Abstract: An aircraft comprising at least one aerodynamic control surface (26) controlled using a remote motor (4), through a transmission comprising a linear device (7) rigid in torsion but flexible in bending and in tension and compression, to absorb thermomechanical deformations. This transmission comprises small clearances, good flexibility, does not require any additional support and makes favourable use of a reduction gear (9) located near the control surface (26) rather than near the motor (4).

Abstract: The invention concerns a rotating missile emitting light pulses. The invention is characterized in that means are provided to interrupt said light pulses (5) when the rotational movement (3) of the missile (2) about its longitudinal axis (L-L) stops.

Abstract: Photodetection cell and laser pulse detector furnished with such a cell, as well as laser pulse detection device comprising a matrix of such detectors. The photodetection cell (1) is embodied in the form of an integrated circuit and comprises a photosensor (3) which is able to transform luminous energy received into an electric current and a means (4) for processing the electric current generated by said photosensor (3). Said processing means (4) comprises a cascoded inverting amplifier (5), looped back through a feedback (6) of slow follower type, which is supplied by the electric current generated by said photosensor (3).

Abstract: The invention relates to a pulsed detonation engine. According to the invention, the transversal base (3) or the flame tube (2) is mounted in such a way that it can move in relation to said tube in order to be able to assume two boundary positions, first position corresponding to the detonation phase of the combustible charge in the combustion chamber (5) of the tube, and a second position corresponding to the phase wherein the combustible charge is supplied to said chamber. At least one supply opening (7) for the combustible charge is provided in the lateral wall (4) of the tube, said opening being closed and separated from the combustion chamber (5) when the mobile base (3) assumes the first position thereof, and communicating with the chamber (5) in a fluidic manner when the mobile base (3) assumes the second position thereof.

Abstract: The invention concerns a combustion chamber whereof the inner wall (17)is made at least partly of a thermostructural composite material, which is porous to the fuel passing through the double wall (14); and the porosity of said inner wall (17) is adjusted so that the proportion of said fuel passing through said inner skin ranges between 5% and 15% of the total amount of fuel input in said ramjet engine.

Abstract: A method for extracting an illuminated zone from a matrix of photosensors may include: (a) dividing the matrix into a plurality of search zones, (b) searching for the presence of an active photosensor in the search zones, (c) stopping the search as soon as an active photosensor is found in a search zone, and (d) further subdividing the first search zone determined to have an active photosensor into a plurality of search zones. Additionally the method may include repeating steps (b) through (d) until a search zone having only active photosensors is obtained.

Abstract: A blanking-plug system for blanking off an orifice of a pipe, particularly for blanking off an orifice of a duct for introducing air into the combustion chamber of a ramjet. The blanking-plug system (16) comprises at least one blanking plug (15) comprising a glass plate (18) which is able to completely blank off said orifice (8) of the pipe (7); and at least one device (17) for destroying said glass plate (18) of said blanking plug (15). Said blanking plug (15) additionally comprises a plurality of elastomer protective elements (21) which are fixed on at least one first face (22) of said glass plate (18) which is likely to be subject to attack, these elements being separated from one another by a predetermined maximum distance at most, and completely covering said first face (22).

Abstract: The invention concerns a rocket engine wherein the combustion chamber includes at least one first monolithic component made of a thermostructural composite material comprising a porous wall through which the fuel is introduced in the core of the combustion chamber. A small part of the fuel is directed towards the neck for it to be cooled.

Abstract: According to the invention, the wall (5) is mounted movably as one so as to be able to slide longitudinally in translation, bringing the joint line (14) closer to the fuel injector (9) so as progressively to modify the geometries of the oxidant inlet (16) and of the combustion chamber (15), said geometries passing progressively from a first state (I) in which, for a Mach number lying between 1.5 and 3, said oxidant inlet (16) constricts said oxidant flow only slightly and the combustion chamber (15) is long and divergent, to a second state (III) in which, for a Mach number lying between 8 and 12, said oxidant inlet (16) strongly constricts said oxidant flow and said combustion chamber (15) is shorter and exhibits a constant cross section.

Abstract: Sight head with integrated laser designator for use in an aircraft such as a rotorcraft. The laser designator (32) is integrated into a zone of a main external assembly of the pod (14) of the sight head (12), enclosed externally in an existing fairing (34). It comprises a laser transmitter (36), a power supply (38) and a radio receiver (40). The laser transmitter (36) is fitted to the site head structure using adjusting screws (46) which allows the alignment to be modified.