Bearing and thermal protection integrated wing leading edge structure based on micro-truss

Abstract

The invention discloses a bearing and thermal protection integrated wing leading edge structure based on a micro-truss and belongs to the field of overall design of aircrafts and design of multifunctional structural materials. The bearing and thermal protection integrated wing leading edge structure is composed by arranging periodic structure units in a matrix mode; the periodic structure units are composed of upper face plates, lower face plates, flow channels and cores; the upper face plates and the lower face plates are each of a curved surface structure and correspond to the outer side face and the inner side face of a wing leading edge correspondingly; two flow channel wall plates extend from the left and right ends of each lower face plate in the core direction and then are connected, and the flow channel wall plates and the lower face plates together form the flow channels in an approximate triangular prism shape; and the two ends of the cores are fixedly connected with the upper face plates and the tops of the flow channels correspondingly. A micro-truss structure with the curvature is provided, the flow channels are introduced in the internal space of the micro-truss, under the situation that bearing is not affected, the effect of insulating the outside high temperature is achieved through cooling of internal fluids, a temperature control part is omitted, and thus theweight is reduced effectively.

Description

technical field [0001] The invention belongs to the field of overall design of aviation aircraft and multifunctional structural material design, and relates to a load-bearing / thermal protection integrated wing leading edge structure based on micro-truss. Background technique [0002] In order to meet the complex and harsh flight environment of hypersonic vehicles, it is usually required to reduce the structural weight as much as possible, and overcome the high temperature caused by aerodynamic heating and the vibration and noise problems caused by engine and air friction, so as to ensure a good working environment for instruments. Therefore, structural materials with light weight, heat insulation, vibration and noise reduction are particularly critical for the development of new aircraft (especially new aircraft and aerospace aircraft that are reused). The traditional aircraft structure-functional system separation design idea not only increases the weight of the aircraft, b...

AI Technical Summary

Problems solved by technology

The core material of the traditional sandwich structure is mostly metal honeycomb and foam sandwich, which has insufficient load-bearing performance, and the slotted thermal protection flow channel will greatly weaken the bonding performance between the panel and the core material

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