All-composite material engine nozzle formed through one-time curing

Abstract

The invention relates to a one-time curing molding all-composite material engine jet pipe, which comprises a throat liner, a convergent section, a heat insulation layer, an inner ablation layer and a composite material shell, the throat liner is used as an initial surface layer, and the convergent section, the ablation layer, the heat insulation layer and the composite material shell are sequentially rotated from inside to outside to form the jet pipe; after all winding work is completed, one-time hot-pressing curing forming is integrally carried out; the convergence section is formed by integrally winding carbon fiber cloth tape prepreg; the ablation layer is formed by winding fibers or cloth tapes on the throat liner and the mold; the thermal insulation layer is formed by obliquely winding fibers or cloth tape prepreg on the outer side of the ablation layer; and the composite material shell is formed by laying or winding fibers or cloth tapes on the outer side of the heat insulation layer. Through the co-curing technology of the transition structure resin, curing of different structures and functional layers of the composite material spray pipe is completed at a time, chemical structural mutation does not exist on an interface, therefore, the interface strength is improved, the debonding risk does not exist, and meanwhile the production period of the all-composite material spray pipe is shortened.

Description

technical field [0001] The patent of the present invention relates to the technical field of solid rocket motors, in particular to an all-composite engine nozzle formed by one-time curing. Background technique [0002] The nozzle of the engine is the worst part of the working environment of the solid rocket motor. According to incomplete statistics, more than 80% of the faults of the solid rocket motor occur in the nozzle. During the working process, the engine nozzle needs to withstand the high temperature above 3000 ℃, the pressure of hundreds of atmospheres, and the high temperature, high pressure and high speed gas of several Machs. Therefore, the engine nozzle is not only a structural component (need to withstand extremely High pressure) is also a functional component (need to resist high temperature, high pressure, high speed gas erosion and ablation). Based on the above reasons, the solid rocket motor nozzle is extremely complex, which is composed of functional layer...

AI Technical Summary

Problems solved by technology

[0007] The present invention aims at the current problem of multi-step curing and multi-step processing of composite material nozzles in integrated molding, adopts the co-curing technology of transitional structure resins, and completes the curing of different structures and functional layers of composite material nozzles at one time, avoiding the need for full-composite material spraying. Thermal expansion stress and unreliable curing interface caused by multiple curing of the tube, while reducing the production cycle of the full-composite nozzle, greatly improving the production capacity and working reliability of the full-composite nozzle

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