• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.5
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• pp.35-47
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• 2011

Dynamic characteristics of a flow control valve, which plays an important role in thrust and O/F control of liquid rocket engines, have been analyzed by the AMESim simulator modeling. The speed control method was proposed for the control of the flow valve equipped with a BLDC motor. The experimental results demonstrated the feasibility of systematical application as well as the performance of the speed control method. Moreover, the speed control method for BLDC motor is much simpler than the P control method in complex flow systems. With the speed control method, the control flow characteristics were evaluated according to plunger shapes. Consequently, same plunger shape proved to be more efficient in the mixture ratio control operated by two flow valves. It was also shown that the appropriate modification of plunger shapes could reduce the mixture ratio perturbation by 0.5%.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.3
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• pp.217-225
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• 2013

Typical quadrotor aircraft use four differential thrust vectors to control the motion. In this study, we design a quadrotor aircraft using collective and cyclic control to improve the shortcomings of existing quadrotor aircraft. The quadrotor aircraft with cyclic control can fly at various attitudes due to the excessive control degrees of freedom. Hence the quadrotor aircraft with cyclic control is suitable as high performance aircraft. In this study, modeling and stability analysis of the quadrotor aircraft have been performed using FLIGHTLAB. LQR control systems were designed using linear models at various flight conditions and verified through nonlinear simulations using MATLAB.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.7
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• pp.552-560
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• 2014

Pulse Detonation Engine(PDE) has been investigated as a next generation propulsion system with the advantages of the higher thermal efficiency by the compression effect and the wide operation ranges from zero speed at ground. In the present study, an efficient theoretical PDE performance prediction program was developed for realistic propellants based on the Endo's theory combining the Chapman-Jouguet detonation theory and expansion process of burnt gas in a constant area tube. The program was validated through the comparison with the experimental data obtained by a ballistic pendulum measurement. PDE performance analyses were carried out for various hydrocarbon fuels and oxidizer compositions by changing the mixture equivalence ratio and initial conditions. Theoretical PDE performance database could be established as a result of the analyses.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.10
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• pp.891-898
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• 2007

Optimal aerodynamic design for the pitch-controlled horizontal axis wind turbine and its aerodynamic performance for various pitch angles are performed numerically by using the blade element momentum theory. The numerical calculation includes effects such as Prandtl‘s tip loss, airfoil distribution, and wake rotation. Six different airfoils are distributed along the blade span, and the special airfoil i.e. airfoil of 40% thickness ratio is adopted at the hub side to have structural integrity. The nonlinear chord obtained from the optimal design procedure is linearized to decrease the weight and to increase the productivity with very little change of the aerodynamic performance. From the comparisons of the power, thrust, and torque coefficients with corresponding values of different pitch angles, the aerodynamic performance shows delicate changes for just $3^{\circ}$ increase or decrease of the pitch angle. For precisive pitch control, it requires the pitch control algorithm and its drive mechanism below $3^{\circ}$ increment of pitch angle. The maximum torque is generated when the speed ratio is smaller than the designed one.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.6
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• pp.102-109
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• 2003

The number of engines for fighters has been decided by thrust required and available engines at the time since the beginning of the jet age. However, many factors such as combat effectiveness, survivability, performance, and cost were considered as engine technology has been progressed. From the vietnam war and desert storm, a twin engine fighter was shown slight superiority to a single engine one in an vulnerability，but single engine fighters were a little predominant in susceptibility This paper includes the trade-off study results on the number of engines for the supersonic light attack aircraft with single and twin engines. Twin engine configuration is 8%, 26%, and 13% higher than single engine one in MTOGW, Flyaway Cost, and LCC respectively. Little difference has been found in RM&S, Maneuver and field performance. According to the factors above, single engine fighter is profitable for low class and twin engine one for medium and higher class.

• Proceedings of the Korean Information Science Society Conference
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• 2011.06a
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• pp.403-406
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• 2011

한국해양연구원에서는 국토해양부의 지원을 받아 2010년 7월부터 새로운 개념의 해저로봇 개발에 착수하였다. 새로이 개발되는 해저로봇은 프로펠러 방식으로 추력을 얻는 기존의 해저로봇과는 달리 여러 개의 관절로 이루어진 6개의 다리를 이용하여 해저면에 근접해서 보행과 유영으로 이동하는 해저로봇으로 강조류와 악시계의 환경에서도 운용이 가능한 로봇이다. 이 해저보행로봇 시스템은 선상시스템과 완충기, 그리고 해저보행로봇으로 구성되며, 이들 사이는 광변환기를 통해서 광케이블로 연결된다. 선상시스템에는 해저로봇의 제어 및 모니터링을 위하여 10대의 컴퓨터가 설치되어 있고, 완충기와 해저로봇에 각각 1대의 입출력 컴퓨터가 내장되어 장착된 센서와 모터의 인터페이스를 담당한다. 본 논문에서는 해저보행로봇의 통신 시스템을 소개하고, 이 통신 시스템에서 사용되기 위하여 설계된 메시지의 통신 프로토콜을 설명한다. 해저보행로봇 시스템의 주 네트워크는 기가비트 이더넷이며, 안정된 통신 환경의 소규모 독립 네트워크이다. 완충기와 해저보행로봇에는 최대 100㎐로 동작하는 다양한 직렬 통신 방식을 갖는 다수의 센서와 모터가 장착되어 있는데, 입출력 컴퓨터가 이더넷 네트워크와의 인터페이스 역할을 수행하여 계층적 네트워크를 구성한다. 로봇 제어에서는 실시간성이 중요하기 때문에 이더넷에서 통신 메시지는 한 번의 전송으로 여러 컴퓨터에 전달할 수 있도록 멀티캐스팅을 사용하여 전송된다. 설계된 통신 프로토콜은 이러한 해저로봇 시스템의 특성에 적합한 간결한 구조로 설계되었으며, 최대 255개의 주소를 지정할 수 있고 255 종류의 메시지 형태를 설정할 수 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.347-350
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• 2006

The rocket grade hydrogen peroxide has been widely used as a monopropellant in propulsion systems. In the present paper, we described an experimental study of a catalytic reactor that employs two stage catalyst beds to enhance the low temperature performance of the reactor. $K_2MnO_4$ was chosen as the catalyst for the initial stage of the reactor bed for its superior behavior in the low temperature regime. LSC was used for the catalyst of the second stage of the reactor. The gas generator with combined catalyst beds was built and tested to exhibit high decomposition efficiency over 90% and successful cold-start characteristics.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.501-504
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• 2011

In this study, structural design of the propeller blade for turboprop aircraft was performed. The propeller shall have high strength to get the thrust to fly at high speed. The high stiffness and strength carbon/epoxy composite material was used for the major structure and skin-spar-foam sandwich structural type was adopted for improvement of lightness. As a design procedure for the present study, firstly the structural design load was estimated through investigation on aerodynamic load and then flanges of spars from major bending loads and the skin from shear loads were preliminarily sized using the netting rule. In order to investigate the structural safety and stability, stress analysis was performed by finite element analysis code MSC. NASTRAN. Finally, it is investigated that designed blade have high efficiency and structural safety to analyze of aerodynamic and structural design results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.213-220
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• 2010

This paper presents the analysis results of trajectory, performance and attitude control based on the first flight data of the KSLV-I. The KSLV-I had a fairing separation problem and failed to inject spacecraft into the orbit. In this paper, the trajectory, flight performance, and attitude control was analyzed considering the influence of unseparated fairing. Moreover, the flight results and performance of the inertial navigation and guidance system were presented. As a results of post-flight analysis, any other problem besides the fairing separation problem was not happened and onboard equipment functioned normally.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.34-40
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• 2006

For a cooling performance research of the combustor operated in a extreme environment of a high temperature and high pressure, we accomplished a cooling performance analysis. Generally a heat transfer characteristic in cooling passage is known well experimentally and theoretically, however heat flux in the combustion chamber isn't. In this study, fluid flow combined with heat transfer and thermal structural analysis is accomplished about a combustor nozzle. We tried to analyze the cooling performance with a heat transfer characteristic of a gas and coolant side in the view point of quantity on the mass flow rate to be supplied to the cooling channel. And finally, evaluation on the thermal and structural safety of nozzle wall material was accomplished.