Abstract: A two-flow jet engine comprising a high-pressure compressor and a drawing system configured to draw air from said jet engine and send it to an air system, and which comprises a pressurized air supply which draws pressurized air from the high-pressure compressor, a pipe which draws outside air, a turbine of which an inlet is connected to the outlet of the pressurized air supply, and a compressor of which an inlet is connected to the pipe, and an outlet is connected to the air system, and where the rotation of the turbine drives the rotation of the compressor. This particular arrangement makes possible an energy gain by virtue of the combined action of the turbine and of the compressor.

Abstract: An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end.

Abstract: A fire extinguisher device for aircraft has a hanger structure and a reservoir of extinguishing agent, the aforementioned reservoir being hung beneath the aforementioned hanger structure by metal fittings held by fasteners to the aforementioned hanger structure. The aforementioned extinguisher wherein the reservoir has means of suspension and the hanger structure has carriers complementary to the means of suspension, the aforementioned means of suspension and the aforementioned carriers being such that when the fasteners are withdrawn, the reservoir is in a position called the “intermediate position,” in which the metal fittings are free and the reservoir is suspended by interaction of the means of suspension and the carriers. The disclosed embodiments also relate to a method for fastening such an extinguishing device.

Abstract: The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs (46) for an aerodynamic fairing of an engine mounting device, including: production, for each rib (46), of a given rib preform (46a) by superplastic forming; and in respect of at least one of the ribs (46) of the group having a smaller size than that of the preform (46a), division of the latter into four preform parts (56a-56d) each incorporating one of the four corners of the quadrilateral formed by the preform, followed by the joining of the four parts to one another so as to obtain the rib.

Abstract: The present invention relates to a method of manufacture of a stiffening transverse internal rib (46) for an aerodynamic fairing of an engine mounting device, including: the production of a rib preform by superplastic forming having an outline of a broadly quadrilateral shape, and a central opening (52) traversing this preform; the division of the preform into two parallel straight-line segments (56, 60), which are diagonally opposed, causing the separation into two half-parts (46a?, 46a?) of the rib preform; and fishplating of the two rib preform half-parts (46a?, 46a?) by bolting.

Abstract: The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs (46) for an aerodynamic fairing of an engine mounting device, including: production, for each rib (46), of a given rib preform (46a) by superplastic forming; and in respect of at least one of the ribs (46) of the group having a smaller size than that of the preform (46a), division of the latter into four preform parts (56a-56d) each incorporating one of the four corners of the quadrilateral formed by the preform, followed by the joining of the four parts to one another so as to obtain the rib.

Abstract: The present invention relates to a method of manufacture of a stiffening transverse internal rib for an aerodynamic fairing of an engine mounting device, including: the production of a rib preform by superplastic forming having an outline of a broadly quadrilateral shape, and a central opening (52) traversing this preform; the division of the preform into two parallel straight-line segments (56, 60), which are diagonally opposed, causing the separation into two half-parts (46a?, 46a?) of the rib preform; and fishplating of the two rib preform half-parts (46a?, 46a?) by bolting.

Abstract: A fire extinguisher device for aircraft has a hanger structure (4) and a reservoir (3) of extinguishing agent, said reservoir being hung beneath said hanger structure by metal fittings (300, 301a, 301b) held by fasteners to said hanger structure. Said extinguisher is characterized in that the reservoir (3) has means of suspension (31) and the hanger structure (4) has carriers (41) complementary to the means of suspension (31), said means of suspension and said carriers being such that when the fasteners are withdrawn, the reservoir (3) is in a position called the “intermediate position,” in which the metal fittings (300, 301a, 301b) are free and the reservoir (3) is suspended by interaction of the means of suspension (31) and the carriers (41). The invention also relates to a method for fastening such an extinguishing device.

Abstract: The invention concerns a device for securing an insert in a structure having a first opening, the insert having a principal body (20) inserted in the first opening, the body (20) having a second opening having a principal axis, the device including a shaft (23) designed to pass through the second opening and at least one detachable or non-detachable head (24, 42).

Abstract: This invention relates to a mounting structure (1) for mounting an engine (2) under an aircraft wing (4), the structure comprising a rigid structure (8) and means (10) of fastening this rigid structure under the wing, the mounting means comprising a forward fastener (14), an intermediate fastener (15) and an aft fastener (16). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis (5) of the engine (2), placed in a vertical plane oriented along a longitudinal direction (X) of the aircraft. Furthermore, the intermediate fastener comprises a connecting rod capable of transferring forces applied in a direction (Y) transverse to the aircraft, and the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Abstract: This invention relates to a structure (1) for mounting an engine (2) under an aircraft wing (4), comprising a rigid structure (8) and means (10) of mounting this rigid structure under the wing, the mounting means (10) comprising a forward fastener (14) and an aft fastener (16). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis (5) of the engine, placed in a vertical plane oriented along a direction inclined with respect to a longitudinal direction (X) and a transverse direction (Y) of the aircraft, and located in a horizontal plane defined by these directions (X) and (Y). Furthermore, the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Abstract: The invention concerns a device for securing an insert in a structure having a first opening, the insert having a principal body (20) inserted in the first opening, the body (20) having a second opening having a principal axis, the device including a shaft (23) designed to pass through the second opening and at least one detachable or non-detachable head (24, 42).

Abstract: A structure for mounting a turboprop under an aircraft wing includes a rigid structure and a device for fastening the turboprop on the rigid structure. The rigid structure is composed of a box, and the device for fastening includes at least two lateral connecting rods resisting the engine torque generated by the turboprop, the connecting rods being arranged on each side of the box and each having a forward end connected to a gear box of the turboprop, and an aft end connected to the box.

Abstract: A mounting structure for mounting a turboprop under an aircraft wing includes a rigid structure provided with an aft underwing box, and at least one forward rigid section. Each forward rigid section has two transverse frames at a spacing from each other. At least one forward rigid section of the rigid structure also includes at least one forward upper box connecting a top part of the two transverse frames of the forward rigid section.

Abstract: The invention relates to a hanging device (1) connecting an engine (2) to a wing (4) of an aircraft, with the device being made up of a rigid structure (8) and hanging equipment (10) interposed between the rigid structure (8) and the wing (4), with the hanging equipment (10) being made up of a forward attachment (14) and a rear attachment (16) made up of at leas one triangular shackle placed in a vertical plane aligned in a transverse direction (Y) of the aircraft. According to the invention, the forward attachment (14) has, on one side and the other of a vertical plane passing through a longitudinal axis (5) of the engine (2), at least one triangular shackle aligned in the longitudinal direction (X) of the aircraft. Furthermore, the hanging equipment is made up exclusively of forward and rear attachments.

Abstract: This invention relates to a structure (1) for mounting an engine (2) under an aircraft wing (4), comprising a rigid structure (8) and means (10) of mounting this rigid structure under the wing, the mounting means (10) comprising a forward fastener (14) and an aft fastener (16). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis (5) of the engine, placed in a vertical plane oriented along a direction inclined with respect to a longitudinal direction (X) and a transverse direction (Y) of the aircraft, and located in a horizontal plane defined by these directions (X) and (Y). Furthermore, the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Abstract: This invention relates to a structure (1) for mounting a turboprop (2) under an aircraft wing (4), comprising a rigid structure and means (10) of fastening the turboprop on the rigid structure. According to the invention, the rigid structure is composed of a box (8), and the mounting means comprise at least two lateral connecting rods (26) resisting the engine torque generated by the turboprop, the connecting rods (26) being arranged on each side of the box and each having a forward end (26a) connected to a gear box (24) of the turboprop (2), and an aft end (26b) connected to said box.

Abstract: This invention relates to a mounting structure (1) for mounting an engine (2) under an aircraft wing (4), the structure comprising a rigid structure (8) and means (10) of fastening this rigid structure under the wing, the mounting means comprising a forward fastener (14), an intermediate fastener (15) and an aft fastener (16). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis (5) of the engine (2), placed in a vertical plane oriented along a longitudinal direction (X) of the aircraft. Furthermore, the intermediate fastener comprises a connecting rod capable of transferring forces applied in a direction (Y) transverse to the aircraft, and the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Abstract: The invention relates to a hanging device (1) connecting an engine (2) to a wing (4) of an aircraft, with the device being made up of a rigid structure (8) and hanging equipment (10) interposed between the rigid structure (8) and the wing (4), with the hanging equipment (10) being made up of a forward attachment (14) and a rear attachment (16) made up of at leas one triangular shackle placed in a vertical plane aligned in a transverse direction (Y) of the aircraft. According to the invention, the forward attachment (14) has, on one side and the other of a vertical plane passing through a longitudinal axis (5) of the engine (2), at least one triangular shackle aligned in the longitudinal direction (X) of the aircraft. Furthermore, the hanging equipment is made up exclusively of forward and rear attachments.

Abstract: This invention relates to a mounting structure (1) for mounting a turboprop (2) under an aircraft wing (4), the structure comprising a rigid structure (8) provided with an aft underwing box (10), and at least one forward rigid segment (12, 14), each forward rigid segment having two transverse frames (30, 32, 54) at a spacing from each other. According to the invention, at least one forward rigid segment (12, 14) of the rigid structure also comprises at least one forward upper box (34, 56) connecting a top part (30a, 32a, 54a) of the two transverse frames (30, 32, 54) of the forward rigid segment.