Abstract: The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant so mixture into the detonation chamber (3) at at least one segment of the injection base (10).

Abstract: The invention relates to a ramjet including a detonation chamber and an aircraft comprising such a ramjet. According to the invention, the ramjet (S1) comprises an annular detonation chamber (2) having a continuous detonation wave and fuel injection means (6) for continuously injecting fuel (F2) directly into the chamber (2) just downstream of an air injection base (3). The fuel (F2) and the air (F1) are injected separately into the detonation chamber (2) in a permanent manner throughout the operation of the ramjet (S1).

Abstract: The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant so mixture into the detonation chamber (3) at at least one segment of the injection base (10).

Abstract: The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant mixture into the detonation chamber (3) at at least one segment of the injection base (10).

Abstract: The chamber (4) of the turbine engine (1) comprises a continuous detonation wave engine (6) provided with an annular detonation chamber (7) and associated means (8, 9) that can be used to generate a continuous production of hot gases from a detonation mixture of fuel and air. The continuous detonation wave engine (6) is arranged such as to form, from a flow of incoming air (E), a first flow (F1) which enters the detonation chamber (7) and which is used by the engine (6) and a second flow (F2) which bypasses the chamber. The turbine engine (1) also includes auxiliary means (10) for mixing the hot gases (F3) leaving the detonation chamber (7) with the second flow of air (F2) before directing same towards the turbine (5). A plurality of detonation chambers (7) are arranged concentrically to one another relative to the axis of the turbine engine.

Abstract: According to the invention, the said engine (I), which comprises at least one flame tube (2) with a mobile transverse end wall (18), comprises an external envelope (3) around the said flame tube (2), which defines a peripheral annular space (4) in which fixed flow guides (11, 12, 13, 14) are positioned, these flow guides forming flow channels (10) for the air, and at least one mobile plug (25), connected to the said mobile end wall (18), to close off and open one of the flow channels (10).

Abstract: The invention relates to a turbine engine including a detonation chamber and an aircraft provided with such a turbine engine. The chamber (4) of the turbine engine (1) comprises a continuous detonation wave engine (6) provided with an annular detonation chamber (7) and associated means (8, 9) that can be used to generate a continuous production of hot gases from a detonation mixture of fuel and air. The continuous detonation wave engine (6) is arranged such as to form, from a flow of incoming air (E), a first flow (F1) which enters the detonation chamber (7) and which is used by the engine (6) and a second flow (F2) which bypasses the chamber. The turbine engine (1) also includes auxiliary means (10) for mixing the hot gases (F3) leaving the detonation chamber (7) with the second flow of air (F2) before directing same towards the turbine (5). A plurality of detonation chambers (7) are arranged concentrically to one another relative to the axis of the turbine engine.

Abstract: An engine including a means for supplying fuel to the combustion chamber of the fire tube, that includes a variable-volume transfer chamber for receiving fuel, a fuel transfer means from the tank of the engine towards the transfer chamber, and injection means for injecting fuel into the combustion chamber from the transfer chamber. The engine further includes an elastic return at least partially defined by the fuel contained in the transfer chamber.

Abstract: The invention relates to a ramjet including a detonation chamber and an aircraft comprising such a ramjet. According to the invention, the ramjet (S1) comprises an annular detonation chamber (2) having a continuous detonation wave and fuel injection means (6) for continuously injecting fuel (F2) directly into the chamber (2) just downstream of an air injection base (3). The fuel (F2) and the air (F1) are injected separately into the detonation chamber (2) in a permanent manner throughout the operation of the ramjet (S1).

Abstract: The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant mixture into the detonation chamber (3) at at least one segment of the injection base (10).

Abstract: The invention relates to a pulse detonation engine operating with an air-fuel mixture. According to the invention, the engine (1) includes at least two predetonation tubes (4, 5) which operate under conditions close to thermal cutoff conditions and the shock waves from which are focused in the combustion chamber (19).

Abstract: According to the invention, the engine (I) includes a means for supplying fuel to the combustion chamber (7) of the fire tube (2), that comprises a variable-volume transfer chamber (9) for receiving fuel, a fuel transfer means (10) from the tank (4) of the engine (I) towards the transfer chamber (9), and injection means (11) for injecting fuel into the combustion chamber (7) from the transfer chamber (9). The engine further includes an elastic return means at least partially defined by the fuel contained in the transfer chamber (9).

Abstract: According to the invention, the said engine (I), which comprises at least one flame tube (2) with a mobile transverse end wall (18), comprises an external envelope (3) around the said flame tube (2), which defines a peripheral annular space (4) in which fixed flow guides (11, 12, 13, 14) are positioned, these flow guides forming flow channels (10) for the air, and at least one mobile plug (25), connected to the said mobile end wall (18), to close off and open one of the flow channels (10).

Abstract: The invention relates to a pulse detonation engine operating with an air-fuel mixture. According to the invention, the engine (1) includes at least two predetonation tubes (4, 5) which operate under conditions close to thermal cutoff conditions and the shock waves from which are focused in the combustion chamber (19).

Abstract: A method of producing a double-walled thermo-structural composite monolith may include assembling, by stitching, a sandwich having a core and outer fibrous armors. The stitched sandwich structure is impregnated with a viscous resin. After the resin hardens, the core is removed from the sandwich structure.

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: 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: The invention concerns a method characterized in that it consists in assembling by stitching a sandwich consisting of a core and outer fibrous armors and impregnating the stitching thread during the impregnation process of said fibrous armours, and thereafter eliminating said core, said stitching fiber forming spacers (23) between the skins (21, 22).

Abstract: According to the invention, the wall (5) is mounted movably as one so as to be able to slide longitudinally in translation, bringing the joint line (14) closer to the fuel injector (9) so as progressively to modify the geometries of the oxidant inlet (16) and of the combustion chamber (15), said geometries passing progressively from a first state (I) in which, for a Mach number lying between 1.5 and 3, said oxidant inlet (16) constricts said oxidant flow only slightly and the combustion chamber (15) is long and divergent, to a second state (III) in which, for a Mach number lying between 8 and 12, said oxidant inlet (16) strongly constricts said oxidant flow and said combustion chamber (15) is shorter and exhibits a constant cross section.

Abstract: According to the invention, the wall (5) is mounted movably as one so as to be able to slide longitudinally in translation, bringing the joint line (14) closer to the fuel injector (9) so as progressively to modify the geometries of the oxidant inlet (16) and of the combustion chamber (15), said geometries passing progressively from a first state (I) in which, for a Mach number lying between 1.5 and 3, said oxidant inlet (16) constricts said oxidant flow only slightly and the combustion chamber (15) is long and divergent, to a second state (III) in which, for a Mach number lying between 8 and 12, said oxidant inlet (16) strongly constricts said oxidant flow and said combustion chamber (15) is shorter and exhibits a constant cross section.