• International Journal of Control, Automation, and Systems
• /
• 제5권2호
• /
• pp.161-169
• /
• 2007

The PLL equivalent augmented system incorporated with state feedback is proposed in this paper. The optimal value of filter time constant of loop filter in the phase-locked loop control system and the optimal state feedback gain designed by using linear quadratic regulator approach are derived. This approach allows the PLL control system to employ the large value of the phase-frequency gain $K_d$ and voltage control oscillator gain $K_o$. In designing, the structure of phase-locked loop control system will be rearranged to be a phase-locked loop equivalent augmented system by including the structure of loop filter into the process and by considering the voltage control oscillator as an additional integrator. The designed controller consisting of state feedback gain matrix K and integral gain $k_1$ is an optimal controller. The integral gain $k_1$ related to weighting matrices q and R will be an optimal value for assigning the filter time constant of loop filter. The experimental results in controlling the second-order lag pressure process using two types of loop filters show that the system response is fast without steady-state error, the output disturbance effect rejection is fast and the tracking to step changes is good.

• 한국항행학회논문지
• /
• 제21권5호
• /
• pp.450-458
• /
• 2017

본 연구에서는 곤충모방 날갯짓 비행체의 모델링과 제자리비행을 위한 자세제어 및 고도제어기를 설계하여 동역학 모델을 이용한 시뮬레이션을 수행하고 그 결과를 분석하였다. 곤충모방 날갯짓 비행체의 간략화한 날갯짓 운동, 날갯짓의 병진운동 및 회전운동에 대한 공력, 동체 동역학에 대해 수치모델링을 수행하였다. 제자리비행 자세제어를 위해 날갯짓 비행체가 가지는 시변 비선형 시스템을 선형화하여 설계한 LQR(Linear Quadratic Regulator) 제어기법을 통하여 자세안정화를 적용하였으며 PID 제어기법을 통해 고도제어를 수행하였다. 수치 시뮬레이션을 통해 설계된 모델과 제어기의 성능을 확인하였으며 제자리비행을 위한 자세안정화 및 고도 제어가 안정적으로 수행되는 것을 확인하였다. 또한 날갯짓에 의해 발생하는 주기적인 피칭 모멘트를 주기적인 제어입력을 통해 임계 안정하도록 자세 안정화를 수행하는 것을 확인 하였다.

• 한국항공우주학회지
• /
• 제42권4호
• /
• pp.305-316
• /
• 2014

항공전자 장비들의 급속한 발전으로 인해 무인항공기의 크기가 소형화 되고 있으나, 무인항공기에 대해 주어지는 임무는 더욱 정확하고 복잡해지고 있다. 정지비행이 가능하고, 간단한 기계적 메커니즘을 가진 쿼드로터는 이 같은 환경에서 활동도가 점차 증가하고 있다. 그러나 쿼드로터는 구조 특성에 따라 출력의 개수보다 입력의 개수가 작은 under actuated 시스템이므로, 쿼드로터 제어에 큰 제약이 따른다. 본 논문에서는 이와 같은 쿼드로터의 단점을 해결하기 위해서 4개의 원동기 외에 2개의 추가적인 원동기를 더 부착한 모델을 제안하여, 입력의 개수와 출력의 개수가 같은 fully actuated 시스템을 구현하도록 한다. 제안한 쿼드로터 모델의 제어기를 설계하기 위해 궤환선형화 기법을 적용하였다. 수치 시뮬레이션을 수행하여 제안한 모델과 설계된 제어기의 성능을 검증하였다.

• Ocean Systems Engineering
• /
• 제6권3호
• /
• pp.265-287
• /
• 2016

The change of the global performance of a turret-moored FPSO (Floating Production Storage Offloading) with DP (Dynamic Positioning) control is simulated, analyzed, and compared for two different internal turret location cases; bow and midship. Both collinear and non-collinear 100-yr GOM (Gulf of Mexico) storm environments and three cases (mooring-only, with DP position control, with DP position+heading control) are considered. The horizontal trajectory, 6DOF (degree of freedom) motions, fairlead mooring and riser tension, and fuel consumptions are compared. The PID (Proportional-Integral-Derivative) controller based on LQR (linear quadratic regulator) theory and the thrust-allocation algorithm which is based on the penalty optimization theory are implemented in the fully-coupled time-domain hull-mooring-riser-DP simulation program. Both in collinear and non-collinear 100-yr WWC (wind-wave-current) environments, the advantage of mid-ship turret is demonstrated by the significant reduction in heave at the turret location due to the minimal coupling with pitch mode, which is beneficial to mooring and riser design. However, in the non-collinear WWC environment, the mid-turret case exhibits unfavorable weathervaning characteristics, which can be reduced by employing DP position and heading controls as demonstrated in the present case studies. The present study also reveals the plausible cause of the failure of mid-turret Gryphon Alpha FPSO in milder environment than its survival condition.

• Advances in aircraft and spacecraft science
• /
• 제7권6호
• /
• pp.553-570
• /
• 2020

To address the problems caused by the strong coupling of an airbreathing hypersonic vehicle's airframe and propulsion to the integrated control system design, an integrated airframe-propulsion model is established, and the coupling characteristics between the aircraft and engine are analyzed. First, the airframe-propulsion integration model is established based on the typical nonlinear longitudinal dynamical model of an air-breathing hypersonic vehicle and the one-dimensional dual-mode scramjet model. Thrust, moment, angle of attack, altitude, and velocity are used as transfer variables between the aircraft model and the engine model. The one-dimensional scramjet model can accurately reflect the working state of the engine and provide data to support the coupling analysis. Second, owing to the static instability of the aircraft model, the linear quadratic regulator (LQR) controller of the aircraft is designed to ensure attitude stability and height tracking. Finally, the coupling relationship between the aircraft and the engine is revealed through simulation examples. The interaction between vehicle attitude and engine working condition is analyzed, and the influence of vehicle attitude on engine safety is considered. When the engine is in a critical working state, the attitude change of the aircraft will not affect the engine safety without considering coupling, whereas when coupling is considered, the attitude change of the aircraft may cause the engine unstart, which demonstrates the significance of considering coupling characteristics.