Abstract: A device and method for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.

Abstract: A method of automatically triggering an emergency buoyancy system (10) for a hybrid helicopter (20) having a fuselage (21), two half-wings (23, 23?), and two propulsive propellers (24, 24?). During the method, said emergency buoyancy system (10) is primed, and then if a risk of said hybrid helicopter (20) ditching is detected, two retractable wing undercarriages (28, 28?) are deployed, each wing undercarriage (28, 28?) being fastened under a respective half-wing (23, 23?) and being provided with at least one immersion sensor (16). Finally, if the beginning of said hybrid helicopter (20) ditching is detected, at least one main inflatable bag (11, 11?) 7B suitable for being arranged under such fuselage (21) and at least one secondary inflatable bag (12, 12?) suitable for being arranged under each half-wing (23, 23?) are inflated so as to ensure that said hybrid helicopter (20) floats in stable manner.

Abstract: An undercarriage (6) provided with an undercarriage leg (10) and a shock absorber (20), said undercarriage (6) including an actuator-shock absorber (30), said undercarriage leg (10) comprising both a first element (11) carrying contact means (13) and a second element (12), which elements are hinged to each other. The undercarriage (6) includes pivot means (40) enabling said undercarriage leg (10) to pivot firstly in a first direction (S1) in order to retract said undercarriage leg (10) into said housing (4) under drive from said actuator-shock absorber (30), and secondly, during an emergency landing, in a second direction (S2) opposite to the first direction (S1) in order to move said undercarriage leg (10) away from said housing (4) while stressing said actuator-shock absorber (30).

Abstract: A method of automatically triggering an emergency buoyancy system (10) for a hybrid helicopter (20) having a fuselage (21), two half-wings (23, 23?), and two propulsive propellers (24, 24?). During the method, said emergency buoyancy system (10) is primed, and then if a risk of said hybrid helicopter (20) ditching is detected, two retractable wing undercarriages (28, 28?) are deployed, each wing undercarriage (28, 28?) being fastened under a respective half-wing (23, 23?) and being provided with at least one immersion sensor (16). Finally, if the beginning of said hybrid helicopter (20) ditching is detected, at least one main inflatable bag (11, 11?) 7B suitable for being arranged under such fuselage (21) and at least one secondary inflatable bag (12, 12?) suitable for being arranged under each half-wing (23, 23?) are inflated so as to ensure that said hybrid helicopter (20) floats in stable manner.

Abstract: An aircraft (1) having a fuselage (2), the aircraft (1) comprising a rotary wing (9) above the fuselage (2) and an extra fixed wing (10), the rotary wing (9) being above both the fuselage (2) and the fixed wing (10), said fixed wing (10) comprising at least one closed wing (20) comprising a first half-wing (21) and a second half-wing (22). Each half-wing (21, 22) is provided with a top lift portion (30) and a bottom lift portion (40), said bottom lift portion (40) of a half-wing being arranged in the wake (S) of the top lift portion (30) of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing (9) and impacting against the top face (30?) of the top lift portion (30) when said aircraft (1) has a forward speed less than a predetermined threshold.

Abstract: Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces. Set of fuselage sections assembled by means of a device of the type described above. Method of assembling two fuselage sections by means of a device of the type described above.

Abstract: An aircraft (1) having a fuselage (2), the aircraft (1) comprising a rotary wing (9) above the fuselage (2) and an extra fixed wing (10), the rotary wing (9) being above both the fuselage (2) and the fixed wing (10), said fixed wing (10) comprising at least one closed wing (20) comprising a first half-wing (21) and a second half-wing (22). Each half-wing (21, 22) is provided with a top lift portion (30) and a bottom lift portion (40), said bottom lift portion (40) of a half-wing being arranged in the wake (S) of the top lift portion (30) of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing (9) and impacting against the top face (30?) of the top lift portion (30) when said aircraft (1) has a forward speed less than a predetermined threshold.

Abstract: An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece.

Abstract: A method for manufacturing an aircraft fuselage includes an internal framework surrounded by an external skin made of composite material, in which the internal framework at least partially constitutes a mould for manufacture and/or the support for the mould for the external skin made of composite material. The disclosed embodiments also relate to an aircraft fuselage produced using this method.

Abstract: An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.

Abstract: An undercarriage (6) provided with an undercarriage leg (10) and a shock absorber (20), said undercarriage (6) including an actuator-shock absorber (30), said undercarriage leg (10) comprising both a first element (11) carrying contact means (13) and a second element (12), which elements are hinged to each other. The undercarriage (6) includes pivot means (40) enabling said undercarriage leg (10) to pivot firstly in a first direction (S1) in order to retract said undercarriage leg (10) into said housing (4) under drive from said actuator-shock absorber (30), and secondly, during an emergency landing, in a second direction (S2) opposite to the first direction (S1) in order to move said undercarriage leg (10) away from said housing (4) while stressing said actuator-shock absorber (30).

Abstract: A composite panel having a first skin forming the outer wall of the panel, known as the lower face (1), and a second skin forming part of the inner wall of the panel. The second skin is formed hollow such as to produce an inner reinforcing frame (2) in the form of a half-box structure (3) which, together with the first skin, forms box parts. The aforementioned frame is equipped with a rim (4a, 4b) for fixing to the first skin, a face known as the upper face (5) and connecting side walls (6, 6a, 6b, 6c, 6d, 6e, 7) between the rim (4a, 4b) and the upper face (5) the first and second skins forming a monolithic self-stiffened panel. The half-box frame (2) has perforated sections (8) which are defined by hollow beam sections forming the half-box frame (2).

Abstract: An aircraft includes a structure with structural elements (16) that are assembled to form a three-dimensional framework to which an aerodynamic envelope (14) is attached. At least some structural elements (16) are at least partly metallic and—at the connection with the aerodynamic envelope (14)—including an interface that is made of material that has a conductivity that is below a threshold on the order of 10,000 S/m so as to form at least one electrical path that ensures the functions of electric return and metallization of the electrical systems, whereby connections that ensure the electrical conduction are provided between the structural elements (16).

Abstract: A windscreen frame, and a method of production for a windscreen frame, designed to hold a windscreen in an opening in a wall, the frame including at least one upper horizontal frame section element, at least one lower horizontal frame section element and at least one vertical mounting, characterized in that it is a single unit in composite material.

Abstract: A structural frame for a fuselage including a lower arched structure (1), a cross-piece (2), supporting a floor element (3) and a connecting lattice (4) between the lower arch (1) and the cross-piece (2), the connecting lattice (4) more particularly may comprise bars (4a, 4b) the ends of which are spliced to the cross-piece (2) and the lower arch (1).

Abstract: An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece.

Abstract: An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.

Abstract: A composite panel having a first skin forming the outer wall of the panel, known as the lower face (1), and a second skin forming part of the inner wall of the panel. The second skin is formed hollow such as to produce an inner reinforcing frame (2) in the form of a half-box structure (3) which, together with the first skin, forms box parts. The aforementioned frame is equipped with a rim (4a, 4b) for fixing to the first skin, a face known as the upper face (5) and connecting side walls (6, 6a, 6b, 6c, 6d, 6e, 7) between the rim (4a, 4b) and the upper face (5) the first and second skins forming a monolithic self-stiffened panel. The half-box frame (2) has perforated sections (8) which are defined by hollow beam sections forming the half-box frame (2).

Abstract: A method for manufacturing an aircraft fuselage includes an internal framework surrounded by an external skin made of composite material, in which the internal framework at least partially constitutes a mould for manufacture and/or the support for the mould for the external skin made of composite material. The disclosed embodiments also relate to an aircraft fuselage produced using this method.

Abstract: An aircraft includes a structure with structural elements (16) that are assembled to form a three-dimensional framework to which an aerodynamic envelope (14) is attached. At least some structural elements (16) are at least partly metallic and—at the connection with the aerodynamic envelope (14)—including an interface that is made of material that has a conductivity that is below a threshold on the order of 10,000 S/m so as to form at least one electrical path that ensures the functions of electric return and metallization of the electrical systems, whereby connections that ensure the electrical conduction are provided between the structural elements (16).