A configuration design of rotor blades for suppressing rotary flutter of tiltrotor aircraft

A technology for tilting rotorcraft and rotor blades, which is applied in the directions of rotorcraft, motor vehicles, aircraft, etc., can solve the problems of increasing the waste resistance of the wings, increasing the wing, reducing the efficiency and performance of the tilting rotor, and achieving the suppression of Swing chatter, the effect of increasing the speed of swing chatter

Inactive Publication Date: 2017-01-18
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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  • A configuration design of rotor blades for suppressing rotary flutter of tiltrotor aircraft
  • A configuration design of rotor blades for suppressing rotary flutter of tiltrotor aircraft
  • A configuration design of rotor blades for suppressing rotary flutter of tiltrotor aircraft

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Embodiment

[0040] In this example, for the XV-15 tilt-rotor aircraft half-span wind tunnel model, the proposed rotor blade configuration is used to suppress rotational 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 a nonlinear negative torsion, the root torsion angle is 0°, the tip torsion angle is -45°; the blade chord is 356mm, the blade root airfoil is NACA64-935a=0.3, and the blade end airfoil is NACA64-208a=0.3. In this example, the position, torsion angle and blade airfoil of the beam 4 are kept unchanged, and only the part near the tip of the blade 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 deflection point 13 of the mid-chord line of the B-B section of the blade tip and the leading edge point 12 of the airfoil is 50% of the chord length. From the radial s...

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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 specifically relates to a configuration design of a rotor blade for suppressing the rotational flutter of a tilt-rotor aircraft. Background technique [0002] Tilt-rotor aircraft is a new configuration aircraft between helicopters and fixed-wing aircraft. Its characteristic is that the rotor can tilt forward 90° relative to the wing. When the rotor is in the vertical position, the rotor generates upward pulling force. At this time, the rotor is equivalent to the rotor of a helicopter, so that the tilt-rotor machine will take off and hover in helicopter mode; when the rotor is in the horizontal position, the rotor produces forward pulling force. The time rotor is equivalent to the propeller of an airplane, and the lift is completely generated by the wing, which makes the tiltrotor fly at high speed in airplane mode. While tilt-rotor aircraft has both the ability of helicopter vertical ...

Claims

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Application Information

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