Abstract: The invention relates to a material with high fracture toughness based on a vinyl ester resin and/or on an epoxide resin and to its process of manufacture. This material comprises at least one polymerized resin chosen from vinyl ester resins and epoxide resins which can be polymerized at a temperature of less than 70° C. and their blends, and a thermoplastic adjuvant present in this resin in the form of particles, and exhibits a fracture toughness (KIc) of greater than or equal to 1.2 MPa·m1/2 as determined according to Standard ISO 13586:2000. It also relates to a composite material comprising a matrix composed of said material and a reinforcement. Applications: automobile, railway, ship-building, aeronautical, aerospatial and other industries.

Abstract: A material having a fracture toughness (K1c) of at least 1.2 Mpam.m1/2 as determined according to Standard ISO 13586:2000 comprises a vinyl ester and/or epoxide resin polymerizable at a temperature of less than 70° C. combined with thermoplastic particles.

Abstract: According to invention, said elements (1.1 to 1.n) are secured to the same side (3) of a flexible inflatable mattress (4) and, when said elements are in the folded state, said mattress (4) is in the deflated state and is folded so that said elements are situated in pairs on either side of a fold (5.1 to 5.n?1) of said mattress.

Abstract: The invention concerns a combustion chamber whereof the inner wall (17)is made at least partly of a thermostructural composite material, which is porous to the fuel passing through the double wall (14); and the porosity of said inner wall (17) is adjusted so that the proportion of said fuel passing through said inner skin ranges between 5% and 15% of the total amount of fuel input in said ramjet engine.

Abstract: This invention relates to a process for manufacturing a refractory material, a protective coating, and uses of this process and this coating. The process comprises the following steps: a) deposit on the surface of a substrate or in a mould a first dispersion containing at least one metallic compound chosen from among borides, carbides and borocarbides containing at least one transition metal, in powder form, and a resin with a coke mass content equal to at least 30% after carbonization; b) dry the resulting deposit; c) cross-link the resin; d) carbonize the resin under an inert atmosphere; e) cover the deposit with a second dispersion containing Si in powder form and a binder; f) heat the deposit to a temperature greater than or equal to the melting temperature of Si, under an inert atmosphere. Applications: manufacture of propulsion parts and fuselage and wing elements for aerospace and aeronautical applications; manufacture of heat exchangers for thermal power stations; metallurgy; chemical industry; etc.

Abstract: The invention concerns a rocket engine wherein the combustion chamber includes at least one first monolithic component made of a thermostructural composite material comprising a porous wall through which the fuel is introduced in the core of the combustion chamber. A small part of the fuel is directed towards the neck for it to be cooled.

Abstract: The invention relates to a material with high fracture toughness based on a vinyl ester resin and/or on an epoxide resin and to its process of manufacture. This material comprises at least one polymerized resin chosen from vinyl ester resins and epoxide resins which can be polymerized at a temperature of less than 70° C. and their blends, and a thermoplastic adjuvant present in this resin in the form of particles, and exhibits a fracture toughness (KIc) of greater than or equal to 1.2 MPa.m½ as determined according to Standard ISO 13586:2000. It also relates to a composite material comprising a matrix composed of said material and a reinforcement. Applications: automobile, railway, ship-building, aeronautical, aerospatial and other industries.

Abstract: Foldable and deployable assembly of elements mounted on board a spacecraft.