• Transactions of the Korean Society of Mechanical Engineers A
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• v.32 no.2
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• pp.162-169
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• 2008

Compliance effect consideration method for real-time multibody vehicle dynamics is proposed using quasi-static analysis. The multibody vehicle model without bush elements is used based on the subsystem synthesis method which provides real-time computation on the multibody vehicle model. Reaction forces are computed in the suspension subsystem. According to deformation from the quasi-static analysis using reaction forces and bush stiffness, suspension hardpoint locations and suspension linkage orientation are changed. To validate the proposed method, quarter car simulations of McPherson strut and multilink suspension subsystems are performed. Full car bump run simulations and fish hook handling test simulations are also carried out comparing with the ADAMS vehicle model with bush elements. CPU times are also measured to see the real-time capabilities of the proposed method.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.21 no.1
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• pp.1-7
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• 2013

To have the competitiveness in the future worldwide small aircraft market, we should be able to develop the aircraft which is highly safe, easy to fly, and having excellent flight characteristics. FBW(Fly-By Wire) system is essential for the enhancement of flight safety and control easiness. FBW system that has been applied only to the modern fighter and transport aircraft is recently applied to smaller aircraft such as regional aircraft, business aircraft and even small aircraft. The purpose of this research includes the development of flight control computer, the definition of FBW system component, the design concept of each component for redundant management, OFP(Operational Flight Program) development, FBW system integration and HILS(Hardware In-the Loop Simulation) verification environment to test this FBW system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.10
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• pp.805-812
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• 2013

The operational flight program(OFP) which has the functions of I/O processing with avionics, flight control logic calculation, fault diagnosis and redundancy mode is embedded in the flight control computer of Smart UAV. The OFP was developed in the environment of PowerPC 755 processor and VxWorks 5.5 real-time operating system. The OFP consists of memory access module, device I/O signal processing module and flight control logic module, and each module was designed to hierarchical structure. Memory access and signal processing modules were verified from bench test, and flight control logic module was verified from hardware-in-the-loop simulation(HILS) test, ground integration test, tethered test and flight test. This paper describes development environment, software structure, verification and management method of the OFP.

• Proceedings of the KIEE Conference
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• 2004.07d
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• pp.2155-2157
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• 2004

본 논문은 항공기용 Brake-By-Wire System 개발을 위한 설계 및 제작 그리고 시험에 관한 내용을 다루고 있다. 개발된 디지털제어기(Digital Control Unit)는 기본적인 제동기능 외에 Anti-skid 기능, Locked Wheel Protection 기능, Touchdown Protection 기능 등을 수행할 수 있다. 기능의 수행검중을 위해 실시간 HILS (Hardware In the Loop Simulation) 시험 및 Dynamometer 시험을 실시하여, 개발된 Brake-By-Wire System의 기능 및 성능을 확인하였다.

• Proceedings of the KIPE Conference
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• 2015.07a
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• pp.425-426
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• 2015

본 논문에서는 실시간 시뮬레이터를 이용하여 1MW PCS(Power Conditioning System)의 불평형 비간섭 전류제어(Unbalanced Current Control under Unbalanced Condition) 알고리즘을 검증하였다. 3상 불평형 발생 시, 기존의 전류제어는 전압의 불안정으로 인해 전류의 목표 값이 흔들리는 현상을 보인다. 하지만, 3상 불평형 비간섭 제어는 불평형 상황 전압과 전류를 정상과 역상 성분으로 나누고, 이를 독립적으로 제어함으로써 더욱 우수한 성능을 가진다. 본 논문은 1MW PCS의 HILS(Hardware-In-the-Loop Simulation) 환경을 구축하여 실시간 시뮬레이터에서 실제 출력되는 전류의 불평형을 확인하고, 이를 개선하는 것을 검증하였다.

• Annual Conference of KIPS
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• 2017.11a
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• pp.526-529
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• 2017

Deep Drive 플랫폼 개발 기술인 HILS(Hardware In the Loop Simulation)는 시스템 모델에 근간을 둔 실시간 시뮬레이션 기법과 H/W를 접목시킨 실시간 해석 기법으로, 플랫폼 개발으로 현재는 난해성이 있는 자율 주행 자동차 실차의 테스트 베드를 구현하여, 여러 가지 실험을 통해 실제 차의 운행에 대한 피드백을 제공, 운전자로부터 안전을 보장하기 위한 기술 보장, 기술의 상용화, 양산화 연구에 도움을 줄수 있음.

• Journal of Aerospace System Engineering
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• v.16 no.4
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• pp.77-87
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• 2022

The Precision Aerial Delivery System is an instrument designed to improve the poor landing accuracy of aerial delivery system with conventional circular parachutes, and is equipped with an Airborne Guidance Unit to safely transport supplies to the desired destination. Currently, the landing accuracy of the PADS product is reported as CEP₅₀ 100m and also differs significantly, depending on the actual topography and weather environment. In this study, HILS was constructed based on the 6DOF nonlinear modeling of PADS to analyze the maneuver characteristics of Ram Air Parachute under wind environments. By using the new algorithm a precision soft landing algorithm including Energy Management and Final Approach is designed. HILS results show that it is possible to achieve a precise soft landing within CEP₅₀ 40m, and it can be exploited to develop an actual PADS drop test.

• The Transactions of the Korean Institute of Power Electronics
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• v.26 no.2
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• pp.75-81
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• 2021

This study analyzes the resonance characteristics caused by the mutual interference between LCL filters and the grid impedance under the parallel operation of the grid-connected inverter using the LCL filter. These characteristics are verified through simulation and experiment. Two inverters are used to connect to the grid in parallel, and the system parameters, including the LCL filter, are set to the same conditions. In the case of inverters running in parallel at the point of common coupling, the presence of grid impedance causes mutual interference between the LCL filters of each inverter, and the deviation of the filter resonance frequency is analyzed to understand the parallel inverter. The correlation between the number of devices and the size of grid impedance is simulated by PSIM and verified by MATLAB. By connecting the real-time digital simulator Typhoon HILS to the DSP 28377 control board, the mutual interference characteristics are tested under the condition of two inverters running in parallel. The experimental and analysis results are the same, indicating the validity of the analysis.

• Transactions of the Korean Society of Automotive Engineers
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• v.17 no.1
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• pp.162-168
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• 2009

The real-time multibody vehicle model based on the subsystem synthesis method has been developed. Suspension, anti roll bar, steering, and tire subsystem models have been developed for vehicle dynamics. The compliance effect from bush element has been considered using a quasi-static method to achieve the real time requirement. To validate the developed vehicle model, a quarter car and a full vehicle simulations have been carried out comparing simulation results with those from the ADAMS vehicle model. Real time capability has been also validated by measuring CPU time of the simulation results.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2016.10a
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• pp.219-220
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• 2016

A power management system (PMS) has been an important part in a ship integrated control system. To evaluate a PMS for a liquefied natural gas carrier (LNGC), this research proposes a real-time hardware-in-the-loop simulation (HILS), which is composed of major component models such as turbine generator, diesel generator, governor, circuit breaker, and 3-phase loads on MATLAB/Simulink. In addition, FPGA based control console and main switchboard (MSBD) are constructed in order to develop an efficient control and a similar real environment in an LNGC PMS. A comparative study on the performance evaluation of PMS functions is conducted using two test cases for sharing electric power to consumers in an LNGC. The result shows that the proposed system has a high verification capability for the operating function and failure insertion evaluation as a PMS simulator.