Tilting mechanism capable of being hidden in wing

A technology of tilting mechanism and wing, which is applied in the direction of rotorcraft, motor vehicles, aircraft, etc., can solve the problems of large air resistance, unstable attitude of the aircraft, affecting the flight range and flight speed, etc., to improve efficiency and fast flight speed , the effect of reducing resistance

Active Publication Date: 2016-10-12
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, during the tilting process of most tilt-rotor aircraft, the high-speed rotating blades will generate large component forces in different directions with the aircraft in level flight, resulting in unstable attitude of the aircraft
However, when many tilt-rotor aircraft are in level flight, the motor at the tail stops and does not tilt, resulting in large air resistance during level flight, which affects the flight range and flight speed.

Method used

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  • Tilting mechanism capable of being hidden in wing
  • Tilting mechanism capable of being hidden in wing
  • Tilting mechanism capable of being hidden in wing

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Embodiment Construction

[0026] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0027] Such as Figure 1 to Figure 2 As shown, a tilting mechanism that can be hidden in the wing, the tilting mechanism is arranged on the wing 1, and a recovery space 2 capable of accommodating the tilting mechanism is reserved in the wing 1, the tilting mechanism The turning mechanism includes a steering gear 3, a tilting seat 4, a motor 5 and a folding paddle 6, the motor 5 is fixedly installed on the bottom of the tilting seat 4, the folding paddle 6 is installed on the motor shaft, and the motor shaft directly drives the folding paddle 6 . The steering gear 3 is ...

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Abstract

The invention discloses a tilting mechanism capable of being hidden in a wing. The tilting mechanism is arranged on the wing; a recovering space capable of accommodating the tilting mechanism is reserved in the wing; the tilting mechanism comprises a steering gear, a tilting seat, a motor and foldable paddles; the motor and the foldable paddles are fixed on the tilting seat; the steering gear and the tilting seat are connected through connecting rod mechanisms. The tilting mechanism can be used as a rotor tilting mechanism for an unmanned tilting rotor aircraft, and can stabilize the aircraft to achieve conversion between multiple rotors and a fixed wing, so that resistance to forward flight can be reduced, and the propulsion efficiency can be improved.

Description

technical field [0001] The invention relates to the technical field of tilt rotor aircraft, in particular to a tilt mechanism that can be hidden in the wing. Background technique [0002] A tiltrotor aircraft is a unique aircraft that can hover, take off and land vertically like a traditional multi-rotor aircraft, or cruise at high speed like a propeller fixed-wing aircraft. The aircraft has the capabilities of vertical take-off and landing, hovering, low-altitude flight, high-speed cruising, and long range. It can quickly lift into the air in relatively complex terrain and environments, complete long-distance flight missions, and can conduct reconnaissance and emergency rescue on the battlefield. It plays a specific role in disaster relief and has broad application prospects. [0003] At present, during the tilting process of most tilt-rotor aircraft, the high-speed rotating blades will generate large force components in different directions with the aircraft in level flig...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/22B64C27/52B64C27/32
CPCB64C27/22B64C27/32B64C27/52
Inventor 张代兵张纪阳向绍华吕飞沈林成方强胡天江胡豆肖乃经习业勋李腾祥赵树龙安臣潘崇煜陈超
Owner NAT UNIV OF DEFENSE TECH
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