TY - JFULL AU - Zaouche Mohammed and Amini Mohammed and Foughali Khaled and Hamissi Aicha and Aktouf Mohand Arezki and Boureghda Ilyes PY - 2016/7/ TI - Application of the Piloting Law Based on Adaptive Differentiators via Second Order Sliding Mode for a Fixed Wing Aircraft T2 - International Journal of Aerospace and Mechanical Engineering SP - 1101 EP - 1113 VL - 10 SN - 1307-6892 UR - https://publications.waset.org/pdf/10004679 PU - World Academy of Science, Engineering and Technology NX - Open Science Index 114, 2016 N2 - In this paper, we present a piloting law based on the adaptive differentiators via high order sliding mode controller, by using an aircraft in virtual simulated environment. To deal with the design of an autopilot controller, we propose a framework based on Software in the Loop (SIL) methodology and we use MicrosoftTM Flight Simulator (FS-2004) as the environment for plane simulation. The aircraft dynamic model is nonlinear, Multi-Input Multi-Output (MIMO) and tightly coupled. The nonlinearity resides in the dynamic equations and also in the aerodynamic coefficients' variability. In our case, two (02) aircrafts are used in the flight tests, the Zlin-142 and MQ-1 Predator. For both aircrafts and in a very low altitude flight, we send the piloting control inputs to the aircraft which has stalled due to a command disconnection. Then, we present the aircraft’s dynamic behavior analysis while reestablishing the command transmission. Finally, a comparative study between the two aircraft’s dynamic behaviors is presented. ER -