• 한국군사과학기술학회지
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• 제3권2호
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• pp.71-80
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• 2000

In Underwater Flight Vehicle depth control system, the followings must be required. Firstly, It need robust depth control performance which can get over parameter variation, modeling error and disturbance. Secondly, It need no oveshoot phenomenon to avoid colliding with ground surface and obstables. Thirdly, It need continuous control input to reduce the acoustic noise and propulsion energy consumption. Finally, It need effective interpolation method which can reduce the dependency of control parameters on speed. To solve these problems, we propose the Fuzzy-PID depth controller with the control parameter interpolators. Simulation results show the proposed control scheme has robust and accurate performance with continuous control input.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.2345-2348
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• 2003

This paper deals with a problem of automatic landing guidance and control system design. The auto-landing control system for the longitudinal motion is designed in the classical PID controller. The controller gains are properly adapted to variation of the performance using fuzzy logic as a gain scheduler for the PID gains. This control logic is applied to the problem of the automatic landing control system design. From the numerical simulation using the 6DOF nonlinear model of the associated airplane, it is shown that the auto-landing maneuver is successfully achieved from the start of the flight conditions: 1500 ft altitude, 250 ft/sec airspeed and zero flight path angle.

• 한국항공운항학회지
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• 제22권1호
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• pp.22-31
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• 2014

Military UAV(Unmanned Aerial Vehicle) operated as a RC(Remotely Control) model level within the limit of the military special use airspace until now. However, the high and medium altitude of URA(Unmanned Reconnaissance Aircraft) which the ROKAF have been trying to import recently is at the UAV level and needs the criteria for the classified airspace flights. The required flight criteria includes operator location, mission operation limit, equipment, etc., which are the principle and standard applied based on the airspace use for UAV. Also, the general flight rules, visual flight rules, instrument flight rules are required in order to have to be applied to the actual flight. Besides, an appliance regulation needs to be arranged regarding two-way communication, ATC and communication issue, airspace and area in-flight between UAS( Unmanned Aircraft System) users. An operation of the UAV in the air significantly requires the guarantee of the aircraft's capacity, and also the standardized flight criteria. A safe and smooth use is ensured only if this criteria is applied and understood by the entire airspace users. For the purpose, a standardized military UAV flight operations criteria that is to be applied for each airspace by UAV is to be prepared through analysis of the present state, a legend UAV system, and a special character analysis.

• 한국항행학회논문지
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• 제5권1호
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• pp.19-25
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• 2001

본 논문에서는 지면효과익기의 종운동 비행특성을 해석하고 비행제어 방식에 관한 비교연구를 한다. 먼저 비행 동특성을 해석하기 위해 지면효과익기가 지닌 것으로 알려진 비선형 특성을 제한 사이클을 통하여 살펴보고 또 선형화되었을 때의 특성과 연관하여 살펴본다. 또한 제어방식을 비교연구하기 위해 순항시에 고도오차가 있는 경우와 상승, 순항, 하강모드에 대한 명령추종관점에서 제어시스템의 성능 및 제어입력 실현 가능성을 비교한다. 제어입력으로는 승강타, 추력제어, 플랩 등의 조합을 고려하고 제어기법으로는 선형이차레귤레이터에 기반한 출력명령추종제어를 적용한다.

• 전기전자학회논문지
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• 제19권4호
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• pp.557-565
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• 2015

본 논문에서는 무인 쿼드콥터의 자율 비행 제어를 위해 기반이 되는 위치 인식을 위하여 EKF-SLAM 기반 위치추정 알고리즘을 제안하고 이를 쿼드콥터의 궤적 추종 제어에 적용하여 시뮬레이션을 통해 위치 추정의 성능과 이를 통한 궤적 추종의 결과를 검증하였다. 쿼드콥터의 EKF-SLAM 기반 위치 추정을 위해 쿼드콥터 비행 동역학 모델을 수립하고 이를 기반으로 EKF-SLAM의 운동 모델 및 관측 모델을 유도하였으며 궤적 추종을 위한 쿼드콥터의 수평제어와 자세제어를 위해 PD 제어기를 적용하였다. 본 논문에서는 다양한 궤적 및 랜드마크 환경에 대해 EKF-SLAM 기반 위치 추정 성능을 시뮬레이션함으로써 EKF-SLAM을 이용한 위치 추정 기반 궤적 추종 제어의 성능을 확인하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2004년도 ICCAS
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• pp.1386-1391
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• 2004

It is known that an aircraft with delta-wings which are attached to the body at a large angle like a kite or a hang glider has a measure of maneuverability and stability. Aircrafts of this kind can fly stably. Even if engine trouble occurs, it will not fall and might be able to land. In this paper, one of the conventional control methods, PID control, is applied to the aircraft with LQ local control block. This is based on an idea that the aircraft flies so stably that the automatic control system might be realized by a simple controller. The proposed PID controller consists of several sub-controllers which are constructed to each system neglecting the interference. In addition, the LQ control is involved as a local loop of the aileron and rudder control in order to increase stability of the attitude when circling. The effectiveness of the proposed method is shown through 3D computer simulations and experiments of the flight path control.

• 한국항공우주학회지
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• 제38권12호
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• pp.1217-1222
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• 2010

본 논문은 근접감시 무인항공기(KUS-9)의 비행제어 소프트웨어(S/W) 개발 과정과 모델기반 개발 기술 적용 결과를 다룬다. 대표적인 상용 모델기반 설계도구인 MATLAB $Simulink^{(R)}$를 활용하여 통합개발 환경을 구축하고 비행제어법칙, 운용로직, 비행 시뮬레이션 모델, HILS(Hardware-in-the-Loop Simulation) 시스템 모델을 설계하였다. 설계 과정에서 요구사항 충족을 위한 시뮬레이션 및 동료검토를 수행하고 DO-178B 검증 도구를 이용하여 모델을 검증한 후 S/W시험 도구를 통해 C코드의 무결성을 검증하였다. 탑재 소프트웨어는 두 기종의 하드웨어 및 실시간운용체제(${\mu}C$/OS-II, VxWorks)에 탑재하여 HILS시험과 비행시험을 수행하였다. 모델기반 개발 기법을 적용함으로써 S/W 재사용성과 확장성을 확보하고 자동코드생성 기술을 이용하여 고신뢰 비행제어 S/W를 단기간에 성공적으로 개발하였다.

• 대한인간공학회지
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• 제16권1호
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• pp.97-105
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• 1997

An aircraft simulator for ergonomics testing and pilot training was developed from the joint work Agency for Defense Development(ADD) and Daewoo Heavy Industry, LTD, in Korea at first time. It is basically to satisfy the requirements established by FAA-AC-120-40C ( 1995-JAN-26). The aircraft simulator will be used mainly for ergonomics testing and pilot training for basic trainer on ADD and Korea Air Force in near futrue. This simulator reproduces faithfully the cockpit and flight characteristics of the KTX-1 aircraft. It is one of the latest full flight simulators that have the CGI(computer graphic image) visual system and six degree of freedom motions system. Development efforts focused on user-oriented design approach for ergonomics testing and flight training of pilots. Main characteristics of each subsystem are described such as cockpit, instruments, control loading system, motion system, visual system, aural system, instructor operation station and aircraft simulation softwear.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2004년도 ICCAS
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• pp.995-1000
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• 2004

A digital adaptive flight control system is presented for a Japanese automatic landing flight experiment vehicle (ALFLEX). In previous adaptive control systems based on a linear-parameter-varying (LPV) form, the output behavior was excellent, while the behavior of the adjusted parameters was unsatisfactory. In the present study, to obtain a more appropriate parameter adjustment law, the relationship between the coefficient matrices in a continuous-time state equation and the coefficients of a pulse transfer function in a discrete system for conventional aircraft is investigated. As a result, it is revealed that the coefficients of the numerator can be treated as a linear function of dynamic pressure (linear-parameter-varying: LPV), while the coefficients of the denominator can be treated as constant (linear-time-invariant: LTI). From the above analysis, an improved parameter adjustment law is derived by reducing the number of the adjustment parameters. Simulation results also revealed both good output tracking and good parameter adjustment compared with the previous results.

• 한국군사과학기술학회지
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• 제16권6호
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• pp.733-738
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• 2013

A guidance kit transforming a general purpose bomb into an air-to-surface gliding bomb was developed. This guidance kit consists of a flight kit and a tail kit. Flight kit contains deployable wing, GPS/INS integrated navigation system, guidance and control system. Also this guidance kit was designed to use neither electrical nor mechanical interface with aircraft, and to increase dramatically the survivabilities of pilot and aircraft with the high accuracy and the mid-range non-powered gliding capability.