• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.525-530
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• 2003

This paper is concerned with a control allocation strategy using the dynamic inversion which generates the nominal control input trajectories, and autopilot design using the time-varying control technique which is time-varying version of pole placement of linear time-invariant system for an agile missile with aerodynamic fin and thrust vectoring control. Dynamic inversion can decide the amount of the deflection of each control effector, aerodynamic fin and thrust vectoring control, to extract the maximum performance by combining the action of them. Time-varying control technique for autopilot design enhance the robustness of the tracking performance for a reference command. Nonlinear simulations demonstrates the dynamic inversion provides the effective nominal control input trajectories to achieve the angle of attack command, and time-varying control technique exhibits good robustness for a wide range of angle of attack.

• 한국군사과학기술학회지
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• 제6권3호
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• pp.122-130
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• 2003

This paper is concerned with a control allocation strategy using the dynamic inversion and the pseudo inverse control which generates the nominal control input trajectories, and autopilot design using time-varying control technique which is time-varying version of pole placement of linear time-invariant system for an agile missile with aerodynamic fin and thrust vectoring control. Control allocation of this paper is capable of extracting the maximum performance from each control effector, aerodynamic fin and thrust vectoring control, by combining the action of them. Time-varying control technique for autopilot design enhance the robustness of the tracking performance for a reference command. The main results are validated through the nonlinear simulation.

• 제어로봇시스템학회논문지
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• 제10권10호
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• pp.947-955
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• 2004

This paper is concerned with a mixed control with aerodynamic fin and side thrust control applied to an agile missile using a dynamic inversion and a time-varying control technique. The nonlinear dynamic inversion method with the weighting function allocates the desired control inputs(aerodynamic fin and side thrust control) to achieve a reference command, and the time-varying control technique plays the role to guarantee the robustness for the uncertainties. The proposed schemes are validated by nonlinear simulations with aerodynamic data.

• 제어로봇시스템학회논문지
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• 제18권1호
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• pp.1-6
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• 2012

In this paper, an adaptive fuzzy control system is proposed for the speed control of the ASV (Autonomous Surface Vehicle) with nonaffine nonlinear system dynamics. We consider the turning speed of the screw propeller to be the control input instead of thrust so that we do not have to know the exact function between turning speed and thrust. But in this case, the ASV becomes a nonaffine nonlinear system because thrust is a nonlinear function of the turning speed. To solve this problem, we propose a Takagi-Sugeno fuzzy-model-based control system and simulation studies are performed. Simulation results show the effectiveness of the proposed control scheme.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 춘계학술대회
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• pp.1948-1954
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• 2003

The thrust vector control using a fluidic counterflow concept is achieved by applying a vacuum to a slot adjacent to a primary jet which is shrouded by a suction collar. The vacuum produces a secondary reverse flowing stream near the primary jet. The shear layers between the two counterflowing streams mix and entrain mass from the surrounding fluid. The presence of the collar inhibits mass entrainment and the flow near the collar accelerates causing a drop in pressure on the collar. For the vacuum asymmetrically applied to one side of the nozzle, the jet will vector toward the low-pressure region. The present study is performed to investigate the effectiveness of thrust vector control using the fluidic counterflow concept. A computational work is carried out using the two-dimensional, compressible Navier-Stokes equations, with several kinds of turbulence models. The computational results are compared with the previous experimental ones. It is found that the present fluidic counterflow concept is a viable method to vector the thrust of a propulsion system.

• 한국추진공학회지
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• 제20권1호
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• pp.28-36
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• 2016

본 논문에서는 핀틀을 이용한 가변추력 고체 추진기관의 추력을 제어하기 위하여 이론적으로 모델을 구하고 압력 제어기를 설계하였다. 고전적인 모델 선형화 및 비례-적분제어를 설계했을 때 실제 모델의 비선형성에 의해 발생하는 제어기 성능 저하를 줄이기 위해 이득 계획 기법을 적용하였다. 시스템의 특징을 고려하여 연소관 내부 체적 변화에 따라 이득을 조절하는 방법과, 연소관 내부 압력에 의해 이득을 조절하는 방법으로 두종류의 이득 계획 제어기를 설계하였다. 각 제어기를 가변 추력기 모델에 적용하여 폐루프 시스템 응답특성을 비교하였으며 가변 추력 추진기관 특성에 따라서 어떤 제어기를 선택하는 것이 유리한지 제안하였다.

• 한국추진공학회지
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• 제9권4호
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• pp.96-103
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• 2005

위성발사체는 인공위성을 정해진 궤도에 정확하게 투입하는 것이 주 목적이며, 이를 위해서는 발사체의 최종 속도와 질량을 미리 설정된 값과 일치시켜 주어야 한다. 위성발사체에 주로 사용되는 액체로켓엔진의 경우 이를 위해 추력제어시스템(TCS) 및 추진제소진시스템(TDS)을 이용하며, 이는 액체로켓엔진에 장착된 제어밸브를 통해 추진제 유량을 제어함으로써 추력 및 혼합비를 제어하는 시스템이다. 본 연구에서는 액체로켓엔진을 설계점에서 안정적으로 운용하기 위해, 추력 및 혼합비 제어밸브의 제어특성을 PID 제어로직을 통해 분석하였다. 우선 상용프로그램인 AMESim을 통해 제어벨브의 제어특성을 이론적으로 분석하고, 이를 바탕으로 한국항공우주연구원(KARI)에 설치된 제어밸브시험설비를 통해 얻은 제어밸브의 제어특성과 비교 분석하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2005년도 제25회 추계학술대회논문집
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• pp.358-362
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• 2005

축추력의 효과적인 제어는 터보펌프 개발의 핵심 기술 중 하나이다. 현재 개발 중인 액체로켓엔진용 연료펌프의 안정성을 입증하기 위해 축추력 측정 장치를 개발하고 수류 시험을 실시하였다. 시험 결과, 연료펌프는 설계 유량에서 펌프 베어링의 축방향 하중 요구 조건을 만족하였다. 또한 이차 유로의 오리피스를 통해 연료펌프에 대한 축추력 제어가 가능한 것을 확인하였다.

• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 2003년도 춘계학술대회 논문집 기술교육전문연구회
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• pp.3-7
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• 2003

Usually, the thrust is calculated by magnetic equivalent circuit modelling method for thrust capacity and accuracy progress of position control about a Linear Pulse Motor of which position precision is good and open-loop control is possible within Linear Motors. Analytical thrust deviation exists to calculating magnetic flux density by using Permeance Modelling Method, Finite Element Method, and Velocity Electric Motive Force Method. For calculating accuracy thrust by using these every method, the thrust is calculated and compared by Lorentz Force Method, Magnetic Coenergy Method, and Maxwell correspondence force Method. And that becomes important factor at the comparison of each capacity and parameter of Motor. So this study wants to compare and analyze measurement data and calculating data of the static force of Linear Pulse Motor. and then we can get more accuracy method, calculating the static thrust of Linear Pulse Motor(LPM).

• 대한전기학회논문지:전기기기및에너지변환시스템부문B
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• 제53권1호
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• pp.16-23
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• 2004

Permanent magnet-excited transverse flux linear motor(TFLM) is known to have more excellent ratio of force to weight than any other linear motors. But, thrust generated by phase current is non-linear with regard to current and relative position like switched reluctance motor. This makes current and speed controller design difficult. This paper presents a method on minimization of thrust ripple of permanent magnet-excited transverse flux linear motor. Using genetic algorithm(GA), optimal current waveform can be found under the constraint conditions such as current limit, minimum of ohmic loss and limited rate of change of current etc. The effectiveness is verified through computer simulation and experimental test results.