Unmanned aerial vehicle wing with two-segment bionic flapping wings

Abstract

The invention discloses an unmanned aerial vehicle airfoil with two-segment bionic flapping wings. A fuselage, ailerons and main wings are sequentially hinged from inside to outside; each aileron is composed of four first bionic airfoil-shaped ribbed plates, two transmission rods and a support rod; each main wing is composed of a first bionic airfoil-shaped ribbed plate, four second bionic airfoil-shaped ribbed plates and a transmission rod; the maximum thickness of each first bionic airfoil-shaped ribbed plate is in a position which is 19.86% of a chord, the maximum camber is in a position which is 49.32 of the chord, and when the unit length of the chord is 1, the maximum thickness is 0.1076 and the maximum camber is 0.1089; and the maximum thickness of each second bionic airfoil-shapedribbed plate 6 is in a position which is 16.64% of the chord, the maximum camber is in a position which is 42.68% of the chord, and when the unit length of the chord is 1, the maximum thickness is 0.1084 and the maximum camber is 0.1097. The unmanned aerial vehicle airfoil disclosed by the invention inherits good characteristics of homing pigeons, plane parameters of the main wings and the ailerons of the airfoil and airfoil shapes of sections are subjected to bionic design, the aerodynamic efficiency and flexibility of an aircraft are improved, the flying and landing of the aircraft are relatively quick, and thus the aircraft has good lift drag characteristics and flexibility.

Description

technical field [0001] The invention belongs to the technical field of aviation, and in particular relates to a double-stage bionic flapping-wing unmanned aerial vehicle wing. Background technique [0002] Research on unmanned aircraft is the research focus in the military field of various countries today, and miniaturized and miniaturized aircraft is a new trend in the development of unmanned aerial vehicles. [0003] The flying speed of the micro-aircraft is only tens of kilometers per hour, and the flying Reynolds number is 2×10 5 about. On the one hand, at such a low Reynolds number, the aerodynamic viscous force and drag are more prominent; the boundary layer of the fuselage tends to be laminar; the boundary layer of the wing is prone to separation from the wing, thereby losing lift. Therefore, the traditional fixed-wing and rotary-wing aircraft research methods are no longer applicable, and the flapping-wing flight method must be studied. On the other hand, the micr...

AI Technical Summary

Problems solved by technology

Therefore, the traditional fixed-wing and rotary-wing aircraft research methods are no longer applicable, and the flapping-wing flight method must be studied

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