Search

This paper presents experimental results obtained with passive high lift systems using a combination of smart flap kinematics and vortex generators. A mid-scale 2.5D wind tunnel model based on DLR-F15 is tested in INCAS Subsonic Wind Tunnel, swept at 30 deg, incorporating the slat, 54 flap/VG/chord extension configurations and test matrix, developed by Dassault-Aviation. INCAS designed, manufactured and instrumented components to be added to the existing INCAS-F15 2D wind tunnel model. The test campaign was completed and results are presented.

Following the successful results of the test campaign on 2D configuration of the oscillatory blowing system in the flap gap of the INCAS F15 wind tunnel model, extensive evaluation of the 2.5D effects have been initiated in order to enable solid understanding of the fluidic integrations mechanisms and to validate this technology at a higher TRL level. Initial experiments on 2D configuration were based on work performed in AVERT EU FP6 project where the oscillatory flap gap blowing system was designed and tested on a INCAS F15 2D wing model. In 2.5D test cases this work has been extended so that the proposed system may be selected as a mature technology in the JTI Clean Sky, Smart Fixed Wing Aircraft ITD. New experimental setup was used and also updated electronics for the blowing system have been introduces. This was complemented by a new extension for the data acquisition system and visualization tools. Complex post-processing of the experimental data was mainly oriented towards system efficiency and TRL evaluation for this active technology.

This work describes the control technique of a Fault-Tolerant electromechanical system aimed to the actuation of the flap panels of the aircraft. The application provides the adoption of a couple of Fault-Tolerant permanent magnet synchronous motors designed to match minimum load requirements even in case of a fault in one or two phases. The consolidated mechanical synchronization of the mutual actuation is replaced by a fully electronic solution. The usual master-slave configuration of the two actuators with speed control and correction of the tracking error is replaced by the adoption of the parallel position control. This solution allows to avoid a complex management of the tracking error and applies to the couple of actuators the same Fault-Tolerant philosophy adopted inside for the single multiphase motor. The technique is developed and tested on a test-bed designed to emulate the real aerodynamic load condition. The achieved results show the effectiveness of the proposed solution.