective areas among them which has an impact on thermal loading, global and local load factors, vehicle acceleration, total energy dissipation, and fuel consumption. The wings play a key role in the aerodynamic performances of a flying machine; therefore, the overall performance of the hypersonic vehicle can be improved by applying morphing technologies on the wing. Morphing can help with reducing wave drag, increasing lift-to-drag ratio as well as enhancing flight endurance, and extending the range for a hypersonic vehicle. In this study, the telescopic wing morphing profile is considered for the aerodynamics and vibration analysis. The experimental validations of the aerodynamics and vibration characteristics are conducted by a wind-tunnel experiment and a vibration-testing arrangement, respectively, using a small-scale model of the wing. The computational analysis of the aerodynamics and vibration characteristics of the morphing wings are conducted and compared. Thus, a comprehensive study including the comparison between morphing modes can establish a standard to choose the appropriate morphing technique for the hypersonic vehicles.
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Reports on the topic "Hypersonic Vehicles"

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Bogdonoff, Seymour M. Hypersonic Flight Vehicles: Perspective and Prognosis,. Fort Belvoir, VA: Defense Technical Information Center, January 1999. http://dx.doi.org/10.21236/ada370547.

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Schierman, John D., David G. Ward, Jason R. Hull, Jeffrey F. Monaco, and Michael J. Ruth. Adaptive Guidance Systems for Hypersonic Reusable Launch Vehicles. Fort Belvoir, VA: Defense Technical Information Center, January 2001. http://dx.doi.org/10.21236/ada436268.

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Feie, John, and Larry Kretz. High Temperature Thermocouple Installation Methods for Hypersonic Vehicles. Fort Belvoir, VA: Defense Technical Information Center, March 2008. http://dx.doi.org/10.21236/ada488092.

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Newell, Alan C., and Vladimir E. Zakharov. Communication with Hypersonic Vehicles via Nonlinear Plasma Processes. Fort Belvoir, VA: Defense Technical Information Center, February 2007. http://dx.doi.org/10.21236/ada479049.

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Bolender, Michael A., and David B. Doman. Flight Path Angle Dynamics of Air-Breathing Hypersonic Vehicles. Fort Belvoir, VA: Defense Technical Information Center, December 2005. http://dx.doi.org/10.21236/ada444974.

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Caledonia, George E., and Robert H. Krech. Ultraviolet Emissions Occurring About Hypersonic Vehicles in Rarefied Flows. Fort Belvoir, VA: Defense Technical Information Center, April 1994. http://dx.doi.org/10.21236/ada281452.

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Noone, Emily, and Lydia Harriss. Hypersonic missiles. Parliamentary Office of Science and Technology, June 2023. http://dx.doi.org/10.58248/pn696.

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This POSTnote looks at hypersonic missile technologies, efforts to develop them, potential applications, and the possible challenges they may present for missile defence and global stability. Key Points: • Hypersonic missiles combine speeds of over five times the speed of sound with significant manoeuvrability during flight. • Their manoeuvrability enables them to change trajectory during flight, making their flight-path and target difficult to predict. • They fly at lower altitudes than ballistic missiles, which means that they may be harder to track at long distances with some surface-based sensors, such as certain radar. • There are two main types of hypersonic missile: hypersonic glide vehicles (HGVs) and hypersonic cruise missiles (HCMs). • HGVs are mounted onto rocket boosters for launch and may be accelerated to speeds of Mach 20 or more. The glider then separates from the booster and flies unpowered in the Earth’s upper atmosphere at altitudes of 30-80 km, before diving towards the target. • HCMs typically have a ramjet or scramjet engine that enables them to reach hypersonic speeds at altitudes of 20-40 km. • China and Russia have reportedly deployed hypersonic missiles that could deliver conventional or nuclear weapons. The US is testing multiple hypersonic technologies. • The AUKUS agreement between the UK, US and Australia includes developing hyper-sonic and counter-hypersonic technologies. • Developing hypersonic missiles requires significant research and development challenges to be overcome, contributing to their high development and manufacturing costs. • The speed, manoeuvrability and altitude of hypersonic missiles may challenge existing missile defences, although their uses and effectiveness are still being assessed. • Defence analysts disagree about the potential implications of hypersonic missiles for global peace and stability. Some suggest they could increase the risk of conflict escalation, while others say that they will not alter the strategic balance between nuclear powers. • Arms control, export controls and other measures may help limit potential harm to peace and stability, but these approaches face challenges.
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Rose, David V., Carsten H. Thoma, and Vladimir Sotnikov. Analysis of Plasma Communication Schemes for Hypersonic Vehicles: Final Report. Fort Belvoir, VA: Defense Technical Information Center, February 2009. http://dx.doi.org/10.21236/ada498289.

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Ferencz, R., F. Felker, and V. Castillo. Computation of Hypersonic Flow about Maneuvering Vehicles with Changing Shapes. Office of Scientific and Technical Information (OSTI), February 2004. http://dx.doi.org/10.2172/15009796.

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Grunlan, Jaime C., K. R. Rajagopal, and J. N. Reddy. Performance Characterization of Polyimide-Carbon Fiber Composites for Future Hypersonic Vehicles. Fort Belvoir, VA: Defense Technical Information Center, August 2010. http://dx.doi.org/10.21236/ada546978.

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