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Man-electric hybrid driven horizontal flapping wing aircraft

A hybrid drive and aircraft technology, applied in the field of aircraft, can solve the problems of the take-off runway requiring taxiing distance and limited application range.

Inactive Publication Date: 2021-03-05
GUANGDONG GUOSHIJIAN TECH DEV CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Its advantage is that it has lower requirements on the take-off runway but still needs to glide distance, and it cannot hover in the air. The application range is limited

Method used

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  • Man-electric hybrid driven horizontal flapping wing aircraft
  • Man-electric hybrid driven horizontal flapping wing aircraft
  • Man-electric hybrid driven horizontal flapping wing aircraft

Examples

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Embodiment Construction

[0019] The technical solutions of the present invention will be described below in conjunction with the accompanying drawings and embodiments.

[0020] Such as figure 1 and figure 2 As shown, a kind of human-electric hybrid-driven flat-wing aircraft of the present invention includes a frame 1, and the frame 1 is provided with a flying device, a human-electric hybrid power device and a thrust device, and the flying device includes a first flying unit and a The second flight unit, the first flight unit comprises an upper level flap wing 11, a transmission rod one 12, a sleeve one 13, a fixed frame one 14 and a fixed rod one 15, and the sleeve one 13 is fixed on the frame 1 by the fixed frame one 14 Above, the upper level flat blade 11 is fixed on the upper end of the transmission rod one 12, the lower end of the transmission rod one 12 passes through the sleeve one 13, and is hinged to the fixed rod one 15, and the fixed rod one 15 is connected to the power device, and the pow...

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PUM

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Abstract

The invention relates to the technical field of aircrafts, and particularly relates to a man-electric hybrid driven horizontal flapping wing aircraft which comprises a rack, wherein the rack is provided with a flight device, a man-electric hybrid power device and a thrust device, the flight device comprises a first flight unit and a second flight unit, the first flight unit comprises an upper-layer horizontal flapping wing, a first transmission rod, a first sleeve, a first fixing frame and a first fixing rod, the first sleeve is fixed above the rack through the first fixing frame, the upper-layer horizontal flapping wing is fixed to the upper end of the first transmission rod, the lower end of the first transmission rod penetrates through the first sleeve and is hinged to the first fixingrod, the first fixing rod is connected to the power device, the second flight unit comprises a lower-layer horizontal flapping wing, a second transmission rod, a second sleeve, a second fixing frame and a second fixing rod, the second sleeve is fixed below the rack through the second fixing frame, the lower-layer horizontal flapping wing is fixed to the lower end of the second transmission rod, the upper end of the second transmission rod penetrates through the second sleeve and is hinged to the second fixing rod, and the second fixing rod is connected to the power device. By the adoption of the structural arrangement, the structure is compact, and cost is low.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a flapping-wing aircraft driven by human-electric hybrid drive. Background technique [0002] The lift device of an aircraft is a device based on aerodynamics. According to the structure, it can be divided into fixed wings and rotors. Fixed wing aircraft generally have a fuselage and symmetrically arranged fixed wings, which are powered by propellers to obtain greater flight speeds. and mobility. The principle of flight is that there is a relative speed between the fixed wing and the air, and the air interacts with the sides of the fixed wing to generate lift so that the aircraft obtains flight capability. The disadvantage of fixed-wing aircraft is that it cannot hover in the air, and needs to taxi on the runway to take off or land and support the construction of airport facilities. A rotorcraft such as a helicopter is characterized in that it does not need a runway when it ta...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/20B64C3/58B64D27/24B64D35/02B64D35/00
CPCB64C3/20B64C3/58B64D27/24B64D35/02B64D35/00Y02T50/60
Inventor 王志成
Owner GUANGDONG GUOSHIJIAN TECH DEV CO LTD
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