• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.333-336
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• 2003

For long time, the takeoff and landing control of airship was worked by human handling. With the development of the autonomous control system, the exact controls during the takeoff and landing were required and lots of methods and algorithms were suggested. This paper presents the result of airship take-off and landing by buoyancy control using air ballonet volume change and performance control of pitch angle for stable flight within the desired altitude. For the complexity of airship's dynamics, firstly, simple PID controller was applied. Due to the various atmospheric conditions, this controller didn’t give satisfactory results. Therefore, new control method was designed to reduce rapidly the error between designed trajectory and actual trajectory by learning algorithm using an artificial neural network. Generally, ANN has various weaknesses such as large training time, selection of neuron and hidden layer numbers required to deal with complex problem. To overcome these drawbacks, in this paper, the RBFN (radial basis function network) controller developed.

• 항공우주시스템공학회지
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• 제14권2호
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• pp.20-27
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• 2020

Several uncertainties in the landing environment of an aircraft are not considered, such as the falling speed, ambient temperature, and sensor noise. These uncertainties negatively affect the performance of the controller applied to a landing gear. The sliding mode control (SMC) method, which maintains the optimal performance of a controller under uncertainties, is used in this study. The landing gear is equipped with a magnetorheological damper that changes the yield shear stress according to the applied magnetic field. The applied controller employs a hybrid control combining Skyhook control and force control. The SMC maintains the optimal performance of the hybrid control by minimizing the tracking error of the damper force, even in various landing environments where parameter uncertainties are applied. The effect of SMC is verified through co-simulation results from Simscape and Simulink.

• 한국항공우주학회지
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• 제50권9호
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• pp.639-646
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• 2022

본 논문은 사전에 알려지지 않은 환경에서 깊이지도를 이용하여 정보를 획득하고, 이를 기반으로 쿼드로터의 착륙 선택 알고리즘 성능을 분석한다. 무인항공기의 유도 및 제어시스템은 궤적 계획 유도시스템과 위치 및 자세 제어기로 구성된다. 아래를 향하는 짐벌 시스템에 부착된 스테레오 비전 센서가 획득한 깊이 정보를 이용하여 착륙 지점을 선정한다. 평탄도 정보는 사전 정의된 깊이지도 영역의 최대 깊이 차이 및 UAV와의 거리를 고려하여 산출한다. 본 논문에서는 3가지 착륙 방법을 제안하며 다양한 성능지수들을 활용하여 성능을 비교한다. 성능지수로는 UAV 이동 거리, 지도 정확도, 장애물 대응 시간 등을 고려한다.

• 한국항공운항학회지
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• 제20권1호
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• pp.86-93
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• 2012

Fuzzy control has emerged as a practical alternative to classical control schemes in controlling certain time-varying, nonlinear, and ill-defined processes. As the current of this kind of a research paradigm, we concluded that there is a need for application study of a fuzzy control theory to the flight control systems of small aircraft being to be developed at KARI. And then, this preliminary study was carried out to the automatic landing system of the canard aircraft (Firefly) for the purpose of the preparation of extension of research contents and various application areas, in which FMRLC was chosen as the fuzzy controller of the system.

• International Journal of Aerospace System Engineering
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• 제2권2호
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• pp.73-78
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• 2015

According to the characteristic of carrier-based aircraft, the method of solving safe set during arresting landing is discussed in this paper based on optimal control and invariant set theory. The safe sets of carrier aircraft are evaluated in different states on the characteristic of longitudinal augmented system by using the level set method. Then, the influence on the boundary of safe set under various factors is analyzed. At last, the maneuverability envelope protection is established based on the corresponding theory, and the validity of the system is verified through simulation. The results demonstrate preliminarily that: compared with mass and thrust, the elevator is the greatest influence factor for the boundary of safe set; the dynamic trajectory of carrier-based aircraft can be located at the interior of safe set effectively with the maneuverability envelope protection.

• 한국전자통신학회논문지
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• 제2권3호
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• pp.143-149
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• 2007

본 발표문에서는 게기착륙시스템이 항공기에 제공하는 유도신호의 기본원리인 공간변조에 대해서 논의함으로써 계기착륙시스템을 심도있게 이해하는데 도움이 되고자 하였다. 우선적으로 공간변조의 기본개념을 설명하였으며, 이와 함께 공간 변조된 신호가 항공기 수신기에 영향을 주어 방위각 및 활공각이 표시되기까지 전반적인 과정을 DDM(difference in depth of modulation) 및 항공기 수신기의 동작원리와 관련시켜 설명하였다.

• 제어로봇시스템학회논문지
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• 제14권6호
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• pp.608-614
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• 2008

This paper describes a location tracking system to guide landing process of an Unmanned Helicopter(UMH) exploiting MIT Cricket nodes. For automatic landing of a UMH, a precise positioning system is indispensable. However, GPS(Global Positioning System) is inadequate for tracking the three dimensional position of a UMH because of large positioning errors. The Cricket systems use Time-Difference-of-Arrival(TDoA) method with ultrasonic and RF(Radio Frequency) signals to measure distances. They operate in passive mode in that a listener attached to a moving device receives distance signals from several beacons located at fixed points on ground. Inevitably, this passive type of implementation causes large disturbances in measuring distances between beacons and the listener due to wind blow from propeller and turbulence of UMH body. To cope with this problem, we proposed active type of implementation for positioning a UMH. In this implementation, a beacon is set up at UMH body and four listeners are located at ground area at least where the UMH will land. A pair of Ultrasonic and RF signals from the beacon arrives at several listeners to calculate the position of the UMH. The distance signals among listeners are synchronized with a counter value appended to each distance signals from the beacon.

• 한국운동역학회지
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• 제25권1호
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• pp.29-37
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• 2015

Objective : The purpose of this study was to investigate the biomechanical properties of shock absorption strategy and postural stability during the drop landing for each types. Methods : The motions were captured with Vicon Motion Capture System, with the fourteen infra-red cameras (100Hz) and synchronized with GRF(ground reaction force) data(1000Hz). Ten male soccer players performed a drop landing with single-leg and bi-legs on the 30cm height box. Dependent variables were the CoM trajectory and the Joint Moment. Statistical computations were performed using the paired t-test and ANOVA with Turkey HSD as post-hoc. Results : The dominant leg was confirmed to show a significant difference between the left leg and right leg as the inverted pendulum model during Drop Landing(Phase 1 & Phase 2). One-leg drop landing type had the higher CoM displacement, the peak of joint moment with the shock absorption than Bi-leg landing type. As a lower extremity joint kinetics analysis, the knee joint showed a function of shock absorption in the anterior-posterior, and the hip joint showed a function of the stability and shock absorption in the medial-lateral directions. Conclusion : These findings indicate that the instant equilibrium of posture balance(phase 1) was assessed by the passive phase as Class 1 leverage on the effect of the stability of shock absorption(phase 2) assessed by the active phase on the effect of Class 2 leverage. Application : This study shows that the cause of musculo-skeletal injuries estimated to be focused on the passive phase of landing and this findings could help the prevention of lower damage from loads involving landing related to the game of sports.

• 한국운동역학회지
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• 제22권4호
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• pp.379-386
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• 2012

The aim of this study was to investigate and identify the differences in lower extremity energy dissipation strategies between drop-landing and countermovement-jump maneuvers. Fourteen recreational athletes(Age : $23.3{\pm}2.1years$, Height : $172.3{\pm}4.0cm$, Weight : $69.2{\pm}4.7kg$) were recruited and instructed to perform drop-landing from 45 cm height and countermovement-jump from 45 cm to 20 cm height. The landing phase was taken as the time between initial contact and peak knee flexion. A motion-capture system consisting of eight infra-red cameras was employed to collect kinematics data at a sampling rate of 200 Hz and a force-plate was used to collect GRF data at a sampling rate of 2000 Hz. Paired t-test was performed to determine the difference in kinematics and kinetics variables between each task. During the countermovement-jump task, all of lower extremity joint ROM and the hip joint eccentric moment were decreased and the ankle joint plantarflexion moment was increased than drop-landing task. In the eccentric work during countermovement-jump task, the ankle joint displayed greater while knee and hip joint showed lesser than drop-landing. Therefore, the knee joint acted as the key energy dissipater during drop-landing while the ankle joint contributed the most energy dissipation during countermovement-jump. Our findings collectively indicated that different energy dissipation strategies were adopted for drop-landing and countermovement-jump.

• 한국산학기술학회논문지
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• 제22권1호
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• pp.751-758
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• 2021

군수품은 품질 보증을 위해 개발과 양산단계에서 위험 식별을 수행해야 한다. 위험 식별은 부품, 구성품, 계통 등에 대한 고장 요소를 분석하는 것으로, 다양한 신뢰성 기법 중에서 고장 모드 영향 분석(FMEA)을 이용하고 있다. FMEA는 위험 식별 중 고장 요인에 대하여 분석하는 방법으로, 위험도(RPN)를 통해 관리할 수 있다. FMEA는 심각도, 발생도, 검출도가 같은 중요도로 평가되기 때문에 단점을 가진다. 퍼지 FMEA는 FMEA의 단점을 보완하기 위해 퍼지이론을 이용한 것이다. 퍼지 이론은 현상의 불확실한 상태를 표현해주는 방법으로, 정량적인 값을 제공한다. 본 논문에서, 퍼지 FMEA는 회전익 항공기 착륙장치의 고장 모드에 대한 객관적인 평가를 위해 적용되었다. 착륙장치에 대한 위험도 분석을 위해, 퍼지 규칙과 소속 함수를 구성하였다. 퍼지화 모델은 심각도, 발생도, 검출도의 크리스프(crisp) 값을 이용하였고, 위험도를 도출하였다. 착륙장치에 대한 퍼지 FMEA 결과는 위험도와 우선순위를 분석할 수 있다. 퍼지 FMEA는 회전익 항공기의 품질 보증 활동에서 기초자료로 활용할 수 있음을 확인하였다.