• 대한조선학회논문집
• /
• 제44권2호
• /
• pp.180-188
• /
• 2007

In this paper the longitudinal control problem for the large WIG(wing-in-ground effect) craft is considered in the sense of the control augmentation system(CAS) derived by control surface of elevator. In order to achieve longitudinally stable systems, two modes of CAS are applied to the control systems which are pitch rate hold mode and pitch hold mode for steady flight. Since the employed CASs include the dynamic properties of the actuator time delay and the low pass filter, it provides the possible solution to be applicable to real systems. Nonlinear model simulations are fulfilled to investigate the effectiveness of the applied CASs with wind disturbance.

• 한국항공우주학회지
• /
• 제31권3호
• /
• pp.50-57
• /
• 2003

본 연구에서 헬리콥더의 궤적추종을 위한 제어기의 설계 및 평가를 수행하였다. 제어시스템의 알고리즘은 선형 되먹임 기법과 두 단계 시간분리 구조를 이용하여 구성하였다. 또한 헬리콥터 동특성에 대한 정확한 정보의 결핍으로 인한 모델 역변화 오차를 보상하기 위해 신경회로망을 이용한 실시간 적응제어 구조를 자세제어 시스템에 적용하였다. 제어 시스템의 궤적추종성능은 아파치 헬기의 동측성을 나타내는TMAN 시뮬레이션 프로그램의 단순형을 사용하여 평가하였다. 이를 통하여 실시간 신경회로망 적응제어 구조가 동특성 정보의 부족으로 이한 궤도 추종 제어의 성능 저하 문제에 매우 효과적으로 기여함을 보였다.

• 융합신호처리학회논문지
• /
• 제5권4호
• /
• pp.301-307
• /
• 2004

본 논문에서는 Takagi-Sugeno(T-S) 퍼지모델에 대한 가변구조제어방식을 제안하며 이를 이용한 바퀴구동 도립 진자의 자세제어를 보인다. 비선형 시스템이 T-S 퍼지모델로 모델링 될 수 있다는 가정 하에서 바퀴구동 도립진자에 대하여 몇 개의 대표 동작점을 기준으로 시스템을 선형화하여 퍼지모델을 얻고 이를 통해 가변구조제어이론을 도입하여 제어기를 설계한다. 제안된 제어법칙은 퍼지모델을 구성하는 각각의 선형 부 시스템의 입력이득 행렬을 동일한 행렬로 단일화하고 그 단일화된 제어이득행렬을 토대로 설계되어진다. 이득행렬의 단일화 과정에서 생성되는 불확실성은 가변구조제어 이론의 입력 외란으로 해석되어질 수 있으며 이러한 단일화 외란은 기존 가변구조제어의 강인성에 의해 해결되어질 수 있다. 바퀴구동 도립진자 시스템 예를 통해 제안된 제어알고리즘의 타당성과 유용성을 보인다.

• 한국해양공학회지
• /
• 제34권6호
• /
• pp.475-480
• /
• 2020

Underwater operating platforms face difficulties regarding power supply and communications. To overcome these difficulties, this study proposes a hybrid surface and underwater vehicle (HSUV) and presents the development of the platform, control algorithms, and results of field tests. The HSUV is capable of supplying reliable power to the unmanned underwater vehicle (UUV) and obtaining data in real time by using a tether cable between the UUV and the unmanned surface vehicle (USV). The HSUV uses global positioning system (GPS) and ultra-short base line sensors to determine the relative location of the UUV. Way point (WP) and dynamic positioning (DP) algorithms were developed to enable the HSUV to perform unmanned exploration. After reaching the target point using the WP algorithm, the DP algorithm enables USV to maintain position while withstanding environmental disturbances. To ensure the navigation performance at sea, performance tests of GPS, attitude/heading reference system, and side scan sonar were conducted. Based on these results, manual operation, WP, and DP tests were conducted at sea. WP and DP test results and side scan sonar images during the sea trials are presented.

• 로봇학회논문지
• /
• 제4권2호
• /
• pp.88-96
• /
• 2009

In this paper, we present a linear controller for attitude of aircraft. We use a rotational matrix in one approach and a quaternion in the other approach. We also find some interesting mathematical properties concerning a symmetric rotational matrix and we use these properties to analyze the stability of the proposed control law. We find that the quaternion approach is better than rotational matrix approach because there exists no singular region problem in quaternion approach. On the other hand, singular region problem may happens in rotational matrix approach. The controller structure of the quaternion is also very simple compared with the one proposed by using a rotational matrix approach. We make use Matlab Simulink to simulate and illustrate the theoretical claims. The graphic animation program is developed based on Open-GL for the computer simulation of the proposed control algorithm.

• 제어로봇시스템학회논문지
• /
• 제19권2호
• /
• pp.95-101
• /
• 2013

The paper investigates the geometric effect of landmarks to the navigation error in the landmark based 3D vision navigation and introduces the INS/Vision integrated navigation system considering its effect. The integrated system uses the vision navigation results taking into account the dilution of precision for landmark geometry. Also, the integrated system helps the vision navigation to consider it. An indirect filter with feedback structure is designed, in which the position and the attitude errors are measurements of the filter. Performance of the integrated system is evaluated through the computer simulations. Simulation results show that the proposed algorithm works well and that better performance can be expected when the error characteristics of vision navigation are considered.

• Journal of Astronomy and Space Sciences
• /
• 제23권4호
• /
• pp.397-404
• /
• 2006

Geometric singularity problems are principle difficulties of single-gimbal control moment gyros in spacecraft attitude control. To overcome these singularities, many steering logics have been studied. In this paper, a new null motion steering law is suggested, which is based on the minimization of the directional components of output torque with respect to the required torque. The suggested steering law has been simulated and verified to work well around several critical singular points which have been classified as testing points of avoidance algorithm in previous literatures.

• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
• /
• pp.201-201
• /
• 2000

Recently in the design of fuel tanks(launch vehicle, ship, automobile) which transport a large amount of liquid in the cargo holds, the structural damage due to liquid-sloshing becomes an important problem. The impact pressure from sloshing is most violent when the liquid motion of a partially filled tank is in resonance with the motion of a system. In this paper, the sloshing natural periods in liquid tanks are estimated for partially filled tanks with various geometries. In addition to, controlled for a launch vehicle with liquid sloshing effect by PD controller and sloshing filter The PD gain and sloshing filter parameter arc determined by optimal algorithm.

• International Journal of Aeronautical and Space Sciences
• /
• 제7권1호
• /
• pp.65-72
• /
• 2006

A variable structure controller with an optimized sliding surface is proposed for slew maneuver of a rigid spacecraft. Rodrigues parameters are chosen to represent the spacecraft attitude. The quadratic type of performance index is used to design the sling surface. For optimization of the sliding surface, a Hamilton- Jacobi-Bellman equation is formulated and it is solved through the numerical algorithm using Galerkin approximation. The solution denotes a nonlinear sliding surface, on which the trajectory of the system satisfies the optimality condition approximately. Simulation result demonstrates that the proposed controller is effectively applied to the slew maneuver of a rigid spacecraft.

• 한국측량학회지
• /
• 제37권6호
• /
• pp.465-472
• /
• 2019

사진 촬영 당시의 외부표정요소 추정 방법에는 공선조건식 기반 후방교회법이 널리 사용되지만 초기값을 필요로 하고, 그 값에 민감하다는 단점이 있다. 본 연구에서는 초기값을 필요로 하지 않는 외부표정요소 알고리즘인 쿼터니언 기반 공간후방교회법과 PnP (Perspective-n-Point algorithm)을 소개하고 그 결과를 비교하였다. 두 결과를 비교하기 위하여 일반 스마트폰으로 취득한 영상을 사용하였고, 지상기준점 취득은 본 연구진이 보유하고 있는 하이브리드 MMS (Mobile Mapping System) 점군 자료를 이용하였다. 그 결과, 공선조건식 기반 SPR (Single Photo Resection)을 참값으로 할 때, 쿼터니언 기반 SPR이 PnP 알고리즘에 비해 자세각 추정 정확도가 높았다. 카메라 위치추정의 경우에는 두 알고리즘 모두 지상기준점과 비교했을 때 0.8m 내의 정확도를 보임을 확인하였다.