Abstract: A satellite designed to be spin-stabilized in geostationary orbit which has, coaxial with a spin rotation axis, a satellite body surrounded with a cylindrical solar generator, an apogee maneuver system disposed along the axis and two axially disposed equipments. The apogee maneuver system has opposite one of the equipments at least two thrusters oriented parallel to the axis but offset relative thereto by the same distance. Equi-angularly spaced around the other of the two equipments, the thrusters are connected to a common liquid propellant feed system.

Abstract: A provisional linking and pyrotechnic separation device is placed between two assemblies made from nonmetallic materials such as composite materials. Prior to separation, parts belonging to each of the two assemblies are fixed to one another, either by direct bonding of the parts to one another, or by bonding a linking part to the parts. The device includes a pyrotechnic expansion tube acting directly on one of the parts to be separated. A precise, clean and well localized separation of the assemblies consequently takes place during the use or operation of the pyrotechnic expansion tube.

Abstract: System for controlling an aerodynamic surface (1) (flap, aileron, control surface, etc.) of an aircraft. According to the invention, this system comprises: an electric machine (8) which can operate either as a motor or as a generator, the output of which is connected mechanically to said aerodynamic surface (1); and a logic device (17) receiving information about the operating status of the electrical power supply (11) of the machine (8) and of the hydraulic servocontrol (2, 5) and controlling the actuation of said surface (1) either by said machine (8) or by said servocontrol (2, 5).

Abstract: The present invention relates to an air inlet cowl (9) for a jet engine, the leading edge (16) of which is hollow and supplied with hot air for deicing by a pipe (10) and an injector (12). According to the invention, the pipe (10) and the connector (12A) to the injector (12) are enclosed in an internal casing (27) which isolates them from heat-sensitive structures (26). The volume (28) inside the internal casing (27) communicates, on the one hand, with the outside through an orifice (34) and, on the other hand, through an orifice (35) with the peripheral annular space (22) which surrounds the engine fan and which is equipped with a vent door (23).

Abstract: A single actuator (35) is controlled so as to successively open two covers (4 and 5) on an aircraft engine nacelle which are adjacent, successively forming two hinges (40 and 47).

Abstract: An antenna reflector for a spacecraft, produced in an elastically deformable way and capable of changing from a folded position to a deployed position at least partly under the action of its own elasticity. The reflector includes at least one fold line, the general direction of which is at least approximately parallel to the axis of the casing and about which said reflector is folded in its folded state.

Abstract: An aircraft fore-structure for wide- and very-wide body freight aircraft that is characterized by the presence of a unpressurized landing gear compartment in the lower fore end section. The landing gear compartment is formed by a ceiling at the top, that is preferably domed, and by a partition towards the rear. A door that is provided in the partition provides access through the landing gear compartment to the pressurized compartment located behind said partition. An opening in the fore of the landing gear compartment also provides access to the radar chamber without requiring the radome to be dismantled. The original layout of the landing gear compartment enables fore landing gear to be installed that is larger than that in existing aircraft.

Abstract: A device (14) for attaching or hooking an engine to an aircraft strut (10) comprises a circular arc-shaped fitting (16), formed from two elementary, coupled portions, which are also circular arc-shaped. These two elementary portions can be separate parts joined by bolts (24). The fitting (16) is fixed to the strut (10) by tension screws (30) and is solely connected to the engine by two connections or links (18). Each of these connections comprises a damping or shock absorber block (36) fixed to a base (40) connected to the engine and connected to one end of the fitting by a spindle (42). A holding part (44), fixed between the shock absorber block (36) and the base (40), is connected to the fitting by a joint (50) with clearance.

Abstract: The present invention relates to on-site repairs of a composite structure (10) such as an aircraft structure in which a concave recess (14) is machined in the damaged zone, a non-polymerized composite part (16) is set into said recess and part (16) is polymerized under pressure using tooling (18) comprising a stack of plates (32) that increase the pressure applied to the composite part. The present invention thus obtains invisible repairs with mechanical characteristics that are similar to those of the initial structure.

Abstract: Method for producing a connecting rod, particularly a monoblock composite connecting rod, and the resulting connecting rod is provided by placing preimpregnated fibers on an extractable mandrel, with the following successive stages. Embodying on a rigid central shaft a meltable mandrel with a shape corresponding to that of the connecting rod; winding and/or laying down the preimpregnated fibers according to a predetermined number of layers and an inclination of the fibers with respect to the longitudinal axis of the mandrel; polymerization with a homogeneous compacting pressure being applied to the entire outer surface of the unit; and then final operations for removing the mandrel and machining to required dimensions of the connecting rod.

Abstract: A thermal protection device (9) adapted to extend along a surface to be protected from a thermally and mechanically severe external environment, having an inside face (9A) adapted to face the surface to be protected and an outside face (9B) adapted to be exposed to the external environment, includes a composite layer (6) containing a refractory armature (2) buried in a thermally insulative material matrix, the device further including a ceramic, metal or metalloid external layer (7) of which the outside face is part and which is attached to the composite layer.

Abstract: A connector composed of two hinged subassemblies (26, 28) that enable a removable rear connector to be fitted onto a plug (10) whether or not fitted with its wiring. Subassembly (26) comprises a collar formed of at least two sections (36a, 36b) capable of being placed behind the plug (10). Subassembly (28) forms a ring formed of at least two sections (56a, 56b) designed simultaneously to encircle the rear of the plug (10) and the collar. The ring operates in conjunction with the connector by means of threads (20, 60) and with the collar by means of a assembly consisting of a throat (62) and a ring-shaped ridge (54). The subassembly (26) is also prevented from rotating relative to plug (10).

Abstract: An elongated part, of composite, metal matrix material, respectively comprises 35 to 45 vol. % of a matrix based on aluminum or magnesium alloy and 65 to 55 vol. % of continuous carbon fibers, arranged in sheets parallel to the length thereof. At least approximately 90% of the carbon fibers are ultra-high modulus fibers. In 25 to 60% of the sheets, said fibers are oriented at 0%±5° with respect to the longitudinal direction of the part, when the matrix is based on aluminum. In the other sheets, the fibers are then oriented between ±20 and ±40° with respect to said direction. When the matrix is based on magnesium, the ultra-high modulus fibers are oriented at 0°±5° in at least 90% of the sheets. This gives a high rigidity and high stability in the indicated direction, which favors applications in the space industry.

Abstract: Deicing device for the leading edge of the air inlet cowl of a jet engine. According to the invention, an injector (12) whose task is to inject pressurized hot air into the leading edge is connected to the pressurized hot air inlet by means of a ball joint (22).

Abstract: The present invention concerns a method for producing a lightened SiC structure, especially for the production of a lightened mirror, with the following stages: cutting of a preform with a honeycomb-shaped structure whose voiles have an organic matrix and a fibrous reinforcement, pyrolysis of this honeycomb-shaped structural preform so as to solely preserve the carbon, silicidation of the carbon of the preform so as to obtain a microporous SiC core, infiltrating type reinforcement by means of a SiC chemical vapor phase depositing of the voiles of the honeycomb structure of the core, embodiment of a felt sheet and assembling on at least one face of the core of the embodied sheet and densification of this sheet so as to obtain at least one SiC skin on the surface of the core. The invention also concerns the structure obtained.

Abstract: A device for limiting the flow rate of a fluid through a conduit operates autonomously without any external energy source, and independently of the level of pressure upstream, by operating on an imposed upstream-downstream pressure difference. The flow limiter is capable of limiting the rate of flow of a fluid through a pipe, the flow rate of the fluid depending on the cross section for passage of the fluid in the pipe, and on the difference between the upstream and downstream pressures relative to the passage cross section, in the direction in which the fluid flows.

Abstract: The bay (12) of a turbofan engine (10) comprises a front structural element (30), whose external surface is continuous and extends over at least 50% of the geometrical chord of the bay. Said element (30) is installed on maintaining and guiding members (44), such as slides, which prevent a significant deformation in flight and allow a sliding to the front of the element (30) for maintenance purposes. A laminar air flow around the front half of the bay (12) is consequently ensured.

Abstract: The invention relates to a device for attaching an aircraft engine onto a pylon fixed to a wing or a fuselage. The device comprises a fitting (26), fixed to the pylon (20) by bolts (34, 36), and at least two connecting arms (28, 30), linking the fitting to a structural component (22) of the engine. To allow the installation of engines with larger diameters while preserving the mechanical strength and without increasing aerodynamic disturbance, barrel nuts (38, 40) are put into position into which the bolts (34, 36) are screwed, and certain pins connecting the connecting arms (28, 30) to the fitting (26) are put into the same bores (42, 43) of the fitting.

Abstract: An antenna reflector for a spacecraft is elastically deformable so as to be capable of changing from a folded position, when inside the spacecraft, to a deployed position, outside the spacecraft, at least partly under the action of its own elasticity. The reflector is separated into at least two parts by first opposing slot edges forming a crossing slot, so that in the folded position, the first opposing edges move with respect to each other so as to allow a protruding peripheral part of the reflector to be arranged closer to a longitudinal end of the spacecraft with damaging any portion of the reflector. In one embodiment, the two parts may be further separated by a radial slot which is arranged substantially orthogonal to the crossing slot.

Abstract: The present invention relates to a data link system between an aircraft and at least one ground station comprising an on-board assembly, a ground-air assembly, a land-based assembly, the last two assemblies being composed of sub-networks interconnected by routers and acting as the medium for distributed applications, the on-board assembly comprising a first (10) and a second (11) application computer. These two computers (10, 11) are distinct and interchangeable and receive both the same data supplied by the on-board user interface (12) and the same data supplied by an interface (13) with the ground-air sub-network access processor or processors (14) on the ground user side.