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

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...

AI Technical Summary

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 variables when the topology remains unchanged, but the topology of the rotor and wing section structures obtained through optimization does not change, so There is a small design space, and it may be difficult to meet the requirements of the specified rigid body properties and shear center position

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