Preparation method of heat-proof and structure-integrated composite fairing

Abstract

The invention provides a preparation method of a heat-proof and structure-integrated composite fairing. The forming mold is used for preparing the force bearing structure firstly, after the force bearing structure is cured, the heat-proof structure is laid with the force bearing structure as a male mold, the heat-proof structure and the force bearing structure are bonded together, secondary curing is conducted under the high-temperature and high-pressure conditions, and the high-strength characteristic of the bonding face between the heat-proof structure and the force bearing structure is guaranteed; according to the method, the problems of gaps, layering defects and the like of the bonding surface are avoided, meanwhile, it is guaranteed that the heat-proof structure and the force-bearing structure are completely matched in appearance, the method has the advantages of being large in bonding area, free of interface layering and excellent in bonding effect, and the time cost, the mold cost and potential quality hazards of the composite fairing with the heat-proof structure are reduced; the invention also solves the quality problems that when the heat-proof functional component is large in size or irregular in shape, the sleeving process is difficult to implement, and the gluing surface is easy to delaminate and debond, and the like.

Description

technical field [0001] The invention relates to the technical field of composite material fairing molding technology, in particular to a preparation method of a composite material fairing integrating heat protection and structure. Background technique [0002] Fiber-reinforced composite materials have been more and more widely used in the aviation field. Their advantages such as high strength, light weight, high temperature resistance, low temperature resistance, and corrosion resistance make their application scenarios in the aerospace field more diverse. Composite fairings are mostly used for The front end of products such as missiles and rockets is used to protect their internal structural parts and electronic instruments from harmful environments such as aerodynamic force, aerodynamic heating, and acoustic vibration. Due to the harsh conditions of use, the front end of the fairing mostly uses an ablation-resistant end structure to protect the load-bearing structure. Howe...

AI Technical Summary

Problems solved by technology

When the size of the heat-resistant functional components is large or the shape is irregular, the traditional method is extremely difficult to implement and is prone to quality problems such as delamination and debonding of the adhesive surface. The assembly of structural parts and heat-resistant functional parts has a high dimensional accuracy Generally, the heat-resistant parts need to be set outside the structural parts and leave a gap within the specified range on the bonding surface. Fill the gap with resin and then cure to obtain an integrated heat-proof-structural part; but when the product shape is irregular, it is not It is conducive to the implementation of the above process. Firstly, it is difficult to ensure the dimensional accuracy of the two components when they are formed, and it is easy to get stuck when they are assembled. Secondly, it is difficult to ensure the effect of glue injection, which may easily lead to local lack of glue or insufficient pressure, resulting in detachment. sticky phenomenon

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