A kind of fairing heat-proof structure and its forming method

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 heat-proof structure of the fairing includes an inner lining, an adhesive interface layer, and a resin-based composite material ablation and heat-insulation layer. The cloth is cut to obtain a prepreg cloth tape; C. The prepreg cloth tape is bonded and continuously wound to obtain a continuous wrapping tape; D. The continuous wrapping tape is tapered and obliquely wound to obtain a wrapping skin; E. The wrapping skin is cured ; F. The resin-based composite material ablative thermal insulation layer is obtained by winding the skin; G. The inner lining and the resin-based composite material ablative thermal insulation layer are connected through the adhesive interface layer; H. The thermal insulation layer is processed. The oblique stack structure realizes the arrangement of the tapes along the airflow, and has better anti-scour and ablation performance, which can solve the problem of debonding between the heat-resistant layer of the large-diameter (diameter>300mm) fairing and the aluminum lining interface.

Description

technical field [0001] The invention relates to the technical field of aircraft fairing manufacturing, in particular to a fairing heat-proof structure and a forming method thereof. Background technique [0002] Air-breathing hypersonic vehicle has become a research and competition hotspot among major aerospace powers because of its advantages of improving propulsion efficiency, enhancing load capacity, and expanding launch window. The power source of the hypersonic vehicle is a special-shaped naturally aspirated scramjet, and the engine needs to start working at a flight speed of more than 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 the flight resistance and improve the fuel utilization rate. [0003] The fairing is generally composed of a metal lining and a heat-proof structure. The aluminum alloy lining has obvious advantages in terms of weight reduct...

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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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