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Tilting four-rotor-wing aircraft

A technology of tilting quadrotors and tilting rotors, which is applied in the field of aircraft to achieve the effects of improving maneuverability, increasing internal carrying space, and improving safety performance

Inactive Publication Date: 2014-04-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the defects of existing tilt-rotor aircraft design, the present invention proposes a four-engine tilt-rotor aircraft whose tail section can be rotated and deformed

Method used

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  • Tilting four-rotor-wing aircraft
  • Tilting four-rotor-wing aircraft
  • Tilting four-rotor-wing aircraft

Examples

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Embodiment Construction

[0016] as the picture shows. A tiltable four-rotor aircraft, comprising a fuselage 1, a main tilt rotor 2, an auxiliary tilt rotor 3, a tail section 4, a main wing 5, and an auxiliary wing 6, the tail section 4 is installed at the tail of the fuselage 1, Two main wings 5 ​​are installed on the two sides of the fuselage 1, and two auxiliary wings 6 are installed on the two sides of the tail section 4, and the end of the main wing 5 away from the fuselage 1 is equipped with a main tilting rotor 2, and the auxiliary wing 6 An auxiliary tilt rotor 3 is installed at the end away from the tail section 4 , the main tilt rotor 2 can rotate along the axial direction of the wing 5 , and the auxiliary tilt rotor 3 can rotate along the axial direction of the wing 6 . When the aircraft takes off, the rotors of the main tilting rotor 2 and the auxiliary tilting rotor 3 face upward, and when the rotors rotate, the aircraft obtains upward power. When the aircraft needs to fly forward, the ma...

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Abstract

The invention provides a tilting four-rotor-wing aircraft, comprising a body, main tilting rotor wings, auxiliary tilting rotor wings, an end-piece, main wings and auxiliary wings, wherein the end-piece is mounted at the tail part of the body; two main wings are mounted at the two sides of the body, respectively; two auxiliary wings are mounted at the two sides of the end-piece, respectively; each main tilting rotor wing is mounted at one end, far away from the body, of each main wing; each auxiliary tilting rotor wing is mounted at one end, far away from the end-piece, of each auxiliary wing; the main tilting rotor wings and the auxiliary tilting rotor wings are capable of rotating in the axial direction of the wings; the end-piece is capable of rotating in the axial direction of the body. The carrying capability of an existing tilting rotor wing aircraft is improved; the controllability of the aircraft at the take-off and landing stages is improved; the safety performance of flying is improved; the internal carrying space of the aircraft is expanded; the forward flight performance of the aircraft is improved; a control vane surface is omitted, so that the structure is light and simple (simplified).

Description

technical field [0001] The invention is an aircraft and belongs to the technical field of flight. Background technique [0002] A tiltrotor aircraft is an aircraft that can take off and land vertically and cruise at high speed. Tilting the rotor, that is, through the tilting of the rotor, the flight state of the aircraft is adjusted: when taking off and landing vertically, the direction of the rotor axis is upward to generate lift; when flying forward, the direction of the rotor axis is forward to generate pulling force. [0003] Existing tilt-rotor aircraft are mainly twin-engine tilt-rotors. The dual-engine tilt-rotor aircraft has some disadvantages: due to the limitation of the fuselage layout, the diameter of the rotor is small, resulting in limited carrying capacity; during the take-off and landing phase, the twin-engine tilt-rotor cannot flexibly provide Controlling force (moment); the twin-engine tilt rotor must be installed close to the center of mass of the fusela...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/28B64C27/26
Inventor 潘立军刘雪松张帅浩王钲云
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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