Earticle

초록

영어

In this paper, we propose to prevent compressor surge and control rotating speed for UAV turbojet engine. Turbojet engine controller is designed by applying PID control algorithm and it was applied to the linearized turbojet engine model. To prevent any surge or a flame out event during the engine acceleration or deceleration, the PID controller effectively controls the fuel flow input of the control system. PID results are used as the fuel flow control inputs to prevent compressor surge and flame-out for turbojet engine and the controller is designed to converge to the desired speed quickly and safely. Using LabVIEW to perform computer simulations verified the performance of the proposed controller. The simulation result using the designed PID controller verified that quickly converge to the desired speed and properly control fuel flow rate while preventing the surge and flame out event.

목차

Abstract
 1. Introduction
 2. Turbojet Engine Control Systems
  2.1. Turbojet Engine and Surge Control
  2.2. Linear Modeling of Turbojet Engine
  2.3. PID Controller
 3. Simulation
 4. Conclusion
 References

키워드

저자

• Haeng-Cheol Shin [ Department of Aeronautical System Engineering, Hanseo University Graduate, Chungcheongnam-do, Korea ]
• Won-Hyuck Choi [ Department of Aeronautical System Engineering, Hanseo University Graduate, Chungcheongnam-do, Korea ]
• Min-Seok Jie [ Department of Aeronautical System Engineering, Hanseo University Graduate, Chungcheongnam-do, Korea ]

참고문헌

발행기관

간행물

표지보기 관심저널 등록

• 간행물명

  International Journal of Control and Automation

• 간기

  월간

• pISSN

  2005-4297

• 수록기간

  2008~2016

• 십진분류

  KDC 505 DDC 605