In the framework of recent investigations on novel UAV propulsion concepts the work behind this publication is a contribution to bring numerical evaluations and experimental data into better agreement. The presented propeller test facility is tailored to measure small scale electric propulsion trains (<15 kW) sufficiently precise so that detailed changes on the design of a propeller can be resolved. The present paper focuses on the specific considerations that have to be made to develop a comprehensive instrument for automatic wind tunnel tests and depicts notable experiences that have made in a first measurement campaign. The results will be mirrored with numerical calculations by an implementation of an enhanced blade element and momentum method.
NomenclatureD = propeller diameter = Temperature cT = thrust coefficient = Air Density cP = power coefficient I = current Indices and Abbreviations J = advance ratio AC = Alternate Current V = speed constant all = overall lc = cord length amb = ambient P = power BT = Blade Tip p = pressure COTS = Commercial Off-The-Shelf ppm = motor control signal DC = Direct Current Q = torque E = Electric R = radius ESC = Electronic Speed Controller T = thrust in = input t = time M = Mechanical V = voltage P = Propeller v = airspeed PWTTF = Propeller Wind Tunnel Test Facility = rotational speed S = Shaft = cord twist angle UAV = Unmanned Aerial Vehicle = efficiency VTOL = Vertical Takeoff and Landing
This publication shows the semi-empiric noise modeling of an electric-powered vertical takeoff and landing (eVTOL) unmanned aerial vehicle (UAV) by means of system identification from flight noise measurement data. This work aims to provide noise models with a compact analytical ansatz for horizontal and vertical flight which are suited for integration into a geographical information system. Therefore, flight noise measurement campaigns were conducted and evaluated. An existing noise model ansatz is adapted to the eVTOL UAV under consideration and noise models are computed from the measurement data using the output error method. The resulting models are checked for plausibility by comparing them to technical literature. The horizontal flight noise model is subjected to a correlation analysis and the influence of meteorological effects are examined. To achieve a higher level of accuracy in future noise modelings, an optimization of the microphone positions as well as the flight trajectory is carried out.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.