Elastic hinge for miniature flapping rotor aircraft and manufacturing method thereof

Abstract

The invention discloses an elastic hinge wing for a miniature flapping rotorcraft and a manufacturing method and belongs to the field of aircraft design. The elastic hinge wing for the miniature flapping rotorcraft comprises a panel flapping wing, a total primary beam, an elastic hinge and a blocking secondary beam; the panel flapping wing comprises a panel flapping wing primary beam, a secondarybeam, an oblique secondary beam and a wing film; the elastic hinge is made of a material which is high in impact resistance, high in mechanical property and moderate in elasticity; the moderate elasticity means that when the air load is applied to the upper portion of the elastic hinge wing, the elastic hinge is prone to deforming under bending, and bending deformation of the elastic hinge enablesthe panel flapping wing to generate a large attack angle; and when the external load is not applied, the elastic hinge keeps flat and cannot deform under bending due to the gravity of the panel flapping wing. The invention further discloses the manufacturing method of the elastic hinge wing for the miniature flapping rotorcraft. The elastic hinge wing can generate the large attack angle in the upward flapping process to reduce negative lift, and the elastic hinge wing has the advantages of being high in energy utilization rate and large in flexibility.

Description

technical field [0001] The invention relates to an elastic hinge used for a miniature flapping rotor aircraft and a manufacturing method thereof, belonging 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. Miniature 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 the speed is relatively slow and the noise is relatively obvious; The designed aircraft can not only take off and land vertically, but also fly at high speed, and has higher aerodynamic efficiency compared with fixed wings and rotors. The micro-flapping-rotor airc...

AI Technical Summary

Problems solved by technology

[0004] (1) The problem of negative lift in the up-shooting stage: the traditional flat flapping wing is prone to insufficient angle of attack during the up-shooting process, resulting in a large negative lift, resulting in low efficiency and unable to achieve high lift;

[0005] (2) The flapping range is small and the lift is insufficient: the general flapping rotor wing is relatively rigid, and the flapping range generated during flapping is small, resulting in insufficient lift generated by the flapping rotor;

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