• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.10
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• pp.34-39
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• 2003

Morphing wing sections actuated by piezoceramic actuator LIPCA have been designed and their actuation displacements estimated by using the therml analogy and MSC/NASTRAN based on the linear elasticity. The wing sections are fabricated as the design and tested for evaluation. Measured actuation displacements were larger than the estimated values mainly due to the material non-linearity of the PIT wafer. The morphing wing sections can be used for control surfaces of small scale UAVs or MAVs.

• Journal of the Korea Society for Simulation
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• v.15 no.1
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• pp.43-50
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• 2006

The major objective of this paper is to propose a hybrid simulation environment for autonomous UAV system by integrating the continuous-time model with discrete-event model. Proposed system is able to support high autonomous behavior by combining the planner, recognizer, and controller model to deal with the HL20 AIRPLANE model. Thus, the high level decision may be efficiently issued even upon the unexpected circumstance. The proposed system model has been successfully verified by several simulation test performed on the DEVS simulation S/W environment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.11
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• pp.999-1005
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• 2007

In case of an abnormal condition of control surface, the real-time estimation of aerodynamic derivatives are required for the reconfigurable control system to be flight for missions or return to the head office. The goal of this paper is to represent a technique of fault detection to the control surface as a base research to the fault tolerant control system for safety improvement of UAV. The real-time system identification for the fault detection to the control surface was applied with the recursive Fourier Transform and verified through the HILS and flight test. The failures of the control surface are detected by comparing the control derivatives in fault condition with the normal condition. As a result from the flight test, we have confirmed that the control derivatives of fault condition less than about 50% in the normal condition.

• Proceedings of the KIEE Conference
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• 2001.07d
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• pp.2234-2236
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• 2001

This paper describes an implementation of a radiocontrolled airplane attitude control. To obtain the model of motion, stabilizing and control coefficients, we derive the related paramaters from aerodynamics, propulsion, gravity, wind correction and atmosphere. In this model, after separating longitudinal axis and lateral axis, we can get longitudinal axis model and lateral axis model by using actuator and dynamic characteristics of engine. From these two models, we experiment two divided parts-linear part, and nonlinear part.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.6
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• pp.574-580
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• 2008

This paper has proposed a controller switching scheme for full-envelope aircraft control using the bumpless transfer implementation algorithm developed recently. This switching scheme has combined by proper rules the common existing method which switches the controller according to attitude and mach number of the aircraft with an optimization method which uses the cost function relating to bump phenomenon by means of controller switching criterion. This paper exemplifies the control performance improvement via simulations applied to a high performance aircraft benchmark problem in a wide operating range to test the proposed controller switching scheme.

• Journal of Aerospace System Engineering
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• v.14 no.5
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• pp.49-57
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• 2020

The KC-100 has completed civil type certification with the Ministry of Land, Infrastructure, and Transport, and is currently under development as an unmanned aerial vehicle as part of the Ministry of Land, Infrastructure, and Transport. The Certification Technology of small Unmanned Airplane system (CTsUA system), which is an unmanned KC-100, is being developed to enable the installation of heavy-duty mission equipment and long-time flight missions. This study investigated the process and results of analyzing various parameters such as aircraft weight, airspeed, flight altitude, required horsepower, and fuel consumption at each stage to construct a mission profile based on the operational concept of the CTsUA system. To maintain a maximum take-off weight of 3,600 lbs (1,633 kg), the analysis determined that the weight of the application equipment for the unmanned system should be kept below 80 lbs (36 kg).

• Current Industrial and Technological Trends in Aerospace
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• v.6 no.2
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• pp.143-153
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• 2008

This paper describes the current research trend and future development direction of autonomous flight of the aircraft. The autonomous flight means that aircraft control system recognize and cope with the emergency situation confronted during the flight by itself. Current research for autonomous flight technology is mainly performed for the application to unmanned air vehicle. Considering advent of future air traffic management system and increasing demand of the unmanned air vehicle application, however, autonomous flight technology required to be combined with future air traffic management system. In this paper, the current air traffic management system and anticipating change in future air traffic management system was investigated and research activities of autonomous flight technology was described as well as future prospect.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.14 no.1
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• pp.267-275
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• 2010

Recently, the implementation & modern policy for Global Navigation Satellite System have actively been performed by USA, RUSSIA, EU & CHINA. Therefore 100+ navigation satellites will be in orbit by 2015, and the user of military and civil will benefit from the use of a total constellation of 100+ satellites. It means that the deepest dependence to GPS would be declined. In the paper, the latest technology development & implementation policy of GNSS have been analyzed. Specially, we focused on circumstance change of GNSS & application of navigation technology for modem weapon system. Finally, the application strategy of the integrated GNSS is suggested for military and civil as well.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.12
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• pp.1217-1224
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• 2009

A simple and effective guidance and control scheme that enables autonomous three-dimensional path-following for a fixed wing aircraft is presented. The method utilizes the nonlinear path-following guidance law for the outer loop that creates steering acceleration command based on the desired flight path and the current position and velocity of the vehicle. The scheme considers the gravity in the guidance level, where it is subtracted from the acceleration command to form the specific force acceleration command which the aircraft is better suited to follow than the total acceleration command in the inner-loop. A roll attitude control scheme is also presented that enables inverted flight or sideslip maneuvers such as slow roll and knife-edge. A series of aerobatic maneuvers are demonstrated through simulations to show the potential of the proposed scheme.

• The Journal of the Convergence on Culture Technology
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• v.9 no.6
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• pp.927-933
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• 2023

In modern times, with advances in semiconductor technology such as electronic devices, the need to improve the quality of onboard equipment with advanced electronic parts in automobiles, drones, airplanes, projectiles, and various fields, and reduce the impact of various disturbances on onboard equipment is becoming more important. Vibration control through hardware must be determined to prevent damage and improve quality to equipment operating in various environments such as automobiles, drones, airplanes, and projectiles. This study focuses on the study of vibration damping systems to protect mounted equipment from various disturbances and improve stability. Dynamic characteristics analysis, including compressive stiffness, damping rate, and frequency response, and vibration characteristics in the frequency domain of rubber dampers were identified through FEM analysis to identify the characteristics of rubber dampers. Through these findings, we would like to present the criteria for selecting a suitable rubber damper under various disturbance conditions.