Currently there are different projects and already existing software tools for the automation of the aircraft design process. The common goal is to increase the design speed and enhance the variety of technically feasible solutions. Hence different approaches like geometric parametrization, parameter variation from existing models or requirements engineering are applied. Integrated in an aircraft design environment, all attempts need a data model in order to save and organize the specific information for calculation tools utilizing them. For that, different high-level languages like C, C++ or python but also XML are used. The main objective of the aircraft design environment of the Institute of Aircraft Design at the Technical University of Munich, called ADEBO (Aircraft DEsign BOx), is to set up a working environment which applies both existing stand-alone and newly developed programs. Especially with the focus on the fields of application which range from academia to research and development, a data model is needed, which has to fulfill the following diverse requirements: definiteness, consistency, intelligibility, expandability, compatibility, transferability, and also user-friendliness. Resulting from these issues a novel object oriented data model ADDAM (Aircraft Design DAta Model) is developed in MATLAB. NomenclatureADDAM = Aircraft Design DAta Model ADEBO = Aircraft DEsign BOx AE = Artificial Engineer C = coding language C++ = coding language, based on C CDT = Conceptual Design Tool COM = Component Object Model by Microsoft CPACS = Common Parametric Aircraft Configuration Schema DLR = German Aerospace Center GUI = Graphical User Interface .NET = software framework by Microsoft RCE = Remote Component Environment R&D = Research & Development RPAS = Remotely Piloted Aircraft System SI = Système International (Fr.) UML = Unified Modelling Language
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
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