Planning, Execution, and Analysis of the Meridian UAS Flight Test Program Including System and Parameter Identification

The purpose of this Master Thesis is to present the flight test procedures, planning, and analysis including system identification, parameter identification, and drag calculations of the Meridian UAS. The system identification is performed using traditional techniques including Modified Transient Peak Ratio method and Time Ratio method. A drag reduction effort on the aircraft is also analyzed and the drag coefficient is calculated during specific flight conditions. The parameter identification is performed using a 6-DOF non-linear model of the Meridian UAS. The 6-DOF non-linear model was adapted from a previous model made for the 1/3 scale Yak-54 UAV. The model was adapted to the Meridian UAS by changing the input stability and control derivatives developed in AAA and integrating an enhanced engine model. The resulting AAA generated model is then compared to flight test telemetry demonstrating that it effectively predicts the dynamics of the Meridian. The input stability and control derivatives are then tuned to the flight test telemetry to improve the fidelity of the model. The tuning identifies error in the derivatives and demonstrates the dominant stability and control derivative for a specific dynamic mode. The performance of the tuned Meridian 6-DOF non-linear model is comparable to a high fidelity model and can be used for Meridian simulation and crew training