• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
• /
• pp.1500-1503
• /
• 1996

This paper combines the disturbance accommodating control(DAC) and nonlinear model inversion control for a skid-to-turn(STT) missile. The missile autopilot may be designed to be robust with respect to a variety of uncertainties. We proposes the two step control design method. Nonlinear model inversion control is used as the main design method. Due to the model uncertainties and external disturbances, the exact nonlinear model inversion can not be achieved. DAC is designed to detect, to identify, and to compensate these uncertainties. DAC's disturbance observer is linear. Thus it is easy to implement. It does not cause the convergence problem due to coexistence between the modeling uncertainties and external disturbances. 6 DOF simulation results show that the proposed method may improve the missile tracking performance.

• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
• /
• pp.1308-1311
• /
• 1996

We propose a new linearized model which can be used very efficiently for the design and analysis of the autopilot of aerodynamically controlled skid-to-turn missiles. Proposed model is based on the linearized equations of the missile dynamics derived in the aerodynamic frame where xz plane contains the missile longitudinal axis and velocity vector. However, to take the effect due to the small perturbation of the missile body into consideration, we introduce a new frame which is identical to the aerodynamic frame in the trim state but after small perturbation it moves fixed with the missile body, and finally, the proposed model is set up in this frame. It is shown by nonlinear simulations and stability analysis of a numerical example that the new model describes the missile motion better than the conventional one linearized in the body frame with a certain amount of simplification.

• 한국군사과학기술학회지
• /
• 제1권1호
• /
• pp.211-218
• /
• 1998

As a part of trajectory modulation to increase system survivability and terminal effectiveness, impact angle control is required in the terminal phase of tactical missile systems. The missile systems are not allowed to have high altitude to reduce probability of detection by sensors of missile defense systems. In this paper, an analytic form of a time-optimal control law is suggested in the case of constrained missile maneuverability and impact angle under the assumption of a zero-lag autopilot. The control law is obtained by establishing optimal missile-target engagement geometry in the vertical plane. Extension of the law for missiles with autopilot response lags requiring a numerical solution is studied by introducing an iterative algorithm for optimal switching time determination of which the initial switching instants are obtained from the analytic solution. Also suggested is a closed-form impact angle control law derived by an energy-optimal approach. The performances of the proposed guidance laws are evaluated by a series of computer runs.

• 한국항해학회지
• /
• 제25권4호
• /
• pp.407-415
• /
• 2001

In the present study, irregular disturbances to ship dynamics is proposed, where irregular disturbances implying irregular wave and the fluctuating component of wind for the evaluation of automatic steering system of ship in following seas. Prediction method based on the principle of linear superposition. Irregular wave disturbances in following seas is calculated by frequency variation method. The mathematical model of each element of an automatic steering system is derived, which takes account of a few non-linear mechanisms. PD(Proportional-Derivative) controller and low-pass filter with a weather adjustment are adopted to modelling the characteristics of an autopilot. Performance index is introduced from the viewpoint of energy saving, which derived from the concept of energy loss on ship propulsion. Finally, the present methods are applied to two typical types of ship ; an ore carrier and a fishing boat. The various effects of control constants of autopilot on propulsive energy loss are investigated

• 한국항해항만학회:학술대회논문집
• /
• 한국항해항만학회 2013년도 추계학술대회
• /
• pp.21-23
• /
• 2013

Autopilot에서의 조타정보 추출, AIS를 통한 조타정보의 송수신, ECDIS에 타각이 표시되도록 프로그램을 적용하여 선회조기감지시스템을 구현하였으며, 이를 실선실험을 통하여 확인하였다. Autopilot을 작동하여 송신용 AIS를 통하여 전송된 조타신호가 수신용 AIS에 수신되어 ECDIS에 3초 이내에 표시됨을 확인하였다. 선회조기감지시스템은 선박 상호간의 충돌사고 예방에 큰 도움이 될 것으로 예상하고 있으며, VTS 관제에 있어서는 선박들의 조타 상황을 파악하여 선박의 움직임을 조기에 파악하여 관제가 가능하다. 또한, 해양안전심판원에서는 AIS를 통하여 조타정보가 저장된 해양안전종합정보시스템(GICOMS)를 통한 사고분석이 가능할 것으로 판단된다. 추후 선회조기감지시스템을 적용한 간이형 시뮬레이터를 개발하여 도선사 및 항해사를 대상으로 적용 평가하여 해당 시스템의 활용가능성, 신뢰성 등을 검증하고자 한다.

• International Journal of Aeronautical and Space Sciences
• /
• 제8권1호
• /
• pp.21-31
• /
• 2007

Relaxed Static Stability (RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. The T-50 advanced supersonic trainer employs the RSS concept in order to improve the aerodynamic performance. And the flight control system stabilizes the unstable aircraft and provides adequate handling qualities. The T-50 longitudinal control laws employ a proportional-plus-integral type controller based on a dynamic inversion method. The longitudinal dynamic modes consist of short period with high frequency and phugoid mode with low frequency. The design goal of longitudinal control law is optimization of short period damping ratio and frequency using Lower Order Equivalent System (LOES) complying the requirement of MIL-F-8785C. This paper addresses phugoid mode characteristics such as damping ratio and natural frequency that is affected by the nonlinear control laws such as angle of attack limiter, auto pitch attitude command system and autopilot of pitch attitude hold.

• 대한조선학회논문집
• /
• 제34권2호
• /
• pp.56-63
• /
• 1997

본 논문에서는 신경망을 이용한 자동조타장치의 개발에 관한 연구결과를 소개한다. 본 연구에서는 먼저 신경망이론에 사용되는 대표적인 방법인 Back-Propagation 알고리즘의 원리를 설명하고 이를 이용하여 선박의 조종모델을 신경망으로 재구성하는 방법을 제시하였다. 신경망이론을 사용하여 선박운동모델을 System Identification 하는 경우의 문제점을 간단한 조종모델을 이용하여 수치적으로 검증하고 보다 복잡한 모델로 적용하는 경우에 대한 토의를 하였다. 본 논문에서 개발된 신경망이론들은 비선형성을 내포하고 있는 선박운동을 재구성하는데 효과적으로 사용될 수 있을 것으로 기대된다.

• 대한전기학회:학술대회논문집
• /
• 대한전기학회 2006년도 심포지엄 논문집 정보 및 제어부문
• /
• pp.219-221
• /
• 2006

The recently developed autopilot controller can make the input-output (I/O) dynamic characteristics of the nonlinear missile dynamics linear and independent of flight conditions. However, significant fin actuator dynamics can degenerate the I/O dynamic performance of the overall system. In this paper, we propose a singular perturbation-like method to compensate the effect of significant fin actuator dynamics in nonlinear missile control. The proposed compensation method does not require the time derivatives of fin angles but can maintain the linear I/O dynamic characteristics provided by the recently developed autopilot controller.

• 항공산업연구
• /
• 통권65호
• /
• pp.89-106
• /
• 2003

항공기의 자동 착륙 알고리즘을 위한 고 정밀 유도방식에 IBLS(Integrity Beacons Landing System)나 MLS(Microwave Landing System)와 같은 유도 제어 방식을 사용하여 유인 항공기나 무인 항공기의 유도 착륙에 사용하고 있다. 당 연구에서는 무인항공기의 자동 착륙을 위한 실제적인 요구사항들이 분석되었고, 자동 착륙 유도장치로 IBLS와 MLS가 선택되어 각각의 기능과 특성들이 수학적으로 모델링 되었다. 또한 고전제어와 최적제어의 2가지 방식으로 무인항공기의 자동 착륙을 통제하기 위한 autopilot이 설계되어 그 유효성과 특징들이 분석되었다. IBLS, MLS, autopilot, 그리고 이러한 자동 착륙 유도제어 시스템이 적용되는 대상체인 무인항공기와 대기환경 및 외란에 대한 수학적 모델들은 Simulink와 ANSI C를 사용하여 단위 S/W 모듈들로 작성되었고, 여기에 GUI모듈이 추가되어 하나의 통합 시뮬레이션 S/W가 완성되었다. 모의시험평가는 총 2단계로 구성되었는데, 대기 외란이 주어졌을 때 IBLS와 MLS의 유효성을 1차적으로 검증하였고, 2단계 모의수치실험에서는 MLS 유도센서 방식에 따른 고전제어기 및 최적제어기의 항공기 종 방향 운동에 대한 강인성 비교를 시도하였다.

• 수산해양기술연구
• /
• 제34권2호
• /
• pp.165-173
• /
• 1998

When an automatic course-keeping is concerned, as is quite popular in modem navigation, the closed-loop steering system consists of autopilot device, power unit (or telemotor unit), steering gear, magnetic or gyro compass and ship dynamics. In order to estimate automatic steering system of ships in open seas. we need to know the characteristics of each component of the system, and also to know the characteristics of disturbance to ship dynamics. In this paper, I provide calculation method of imposing irregular disturbance to autopilot navigation system of the ship in open seas, and also show calculation examples about fishing boat. The disturbance consists of the irregular wave and the fluctuating component of wind. Finally, The disturbances are calculated in terms of equivalent yaw angular velocity. Each spectrum and time history of disturbance are reasonably evaluated.