Abstract: A process and apparatus for depositing simultaneously by winding on a support, several rovings of pre-impregnated fibers. The rovings are deposited simultaneously by winding on a rotating support. At least two rovings are brought into superposition near where they will be applied to the support, and the various rovings are subjected to different tensions depending on their position relative to the support. Specifically, the roving nearest the support is subjected to a greater tension than a roving farther from the support. Composite structures are thus produced.

Abstract: An antenna reflector for a spacecraft includes a radial slot which facilitates stowage of the reflector in the spacecraft. When the reflector is in a folded position, opposing edges of the radial slot overlap in such a way that the reflector assumes an at least approximately conical shape, thereby allowing the reflector to be housed in a casing so as to be oriented vertically in line with the spacecraft.

Abstract: The invention concerns a method for placing an artificial satellite on a geostationary orbit injected on said orbit by a launch vehicle. The method is characterised in that the assembly consisting of the last stage (L) of said launch vehicle and satellite (S) be injected on the geostationary orbit (G) is first directly sent on a circular orbit (C), called extinction orbit, near the geostationary orbit, but sufficiently distant therefrom to avoid possible interferene with space objects already on the geostationary orbit (G), the satellite (S) is separated from said last stage (L), which stays on said extinction orbit (C), and the satellite (S) reaches the geostationary orbit (G) from said extinction orbit (C).

Abstract: The present invention relates to an air inlet cowl (9) for a jet engine. According to the invention, provided in the partition (20) delimiting the de-icing chamber (21) in the hollow leading edge (16) of the cowl is a trough-shaped duct (22) for ejecting to the outside pressurized hot air which has flowed through the chamber (21). The duct (22) is reduced in cross section by a single oblong orifice (18) made, parallel to the leading edge (16), in a part (23) that forms part of the external surface (9E) of the cowl (9).

Abstract: The present invention relates to a shut-off system for an orifice for introducing combustion air into a ramjet with a consumable auxiliary motor (14).According to the invention, this shut-off system comprises:an elastic system (28, 29, 31, 32) connected to the shut-off flap (20A, 20B); anda retaining element (33) for keeping the said elastic system in the said tense state during the initial phase of rocket operation, the said retaining element being sensitive to the hot gases emitted by the said consumable auxiliary motor (14) so that on completion of combustion thereof, the said retaining element (33) releases the said elastic system which spontaneously changes from its tense state to its relaxed state, bringing the said flap from its shut-off position to its open position.

Abstract: The present invention relates to a process and to a device for determining the contour of valleys of a specified geographical area. According to the invention, said device comprises:means for determining the hydrographic net of the geographical area which is presented in a first matrix which includes, at each point liable to form part of a watercourse, a characteristic code designating said watercourse;means for forming a second matrix which includes at each point the altitude of the corresponding part of said geographical area; andmeans for determining, from said first and second matrices, the contours of the valleys.

Abstract: An engine control system for a first aircraft belonging to a family of aircraft which includes at least a second aircraft, the first aircraft having a maximum mass which is greater, within a predetermined limit, than that of the second aircraft. For an engine of the first aircraft, a first thrust command law controls a thrust of an engine of the first aircraft during take-off phase (T), and a second thrust command law, controls a thrust of the engine to correspond with a part of the thrust command laws applicable to the second aircraft during all other flight phases (R) of the first aircraft. The transition from one flight phase to another is detected to supply the engine with a control signal corresponding to one or the other of the first thrust command law or the second thrust command law.

Abstract: A method for producing a high dimensional precision composite element using ionization polymerization and an element made by such method. The element includes a support panel flanked on at least one side with a skin fixed by an adhesive resin and including at least one lap of organic or mineral fibers and an organic linking matrix. The method includes placing at least one lap of fibers preimpregnated with an ionization polymerizable resin on a mold to form the skin, the mold having a predetermined shape and dimensions for the element to be produced; placing a film of an ionization polymerizable adhesive resin on the skin; placing the support panel on the film to form a skin/film/panel unit, the support panel having a predetermined thickness; compacting the skin/film/panel unit; and polymerizing the polymerizable resins during the compacting by subjecting the skin/film/panel unit to ionization.

Abstract: A rotation center type joint has a one-piece body with an inner part, an outer part and a plurality of elastically deformable transverse arms inclined relative to the axis of the body, linking the inner and outer parts and converging towards the rotation center.

Abstract: To command notably the unclamping and the separation of two components, on a spacecraft, such as a satellite or a probe, a single actuation pushing device (10) is driven by a form memory device (36) positioned in a casing (12), between a wall (18) of the latter and a boss (24). It is linked to a heater (38). A system to prevent mistakes (20, 26, 32), sensitive to a displacement of the component (24) caused by an elongation of the device (36), prevents assembly of the pushing device (10) when it has already been actuated.

Abstract: A pyrotechnic ignition device for a gas generator (G), in which: (i) at least in the vicinity of the primary charge (CP), the transmission line (L) is at least substantially perpendicular to the longitudinal axis (X--X) of the outer case (E) of the generator (G); (ii) the end of the transmission line, provided with a deflagrating terminal lead charge (r), emerges in a sealed intermediate chamber (CI); and (iii) the intermediate chamber (CI) is connected to the primary charge (CP) via at least one throttling vent (e) having an axis (1--1) at least approximately parallel to the longitudinal axis (X--X) of the outer case (E).

Abstract: The proposed accelerator comprises a magnetic system (2), having an external magnetic pole (10) and an internal magnetic pole (9) which are interconnected by a magnetic circuit (8), an outer magnetic screen (13), an inner magnetic screen (12), a central magnetizing coil (5) and external magnetizing coils (7). Besides, the accelerator has a discharge chamber (3) comprising a concave anode (18) encompassing magnetic force surfaces (25) of a ionization zone (22), a sectional gas distributor (26), an inner side wall (15) and an outer side wall (16), the internal surfaces (20) whereof in the ionization zone (22) are located at an angle to a longitudinal axis (A--A) of the accelerator.

Abstract: Method for producing a shaped part made of a graphitized carbon/carbon composite material in which a compound of carbon fibers is prepared impregnated with a solution of carbon precursors and then cut into sections placed in a mould subjected to a carbonization stage by means of hot unidirectional pressing, wherein, so as to prepare the compound, the fiber is subjected to a heat deoxidation and oil removal treatment followed by a softening in a bath for increasing wettability and hooking and then impregnation in a bath formed of an aqueous solution containing pitch mesophase, high-yield pitch and a binder, the required sufficient calculated amount of compound being placed in bulk in a hot constant volume pressing mould so as to accurately fill the mould at the end of pressing before carrying out said carbonization, the moulded part finally being graphitized at a high temperature. Applications include the aeronautic and spatial fields.

Abstract: A draining apparatus drains and dries hydraulic equipment such as aircraft circuits. The draining equipment includes a reservoir connected to the equipment by a suction line. (Venturi 20) which produces a vacuum in the reservoir responsive to compressed air injected by a line from an external compressed air source. If a calibrated valve is connected to an inlet of the equipment then a branch line of the equipment supplies part of the compressed air to the inlet connection of the equipment so that pressure which enters the equipment is inadequate to produce an overpressure at an outlet.

Abstract: The invention concerns a pod (16) of an aircraft motor (10) suspended from a pole (14) and comprising a pod cowling (24) joined to the pole (14) along a hinge pin (26) which forms a first angle .alpha. with a first plane (27) passing through the axis of the motor and perpendicular to a second median plane (29) of the pole. According to the invention, the hinge pin (26) forms a second angle .beta. with the median plane (29) so as to make the closing elements of the cowling (25) coincide with complementary corresponding elements of the adjacent edges (30) of the pod (16) when the cowling is closed.

Abstract: A device for accurately positioning the vertex of a secondary mirror (5) off-centered with respect to that of a primary mirror (3) of a telescope (1). The secondary mirror (5) is connected to a support (8). The connection (9) includes two radial and crossed elongate connecting members (10) which extend on either side of the support (8) (along a first direction X--X and a second direction Y--Y) passing through the center (0) of the support, corresponding to the vertex (5A) of the secondary mirror (5). Each of the connecting members (10) is longitudinally rigid and transversely flexible. Each of the connecting members is capable of being controlled, in order to move along its longitudinal extent by an actuation device (11).

Abstract: A rotary actuator (16) has an inner body (32) forming a rotor and at least one outer body (34) forming a stator. The inner body (32) and outer body (34) carry blades (40,44) arranged in an alternating manner and defining between them two series of variable volume chambers. The cross-section of the chambers and the height of the triangular blades (40,44) decreases from one end to the other, as a result of a substantially frustum-shape of the inner body (32). Such an actuator (16) can be used for controlling an aircraft rudder or control surface and it is then positioned along the articulation axis of the rudder or control surface.

Abstract: An adjustable seat of a vehicle such as an aircraft, comprises a fixed baseplate, the top plate of which is mounted on two lower components by two hinged joints. These hinged joints define two pins oriented parallel to the plane of the top plate, in the vehicle's transverse and longitudinal directions respectively. Moreover, one of these hinged joints is placed at the apex of a triangle, the opposite side of which is coincident with the pin of the other hinged joint. The integrity of the bed of the seat is thereby preserved in the event of twisting of the floor.

Abstract: A unit for controlling the retraction of a mobile structure such as a mirror used for calibrating an optical system on board a spacecraft, which includes a spring which permanently forces the mobile structure towards its retracted position and a memory material member, wherein a change of state of the memory material disconnects a connecting system placed in a transmission mechanism normally connecting a control motor to the mobile structure. The connecting system normally ensures the joining by friction of two parts of the transmission mechanism between which the spring acts. A heating system controls the change of state of the memory material member.

Abstract: Aluminum nitride whiskers are produced by reducing alumina with carbon in a nitrogen atmosphere, at a temperature of 1800.degree. to 2000.degree. C., in the presence of a growth activator containing a solvent element, according to a process that essentially comprises the step of periodically feeding, through the working area of a horizontal furnace equipped with a graphite heating device, counter to a flow of nitrogen, a graphite container charged with a mixture of alumina, carbon and carbonyl iron, as a growth activator, which is present in an amount capable of implementing the VLS mechanism, the time taken by the container to pass through the working zone being in the range of 20 to 120 minutes.