Self-adaption variable-rigidity bow wing for micro flapping-wing and flapping rotor crafts

Abstract

The invention belongs to the field of aircraft design and relates to a bow wing for micro flapping-wing and flapping rotor crafts. The bow wing comprises a main beam, bow beams, bowstrings and a wingmembrane. The main beam is a beam in a spanwise direction of the wing, one side of the wing membrane is fixedly connected with the main beam, the bow beams are fixedly connected with the wing membranes, two ends of each bowstring are fixedly connected with two ends of the corresponding bow beam, and a required pneumatic appearance is formed through the wing membrane. The wing surface of the bow wing is cambered to some extent intrinsically, and high lift coefficient in a steady flow field is realized. The negative lift of bow wing in an upbeat stage is reduced while instantaneous lift is increased in a downbeat stage, and high energy utilization rate is realized. In material selection of the bow wing, a material low in Young modulus is selected for the bow wing, and high chordwise flexibility is achieved.

Description

technical field [0001] The invention relates to an adaptive variable stiffness bow-shaped wing used for micro-flapping-wing and flapping-rotor aircraft, and belongs to the field of aircraft design. Background technique [0002] Micro air vehicles are small in size, easy to carry, have good maneuverability and concealment, and are widely used in military and civilian fields. According to its flight mode and layout, micro air vehicles can be divided into: micro fixed-wing aircraft, micro rotor aircraft and micro flapping wing aircraft. Micro-fixed-wing aircraft have fast flight speed and high structural stability, but cannot fly at low speed and hover; micro-rotor aircraft can take off and land vertically and hover, but their speed is relatively slow and the noise is relatively obvious. The micro flapping wing aircraft is an aircraft designed according to the principle of bionics. It can take off and land vertically, and can fly at high speed. Compared with fixed wings and ro...

AI Technical Summary

Problems solved by technology

[0005] (2) If the ideal stiffness in the down-shooting stage is selected as the design stiffness of the flapping wing, then the stiffness in the up-shooting stage is too large, and the angle of attack is likely to be too small, resulting in a large negative lift and low aerodynamic positive lift and efficiency;

[0006] (3) At the present stage, the variable stiffness of the flapping wing is realized by adding a driving mechanism to twist the flapping wing or bend the outer wing, but this will cause the complexity of the wing structure and increase the weight

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