• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2008.10a
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• pp.183-188
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• 2008

Engine control/performance model for helicopter simulator is one of the most important models which affect flight performance and handling quality. It is typical to develop the model based on the raw data and models from the engine designers/manufacturers. The approaches in this study were to develop the basic model based on the available resources and to tune and verify it based on the ground/flight test results. The maintenance manuals of TB3-117 which is installed in KA-32T were reviewed and the components to be simulated for the engine control model were categorized and modeled. Piece-wise linear modeling method was used for the engine performance model. The engine performance data in the engine maintenance manuals were incorporated into the engine steady state performance tables, which were incorporated with the transfer functions for the dynamic performance. Engine control/performance model was compared and tuned with the ground/flight test results. It was verified that the fidelity of the model was within the tolerances in FAA AC120-63.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.12 no.12
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• pp.2239-2246
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• 2008

Engine control/performance model for helicopter simulator if one of the most important models which affect flight performance and handling quality. It is typical to develop the model based on the raw data and models from the engine designers/manufacturers. The approaches in this study were to develop the basic model bated on the available resources and to tune and verify it based on the ground/flight test results. The maintenance manuals of TB3-117 which is installed in KA-327 were reviewed and the components to be simulated for the engine control model were categorized and modeled. Piece-wise linear modeling method was used for the engine performance model. The engine performance data in the engine maintenance manuals were incorporated into the engine steady state performance tablet, which were incorporated with the transfer functions for the dynamic performance. Engine control/performance model was compared and tuned with the round/flight test results. It was verified that the fidelity of the model was within the tolerances in FAA AC120-63.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.6
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• pp.116-123
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• 2002

This paper describes the development of gimbals engine actuation system for KSR(Korean Sounding Rocket)-III which performs the attitude control of pitch and yaw axes by thrust vector control of liquid propellant gimbals engine. The development requirements of configuration, performance and environment are introduced, and the principles and details of components and system development are discussed. The developed system successfully fulfilled its own performance and environmental evaluation. It will be planned to perform verification of interface and integration compatibility with other related systems, and then mounted on KSR-III as a flight hardware system.

• Journal of the Korea Institute of Military Science and Technology
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• v.3 no.1
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• pp.92-105
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• 2000

Core technologies of powerplants, which are necessary for the development of Korean type combat aircraft, are analyzed. And then, the acquisition methodologies for the technologies are proposed. With respect to the aircraft engine design and manufacturing technologies, simple basic technologies such as component manufacturing and assembling technology come to close to those of advanced countries, but the core technologies were not acquired or in the understanding level only. Therefore, the research on the component manufacturing technology should be specialized for buildup of international competition first, and the research on core technologies such as high pressure compressor design, blisk, FADEC and hollow fan blade design should be concentrated step by step by taking an active participation in the development project of international cooperative aircraft powerplants.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1196-1199
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• 2017

A series-hybrid power system was designed for quad-tilt prop UAV and the characteristics was analysed. The power system consists of a 4.5kW rotary engine-generator and a li-battery as power sources, a power controller manages the overall power and supplies to the vehicle system. The output power of the engine is to be matched with the generator performance considering mechanical driving loss and generating efficiency, and also loss for charging and discharging of the battery energy. It is applied that the constant speed operation of the engine-generator to minimize overall fuel consumption by integrating the generating power and the battery energy, consequentially the battery capacity and characteristics could be important factors for improvement of the system efficiency.

• Journal of the Korea Institute of Military Science and Technology
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• v.2 no.1
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• pp.121-131
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• 1999

Automatic Rudder Trim System(ARTS) is a device to reduce the pilot's work load for rudder trimming greatly required in varying abruptly aircraft's engine power. This paper represents a technical analysis and a design of control law of the ARTS. The control law of the ARTS is designed based on the analysis of aircraft's characteristics, system's requirements, and limitations. The control law is comprised of open loop control using the rudder trim map for a specific aircraft and closed loop control to compensate the error of the open loop control system. flight test results show that the ARTS can reduce pilot's work load for rudder trimming dramatically and can compensate the aircraft's transient yaw motion.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.9
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• pp.825-832
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• 2016

This paper describes the development of a data bus analyzer for use in avionics systems integration test. The data bus analyzer is equipped with MIL-STD-1553B, CAN and Ethernet interface cards which is incorporated in a majority of the avionics systems to accommodate a variety of interfaces. It has an individual hardware for a capture engine and a analyzing engine in order to perform the collection and the analysis of the bus data at the same time efficiently. It provides a data display function of the grid, 2-dimensional and 3-dimensional form to increase the data analysis efficiency. Verification of the data bus analyzer was carried out module unit testing and inter-module integration testing on the basis of the test procedures. Verification of interlocking requirement and usefulness of developed equipment was confirmed through an integration test result performed on a system integration laboratory of aircraft which is an actual testing environment.