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A flapping-wing aircraft with twisted inner wings

A flapping-wing aircraft and inner wing technology, applied in the field of flapping-wing aircraft, can solve the problem that the wing structure fails to achieve flapping and torsion, achieve smooth flapping and torsion, reduce the weight of the fuselage, and improve the processing and assembly performance Effect

Active Publication Date: 2020-06-12
NANTONG UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] However, the wing structures of prior art aircraft still fail to achieve ideal flapping and twisting

Method used

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  • A flapping-wing aircraft with twisted inner wings
  • A flapping-wing aircraft with twisted inner wings
  • A flapping-wing aircraft with twisted inner wings

Examples

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Embodiment Construction

[0062] The invention provides a flapping-wing aircraft with twisted inner wings. A pair of fully symmetrical double crank and double rocker mechanisms are used as the flapping wing mechanism. The motor drives the flapping wing mechanism to flap up and down through the deceleration mechanism to generate the lift required for flight. A set of internal wing mechanisms distributed forward and backward is designed. The front and rear driving structure is the same, and there is a 45° movement phase difference, which generates corresponding lift and thrust, and realizes flapping wing action in accordance with the principle of flapping wing flight.

[0063] 1. Structure introduction:

[0064] In an exemplary embodiment of the present invention, a flapping-wing aircraft with twisted inner wings is provided. Such as Figure 1-3 As shown, the present invention includes: a frame 1, a wing, and a driving device capable of simultaneously realizing flapping and twisting of the wing.

[0065] Each...

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PUM

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Abstract

The invention provides a flapping wing aircraft capable of realizing twisting of inner wings. The flapping wing aircraft comprises a rack, wings, rear drive devices and front drive devices. The rack has mounting positions. The wings are symmetrically arranged on the both sides of the rack. The wing on each side comprises an inner wing main flapping rod and an inner wing auxiliary flapping rod. The inner wing main flapping rods generate lift required during the flapping wing flight process. The inner wing auxiliary flapping rods generate lift and thrust required during the flapping wing flight process. The front drive devices are mounted in the mounting positions of the rack at the front and used for driving the inner wing main flapping rods. The rear drive devices are mounted in the mounting positions of the rack at the rear and used for driving the inner wing auxiliary flapping rods. The inner wing main flapping rods and the inner wing auxiliary flapping rods on the both sides of the rack have phase differences. The flapping wing aircraft has the advantages that the design of front and rear inner wing flapping mechanisms having the phase differences is provided, the flapping wing motions which are in accordance with the flapping wing flight principle are conducted, and the takeoff, direct flight and landing functions can be fulfilled when the left and right wings are synchronized; and when differential motions are conducted, the functions such as pitching, yawing and steering under the asynchronous control of frequencies and amplitudes of the left and right flapping wings can be fulfilled.

Description

Technical field [0001] The invention relates to the technical field of aircraft, in particular to a flapping-wing aircraft with twisted inner wings. Background technique [0002] Bionic flapping-wing aircraft is an aircraft designed to simulate the flapping wing action of natural animals and achieve basic flight characteristics; compared to the research of fixed-wing and rotary-wing aircraft, flapping-wing aircraft is still in the exploratory stage. However, flapping-wing aircraft has been widely studied in the fields of national defense and civil use because of its advantages of high flight efficiency, low energy consumption, light weight, small size, low cost and good operability. [0003] The asymmetric flapping wing structure with single crank and double rocker designed by Northwestern Polytechnical University uses the left and right connecting rods to drive the rocker to control the flapping action of the wings on both sides that are not completely synchronized; the seven-bar ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C33/02
CPCB64C33/02
Inventor 邢强顾光健王浩杨预立徐海黎
Owner NANTONG UNIVERSITY
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