FE Simulation of Control Surfaces with SMA Actuators for Small Size Aircrafts

In this study an attempt has been made to simulate the control surfaces, which has been equipped with SMA based actuating mechanism for deploying the trim tab, for a small scale aircraft. The existing elevator has been modified to incorporate the shape memory alloy (SMA) mechanism. Analysis of modified elevator with trim tab has been carried out using finite element method. Experimental investigation has also been carried out to validate the theoretical results by mounting the strain gauges in the elevator. The strains obtained from the theoretical study correlate reasonably well with the experimental data. The results of the study clearly show that the stress and strain field of elevator due to the SMA actuation is within the permissible limits