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Laser Dot Projection Photogrammetry and Force Measurement for Flapping Wing Micro Air Vehicles60,99 €![Flapping Wing Micro Air Vehicle Wing Manufacture and Force Testing]( "Flapping Wing Micro Air Vehicle Wing Manufacture and Force Testing")
Flapping Wing Micro Air Vehicle Wing Manufacture and Force Testing61,99 €![Finite Element Solution: Nonlinear Flapping Beams for Use with Micro Air Vehicle Design]( "Finite Element Solution: Nonlinear Flapping Beams for Use with Micro Air Vehicle Design")
Finite Element Solution: Nonlinear Flapping Beams for Use with Micro Air Vehicle Design60,99 €![Biomimetic Micro Air Vehicle Testing Development and Small Scale Flapping-Wing Analysis]( "Biomimetic Micro Air Vehicle Testing Development and Small Scale Flapping-Wing Analysis")
Biomimetic Micro Air Vehicle Testing Development and Small Scale Flapping-Wing Analysis60,99 €![Conceptual Design Tool to Analyze Electrochemically-Powered Micro Air Vehicles]( "Conceptual Design Tool to Analyze Electrochemically-Powered Micro Air Vehicles")
Conceptual Design Tool to Analyze Electrochemically-Powered Micro Air Vehicles60,99 €![Knock'em to the Stone Age! The Fusion of Micro Air Vehicles and Nano Sensors]( "Knock'em to the Stone Age! The Fusion of Micro Air Vehicles and Nano Sensors")
Knock'em to the Stone Age! The Fusion of Micro Air Vehicles and Nano Sensors60,99 €![Damage Considerations of a Flexible Micro Air Vehicle Wing Using 3-D Laser Vibrometry]( "Damage Considerations of a Flexible Micro Air Vehicle Wing Using 3-D Laser Vibrometry")
Damage Considerations of a Flexible Micro Air Vehicle Wing Using 3-D Laser Vibrometry60,99 €
For urban combat reconnaissance, the flapping wing micro air vehicle concept is ideal because of its low speed and miniature size, which are both conducive to indoor operations. The focus of this research is the development of experimental methods best suited for the vibration testing of the wing structure of a flapping wing micro air vehicle. This study utilizes the similarity of a beam resonating at its first bending mode to actual wing flapping motion. While computational finite element analysis based on linear vibration theory is employed for preliminary beam sizing, an emphasis is placed on experimental measurement of the nonlinear vibration characteristics introduced as a result of large movement. Beam specimens fabricated from 2024-T3 aluminum alloy and IM7/5250-4 carbon epoxy were examined using a high speed optical system and a scanning laser vibrometer configured in both three and one dimensions, respectively.