Triaxial tilting rotor wing aircraft

A rotorcraft and tilt-rotation technology, which is applied in the field of aircraft, can solve the problems of affecting the flight state and wasting aviation load, etc., and achieve the effect of increasing the thrust-to-weight ratio, improving the maneuverability, and reducing the ground propeller effect

Inactive Publication Date: 2020-01-31
SHANGHAI DIANJI UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The existing common VLOT unmanned aerial vehicle (vertical take-off and landing) has two sets of power systems. According to its design, there is always one power system in standby state, which greatly wastes the aviation load. The standby power system will also be aerodynamically Affect flight status

Method used

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  • Triaxial tilting rotor wing aircraft

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Embodiment

[0026] like figure 1 Shown, a kind of three-axis inclined-rotor aircraft comprises a frame 1, wings 2 on both sides of the frame 1 and an empennage 3 at the tail of the frame 1, and a front inclined-rotor 4 is respectively provided in the middle of the two wings 2, The empennage 3 top is provided with a tail tilt rotor 5, the front tilt rotor 4 can do 90 ° tilt rotation on the vertical plane, and the tail tilt rotor 5 can do 180 ° tilt rotation on the horizontal plane and the vertical plane respectively.

[0027] The front inclined rotor 4 stretches out to the front of the wing 2 through a support rod 6 respectively, and the vertical distance between the support rod 6 and the side of the frame 1 is 1 / 3~2 / 5 of the length of the wing 2. In this embodiment, the support rod 6 The vertical distance from the side of the frame 1 is 1 / 3 of the length of the wing 2, and the support rod 6 adopts an integrated carbon fiber rod, which improves the structural strength.

[0028] The wing 2...

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Abstract

The invention relates to a triaxial tilting rotor wing aircraft. The triaxial tilting rotor wing aircraft comprises a rack (1), wings (2) on the two sides of the rack (1) and a tail wing (3) arrangedat the tail of the rack (1); the middles of the two wings (2) are each provided with a front tilting rotor wing (4); a tail tilting rotor wing (5) is arranged over the tail wing (3); the front tiltingrotor wings (4) can do 90-degree tilting rotation on the vertical plane; and the tail tilting rotor wing (5) can do 180-degree tilting rotation on the horizontal plane and the vertical plane. Compared with the prior art, the utilization rate of an aircraft power system is high, and the flying effective load, air speed and reliability are improved under the same power condition.

Description

technical field [0001] The invention relates to an aircraft, in particular to a three-axis tilt-rotor aircraft. Background technique [0002] Existing tilt-rotor aircraft such as the American V-22 transport aircraft have an obvious problem in their configuration, that is, the size of the rotor should not be too large. This is to ensure that the two rotors will not be caught in the middle when they are flattened. The fuselage of the V-22 transport plane is cut off, and in order to ensure lift, the propeller of the V-22 transport plane rotates much faster than other helicopters. Excessive downwash flow is detrimental to operation and safety. However, the biggest disadvantage of the V-22 transport aircraft lies in its handling performance. Since the source of lift is far away from the two sides of the fuselage, once the left and right lift of the aircraft is unbalanced, the aircraft will roll over. This problem can be alleviated by training and upgrading equipment, but there ...

Claims

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Application Information

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IPC IPC(8): B64C27/28B64C3/54B64C3/56B64C9/00B64C25/66
CPCB64C3/546B64C3/56B64C9/00B64C25/66B64C27/28
Inventor 江潮李彬彬
Owner SHANGHAI DIANJI UNIV
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