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A Calculation Method for Composite Blade Sectional Characteristics

A blade profile and characteristic calculation technology, applied in calculation, computer-aided design, design optimization/simulation, etc., can solve problems such as inaccurate calculation of torsional stiffness, long cycle, heavy workload, etc., to save scientific research cycle and improve efficiency , the effect of accurate calculation

Active Publication Date: 2020-12-29
哈尔滨哈飞航空工业有限责任公司
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  • Application Information

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Problems solved by technology

[0004] 1) Euler-Bernoulli beam theory is adopted, but this method is mainly applicable to metal blades, and the calculation of torsional stiffness is inaccurate;
[0005] 2) The finite element method is used for calculation, which can fully consider the complexity of the structure, and can also consider the coupling between swing, swing and twist, but it needs to manually divide the grid, which requires a lot of work and a long cycle

Method used

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  • A Calculation Method for Composite Blade Sectional Characteristics
  • A Calculation Method for Composite Blade Sectional Characteristics
  • A Calculation Method for Composite Blade Sectional Characteristics

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Embodiment Construction

[0041] The section characteristics of the H425 main blade are calculated. The blade includes a C-beam 1 at the front, a Z-beam 2 in the middle and a Z-beam 3 in the rear. Between the C-beam and the Z-beam in the middle Between the Z-beams in the middle and the rear Z-beams, the wall chamber 5 is formed, and the Z-beams at the rear and the end form the wall chamber 6. The calculation results are given and compared with The experimental data were compared.

[0042] 1) Prepare the blade data file;

[0043] 2) Calculate according to the calculation formula of section characteristics:

[0044] Linear density:

[0045] Centroid Offset:

[0046] Tension Center Offset:

[0047] Tensile stiffness: EA=∫∫ A E·dA (4)

[0048] Swing stiffness: EI y =∫∫ A E·(Z-Z T ) 2 dA (5)

[0049] Shimmy stiffness: EI z =∫∫ A E·(Y-Y T ) 2 dA (6)

[0050] Swing coupling stiffness: EI yz =∫∫ A E·(Y-Y T )·(Z-Z T )dA (7)

[0051] Swing inertia: PI y =∫∫ A ρ·(Z-Z T ) 2 dA (8)

...

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Abstract

The invention belongs to the field of helicopter design, and particularly relates to a composite blade section property calculation method. Blade section properties are the most basic original parameters for helicopter rotor dynamic calculation. Accuracy of the blade section properties is a premise for judging helicopter rotor dynamic properties and vital to rotor dynamic design. According to the composite blade section property calculation method, data files of sections of blades are built according to blade structures, wing profile theory contour data and material data, rigidity is calculated by a modulus weighting method according to anisotropic performances of composites, and mass is calculated by a finite element concept. Accurate basic data are provided for blade dynamic analysis and design, the blade section properties can be rapidly and accurately calculated, optimal design of the blades can be rapidly finished, and rotor system dynamic design technology is broken through.

Description

technical field [0001] The invention belongs to the field of helicopter design, and in particular relates to a method for calculating the profile characteristics of a composite material blade. Background technique [0002] The blade profile characteristics are the most basic original parameters for the calculation of helicopter rotor dynamics. The accuracy of the blade profile characteristics is the prerequisite for judging the quality of the helicopter rotor dynamics characteristics, and it is very important for the rotor dynamics design. [0003] At present, there are mainly two methods for calculating the profile characteristics of helicopter blades: [0004] 1) Euler-Bernoulli beam theory is adopted, but this method is mainly applicable to metal blades, and the calculation of torsional stiffness is inaccurate; [0005] 2) The finite element method is used for calculation, which can fully consider the complexity of the structure, and can also consider the coupling betwee...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F30/15G06F119/14G06F113/26
CPCG06F30/15G06F30/23
Inventor 高磊夏双满谢志远
Owner 哈尔滨哈飞航空工业有限责任公司
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