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Method for reducing vibration load of helicopter rotor hub

A helicopter rotor, vibration load technology, applied in special data processing applications, instruments, electrical digital data processing and other directions, can solve the problems of adoption, and achieve the effect of reducing the vibration load of the propeller hub

Inactive Publication Date: 2014-05-14
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional optimal design method for reducing the load on the hub mainly revolves around the simplified rotor blade structure of the relatively simple single-box or double-box beam section, and the method proposed in this case is difficult to adopt in the actual blade design

Method used

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  • Method for reducing vibration load of helicopter rotor hub
  • Method for reducing vibration load of helicopter rotor hub
  • Method for reducing vibration load of helicopter rotor hub

Examples

Experimental program
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Effect test

Embodiment

[0092] The helicopter rotor system used in this example has 3 blades, each blade is divided into 4 units, and the wingtip is used as a single unit. The section of the composite blade is a C-shaped spar and two unit structures, and the actual values ​​are adopted for the structure of the blade root and the hub. The forward ratio of the blade is 0.3, and the moment of inertia I of the blade is 0 =334kg·m 2 , the diameter of the propeller disc is 10.69m, the rotational speed is 386r / min, the diameter of the propeller hub is 0.565m, the offset distance of the flapping hinge and the shimmy hinge are both 0.205m, the chord length of the blade is 0.35m, and the airfoil is OA212 / 0A209. The function is only a function of the hub force, and specify K 1 = K 2 = K 3 =1.

[0093] Through calculation, when using structural section parameters and composite material layered structure as design variables, compared with the initial design blade and the reference blade, the vertical shear f...

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Abstract

The invention discloses a method for reducing the vibration load of a helicopter rotor hub. The provided method aims at an actual composite material rotor blade, wherein the cross section of the blade is provided with the structures such as a C-shaped wing beam, a D-shaped wing box, a front rib, a back rib and skin; and a blade tip structure is arranged at the back end of the blade. According to a blade optimal design, an optimization model is built by taking blade airfoil typical section parameters, a composite material overlay, a wingtip sweep back angle, concentrated mass and the like as design variables, taking a hub load as a target function, and taking the natural frequency, the aero-elastic stability and the autogyration inertia as constraint conditions. When an optimization problem is solved, a graded optimization strategy is used, and a complex method and an improved feasible direction method combined algorithm are adopted. The hub load can be reduced remarkably by performing damping optimization design on the rotor hub by adopting the method provided by the invention.

Description

technical field [0001] The invention belongs to the field of helicopter dynamics design, and in particular relates to a new method for reducing the vibration load of a helicopter propeller hub. Can be applied to hingeless and bearingless helicopter composite rotor blade design. Background technique [0002] The rotor structure is the key structural part of the helicopter, and its periodic vibration is the source of the vibration of the helicopter. Reducing the vibration level of helicopter rotors can greatly improve occupant comfort and the functional and safety performance of systems and equipment. From the birth of helicopters to the present, rotor vibration reduction has always been one of the most important issues in helicopter design. Vibration levels in modern helicopters have been significantly reduced over the course of decades. With the continuous development of the aviation industry, although the performance of the helicopter is constantly improving, in order to...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 向锦武任毅如罗漳平张连鸿郭俊贤张亚军
Owner BEIHANG UNIV