• Journal of the Korean Society for Aviation and Aeronautics
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• v.17 no.1
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• pp.9-16
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• 2009

The analysis of an aircraft flight dynamics is recently very convenient because of the introduction of state-space method and a well-developed package software. The representation of a dynamic system is described as a simple form of matrix calculation and the unique form of model is available for the linear or nonlinear, time variant or time invariant, mono variable or multi variable system with state-space method. And this analysis can be simplified with the specific functions of a package software and it is very simplified to execute the simulation of the dynamic characteristics for an aircraft model with an interactive graphical treatment. The purpose of this study is to develope an educational flight simulator for the students who need to analyze the dynamic characteristics of an aircraft that is primarily to execute the simulation for the analysis of the transient response and frequency response of an aircraft stability. Furthermore the dynamic characteristics of an aircraft motion is set up as dynamical animation tool for the control response on 3-axis motions of an aircraft.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.2215-2216
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• 2011

In this study, the dynamic characteristic of a contact wire and pantograph suppling electrical power to electrical railway vehicle is investigated from an electrical response point of view. To analysis voltage and current waveforms by induced contact loss phenomenon on driving electrical railway vehicle, a hardware Simulator which considered contact loss between contact wire and the pantograph as well as contact wire deviation is developed. It is confirmed that a contact wire and pantograph model are necessary for studying the dynamic behavior of the pantograph system. Throughout prototype simulator and contact wire and catenary wire experiments, it is confirmed that current waveforms is distorted by contact loss phenomenon and in case of driving electrical railway vehicle.

• Proceedings of the KIPE Conference
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• 2003.07a
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• pp.383-388
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• 2003

The stand alone PV system's stability and cost is influenced by a design method, as its application products are various. In order to systematize the the stand alone PV system's design method based on experience, this research settled the capacity computation method of PV module and battery and developed a simulator. And Its characteristic is confirmed by applying to PV street lamp design.

• 제어로봇시스템학회:학술대회논문집
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• 1989.10a
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• pp.1-6
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• 1989

For the design of synergistic hydraulic motion simulator, the load locus method is introduced. The given mass property of load and its velocity profile is resolved into the load locus of each actuator which decides the suitable valve and cylinder. This asymmtic cylinder and 4 way valve system have the pressure oscillation on zero velocity. The variable structure position controller which based on linearized flow equation makes elimination of the unstable pressure oscillation.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2001.04a
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• pp.715-718
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• 2001

Test in the development of vehicle consist of driving test and simulation test. The last one has many advantages. It can reduce time and cost during development, can overcome the spacial and environmental limitation, and can provides repeatabilities of similar experiments and various data. In these reason, the simulation test is used more for analysis and development of new vehicle. In this research the result of kinematic analysis on multi-axis simulator is compared with the simulated result using dynamic analysis program, ADAMS, and the maximum stress and strain are analyzed for the safety of link and specifications of optimal design using finite element method.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.25 no.3
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• pp.478-485
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• 2001

A dynamic load simulator(DLS) which can reproduce on-ground the aerodynamic hinge moment of control surface is an essential rig for the performance and stability test of aircraft actuation system. By setting up load actuator as counter acting with the control surface driving actuator and designing an appropriate force control system for load actuator, DLS can be mechanized. Obtaining an accurate mathematical model for the DLS is the first step to successfully design an aerodynamic load replicati on system. Two theoretical models are presented and tested for their validities with the experimental results, which turns out to be not successful. An alternative way of using system identification approaches in investigated to develop a good nominal model for DLS dynamics, and suitable uncertainty bounds for this nominal model are proposed with the consideration of experimental results.

• Proceedings of the Korea Society for Simulation Conference
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• 2005.05a
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• pp.106-111
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• 2005

LCC(Launch Control Center) in NARO Space Center perform a data monitoring and control through the interface to the external system of launch vehicle. Launch Control function needs a high reliability and processing speed. Hence, LCC's remote control system configure a real time system. An important role of the Simulation system is discovering a risk element and minimize it When developing a launch control system. Also, secure a development technique to solve the risks. Launch Vehicle simulator is composed of various component at characteristic of the Launch Vehicle. To be like this each function component the developer will be able to develop easily in order, it using the LabVIEW which is a Graphical Program and it programs, The LabVIEW GOOP(Graphical Object-orinted Programming) which supports an Object-orinted programming it uses with the Component it develops will have a strong point which reusability and a unit test, maintenance, size of program and individual developments.

• Journal of the Society of Naval Architects of Korea
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• v.47 no.6
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• pp.776-781
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• 2010

In the ship-handling simulator, it is important for a ship manoeuvring model to represent the dynamic characteristic of a ship and to be simple for reducing calculation time. Especially, even if principal dimensions of a ship are given in initial design stage, or manoeuvring test data are only given by model or real ship's trials, simulations are often needed to check the manoeuvrability of a ship. In this paper, a simple manoeuvring model based on turning test data of a ship is mathematically developed. And the simulation results are verified by comparing with turning test results of a real ship.

• The Transactions of The Korean Institute of Electrical Engineers
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• v.57 no.4
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• pp.617-624
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• 2008

This paper proposes design and implementation of wind turbine simulators which incorporate the turbine dynamic characteristics. At first, the turbine output characteristic in steady state is modelled as a function of wind speed and then dynamic characteristics are modelled such as pitch angle control, torsional vibration, tower shadow effect, wind shear effect, and inertia effect. In addition, a wind speed simulator is developed which can generate the real wind speed pattern. The wind turbine simulator is implemented with 3[kW] M-G set(cage-type induction motor coupled with doubly-fed induction generator) at laboratory.

• Journal of the Korean Society for Railway
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• v.7 no.1
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• pp.1-8
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• 2004

A newly-built inverter has to undergo a series of stress tests in the final stage of production line. This can be achieved by connecting it to a dynamometer consisting of a three-phase machine joined by a rigid shaft to a DC load machine. The latter is controlled to create some specific load characteristic needed for the test. In this paper a test method is proposed, in which no mechanical equipment is needed. The suggested test stand consists only of a inverter to be tested and a simulator converter. Both devices are connected back-to-back on the AC-side via smoothing reactors. The simulator operates in real-time as an equivalent load circuit, so that the device under test will only notice the behaviour of a three-phase machine under consideration of the load. In oder to prove rightness of the suggested test method, the simulation and actural experiment carried out emulation for a 2.2kW induction motor.