C/C and C/SiC composite material and metal connecting method

Abstract

The invention is a method of binding compound materials of the C/SiC and C/C, which belongs to the technology field of binding heterogeneous materials. The processing procedures are as following: 1. The surface of the e compound materials of the C/SiC and C/Cis pretreated, which comprise the surface of the connecting are grinding, cleaning, vacuum biscuit firing, preparation of double-layer metal film and microvacum heat treatment and so on. 2. The transition layer of the connecting area surface gradient of the compound materials of the C/SiC is coated and sintered. 3. The compound materials with the gradient transition layer as the felted phase is brazed with the metal in vacuum. The invention is characterized in that the gradient transition layer is directly used as the materials that bind the compound materials with the metal; the gradient transition layer is double-layered or multilayered (sub-layered) structure; from the inner basal body to the outer part of the compound materials, the melting points of active brazing alloy adopted by each sub-layer gradually lower, the coefficient of heat expansion that adjust volume percentage composition gradually lower and the coefficient of heat expansion of the sub-layers gradually rise. The brazing ceramic metal connecting piece of the invention has good strength, air tightness and wide application field, which is suitable for various non-metallic fibers, such as ceramics of SiC, Si3N4, Al2O3, AlN and so on and applicable for connecting the ceramic matrix compound materials with particulate reinforced with the metal.

Description

technical field [0001] The invention relates to a connection method between C / C and C / SiC composite materials and metals, and belongs to the technical field of connection (welding) of heterogeneous materials. Background technique [0002] The space vehicle power system requires its thrust chambers (missile engine thrust chambers, satellite attitude, orbit control thrust chambers, long-range missile warhead terminal attitude modification engine thrust chambers, etc.) to have the characteristics of light weight, fast response, small size, and high reliability. This type of thrust chamber is composed of a nozzle (body) and a propellant injector (head) in a sealed connection. C fiber reinforced SiC (C / SiC), C fiber reinforced graphite (C / C) composite materials have a series of excellent properties such as: low density (general density 1.75-2.10g / cm 3 ), light weight, outstanding high temperature performance (high strength, high modulus, excellent fracture toughness and wear res...

AI Technical Summary

Problems solved by technology

[0003] The purpose of this invention is to provide a new method for connecting C / C, C / SiC composite materials and metals, to realize the reliable connection (welding) of C / SiC, C / C composite material nozzle pipes and metal injectors, and to effectively solve the problem of The mechanical connection method has problems such as poor sealing performance, complex structure, low reliability, and decreased specific impulse of the thrust chamber.