Fairing heat-proof structure and forming method thereof

Abstract

The invention provides a fairing heat-proof structure and a forming method thereof and relates to the technical field of aircraft fairing manufacturing. The fairing heat-proof structure comprises a lining, an adhesive interface layer and a resin matrix composite ablation heat insulation layer. The forming method of the fairing heat protection structure comprises steps that A, a reinforcing material infiltrates matrix resin and then is dried and rolled to obtain continuous prepreg cloth; B, continuously cutting the prepreg cloth to obtain prepreg cloth belts; C, bonding and continuously rollingthe prepreg cloth belts to obtain a continuously-wound cloth belt; D, continuously winding the cloth belt in a variable-taper oblique stacking manner to obtain a winding skin; E, performing skin winding and curing; F, winding the skin and processing to obtain a resin-based composite material ablation heat insulation layer; G, connecting the lining and the resin-based composite material ablation heat insulation layer through an adhesive interface layer; and H, processing the heat-proof layer. The obliquely-stacked structure realizes arrangement of the cloth belt along the airflow, has better erosion resistance and ablation resistance, and can solve a problem of interface debonding of a heat-proof layer and an aluminum lining of a large-caliber (the diameter is more than 300mm) fairing.

Description

Technical field [0001] The invention relates to the technical field of aircraft fairing manufacturing, in particular to a heat-proof structure of the fairing and a forming method thereof. Background technique [0002] The air-breathing hypersonic vehicle has become a hotspot of research and competition in major aerospace countries due to its advantages such as improved propulsion efficiency, enhanced load capacity, and expanded launch window. The power source of the hypersonic aircraft is a special-shaped naturally aspirated scramjet. The engine needs to start working at a flight speed above 5Ma to achieve supersonic combustion. Before the engine reaches the required flight speed of the working window, the engine flow field needs to be corrected to reduce flight resistance and improve fuel utilization. [0003] The fairing is generally composed of a metal lining and a heat-proof structure. In terms of weight reduction, the aluminum alloy lining has obvious advantages, and the matc...

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Problems solved by technology

[0005] However, there is a difference in thermal expansion coefficient between high-temperature epoxy resin, phenolic-based composite materials, etc., and the aluminum alloy lining, and problems such as interface debonding often occur in fairings with this structure

However, the common molding method of phenolic-based composite materials is overlapping winding of cloth tapes. This winding method cannot realize the arrangement of cloth tapes along the air flow, and the winding layers are exposed to the outside, and it is easy to cause interlayer failure and peeling during the external heat protection process. question

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