• 한국자동차공학회논문집
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• 제25권1호
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• pp.19-27
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• 2017

In this paper, a simulator hardware and control design for an electronic parking brake (EPB) are proposed for emergency vehicle braking when the hydraulic break and anti-lock brake systems (ABS) fail to function. EPB systems are designed specifically for park braking and are usually installed on the rear wheels. However, in an emergency situation when all vehicle brake systems fail, the EPB can be utilized to stop the vehicle and track the target slip ratio as the ABS. This paper analyzed the non-linear EBP of the type of motor on caliper (MoC) based on experiments. A simulator hardware is also designed to validate the performance of the designed EPB controller in terms of braking distance and performance in tracking the target slip ratio. Through the experimental analysis, it is confirmed that a sliding mode controller can be applied on a non-linear EPB to track the target slip ratio.

• 제어로봇시스템학회논문지
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• 제14권8호
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• pp.824-836
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• 2008

Relaxed static stability(RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. Therefore, flight control systems are necessary to stabilize an unstable aircraft, and provides adequate handling qualities and achieve performance enhancements. Standard FCSDVP (Flight Control System Design and Verification Process) is provided to reduce development period of the flight control system. In addition, if this process is employed in developing flight control system, it reduces the trial and error for development and verification of flight control system. This paper addresses the flight control system design and verification process for the RSS aircraft utilizing design goal based on military specifications, linear and nonlinear system design and verification based on universal software, handling quality test based on HILS(Hardware In-the-Loop Simulator) environment, and ground and flight test results to verify aircraft dynamic flight responses.

• 제어로봇시스템학회논문지
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• 제10권10호
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• pp.956-960
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• 2004

The Vehicle Dynamic Simulator(VDS) is a key equipment of the performance verification of attitude control subsystem and it simulates the real dynamic environment that spacecraft undergoes during mission operation. All the software models and hardware interfaces necessary for the closed-loop simulation of the spacecraft dynamics are implemented. Using VDS, KOMPAT-2 attitude control logic functions and performance was verified. In this paper, the hardware and software configurations of KOMPSAT-2 VDS was described briefly and the information flow and exchanges between software models and actual hardwares during close loop simulation was described in the systematic point of view.

• 대한전기학회논문지:전력기술부문A
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• 제52권1호
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• pp.1-8
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• 2003

This paper presents a novel application method of H$_{\infty}$ optimization method to the design of Power System Stabilizer(PSS) and experimental results through hardware simulator. The approach is focused on decision of performance index and selection strategy of weighting functions together with its tuning for direct design. As the Purpose of the PSS is to increase system damping at very narrow frequency band, weighting functions are determined differently from the case of general servo system control. The designed PSS was confirmed through experiments on a hardware simulator.

• Journal of Electrical Engineering and Technology
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• 제9권3호
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• pp.1072-1079
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• 2014

This paper introduces a coordinated droop control for the stand-alone DC micro-grid, which is composed of photo-voltaic generator, wind power generator, engine generator, and battery storage with SOC (state of charge) management system. The operation of stand-alone DC micro-grid with the coordinated droop control was analyzed with computer simulation. Based on simulation results, a hardware simulator was built and tested to analyze the performance of proposed system. The developed simulation model and hardware simulator can be utilized to design the actual stand-alone DC micro-grid and to analyze its performance. The coordinated droop control can improve the reliability and efficiency of the stand-alone DC micro-grid.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2003년도 춘계학술대회 논문집
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• pp.1139-1143
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• 2003

HILS(Hardware-In-the-Loop Simulation) is a scheme that incorporates hardware components of primary concern in the numerical simulation environment. Due to its advantages over actual vehicle test and pure simulation, HILS is being widely accepted in automotive industries as test benches for vehicle control units. Developed in this study is a HILS system for EHB(Electro-Hydraulic Brake) systems that include a high pressure generator and a valve control system that independently modulates the brake pressures at four wheels. An EHB control logic was tested in the HILS system. Test results under various driving conditions are presented and compared with the VDC logic.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.1465-1469
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• 2003

In general satellite verification process, the AOCS (Attitude & Orbit Control Subsystem) should be verified through several kinds of verification test which can be divided into two major category like FBT (Fixed Bed Test) and polarity test. And each test performed in different levels such as ETB (Electrical Test Bed) and satellite level. The test method of FBT is to simulate satellite dynamics with sensors and actuators supported by necessary environmental models in ETB level. The VDS (Vehicle Dynamic Simulator) try to make the real situation as possible as the on-board processor will undergo after launch. The purpose of FBT test is to verify that attitude control logic function and hardware interface is designed as expected with closed loop simulation. The VDS is one of major equipments for performing FBT and consists of software and hardware parts. The VDS operates in VME environments with target board, several commercial boards and custom boards based on the VxWorks real time operating system. In order to make time synchronization between VDS and satellite on-board processor, high reliable semaphore was implemented to make synchronization with the interrupt signal from on-board processor. In this paper, the real-time operating environment used on VDS equipment is introduced, and the hardware and software configurations of VDS summarized in the systematic point of view. Also, we try to figure out the operational concept of VDS and AOCS verification test method with close-loop simulation.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2005년도 ICCAS
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• pp.2290-2295
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• 2005

In this paper, it is developed simulator system of 3 D.O.F parallel robot for educate of expertness. This simulator system is composed of three parts ? 3 D.O.F parallel robot, controller (hardware) and software. First, basic structure of the robot is 3 active rotary actuator that small geared step motor with fixed base. An input-link is connected to this actuator, and this input-link can connect two ball joints. Thus, two couplers can be connected to the input-link as a pair. An end-plate, which is jointed by a ball joint, can be connected to the opposite side of the coupler. A sub-link is produced and installed to the internal spring, and then this sub-link is connected to the upper and bottom side of the coupler in order to prevent a certain bending or deformation of the two couplers. The robot has the maximum diameter of 230 mm, 10 kg of weight (include the table), and maximum height of 300 mm. Hardware for control of the robot is composed of computer, micro controller, pulse generator, and motor driver. The PC used in the controller sends commands to the controller, and transform signals input by the user to the coordinate value of the robot by substituting it into equations of kinematics and inverse kinematics. A controller transfer the coordinate value calculated in the PC to a pulse generator by transforming it into signals. A pulse generator analyzes commands, which include the information received from the micro controller. A motor driver transfer the pulse received from the pulse generator to a step motor, and protects against the over-load of the motor Finally, software is a learning purposed control program, which presents the principle of a robot operation and actual implementation. The benefit of this program is that easy for a novice to use. Developed robot simulator system can be practically applied to understand the principle of parallel mechanism, motors, sensor, and various other parts.

• 한국위성정보통신학회논문지
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• 제5권2호
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• pp.1-7
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• 2010

기존 위성 탑재소프트웨어 개발은 제한된 하드웨어 기반의 Software Test Bed(STB)에서 개발 및 검증이 이루어졌다. 하지만 탑재소프트웨어 개발 시 하드웨어의 개발 진행에 따라 소프트웨어 개발 일정이 심각한 영향을 받았으며 다수의 소프트웨어 엔지니어가 제한된 STB를 동시에 사용할 수 없는 문제가 지속적으로 제기 되었다. 또한 최종 비행 하드웨어 모델과 상이한 형상으로 인하여 실제 운영을 고려한 부분의 경우 소프트웨어 개발 및 검증에 많은 어려움이 있었다. 이러한 문제를 해결하기 위하여 위성 개발초기부터 소프트웨어 기반의 위성 시뮬레이터 개발이 시작되었으며, 위성 시뮬레이터는 탑재 컴퓨터 및 이와 관련된 모든 하드웨어를 모사해주며 비행 하드웨어 모델과 동일한 형상을 갖추고 있다. 또한 소프트웨어 개발자를 위한 디버깅 채널과 테스트 환경을 제공하며, 별도의 수정 없이 탑재소프트웨어를 로딩 할 수 있으며 유사 실시간 시스템 실행을 지원한다. 본 논문에서는 소프트웨어 기반의 시뮬레이터의 구조와 개발방안을 제시하고 시뮬레이터 기반에서 탑재소프트웨어 개발 및 검증 결과를 소개한다.

• 한국위성정보통신학회논문지
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• 제7권2호
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• pp.80-86
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• 2012

기존 하드웨어 기반의 소프트웨어 검증 플랫폼이 가지는 제한 조건을 해결하는 방안으로 위성 개발 초기부터 소프트웨어 기반의 위성 시뮬레이터 개발이 함께 시작되며, 위성 시뮬레이터를 활용할 경우 탑재소프트웨어 개발이 지속적으로 이루어 질 수 있는 큰 장점을 가지게 된다. 위성 시뮬레이터는 탑재컴퓨터, 위성의 전자장비 그리고 탑재체까지 모두 모사해주며 소프트웨어 개발자들이 사용할 수 있도록 쉽게 복제, 배포가 가능하며 위성 하드웨어 형상이 변경되더라도 적용 및 변경이 용이하다. 그리고 실제 하드웨어에서 동작하는 탑재소프트웨어를 별도의 수정 없이 로딩할 수 있으며, 개발자를 위한 디버깅 채널과 테스트 환경을 제공하며 실제 수행시간 보다 빠르게 가속화 할 수 있는 기능을 제공한다. 본 논문에서는 현재 개발 중인 정지궤도복합위성의 특징인 Hot-Standby 잉여구조를 지원하기 위한 위성 시뮬레이터의 구조와 개발방안을 제시하고, 시뮬레이터 기반에서 탑재소프트웨어 개발 및 테스트 방안을 제시한다.