A multi-gain sliding mode based controller for the pitch angle control of a civil aircraft

A multi-gain sliding mode based controller for the pitch angle control of a civil aircraft is presented in this paper. The proposed controller is based on a novel concept of the sliding mode controllers in which multiple gains are being used to control the pitch angle of an aircraft and make it insensitive to parameter variations while reducing the chattering and guaranteeing the stability of the closed loop system. The proposed approach was implemented on a Delilah aircraft model to control the pitch angle under faulty conditions. Performance comparison between the traditional one gain SMC and the proposed multi-gains SMC are discussed.