• Title/Summary/Keyword: Hypersonic

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Computational Study of Hypersonic Real Gas Flows Over Cylinder Using Energy Relaxation Method (에너지 완화법을 이용한 실린더 주위의 극초음속 실제기체 유동에 관한 수치해석적 연구)

  • Nagdewe, Suryakant;Kim, H.D.
    • 한국전산유체공학회:학술대회논문집
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    • 2008.03b
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    • pp.216-217
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    • 2008
  • In recent years, scientific community has found renewed interest in hypersonic flight research. These hypersonic vehicles undergo severe aero-thermal environment during their flight regimes. During reentry and hypersonic flight of these vehicles through atmosphere real gas effects come into play. The analysis of such hypersonic flows is critical for proper aero-thermal design of these vehicles. The numerical simulation of hypersonic real gas flows is a very challenging task. The present work emphasizes numerical simulation of hypersonic flows with thermal non-equilibrium. Hyperbolic system of equations with stiff relaxation method are identified in recent literature as a novel method of predicting long time behaviour of systems such as gas at high temperature. In present work, Energy Relaxation Method (ERM) has been considered to simulate the real gas flows. Navier-Stokes equations A numerical scheme Advection Upstream Splitting Method (AUSM) has been selected. Navier-Stokes solver along with relaxation method has been used for the simulation of real flow over a circular cylinder. Pressure distribution and heat flux over the surface of cylinder has been compared with experiment results of Hannemann. Present heat flux results over the cylinder compared well with experiment. Thus, real gas effects in hypersonic flows can be modeled through energy relaxation method.

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Review on the Hypersonic Propulsion System Development Plan of DARPA (DARPA의 극초음속 추진기관 개발 계획: 리뷰)

  • Choi, Jeong-Yeol;Noh, Jin-Hyeon;Parent, Bernard
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.314-317
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    • 2008
  • Present review introduces the on-going or planed hypersonic vehicles by DARPA including X-51A, HTV-3X and HCV. The configuration and the R&D strategies of the hypersonic propulsion systems will be also introduced with its core technologies.

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Effect of Hypersonic Missiles on Maritime Strategy: Focus on Securing and Exploiting Sea Control (극초음속 미사일이 해양전략에 미치는 영향: 해양통제의 확보와 행사를 중심으로)

  • Cho, Seongjin
    • Maritime Security
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    • v.1 no.1
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    • pp.241-271
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    • 2020
  • The military technology currently receiving the most attention is the hypersonic missile. hypersonic is faster than the speed of sound or Mach 5+. The vast majority of the ballistic missiles that it inspired achieved hypersonic speeds as they fell from the sky. Rather than speed, today's renewed attention to hypersonic weapons owes to developments that enable controlled flight. These new systems have two sub-varieties: hypersonic glide vehicles and hypersonic cruise missiles. Hypersonic weapons could challenge detection and defense due to their speed, maneuverability, and low altitude of flight. The fundamental question of this study is: 'What effect will the hypersonic missile have on the maritime strategy?' It is quite prudent to analyze and predict the impact of technology in the development stage on strategy in advance. However, strategy is essential because it affect future force construction. hypersonic missiles act as a limiting factor in securing sea control. The high speed and powerful destructive power of the hypersonic missile are not only difficult to intercept, but it also causes massive ship damage at a single shot. As a result, it is analyzed that the Securing sea control will be as difficult as the capacity of sea denial will be improved geographically and qualitatively. In addition, the concept of Fortress Fleet, which was criticized for its passive strategy in the past, could be reborn in a modern era. There are maritime power projection/defence, SLOC attack/defence in exploiting sea control. The effects of hypersonic missiles on exploiting sea control could be seen as both limiting and opportunity factors.

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Compromise Optimal Design using Control-based Analysis of Hypersonic Vehicles

  • Liu, Yanbin;bing, Hua
    • International Journal of Aeronautical and Space Sciences
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    • v.16 no.2
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    • pp.137-147
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    • 2015
  • Hypersonic vehicles exhibit distinct dynamic and static characteristics, such as unstable dynamics, strict altitude angle limitation, large control bandwidth, and unconventional system sensitivity. In this study, compromise relations between the dynamic features and static performances for hypersonic vehicles are investigated. A compromise optimal design for hypersonic vehicles is discussed. A parametric model for analyzing the dynamic and static characteristics is established, and then the optimal performance indices are provided according to the different design goals. A compromise optimization method to balance the dynamic and static characteristics is also discussed. The feasibility of this method for hypersonic vehicles is demonstrated.

Computational Study on the Heat Transfer Prediction Hypersonic Flows (극초음속 유동의 열전달 예측에 관한 수치해석적 연구)

  • Nagdewe, Suryakant;Kim, H.D.
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.11a
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    • pp.27-30
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    • 2007
  • In recent years, scientific community has found renewed interest in hypersonic flight research. These hypersonic vehicles undergo severe aero-thermal environments during their flight regimes. One of the most important topics of research in hypersonic aerodynamics is to find a reasonable way of calculating either the surface temperature or the heat flux to surface when its temperature is held fixed. This requires modeling of physical and chemical processes. Hyperbolic system of equations with stiff relaxation method are being identified in recent literature as a novel method of predicting long time behavior of systems such as gas at high temperatures. In present work, Energy Relaxation Method (ERM) has been considered to simulate the real gas flow over a 2-D cylinder. Present heat flux results over the cylinder compared well with the experiment. Thus, real gas effects in hypersonic flows can be modeled through energy relaxation method.

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Current Technological Trends in Hypersonic Flight with Air-Breathing Propulsion System (차세대 극초음속 공기흡입식 추진기관의 개발 동향)

  • Lee, Yang-Ji;Kang, Sang-Hun;Yang, Soo-Seok
    • Current Industrial and Technological Trends in Aerospace
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    • v.7 no.1
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    • pp.43-55
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    • 2009
  • Advanced countries in aerospace have been struggle to realize the hypersonic air-breathing system since originating the concept of the hypersonic air-breathing propulsion system during the first half of the twentieth century. At last, NASA's X-43A Hyper-X did successful Mach 10 flight in November 2004. Each countries are running the program to applicate this hypersonic air-breathing propulsion system to SSTO(Single Stage to Orbit) or TSTO(Two Stage to Orbit) vehicle or hypersonic missile system at present. In this paper, we wrote the history and current issues of the hypersonic air-breathing propulsion system and hypersonic flight with the hypersonic air-breathing propulsion system.

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Hypersonic Aero-Heating Ground-Test Simulation Technique

  • Li, Ruiqu;Yao, Dapeng;Sha, Xinguo;Gong, Jian
    • International Journal of Aerospace System Engineering
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    • v.2 no.2
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    • pp.50-53
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    • 2015
  • It would encounter some complicated flow fields, such as transition, separation, reattachment and disturbances, in the hypersonic flight. Thus, it is difficult to theoretically analyze the hypersonic aerothermodynamics effects, so that the ground-test simulation is thought of as one of the most important methods to improve the understanding level of the hypersonic aerothermodynamics. However, the aero-heating tests could not simulate all aerodynamics and geometry parameters in the real flight due to the differences between the experimental environments supplied by the ground facilities and the flight, so that the feasible technique for the ground-test simulation of the hypersonic aerothermodynamics effects is required to be advanced. The key parameters that are especially required to simulate for aero-heating tests are analyzed and one detailed approach is suggested to perform the experimental investigation on the hypersonic aero-heating effects in the ground facilities in this paper, and the tests are performed in the FD-20 gun tunnel of CAAA (China Academy of Aerospace Aerodynamics) to give out the data which could be used to confirm the equation from the theoretical analysis.

Aerodynamics Simulation of Three Hypersonic Forebody/Inlet Models

  • Xiao, Hong;Liu, Zhenxia;Lian, Xiaochun
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.03a
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    • pp.456-459
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    • 2008
  • The purpose of this paper is to examine the aerodynamic characteristics of three hypersonic configurations including pure liftbody configuration, pure waverider configuration and liftbody integrated with waverider configuration. Hypersonic forbodies were designed based on these configurations. For the purpose to integrate with ramjet or scramjet, all the forebodies were designed integrated with hypersonic inlet. To better understand the forebody performance, three dimensional flow field calculation of these hypersonic forebodies integrated with hypersonic inlet were conducted in the design and off design conditions. The computational results show that waverider offer an aerodynamic performance advantage in the terms of higher lift-drag ratios over the other two configurations. Liftbody offer good aerodynamic performance in subsonic region. The aerodynamic performance of the liftbody integrated with waverider configuration is not comparable to that of pure waverider in the terms of lift-drag ratios and is not comparable to that of pure liftbody in subsonic. But the liftbody integrated with waverider configuration exhibit good lateral-directional and longitudinal-directional stability characteristics. Both pure waverider and liftbody integrated with waverider configuration can provide relatively uniform flow for the inlet and offer good aerodynamic characteristics in the terms of recovery coefficient of total pressure and uniformity coefficient.

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Constant Volume Combustion (CVC)-based Hypersonic Propulsion System Development Program by DARPA (DARPA의 정적연소 (CVC) 기반 극초음속 추진기관 개발 프로그램)

  • Choi, Jeong-Yeol;Noh, Jin-Hyeon;Cho, Deok-Rae
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.05a
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    • pp.402-405
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    • 2009
  • Present review introduces the constant volume combustion (CVC)-based hypersonic propulsion system development program recently initiated by DARPA for the hypersonic cruse vehicle (HCV).

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Trajectory Optimization of a Hypersonic Airplane

  • Takano, H.;Baba, Y.
    • 제어로봇시스템학회:학술대회논문집
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    • 2001.10a
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    • pp.156.2-156
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    • 2001
  • Hypersonic civil airplanes are recently heated up again in USA and Japan, but there are several difficulties when we obtain its optimal trajectories. In this paper, we formulated the trajectory optimization problem as an optimal control problem and solved it by the direct shooting method with the Genetic Algorithm, GA. The result shows it is effective to use this method for the trajectory optimization of the hypersonic flight.

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