International Journal of Control, Automation, and Systems

Institute of Control, Robotics and Systems (제어로봇시스템학회)
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Aircraft CAS Design with Input Saturation Using Dynamic Model Inversion

  • Sangsoo Lim (School of Mechanical and Aerospace Engineering, Gyeong-sang National University) ;
  • Kim, Byoung-Soo (School of Mechanical and Aerospace Engineering, Gyeong-sang National University)
  • Published : 2003.09.01
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Abstract

This paper presents a control augmentation system (CAS) based on the dynamic model inversion (DMI) architecture for a highly maneuverable aircraft. In the application of DMI not treating actuator dynamics, significant instabilities arise due to limitations on the aircraft inputs, such as actuator time delay based on dynamics and actuator displacement limit. Actuator input saturation usually occurs during high angles of attack maneuvering in low dynamic pressure conditions. The pseudo-control hedging (PCH) algorithm is applied to prevent or delay the instability of the CAS due to a slow actuator or occurrence of actuator saturation. The performance of the proposed CAS with PCH architecture is demonstrated through a nonlinear flight simulation.

Keywords

References

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