Method for designing composite material beam for helicopter and fixed-wing aircraft

A composite material and design method technology, applied in the field of composite material beam design and section structure design, can solve the problems of small design space, complex beam structure design, difficult to meet rigid body characteristics and shear center position, etc., to improve performance and improve performance. Effect

Active Publication Date: 2013-10-23
BEIHANG UNIV
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Problems solved by technology

Although the application of composite materials provides more options for helicopter and fixed-wing aircraft design, it also makes the beam structure design more complex
Traditional composite material beam design methods often use composite material layup angle, thickness and material as design va

Method used

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  • Method for designing composite material beam for helicopter and fixed-wing aircraft
  • Method for designing composite material beam for helicopter and fixed-wing aircraft
  • Method for designing composite material beam for helicopter and fixed-wing aircraft

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Embodiment

[0087] In order to verify the composite material beam design method proposed in the present invention, the topological structures of the fixed-wing aircraft wing sections with square section and NACA0018 section shapes are designed respectively. The square section consists of 25×25 grids, each with 9 types of materials. One isotropic material and one anisotropic material are included, and the anisotropic material considers two fiber plane directions and four fiber directions, so there are eight candidate anisotropic material types. The material properties of the two materials are shown in Table 1:

[0088] Table 1 Material properties

[0089]

[0090] The length of the square section beam is 80mm, and the end shear force is loaded. The fibers and fiber plane directions in the final topological structure of the section are as follows: Figure 6 and Figure 7 shown. A blank cell indicates that the cell is mainly composed of isotropic materials, while the length and angle ...

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Abstract

The invention discloses a method for designing a composite material beam for a helicopter and a fixed-wing aircraft, and belongs to the field of designing an aircraft structure. The method comprises the steps of firstly establishing a composite material beam optimal design model according to the general design performance of the helicopter or the fixed-wing aircraft, wherein a design variable is a volume fraction of each material at each unit; then establishing a composite material beam profile finite element model by finite element software; optimally designing the composite material beam profile finite element model by the composite material beam optimal design model through a volume fraction filtering method or a sensitivity filtering method, and updating the volume fraction based on a sequential linear programming algorithm to obtain material distribution rules of the beam profiles; and finally obtaining a topological structure of the beam profile according to the material distribution rules. The method for designing the composite material beam profiles can be applied to profile design of various helicopter rotors and fixed-wing aircraft wings.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure design, and in particular relates to a composite material beam design method applicable to helicopters and fixed-wing aircraft, which can be applied to the section structure design of helicopter rotors and fixed-wing wings in the conceptual design stage. Background technique [0002] Helicopter rotors and fixed-wing aircraft wings are an important part of aircraft structure, directly bear aerodynamic force, and provide lift and control force for helicopters and fixed-wing aircraft. They have a common feature: they are all slender structures, so they are often simplified as beam structures in analysis. The profile properties of beam structures have a significant impact on the overall performance of helicopters and fixed-wing aircraft. Its section stiffness characteristics are the basis for aeroelastic analysis and dynamic design, and reasonable structural stiffness can greatly improve d...

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庄南剑郭俊贤张亚军黄明其
Owner BEIHANG UNIV
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