Bionic folding unmanned aerial vehicle using flexible airfoil

Abstract

The invention discloses a bionic folding unmanned aerial vehicle using flexible airfoils and a using method thereof, which belong to the technical field of miniature unmanned aerial vehicles. The specific structure of the unmanned aerial vehicle comprises a micro power system, a wing leading edge, a main fuselage, a servo mechanism, a foldable control surface control mechanism, a V-shaped empennage and a flexible wing surface. The micro power system is fixed at the front end of the main fuselage; the left side and the right side of the front end of the main fuselage are each provided with a foldable wing leading edge, and the left side and the right side of the rear end of the main fuselage are each provided with a foldable control surface control mechanism controlled by a servo mechanism. And the foldable V-shaped empennage is arranged at the tail end of the main fuselage. After the unmanned aerial vehicle pops up, the wing leading edge, the unmanned aerial vehicle foldable control surface control mechanism and the V-shaped empennage are automatically opened under the elastic effect, so that the flexible wing surface is unfolded. The flexible airfoil design is adopted, so that the folding unmanned aerial vehicle can obtain a larger wing area and higher aerodynamic efficiency, the lift coefficient is improved, the minimum level flight speed of the unmanned aerial vehicle is reduced, and the folding unmanned aerial vehicle has better maneuverability.

Description

technical field [0001] The invention relates to the technical field of micro drones, in particular to a bionic folding drone using flexible wings. Background technique [0002] With the continuous expansion of UAV market demand and the continuous development of UAV technology, the miniaturization of UAV has become one of the important development directions in this field. [0003] As a category of unmanned aerial vehicles, Micro Air Vehicle (MAV) was first proposed by the US Defense Advanced Research Projects Agency (DARPA) at the Future Military Conference in 1992. At that time, DARPA defined MAV as: the flight speed of MAV is about 5-20m / s, and the maximum design length of its fuselage is between 10-15cm, which is about the size of an adult's palm. With the development of science and technology and in-depth research on actual use, the U.S. military has gradually relaxed the size restrictions on micro air vehicles, and has higher requirements for the functions and practica...

AI Technical Summary

Problems solved by technology

Most of the existing folding micro-UAVs are in a large aspect ratio configuration, so that the wings are retracted to coincide with the fuselage, such as the gray partridge UAV in the United States. In the case of limited size, the wing area is small, which also leads to a large aspect ratio of the aircraft wing, a large minimum level flight speed, and insufficient maneuverability of the aircraft

At the same time, the Reynolds number of the micro-UAV itself is low, resulting in low aerodynamic efficiency, making it difficult to carry out more detailed reconnaissance operations, etc.

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