Variable-camber trailing edge sectional type wing rib and flexible skin supporting and connecting structure

Abstract

The invention discloses a variable-camber trailing edge sectional type wing rib and flexible skin supporting and connecting structure, and belongs to the field of structural design of morphing aircrafts. A variable-camber trailing edge structure of a flexible wing consists of a corrugated structure flexible skin, sectional type wing ribs, a supporting plate, distributed drivers and a rear end conebody. The distributed drivers are arranged below the flexible skin and supported on the sectional type wing ribs through driver supports, mutual deflection between rib sections is caused by stretching and retracting of the drivers, and the flexible skin stretches and retracts under the action of driving force so as to achieve trailing edge camber changing. When an upper wing surface extends, a lower wing surface is shortened, the rib sections deflects downwards, and a trailing edge is bent downwards. According to the device, the flexible skin can be uniformly supported to transmit loads, anduniform and harmonious deformation of the flexible skin can be achieved.

Description

technical field [0001] The invention belongs to the field of variant aircraft structure design, and specifically relates to a structure applied to the trailing edge of a variable-camber wing, supporting a corrugated structure flexible skin and connected with a segmented wing rib. Background technique [0002] The morphing aircraft can change the shape of the aircraft structure in real time during flight, so as to have the best aerodynamic performance when performing different flight actions under different flight states. Changes in the shape of the wing structure include variable area (mostly variable span length, but also variable chord length), variable sweep angle, and variable camber. Changing the camber of the wing can increase the force generation coefficient. The camber of the conventional wing is changed by deflecting the leading and trailing edge rudder surfaces, but the airflow separation when the rudder surfaces are deflected also increases the resistance. In ord...

AI Technical Summary

Problems solved by technology

At present, there are many schemes for the research of variable camber structures at the trailing edge, including flexible skin schemes based on negative Poisson’s ratio materials, flexible skin schemes based on deformable honeycombs, active deformation rib schemes, etc. There are deficiencies in the connection of deformed ribs. For example, when the web is used as the supporting connection structure, it has a certain load-bearing capacity, but it cannot meet the requirements of smooth and continuously variable camber of the trailing edge.

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