• International Journal of Aeronautical and Space Sciences
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• 제11권3호
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• pp.184-192
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• 2010

In this paper, an initial fine alignment algorithm, which is developed for the strap-down inertial navigation systems of satellite launch vehicles, is considered. For fast and accurate alignment, a simple closed-loop estimation algorithm using a proportional-integral controller is introduced. Through computer simulation for the sway condition in the launch pad, it is shown that a simple filter structure can guarantee fast computational speed that is adequate for real-time implementation as well as the required alignment accuracy and robustness. In addition, its implementation results are presented for the Naro-1 flight test.

• International Journal of Aeronautical and Space Sciences
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• 제11권2호
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• pp.131-135
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• 2010

We report on the design of a three-axis missile autopilot using multi-objective control synthesis via linear matrix inequality techniques. This autopilot design guarantees $H_2/H_{\infty}$ performance criteria for a set of finite linear models. These models are linearized at different aerodynamic roll angle conditions over the flight envelope to capture uncertainties that occur in the high-angle-of-attack regime. Simulation results are presented for different aerodynamic roll angle variations and show that the performance of the controller is very satisfactory.

• International Journal of Aeronautical and Space Sciences
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• 제15권2호
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• pp.153-162
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• 2014

A novel robust $H_{\infty}$ switching tracking control design method with disturbance observer is proposed for the near space interceptor (NSI) with aerodynamic fins and reaction jets. Initially, the flight envelop of the NSI is divided into small subregions, and a slow-fast loop polytopic linear parameter varying (LPV) model is proposed, to approximate the nonlinear dynamic of the NSI, based on the Jacobian linearization and Tensor-Product (T-P) model transformation approach. A disturbance observer is then constructed, to estimate the modeled disturbance. Subsequently, based on the descriptor system method, a robust switching controller is developed, to ensure that the closed-loop descriptor system is stable with a desired $H_{\infty}$ disturbance attenuation level. Furthermore, the outcome of the proposed switching tracking control problem is formulated as a set of linear matrix inequalities (LMIs). Finally, simulation results demonstrate the effectiveness of the proposed design method.

• 대한인간공학회지
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• 제15권2호
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• pp.99-111
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• 1996

In today's highly automated aircraft, the role of the pilot has changed from an airplane controller to a system manager. As a system manager in a cockpit, today's pilot is in charge of a management-level activity called cockpit task management( CTM). According to earlier studies, pilot errors in performing CTM activities were significant factors in a large number of aircraft accidents and incidents. The primary objective of this research was to reduce CTM-related pilot errors. A prototype pilot- vehicle interface called the cockpit task management system (CTMS) was developed and its effectiveness in improving CTM performance was evaluated. After the CTMS was implemented, it was integrated into a PC-based flight simulator to perform an experiment to evaluate its effectiveness. Eight volunteer subjects were used to collect performance data. The results of the experiment indicated that a statistically significant improvement was observed when the subjects flew with the assistance of the CTMS.

• International Journal of Aeronautical and Space Sciences
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• 제8권1호
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• pp.79-86
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• 2007

In this paper, an adaptive control algorithm using system identification is proposed for an aircraft fault tolerant control system. A discrete state-space system is reformulated to be the ARX model which has the advantage in handing variable structure systems. Discrete model reference adaptive control is used to make the output of fault system follow the output of reference model. To validate the performance of the proposed control scheme, numerical simulations are performed for the high performance aircraft with control surface damage.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1986년도 한국자동제어학술회의논문집; 한국과학기술대학, 충남; 17-18 Oct. 1986
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• pp.266-268
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• 1986

최근에 측정할 수 있는 상태만을 피드백하여 시스템의 극점을 의도한 영역에 배치하는 상수들의 영역을 찾아내는 방법이 제시되었고, 비행체의 제어에 적용한 결과가 발표되었다. 이 방법은 근궤적법과 극점배치법의 단점을 상호 보완하며 견실성(Robustness)에 대한 판단을 용이하게 할 뿐 아니라 컴퓨터를 사용하여 쉽게 설계에 이용될 수 있는 장점이 있다. 그러나 S 평면상에 배치되는 각각의 극점쌍의 위치를 제어 상수들의 조합으로 부터 유추해내기 어렵고, 중요하지 않은 극점이 의도하는 영역밖에 있는 경우에는 적용하는데 난점이 있었다. 본 논문에서는 이 방법을 확장하여 S 평면상에 배치되는 복소극점쌍의 위치를 제어상수 평면에서 간단하게 유추할 수 있고, 이득여유 위상여유를 동시에 고려할 수 있는 제어상수 영역 그래프법을 제시하고 노드롭(Northrop) 항공사의 시험용 비행기를 대상으로 하여 종방향운동 제어기의 설계 예를 보인다.

• 제어로봇시스템학회논문지
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• 제14권12호
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• pp.1260-1265
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• 2008

This study deals with modeling and flight control of quadrotor type (QRT) unmanned aerial vehicles (UAVs). Rigorous dynamic model of a QRT UAV is obtained both in reference and body frame coordinate systems. A disturbance observer (DOB) based controller using the derived dynamic models is also proposed for robust hovering control. The control input induced by DOB is helpful to use simple equations of motion satisfying accurate derived dynamics. The experimental results show the performance of the proposed control algorithm.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.92-92
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• 2000

Helicopter offer the signigicant advantage over traditional air vehicles, in that the provide extended maneuverability, such as vertical climb, hovering, longitudinal and lateral flight, hovering turns and bank turns. But helicopter have the strong cross couplings and nonlinearities for each lateral, longitudinal and rotational motion mutually. However, it is possible to ignore this couplings for the hovering condition, so using this properties we can control the attitude of helicopter. That is, by implementing the dynamic of each rotational axis(roll, pitch, yaw) of independent mutually, 3-DOF(degree of Freedom) attitude control for the helicopter is possible. In this paper, we identify decoupled input-coutput relations of each three rotational axis about the helicopter mounted on the 3-DOF gimbal by experiment, and on these basis implement 3-DOF attitude controller using the PID control method.

• 한국항공운항학회지
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• 제21권4호
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• pp.34-40
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• 2013

Attitude command response type required for enhanced handling qualities of helicopter can be implemented by mechanical automatic flight control system with SAS actuators which have limited authorities. However, the early saturation of SAS actuator hinders the helicopter from following the attitude command for large stick command. Auto-trim controller can delay SAS actuator's saturation by utilizing trim actuators and allows the attitude command response type for larger stick command. This paper describes the control law for limited authority system of helicopter with auto-trim. Limited authority system is applied to BO-105 linear dynamic model and simulation is performed along with handling quality analysis.

• 한국항공우주학회지
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• 제33권7호
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• pp.106-113
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• 2005

ASDR은 군용 항공기의 주 장비인 ASC와 이에 탑재되는 임무 운용 소프트웨어인 OFP 개발중에는 개발도구로 사용되며 또한 ASC/OFP 개발 후에는 유지/보수용 도구로 사용될 수 있다. 본 논문에서는 저속통제기용으로 개발된 ASDR의 전체 구조, 기능 및 특히 관성 및 공기 데이터 센서 시뮬레이션 부분에 대하여 기술한다.