Flexible leading edge structure and design method thereof

Abstract

The invention provides a flexible leading edge structure. The structure comprises a flexible structure which is used for forming an aerodynamic configuration of a wing leading edge, and driving structures which are arranged in the flexible structure in a distributed mode and can generate driving force under excitation of excitation signals, wherein the driving force acts on the flexible structureto change the aerodynamic configuration of the flexible structure. Compared with an existing variable camber wing leading edge device, the flexible leading edge structure is advantaged in that on onehand, true integration of the structure and functions can be achieved, the driving structure can serve as a driver and can further serve as a bearing structure, structural complexity can be effectively reduced, the weight can be reduced, and comprehensive performance of an airplane can be improved; on the other hand, deformation precision can be improved through the multiple driving mechanisms arranged in a distributed mode, deformation control over the multiple target configurations can be further achieved, and real-time optimization of the front edge configuration is truly achieved.

Description

technical field [0001] The application belongs to the technical field of wing aerodynamic design, and in particular relates to a flexible leading edge structure and a design method thereof. Background technique [0002] The traditional wing can only guarantee the optimal aerodynamic efficiency in the cruising state. In order to meet the aerodynamic requirements in other working conditions, the traditional wing is usually based on the leading edge lift device of the rigid hinge to realize the change and adjustment of the aerodynamic shape. However, there are often gaps in the traditional leading edge flaps, which make the aerodynamic surface discontinuous, increase the friction between the sharp part of the structure and the air, and increase the noise of takeoff and approach landing, and the traditional flaps cannot realize the real-time aerodynamic shape of the full flight envelope. Precise deformation control cannot meet the purpose of real-time optimization of aerodynamic...

AI Technical Summary

Problems solved by technology

However, there are often gaps in the traditional leading edge flaps, which make the aerodynamic surface discontinuous, increase the friction between the sharp part of the structure and the air, and increase the noise of takeoff and approach landing, and the traditional flaps cannot realize the real-time aerodynamic shape of the full flight envelope. Precise deformation control cannot meet the purpose of real-time optimization of aerodynamic shape

[0003] In order to realize the continuous and precise deformation control of the leading edge of the deformable wing, a variety of continuously variable camber leading edge structures have been proposed at home and abroad, but they are basically based on rigid or semi-rigid structures, which often have complex structures, heavy weight and low reliability issues

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