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Method for designing blade sections of helicopter rotors

A technology for helicopter rotor and blade profiles, which is applied in calculation, instrumentation, electrical digital data processing, etc., can solve the problems that the structure cannot be obtained, and the topological type of the blade structure cannot be changed, so as to achieve the effect of improving performance and high calculation accuracy

Active Publication Date: 2013-01-30
BEIHANG UNIV
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  • Claims
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AI Technical Summary

Problems solved by technology

Since the traditional design method cannot change the topology of the blade structure, it cannot obtain the optimal structure

Method used

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  • Method for designing blade sections of helicopter rotors
  • Method for designing blade sections of helicopter rotors
  • Method for designing blade sections of helicopter rotors

Examples

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Embodiment

[0101] In this example, the rotor blade section design method based on topology optimization proposed by the present invention is applied to the actual helicopter blade design. like Figure 5 As shown, the blade bears the same resistance 4 and vertical lift 5 as the air flow direction 3, and the resultant force 6 of the lift and resistance is shown in the figure. To simplify the optimization process, it is assumed that the aerodynamic center coincides with the shear center of the blade, so no additional bending load is generated. The NACA0018 airfoil is adopted, and the chord length of the blade is 1m. Since the shape of the blade has aerodynamic performance, it is not considered here. The optimization method proposed by the present invention is used to obtain the cross-sectional structure of the blade as follows: Figure 6 As shown, the black cells in the figure represent the density of 1, the white cells represent the density of 0, and the gray cells are in between. It can...

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Abstract

The invention discloses a method for designing blade sections of helicopter rotors, and belongs to the technical field of helicopters. The method comprises determining appearance parameters according to pneumatic requirements, designating optimization objective functions and constraint functions, and establishing optimization models; utilizing finite element software to establish blade geometric models and dividing grids, importing node, grid and material information into matrix laboratory (MATLAB) software, and utilizing an implicit method for pressure linked equations (SIMP), wherein the SIMP uses every cell density as a design variable; calculating rotor blade sensitivity information in a current design state again, utilizing a sensitivity filter method to avoid checkerboard problems, and updating density information of blade section units; and calculating density differences before and after update, ending optimization if convergence conditions are met, otherwise, continuing iterative computations with updated densities as initial design parameters till convergence is achieved, and outputting blade structural styles. The method for designing blade sections of helicopter rotors can be applied to initial designs of blade structures of conceptual phases.

Description

technical field [0001] The invention belongs to the field of helicopter rotor system design, in particular to a helicopter rotor blade section design method, which can be applied to the structural design of the helicopter rotor blade in the conceptual design stage. Background technique [0002] The rotor system provides lift, propulsion and operating force for the helicopter, but also brings vibration and noise to the helicopter. It is the most important part of the helicopter. A reasonable design of the rotor structure plays an important role in improving the performance of the helicopter. In the rotor system, the blade directly bears the aerodynamic force and transmits it to the fuselage to complete the operation process such as advancing. Therefore, the blade structure is a key part of the rotor system design. [0003] Since the length of the blade structure is much larger than the dimensions of the two directions of the section, the beam theory is used to analyze the bla...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 向锦武任毅如罗漳平郭俊贤张亚军黄明其
Owner BEIHANG UNIV
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