Fixed wing and flapping wing composite aircraft

An aircraft and fixed-wing technology, which is applied in the field of aviation aircraft design, can solve problems such as high requirements, poor flight flexibility, and susceptibility to crosswinds, and achieve high stability, expand social and economic benefits, and improve lift characteristics.

Active Publication Date: 2020-02-07
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The take-off and landing of existing fixed-wing aircraft has high requirements on the sit...

Method used

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  • Fixed wing and flapping wing composite aircraft
  • Fixed wing and flapping wing composite aircraft
  • Fixed wing and flapping wing composite aircraft

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Embodiment Construction

[0027] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0028] Flapping-wing fixed-wing composite aircraft of the present invention, as figure 1 As shown, it includes a body 1, a wing lifting surface 2, an empennage 3 and a flapping wing drive system 4.

[0029] The body 1 includes a hanging bag 101 , a suspension beam 102 , a connecting rod 103 , a control tripod 104 and a wheel 105 . Among them, the hanging bag 101 is mainly used for hanging people or objects, and its shape is pupa-like and streamlined, with a blunt front edge and a sharp rear edge. Hanging bag 101 top is apart from hanging bag 101 rear end 1 / 3 hanging bag 101 front and back direction length positions and is equipped with vertical suspension beam 102, and suspension beam 102 bottom is fixed with hanging bag 101 top, and connecting rod 103 is installed on the top. The connecting rod 103 is horizontal along the front-back direction; the middle p...

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Abstract

The invention discloses a fixed wing and flapping wing composite aircraft. The aircraft is characterized in that a whole aircraft skin adopts a flexible material, wings with an inner wing structure and an outer wing structure are designed, in the takeoff process, the inner section wings provide stable lifting force, and the outer section wings generate all the thrust and partial lifting force through large flapping and chord direction twisting; and in the flight process, gliding flight is mainly used, the lifting force is provided through the inner section wings and the outer section wings, flapping of the outer wings with the lower flapping frequency is adopted for assistance, and the flight stability of the aircraft is improved through tail wings. According to the fixed wing and flappingwing composite aircraft, the flight attitude of the aircraft is adjusted by changing the center of gravity of a suspension object below the airfoil; and in the emergency state, the outer section flapping wings can stop flapping and are locked in the designated positions and are parallel to the fixed wings to form a fixed wing layout and realize gliding flight. The aircraft has higher stability, safety and comfort, and can improve the lifting force characteristic of the whole miniature aircraft.

Description

technical field [0001] The invention belongs to the field of aviation vehicle design, and in particular relates to a compound aircraft with fixed wings and flapping wings. Background technique [0002] Based on the lift-thrust and maneuvering mechanism of large birds and bats, a fixed-wing and flapping-wing compound aircraft is proposed. The inner wing is fixed to provide a certain stable lift; the outer wing generates lift and thrust through flapping and chord torsion . [0003] The composite aircraft is a combination of the respective advantages of fixed-wing aircraft and flapping-wing aircraft, and has the characteristics of high aerodynamic efficiency and horizontal take-off and landing. The aircraft integrates lift and thrust, has fewer restrictions on the take-off and landing site, and can realize low-noise power flight. [0004] The take-off and landing of the existing fixed-wing aircraft has high requirements on the site, is easily affected by crosswinds during fli...

Claims

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Application Information

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IPC IPC(8): B64C33/02B64C39/00
CPCB64C33/02B64C39/00B64C2039/105
Inventor 李道春孙毅邵浩原李华东张尧
Owner BEIHANG UNIV
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