DEVELOPMENT OF A VALIDATED DYNAMICS MODEL FOR THE STOPROTOR UAV REPORT 2: Rotary Wing Configuration Experimental and Numerical Methods

This report describes the works performed by RMIT University as contractually agreed with StopRotor Unmanned Aircraft Systems Pty Ltd (project code: 0200314150). This is the second report of a series of three planned deliverables and it details the rotary-wing 6-DOF analytical development and the technical preparation activities performed to carry out, in the subsequent phases of the program, experimental research work in the RMIT industrial wind tunnel and in flight. A suitable form of the aircraft 6DOF model is presented that will be used as a basis for the development of a complete rotary wing 6DOF model for the StopRotor aircraft. The derivatives and coefficients are to be acquired using various engineering methods including: analytical tools, wind tunnel experiments (utilizing the RMIT industrial Wind Tunnel) and experimental flight test. In addition to the 6DOF model for fixed-wing configuration presented in report 1, this report presents preliminary analysis of the main performance parameters relevant to the rotary wing flight phase. Due to the complexity of the full experimental aerodynamic analysis of the StopRotor in its rotary wing configuration, some derivatives will be approximated using the engineering methodologies presented in this report and others will be taken from the wind tunnel experiments. Wind tunnel experiments are more complex than those of the fixed wing configuration. This is mainly due to the rotary wing aerodynamics and the fluids interaction to the surrounding environment. In this case the StopRotor is situated inside a closed wind tunnel. The floor and walls surrounding the StopRotor will significantly influence the flow. As this is a common problem with wind tunnel testing of rotary wing aircraft, suitable correction factors can be applied to account for the influence of these items as described in the report