• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.167-170
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• 2008

A TBCC(Turbine Based Combined Cycle) engine performance design method for reusable launch vehicles flying both in subsonic and supersonic regime was proposed. The TBCC consists of turbo jet engines and ramjet engines, operating individually or together according to operation schedule. The performance scheme of turbojet and ramjet was validated and the combined engine performance of the TBCC at a typical flight condition was analyzed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.2
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• pp.116-122
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• 2016

The performance characteristics of a TBCC engine considering the transition mode from a turbojet to a ramjet engine has been investigated. The performance of each engine was proposed and a transition mode of the TBCC engine has been evaluated by adjusting the operating rate of the ramjet engine and turbojet engine performance changes continuously. Based on the transition model, it was confirmed that the performance is continuously changed at various flight Mach numbers and altitudes. The performance characteristics including thrust and specific impulse considering various flight conditions and transition mode were analyzed, which testifies characteristics of the engine itself, as well as transition of the combined cycle.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.326-329
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• 2008

DARPA's hypersonic propulsion program VULCAN is aimed for development of Mach 4+ capable engine by combining current production turbofan engine such as F119 with CVC (Constant Volume Combustion) engine. Final goal is a TBCC(Turbo-based Combined Cycle) engine by combining with dual mode ramjet/scramjet engine. CVC is a common designation of new concept of high efficiency engines, such as Pulse Detonation Engine (PDE) or Continuous Detonation Engine (CDE), which use the detonation as a combustion mechanism. Present paper introduces the internationally collaborative research activities carried out in Aerospace Combustion and Propulsion Laboratory of the department of Aerospace Engineering of the Pusan national University.

• Asian-Australasian Journal of Animal Sciences
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• v.31 no.6
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• pp.873-880
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• 2018

Objective: The objective of this experiment was to compare the effects of adding 130 mg/kg Cu from either copper sulfate (CS) or tribasic copper chloride (TBCC) on growth performance, mineral deposition in tissues, and the excretion in feces of pigs as well as changes in the mineral contents in tissues and feces when the supplemental Cu level was decreased from 130 mg/kg to 10 mg/kg. Methods: A total of 72 pigs ($32.6{\pm}1.2kg$) were randomly assigned to a CS diet or a TBCC diet with 6 pens per treatment. The trial lasted 102 d and included 3 phases (phase 1, 1 to 30 d; phase 2, 31 to 81 d; and phase 3, 82 to 102 d). The supplemental levels of Cu in the 2 treatments were 130 mg/kg in phase 1 and 2 and 10 mg/kg in phase 3. Results: The results showed that pigs fed the CS diet tended to have higher average daily gain than pigs fed the TBCC diet during d 1 to 81 (p<0.10). Compared with CS, TBCC increased the activities of aspartate transaminase (AST), ceruloplasmin, and superoxide dismutase in serum on d 30 (p<0.05). The TBCC decreased the Cu level in the liver on d 81 (p<0.05) and increased the Mn level in the liver on d 102 (p<0.05). The concentration of Cu in feces sharply decreased when the supplemental Cu level in diet changed from 130 mg/kg to 10 mg/kg in both diets (p<0.05). Conclusion: The result suggested that TBCC and CS had no significant difference on growth performance but TBCC had higher activities of AST and antioxidant enzymes and lower liver Cu than CS when pigs fed diets with 130 mg Cu /kg diet.

• Proceedings of the Korea Information Processing Society Conference
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• 2001.04b
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• pp.891-894
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• 2001

본 논문은 서로 다른 얼굴이미지 사이의 얼굴매칭기법의 새로운 방법인 TBCC(T-Block constraints Condition)얼굴매칭기법을 제안한다. 본 논문에서 제안하는 방법은 T영역안의 이목구비에다가 제어영역을 두고, T영역과 제어영역들을 분리하여 2개의 영상으로 각각 만든 다음에 각각의 correspondence가 있는 영상끼리 와핑(Warping)을 한 후에, 제어영역들은 2단계구조를 가진 계층적인 선형조합(Linear Combination)모델에 적용시켜 최적의 위치를 찾아낸 후에, T영역에 와핑시켜서 하나의 합성사진을 만들어 낸다. 합성사진에서 피부색이 다른 문제는 정규분표를 이용한 크로스디졸브(Cross-Dissolve)방법인 이미지프로세싱 기법을 새롭게 적용하며, 그리고, T모양의 자국이 남는 것은 본 논문에서 제안하는 T-Block Color Interpolation방법을 적용해서 해결한다.

• Advances in aircraft and spacecraft science
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• v.5 no.4
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• pp.431-444
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• 2018

Numerical simulations have been conducted to study the unstart/restart characteristics of an over-under turbine-based combined-cycle propulsion system (TBCC) inlet during the inlet transition phase. A dual-solution area exists according to the Kantrowitz theory, in which the inlet states may be different even with the same input parameters. The entire transition process was divided into five stages and the unstart/restart hysteresis loop for each stage was also obtained. These loops construct a hysteresis surface which separates the operating space of the engine into three parts: in which a) inlet can maintain a started state; b) inlet keeps an unstarted state; c) inlet state depends on its initial state. During the transition, the operation of the engine follows a certain order with different backpressures and splitter angles, namely control route, which may result in disparate inlet states. Nine control routes with different backpressures and transition stages were designed to illuminate the route-dependent behavior of the inlet. The control routes operating towards the unstart boundary can make the inlet transit from a started state into an unstarted one. But operating backward the same route cannot make the inlet restart, additional effort should be made.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.395-399
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• 2009

Advanced afterburner used in the most modernized gas turbine has new designing paradigm to cope with reinforced power density. The most distinct change is the designing trend to integrate fuel injectors and flame holder in order to manage higher temperature of inlet air. F414 and F110-GE-132 engine adopted this methodology and installed a variable nozzle utilizing CMC(Ceramic Matric Composite) material and active cooling of nozzle flap with ejector nozzle in order to enhance the life cycle of engine components and an economical aspect. These technological trends can be utilized for an advanced ramjet engine and combined cycle engine like TBCC.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.693-698
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• 2004

This paper describes development status and program of ATREX engine as a propulsion system of future spaceplane. Development activities using ATREX-500 engine from 1990 were finished in 2003 with large number of outcomes. We made system-level validation of the hydrogen fuel turbojet engine with air precooling device under sea level static condition. As a next step, we started design of the flight-type ATREX engine with large thrust and lightweight.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.665-670
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• 2004

This paper reviews the latest studies of the expander cycle Air Turbo Ramjet engine (ATREX) conducted in JAXA. First, a system analysis including the vehicle and trajectory was conducted to optimize the engine cycle and turbo-machine configuration. We selected the precooled turbo-jet cycle for a prototype engine using the near term technologies. Second, a system ground-firing test was conducted to verify a defrosting system for the precooler. Methanol injection with its particles atomization could compensate 80 % of pressure loss caused by the frost. Thirdly, a feasibility of carbon/carbon composites for the engine components was investigated by making complex shapes such as a heat exchanger and a plug nozzle. Basic technologies on the gas leakage, the junction and bonding were also studied. The end of the paper, some basic studies such as wind tunnel tests of a new type air inlet and a plug nozzle are described.