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Aufbau einer flugmechanischen Simulation eines Starrflügel-UAV und Validierung durch Flugversuche
(2023)
The development of aircraft, especially UAVs, is increasingly taking place in simulation environments. The estimation of the flight performance and a possible parametric design of the aircraft provides a fast, efficient and low-risk way to obtain the required mission parameters in the design and prototyping phase as well for further capability development. In the presented work, the necessary modeling of a fixed-wing UAV is conducted regarding the aerodynamics, the engine (electric motor with propeller) and the mass as well as inertia and implemented in a Simulink environment as a point mass with 6 degrees of freedom. The aerodynamics are calculated with the software XFLR5, which is especially designed for model aircraft. The thrust of the engine is obtained via wind tunnel tests. The inertia of the aircraft configuration is determined both experimentally and by means of calculations and estimates. The behavior of the simulated aircraft is validated using flight test data from the real aircraft. The methods used for the execution and post-processing of the flight tests are presented. Finally, a recommendation to lead further
development steps of the simulation is given based on the comparison results.