• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.303-306
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• 2008

After the successful flight test of X-43A, U.S. Airforce is developing missile-type X-51A SED (Scramjet Engine Demonstrator-Wave Rider). X-51A using PWR (Pratt and Whitney Rocketdyne) X-1 hydrocarbon fueled scramjet engine will have a ground test in 2008 and flight test in 2009. Technologies established though the X-51A program will be transferred to DARPA's Falcon program developing HTV (Hypersonic Test Vehicle)-3X and HCV (Hypersonic Cruise Vehicle). Present paper is an overview of propulsion core technologies of X-51 such as regenerative cooling of engine structures and combustion using liquid/supercritical JP-7 fuel.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.199-202
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• 2008

The advantage of ultrasonic burning rate measurement of solid propellant is measuring burning rates with wide range of pressure in a single test. In the ultrasonic method, instantaneous thickness of solid propellants as function of pressure or time were measured using time of flight(TOF) of ultrasonic signals. So, uncertainties of the measured burning rates by ultrasonic method have to evaluate with variation of pressure, TOF and initial propellant thickness. In this study, we evaluated uncertainties of ultrasonic method for measuring burning rates on the types 317 and the 318 propellants.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.207-210
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• 2008

In this study, one type of ramjet intake were designed for the flight condition of Mach number 4 and numerical analysis was performed. In order to widen the flight envelope range (Mach number $2{\sim}6$), movable intake concept was applied. The central body was designed so that the capture area ratio which is one of most important factors of ramjet intake design could be adjusted. And various types of cowl and movable insert part of shell were designed in order to control throat area which could increase total pressure recovery. The numerical results showed that the designed ramjet intake could be applied in various flights Mach number.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.381-384
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• 2009

The Air-breathing engine like Sea-Star I is a second propulsive force generator to fly to the target after the booster generating initial propulsive force is separated. The performance of Sea-Star I engine should be verified because the cruise missile controls direction and altitude during flight, so ground engine test is executed before flight test. This these presents evaluation method of ground engine test to verify performance of Sea-Star I's engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.79-82
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• 2009

Unsteady numerical analysis of an entire supersonic propulsion system from intake to nozzle was performed to study dynamic interaction between terminal shock in the intake and flame in the combustor. Both acceleration and cruise flight-modes were considered. Acoustic mode of the entire engine for both flight-modes were investigated by detail analysis of pressure fluctuation at each location of engine.

• Journal of the Institute of Electronics Engineers of Korea SD
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• v.37 no.3
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• pp.27-33
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• 2000

The selective chemical vapor deposition techniques for Cu metallization were studied. For enhancing the selectivity, furnace annealing and N$_{2}$ plasma were treated on patterned TiN/BPSG prior to the copper deposition. As a result, Cu did not deposited lead to suppressing the nucleation on BPSG singificantly. With the increasement the plasma treatment temperature, copper nucleation on BPSG was suppressed mote effectively, From TOF-SIMS(Time-of-Flight Secondary ion Mass Spectrometry), it is considered that annealing and N$_{2}$ plasma treatment remove hydroxyl(0-H) group so that eliminating the nucleation site for copper precursor enhance the selectivity.

• Transactions of the Korean Society of Mechanical Engineers
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• v.18 no.9
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• pp.2404-2412
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• 1994

A mathematical model has been developed for predicting kinematic, thermal, and solidification histories of atomized droplets during flight. Liquid droplet convective cooling, recalescence, equilibrium-state solidification, and solid-phase cooling were taken into account in the analysis of the solidification process. The spherical shell model was adopted where the heterogeneous nucleation is initiated from the whole surface of a droplet. The growth rate of the solid-liquid interface was determined from the theory of crystal growth kinetics with undercooling caused by the rapid solidification. The solid fraction after recalescence was obtained by using the integral method. The thermal responses of atomized droplets to gas velocity, particle size variation, and degree of undercooling were investigated through the parametric studies. It is possible to evaluate the solid fraction of the droplet according to flight distance and time in terms of a dimensionless parameter derived from the overall energy balance of the system. It is also found that the solid fraction at the end of recalescence is not dependent on the droplet size and nozzle exit velocity but on the degree of subcooling.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.1
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• pp.64-71
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• 2012

While a conventional ECS mainly consisted of an air cycle machine and heat exchangers, a new concept of a phase change heat exchanger was added to improve the transient performance of the ECS. As a result, an ECS modeling program including the phase change heat exchanger is newly developed to estimate its effect in various flight conditions such as take-off, maneuver, cruise, and landing. The simulation result regarding a virtual flight profile has confirmed the new ECS fulfilled the requirement by showing the temperature of the cooling air returned from the bay was always kept below $80^{\circ}C$. Through this study, the new ECS concept with PCHE was verified successfully.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.6
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• pp.7-11
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• 2008

The helicopter flies at low level flight mode in its own operational range comparing to other aircraft categories. The low level flight means that the engine operates at variable atmospheric condition such as hot and cold temperature, snow, heavy rain, etc. Furthermore it may increase the entering possibility of engine foreign object damage particles like sand, dust, etc., i.e. this operating condition gives rise to damages of engine gas path components. An on-line condition monitoring program was developed by using SIMULINK, where measurement signals were simulated as an input module. The reliability and capability of the developed on-line condition monitoring were confirmed through application to a real helicopter engine health monitoring.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.245-249
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• 2007

In this study a model-based diagnostic method using the Neural Network was proposed for PW206C turbo shaft engine and performance model was developed by SIMULINK. Fault and test database to build the NN was obtained at various off-design operating range such as flight altitude, flight Mach number and gas generator rotational speed variation. According to the fault detection analysis results, it was confirmed that the proposed fault detection method could find well the fault of compressor, compressor turbine and power turbine at on-design point as well as off-design point conditions.