Skin for morphing wings

Abstract

The invention discloses a skin for morphing wings, belonging to the technical field of design of morphing aircrafts. The skin for the morphing wings is made from fibre reinforced composites, and the cross section of the skin is in an isosceles trapezoid ripple structure. The invention also carries out analysis aiming at the chordwise and spanwise equivalent elastic modulus and flexural modulus ofthe skin structure with isosceles trapezoid ripples, provides a corresponding mathematical model and can further optimize the skin structure according to the mathematical model. The invention meets the requirements of the skin of the morphing wings of the morphing aircrafts for large deformation aerodynamic load bearing, can realize the design optimization of the skin structure under different load operating conditions according to the mathematical analysis model of the equivalent elastic modulus and the flexural modulus in two different directions of the skin structure, also has structure health monitoring and self-adapting deformation capability and can realize optimal aerodynamic characteristics by controlling the shape and the vibration of the skin.

Description

technical field [0001] The invention relates to a skin of an aircraft, in particular to a skin for a modified wing, and belongs to the technical field of aircraft design. Background technique [0002] The variant aircraft is a new type of aircraft proposed in recent years, and the variant wing is an important research content in the variant aircraft. It is a new type of aircraft wing structure. Significant changes in geometric structure dimensions such as area and chord length make it possible to restructure the wing shape and surface structure when the flight environment changes in a large range (such as cruising, extremely high-speed flight, rapid dive, maneuvering at a high angle of attack, etc.) , to adapt to the monitored changes in flight conditions to obtain the best aerodynamic and aeroelastic characteristics. Since the 1980s, countries such as the United States, Britain, and Germany have successively carried out research on smart wings, adaptive wings, and variant ...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the contradiction between the variant wing skin requiring large deformation in the chord direction and the span direction requiring strong bearing capacity, and to provide a skin for the variant wing. The rigidity in the direction of the wing is very small and can achieve large deformation; while it has extremely high stiffness in the spanwise direction and can withstand large bending loads

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