• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.9
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• pp.731-743
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• 2020

The hypersonic glide vehicle ascends to a high altitude by a rocket booster, separates it from the booster, and glides at a hypersonic speed of Mach 5 or higher at an altitude of about 30~70 km, changing its direction in the atmosphere. Since it moves on an unpredictable flight path rather than a parabolic trajectory, it is difficult to intercept with current missile defense systems. The U.S. conducted HTV-2 and AHW flight tests in the early 2010s to confirm the possibility of hypersonic gliding flights, and recently it has been developing hypersonic glide vehicle systems such as LRHW and ARRW. China has conducted several flight tests of the DF-ZF (WU-14) glide vehicle since 2014 and has been operating it with DF-17 missiles. Russia has conducted hypersonic glide vehicle research since the former Soviet Union, but it has repeatedly failed, and recently it has been successfully tested with the Avangard (Yu-71) glide vehicle mounted on the SS-19 ICBM. In this paper, the characteristics, flight test cases, and development trends of hypersonic glide vehicles developed or currently being developed in the United States, China, Russia, Japan, India, and Europe are reviewed and summarized.

• Journal of the KSME
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• v.32 no.9
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• pp.788-796
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• 1992

이 글에서는 극초음속 항공우주 비행기의 개요 및 개발배경, 구조기능 및 추진체계, 그리고 개발 및 설계의 제반고려사항 등에 관하여 알아보았다. 단단계형 공기흡입식 추진체계라는 새로운 개념의 도입은 미래 극초음속 비행체의 재활전용성과 항공 및 우주의 운항 용이성이라는 두 가 지의 가능성을 제시한다는 점에서 큰 의미를 갖고 있다. 극초음속 항공우주비행기의 실현가능 성은 공기흡입식 추진체계의 핵심부분인 스크램제트엔진 개발의 성공여부에 달려 있다고 하겠다. 이러한 스크램제트엔진에 관한 연구 및 개발은 현재 진행중이며, 오늘날 첨단 추진체 연구분야 중의 하나로 여겨지고 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.3
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• pp.243-256
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• 2015

As a part of the R&D efforts for the hypersonic vehicles, various flight test programs has been carried out using small launch vehicles or sounding rockets. Australian HyShot program is a representative case of the flight test program for scramjet engines carried by international collaborations. A number of hypersonic flight test programs has followed in a similar way. In USA, Falcon HTV-2 was carried by DARPA, X-51A by AFRL and HyFly by ONR. HyCAUSE and HIFiRE were carried in collaboration with Australia. In France, LEA program is on the way similarly to X-51A. Russia, China and India seems like carrying out flight test programs for the development of hypersonic defense system. The goals, technical elements, the status and the relation between the programs were summarized in this paper as a reference for the similar program of the country in the future.

• 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.

• Proceeding of EDISON Challenge
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• 2016.11a
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• pp.78-80
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• 2016

우주발사체와 항공 분야에서 초음속과 극초음속 영역에서 비행체의 항력을 최소화하기 위한 최적 형상설계 연구가 활발히 진행되고 있다. 본 논문에서는 마하수 2의 초음속 영역에서 대표적인 비행체 선두부 형상 3가지에 대한 수치해석을 eMEGA 프로그램을 활용해 격자를 생성하고 eDAVA 프로그램을 활용해 유동 해석을 수행하였다. 그 결과 자유유동 마하수 2의 초음속 영역에서는 선두부 형상이 뾰족한 Cone 형상이 3가지 형상 중 작용하는 항력이 가장 적게 나타났고, 선두부가 무딘 형상이 극초음속 영역에서 가장 적합한 현상과 다르게 나타났다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.11
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• pp.892-901
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• 2018

An efficient aerodynamic thermal load element is developed to reflect the effect of coupled aero-thermo-elastic behaviors in the early design stage of hypersonic vehicle. To this aim, semi-analytic relationships depending on structural deformation are adopted for pressure and thermal load, and the element is formulated based on the relations. The proposed element is implemented in the form of ABAQUS user subroutine, and coupled finite element analysis is carried out to investigate the aero-thermo-elastic behaviors of control surface of hypersonic vehicle. Through the analysis, usefulness of the proposed aerodynamic thermal load element is identified.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.1
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• pp.29-41
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• 2021

The PID controller with fin angle and thrust as control input was designed based on the aerodynamic data of scramjet system. Flight simulation following a given trajectory which strike the target point after climb and cruise with constant dynamic pressure was conducted. After that, the required thrust for the climb and cruise was calculated and the required fuel flow rate for the hydrogen fuel dual mode scramjet combustor was analyzed. The combustor analysis of this study which conducted on integrated model of independently developed inlet, combustor, nozzles and external aerodynamic models, laying the foundation for the integrated design of the air breathing hypersonic system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.10
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• pp.695-704
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• 2019

In hypersonic regime, the complicated interaction between the air and surface of aircraft results in intensive aerodynamic heating on body. Provided this phenomenon occurs on a hypersonic vehicle, the temperature of the body extremely increases. And consequently, thermal deformation is produced and material properties are degraded. Furthermore, those affect both the aerothermoelastic stability and thermal safety of structures significantly. With the background, thermal safety and dynamic stability are studied according to the altitude, flight time and Mach number. Based on the investigation, design guideline is suggested to guarantees the structural integrity of hypersonic vehicles in terms of both of thermal safety and dynamic stability.

• 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).

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.65-78
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• 2010

DARPA carries out several R&D programs for hypersonic vehicles to maintain the U.S. military superiority in air and space. Falcon program is the core of the DARPA's activitiy for the hypersonics including the long-term step-by-step approach from HTV-1, HTV-2, HTV-3X to HCV. Hypersonic Turbo-Based Combined Cycle (TBCC) engine technologies research and development programs, HiSTED, FaCET and Vulcan, are also the parts of their activities. Present article presents the summarized review on the backgrounds, technologies and relationships of those programs.