DEVELOPMENT OF A FLIGHT SIMULATOR

Abstract

This project’s aim is the development of a virtual flight simulator (VFS) to predict the trajectory of a model plane undergoing free pitch motion in a wind tunnel. The project incorporates the design and building of a model plane with a pitch rotation degree of freedom, the development of a VFS for plotting the real-time flight trajectory in LabVIEW using the Hardware-in-a-Loop approach, and the evaluation of the performance of the model and VFS developed by conducting three experiments assessing flight behavior. The model design was completed based on the longitudinal static stability and steady-level flight analyses via XFLR5 and an in-house code using MATLAB. This study integrated advanced aerodynamic testing systems, including the ATI Mini 40 sensor and Arduino BLE Sense 33, within a wind tunnel setting to capture and analyze real-time data.

Three experiments were conducted to assess the model and VFS: the accelerating flight mode assessing the thrust required to fly at the desired velocity, the effect of the pitch trim angle on the flight trajectory in x- and z-axis directions, and the steady-level flight mode assessing the relation between the flight velocity and the plane pitch trim angle. The first experiment showed the same trend as results calculated numerically using mathematical models for aerodynamic parameters and the XFLR5 wing-only based analysis. However, the experimental drag coefficient and thrust required to fly at the desired velocity were about a hundred times higher than the numerical estimations since the numerical estimations considered drag from the wing only, while, in reality, there were additional sources of drag such as the fuselage, motors, propellers, and the support system. The second experiment resulted in the expected flight trajectory with a higher pitch trim angle resulting in a higher altitude increase, which complies with the flight mechanics laws. The third experiment showed an unexpected result that was justified as even though it is expected for a conventional plane that the trim angle reduces as the flight velocity increases, the plane model developed in this project had unconventional thrust vectoring that may have added a non-linear effect, which caused the opposite trend. To evaluate the given justification, further studies are needed. In general, the experiments showed plausible results. Thus, the developed VFS can be used for complex and unconventional aircraft models for educational purposes and future pilot training.