Abstract: The present invention relates to an engine assembly for an aircraft comprising an attachment means, a turboprop on an attachment mast, this means including a plurality of front engine attachments (16) each having an engine vibration insulation system (20) including a housing (22), a stress transmitting member (24) extending along a first axis (26) parallel to an axis of rotation of the propeller and a hollow member (28) integrated in the housing and extending along a second axis (30) orthogonal to and intersecting the first axis. According to the invention, a support means for supporting the system (20) is formed by a plurality of clevises (32a, 32b) each having a middle plane parallel to its clevis heads, integrating one of the first and second axes and orthogonal to the other of said axes.

Abstract: The present invention relates to an engine assembly for an aircraft comprising an attachment means, a turboprop on an attachment mast, this means including a plurality of front engine attachments (16) each having an engine vibration insulation system (20) including a housing (22), a stress transmitting member (24) extending along a first axis (26) parallel to an axis of rotation of the propeller and a hollow member (28) integrated in the housing and extending along a second axis (30) orthogonal to and intersecting the first axis. According to the invention, a support means for supporting the system (20) is formed by a plurality of clevises (32a, 32b) each having a middle plane parallel to its clevis heads, integrating one of the first and second axes and orthogonal to the other of said axes.

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: 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.