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Vertical take-off and landing aircraft and control method thereof

A vertical take-off and landing aircraft, aircraft technology, applied in the direction of vertical take-off and landing aircraft, aircraft control, aircraft stability, etc., can solve the problems of complex tilting rotor mechanism, low reliability of mechanical structure, frequent accidents, etc., to achieve effective thrust Ratio, improved operability, and high reliability

Pending Publication Date: 2021-08-20
中电科芜湖通用航空产业技术研究院有限公司 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The tilting rotor mechanism is complex and the reliability of the mechanical structure is low, which is likely to cause safety hazards, such as the frequent accidents of the American Osprey V22 tilting rotor aircraft

Method used

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  • Vertical take-off and landing aircraft and control method thereof
  • Vertical take-off and landing aircraft and control method thereof
  • Vertical take-off and landing aircraft and control method thereof

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Embodiment Construction

[0027] The technical solutions of the present application are clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present application. Apparently, the described embodiments are part of the embodiments of the present application, not all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without making creative efforts belong to the scope of protection of this application.

[0028] like figure 1 , figure 2 and image 3 As shown, this embodiment provides a vertical take-off and landing aircraft 100 . The vertical take-off and landing aircraft 100 includes: a fuselage 1 , a wing 2 , a rotor 3 , an empennage assembly 4 and an auxiliary operating system 5 . Wing 2 , rotor 3 , empennage assembly 4 and auxiliary operating system 5 are all arranged on fuselage 1 .

[0029] The wings 2 are arranged on both sides of the fuselage 1, and the wings 2 of the present...

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PUM

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Abstract

The invention relates to a vertical take-off and landing aircraft and a control method thereof. The vertical take-off and landing aircraft comprises a body; wings arranged on the two sides of the body; multiple rotor wings arranged on the wings, wherein the axes of the rotor wings are parallel to the axis of the body, and every two rotor wings coaxially rotate reversely; an empennage assembly which comprises empennages and an empennage driving unit, wherein the empennages are provided with main control surfaces and are used for controlling pitching and yawing of the airplane, the multiple empennages are hinged to the tail of the airplane body, the empennage driving unit drives the empennages to be unfolded or folded, the empennage assembly serves as an airplane landing leg when unfolded, when the empennages are withdrawn, the empennages are used for aircraft air attitude trimming and pitching yaw control; and nozzles of an auxiliary control system are arranged at the two ends of the wings, the nose and the tail respectively, and the conversion and adjustment of the attitude of the aircraft in the air are achieved through counter force generated by high-speed jet flow. According to the vertical take-off and landing aircraft, the vertical take-off and landing and horizontal flight of the aircraft are achieved through the same power system, and the thrust-weight ratio of the aircraft is effectively increased.

Description

technical field [0001] The present application relates to the field of flight equipment, in particular to a vertical take-off and landing aircraft and a control method thereof. Background technique [0002] At present, one structure of vertical take-off and landing aircraft is to adopt multi-rotors to take off vertically, and use paddles or push paddles to provide aircraft forward power during level flight, while the multi-rotors remain static during vertical take-off and landing during level flight, unable to produce The effective thrust becomes the burden of the aircraft in level flight. [0003] Another type of vertical take-off and landing aircraft adopts the combination of tilting rotor and vertical take-off and landing multi-rotor. When the aircraft takes off and lands, part of the rotor tilts to provide lifting force, and part of the tilting engine rotates 90° to provide direction when the aircraft is in level flight. front force. Or, all adopt the tiltable rotor to...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/28B64C5/10B64C15/02B64C29/02
CPCB64C27/28B64C5/10B64C15/02B64C29/02
Inventor 熊俊吴凡刘照琳
Owner 中电科芜湖通用航空产业技术研究院有限公司
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