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This thesis describes a method for a mission oriented multidisciplinary design for controlled Micro Air Vehicles (MAV). MAV’s are unmanned air vehicles with maximum dimensions smaller than 50 centimetres, whereby their dimensions are much smaller than the ones a unmanned air vehicles used up to now. Because of the manifold applications for Micro Air Vehicles the mission requirements differ very much. To tap the full potential of a MAV, it is necessary to adapt the Vehicle to the specific mission requirements. For this reason the presented method was developed offering the possibility to adapt the Micro Air Vehicle to user specified mission requirements. Therefore the method performs the aerodynamic design of the configuration, the choice of all necessary hardware components and the determination of the on-board flight controller, which is necessary to improve the flying qualities and to reduce the pilot’s work load. Using an integrated optimization algorithm, which estimates all subsystem similar and at the same time, the best compromise to fulfil the mission requirements is determined. Using several examples of use the function of the design method could be approved. For the final validation of the whole design procedure two Micro Air Vehicles were realized and flight tested. Based on the flight test data the predicted results of the design procedure could be confirmed.