Rotor blade structure design capable of inhibiting rotation chattering of tilt rotor

A technology of tilting rotorcraft and rotor blades, which is applied in the direction of rotorcraft, motor vehicles, aircraft, etc., can solve the problems of increased wing waste resistance, increased wings, reduced efficiency and performance of the tilting rotorcraft, and achieves suppression Rotary chatter, the effect of increasing the speed of the rotary chatter

Inactive Publication Date: 2014-08-27
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This will inevitably lead to an increase in the relative thickness of the wing (usually 23% of the chord length of the wing), and at the same time increase the weight of the whole machine and the waste resistance of the wing, thereby greatly reducing the efficiency and performance of the tiltrotor when flying at high speed

Method used

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  • Rotor blade structure design capable of inhibiting rotation chattering of tilt rotor
  • Rotor blade structure design capable of inhibiting rotation chattering of tilt rotor
  • Rotor blade structure design capable of inhibiting rotation chattering of tilt rotor

Examples

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Embodiment

[0040]In this example, aiming at the semi-extended wind tunnel model of XV-15 tiltrotor, the proposed rotor blade configuration is used to suppress the rotary flutter. The rotor used in this model is a universal hinged rotor, the rotor speed Ω=458r / min, the rotor radius R=3.82m, and there are 3 blades in total. The blade has nonlinear negative torsion, the root torsion angle is 0°, and the tip torsion angle is -45°; the chord length of the blade is 356mm, the airfoil at the root of the blade is NACA64-935a=0.3, and the airfoil at the end of the blade is NACA64-208a=0.3. In this example, the position, torsion angle, and blade airfoil of the girder 4 are kept unchanged, and only the part near the blade tip is improved. figure 1 The radial starting point of the blade deflection is located at 0.75R from the center of rotation. The distance between the midchord deflection point 13 and the airfoil leading edge point 12 of the B-B section at the blade tip is 50% of the chord length...

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Abstract

The invention discloses a rotor blade structure capable of inhibiting the rotation chattering of a tilt rotor, belonging to the technical field of tilt rotors. The rotor blade structure comprises a blade girder, a skin and a filler core; on the basis that the position of the girder, the wing shape of the blade and the torsion angle are maintained not to be changed, middle chord lines on all cross sections are bended upwards by a certain angle at the part which is a certain distance away from a front edge point from some radial position of a blade to the tip; meanwhile, the skin and the filler are bended upwards by the same angle; the lengths of the bended parts are linearly increased along with the increment of the radial position. After the rotor blade structure is used, the shearing gas power in a rotor wing shimmy surface can be effectively reduced, and the system damping is improved, so that the rotor blade structure has a good effect of inhibiting the rotation chattering and is capable of effectively accelerating the speed of the rotation chattering. The structure meets the basic performance requirement of the rotor blade structure of the tilt rotor and is simple in structure, and the weight of the blade is not increased.

Description

technical field [0001] The invention belongs to the technical field of tilt rotor aircraft, and in particular relates to a rotor blade configuration design for suppressing the rotary flutter of the tilt rotor aircraft. Background technique [0002] Tilting rotorcraft is a new type of aircraft between helicopters and fixed-wing aircraft. Its characteristic is that the rotor can be tilted forward by 90° relative to the wings. When the rotor is in the vertical position, the rotor generates an upward pulling force. At this time, the rotor is equivalent to the rotor of a helicopter, so that the tilt rotor can take off, land and hover in the helicopter mode; when the rotor is in a horizontal position, the rotor generates a forward pulling force. The rotor is equivalent to the propeller of the aircraft, and the lift is completely generated by the wings, so that the tilt rotor can fly at high speed in the aircraft mode. While the tiltrotor has both the vertical flight capability of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/467B64C27/473
Inventor 罗漳平金万增向锦武
Owner BEIHANG UNIV
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