Abstract: The present invention relates to a device for the suspension and translational guidance of an item of apparatus (1) intended to be displaced, parallel to its longitudinal axis (X--X) with respect to a stationary support (2), having one pair of suspension elements (4A, 4B) spaced along said longitudinal axis (X--X) while being flexible parallel to said axis, and controllable actuating means (10) intended to exert a force parallel to said axis (X--X) on said suspension elements.According to the invention, each of said suspension elements (4A, 4B) consists of at least one pair of blades (5A, 5B, 6A, 6B), one end of one of said blades being secured to said support (2) and one end of the other of said blades being secured to said item of apparatus (1), the other ends of said blades being secured to each other.

Abstract: This invention relates to a system for measuring the characteristics of an object, comprising: a least two cameras (18, 19) pointing along two different directions towards the space in which the object (23) is positioned located above the upper plane of the first light box, and connected to the processing unit. two light boxes (11, 12), the first being located in a upper horizontal plane above the platform of scales (10), the second being located in a vertical plane above and to the side of the plane above the first plane; a processing unit (13) connected firstly to an information input device (14) and secondly to a display device (15); scales (10) equipped with a weighing platform.

Abstract: A satellite embodying at least one surface intended mainly for exposure to solar radiation and extending away from the satellite in a predetermined direction (Y), an on board computer having connected thereto an attitude sensing system, an orbit control system for imparting thrust to the satellite along predetermined axes, and an attitude control system. The satellite further embodies a device for controlling the tilt of the surface in parallel with a plurality of planes containing the predetermined direction; and, therefore, particularly in parallel with the plane of a solar panel forming the surface. The tilt control device is controlled by the on-board computer. The tilting can generate a moment of pitch or relocate the center of gravity onto the axis of the orbit control system.

Abstract: A structure obtained by laying filaments on a convex axisymmetric surface to provide a hemispherical surface. The structure may include with a circular hole or a dead zone centered on an axis of the surface and may be formed by laying filaments along a geodesic path. The structure includes a first and second part, in which the first part includes the axis. The geodesic path formed by the filaments on the first part may be spaced a predetermined distance the opening or circular dead zone.

Abstract: A mechanism for isostatic fitting of a fragile element, such as a mirror, to a support, generally carried on board a spacecraft, is provided. The mechanism includes three identical connecting devices circumferentially distributed around the optical axis of the mirror. Each device has a flexible blade or plate, whose longitudinal axis is preferably oriented in a direction tangential to a circle centered on the optical axis. The cross-section of the flexible blade decreases progressively from a first end fixed to the support to a second end fixed to the mirror, through a deformable member. The deformable member is adapted to flex in order to permit a relative rotation about a radially oriented axis. The fixtures to the support and the mirror are provided by rods operating only in tension and compression.

Abstract: A device for monitoring a complex system includes a central unit for transmitting monitoring information to a display unit, the display unit displaying messages concerning the information received. The central unit is loaded with a database containing additional information. At the time of transmitting monitoring information it indicates the existence of additional information. The display unit displays a signal indicating the existence of the additional information.

Abstract: A device placed by a support in front of the eyes of a user protects them against luminous aggression, in particular by a laser beam. The device includes a light attenuation system to attenuate the intensity of the received beam by a particular attenuation value. A light amplification system is disposed between the light attenuation system and the eyes of the user to amplify the intensity of the light received from the light attenuation system by a particular amplification value, but such that the intensity of the light transmitted towards the eyes does not exceed a prescribed maximal intensity that is not harmful for the eyes. The attenuation and amplification values are substantially equal.

Abstract: A guidance system for guiding a missile to a target including an array of photosensitive elements arranged orthogonally to the axis of the missile, a scanning arrangement for enabling scanning of the array of photosensitive elements by means of an optical system, and a target detecting arrangement for controlling the field and the pace of scanning executed by the scanning arrangement so that the field of scanning is smaller and the pace of scanning is greater after detecting a target than before target detection.

Abstract: A method and system providing a specification of an interface between a control terminal in an aircraft at the disposal of an operator, such as a pilot, and a computer assisting in the piloting and navigation of the aircraft. The computer includes at least one memory containing at least one management software for managing the interface. The specification implements alphanumeric displays on the screen for controlling the actions of the operator on the keyboard. The specification is expressed in a data flow type graphic language including symbols relating to all the specified functions by using a data processing system. The symbols are connected by links so as to express a display configuration on the screen, a description of elementary actions able to be carried out by the operator, and a description of the responses of the terminal on order issued by the computer(s) and independent of the actions of the operator.

Abstract: The present invention provides a method and a machine for marking an electric cable that comprises a conductive core, an insulating coating, and a varnish comprising an outer layer and an inner layer of contrasting colors, with the marking being performed by ablating the outer layer of said varnish with a laser, the outer layer of varnish being based on polytetrafluoroethylene and being 10 .mu.m to 20 .mu.m thick. According to the invention the machine comprises:a pulsed CO.sub.2 laser (2) whose power is adjusted to obtain an energy density lying in the range 8 J/cm.sup.2 to 15 J/cm.sup.2 at the outer layer of the cable varnish;drive means (9) for driving the cable (4) so as to cause it to run past the laser beam (5);guide means (13, 14, 15) for guiding the cable (4) in the vicinity of the point of impact of said beam (5) on the cable; andcomputerized control means (6).

Abstract: The invention concerns a device for externally cooling a plasma torch. The invention concerns a device for cooling a plasma torch in which the electrode(s) and plasma fluid and cooling circuits are housed in a tubular casing, wherein the cooling device includes an independent sheath surrounding at least one main portion of the tubular casing and formed of two concentric casings, at least one cooling fluid inlet and at least one outlet disposed at the proximal extremity of the sheath, a system of baffles being disposed between the two casings of the sheath so as to constitute between the inlet and outlet a cooling circuit substantially covering the entire surface of the sheath, the inlet and outlet being connected to a suitable cooling fluid source.

Abstract: A system for controlling a control surface articulated to a structure of a vehicle about a first axis includes a tab articulated to the trailing edge of the control surface about a second axis parallel to the first axis, an elastic link provided between the control surface and the tab, a pilot input control mechanism to which the elastic link is connected and which acts on the tab, and an actuating member provided between the control surface and the link for keeping the tab/control surface assembly in any position whatever. The elastic link and the actuating member are arranged to be at least substantially parallel to the first axis of articulation of the control surface. The first axis is disposed near, and upstream from, the elastic link and the actuating member.

Abstract: An electromagnetic linear actuator having a stationary annular assembly with a magnetic outer shell and a magnetic inner core. Monostable or bistable control components may be mounted interchangeably between the outer shell and inner core. An assembly which is moveable in the axis of the annular assembly includes two magnetic plates which face the extremities of the annular assembly and a rod which is mounted so that it can slide inside the core. The first core is made of a material chosen for its frictional characteristics. The actuator may be used to control the valve of a regulator in the fuel supply circuit of a satellite engine.

Abstract: A drive device for rotating a main mobile assembly relative to a support about a rotation axis includes an intermediate mobile assembly rotated about the same rotation axis. A small travel linear electromagnetic drive device operates tangentially between the intermediate mobile assembly and the mobile assembly, being controlled in accordance with the position of the main mobile assembly relative to the support. A large travel drive device rotates the intermediate mobile assembly relative to the support in accordance with the relative position of the intermediate mobile assembly and the main mobile assembly. End stops delimit predetermined movement of the main mobile assembly relative to the intermediate mobile assembly.

Abstract: A device for magnetically centering, with respect to a reference axis, a second body mobile relative to a first body includes a magnetic bearing that is active along the reference axis. It further includes two magnetic centering devices offset axially along that axis, on opposite sides of the magnetic bearing.

Abstract: Information, an alert or an alarm is supplied to an aircraft in proximity to the ground. A grid of geographic coordinates is established, each mesh of which exhibits a defined relief. The trajectory of the aircraft is predicted over a predetermined time interval. An intersection, if any, between the predicted trajectory and the relief of at least one of the meshes is determined. An alert or alarm is activated in the case of such an intersection. The alert or alarm is inhibited when the aircraft is in landing configuration or when the runway is detected and a series of conditions relating to landing are fulfilled.

Abstract: A device for controlling a rudder of an aircraft has at least two servo-systems each including at least one electric control input. At least one of the servo-systems is a mixed servo-system that also has a mechanical control input. When an engine fault occurs, an electric control system causes at least two of the servo-systems to simultaneously operate the rudder. When the electric control system is not operational due to an electric fault, the mixed servo-system operates the rudder based on control signals from the mechanical control input.

Abstract: For the testing of radio navigation instruments by means of an automatic testing system controlling electric signal measuring and generating equipment, said instruments using radio navigation signals comprised of complex-shaped composite low-frequency signals modulating a high-frequency carrier wave, the method embodying the invention comprises the utilisation of standard signal generating equipment (11, 13, 14, 15) to generate primary low-frequency signals and a high-frequency carrier wave, the combining of these primary signals to obtain said composite low-frequency signals, and the modulation of the high-frequency carrier wave by the composite signals.

Abstract: The present invention relates to a device for bleeding off and cooling hot air in an aircraft engine, including:at least one hot air take-off at the outlet of the compressors of the engine,a cold air take-off downstream of the fan of the engine,a precooling heat exchanger between said hot air and said cold air.According to the invention, said precooling heat exchanger (18) comprises at least one (12A) of said linking arms (12) between the engine body (2) and the fan shroud (9), the said linking arm or arms (12A) acting as the exchanger, exhibiting a hollow structure traversed longitudinally by at least some of the hot air bled off at the outlet of the low pressure and/or high pressure stages of the compressors (3) of the engine.

Abstract: A process and device for identifying faults in a complex system containing a plurality of elements connected together are disclosed. The device has a centralized processing station monitoring a system of complex elements which issue fault cues, within a predetermined time, to the central processing station. The fault cues are composed of an identification indicator and an origin indicator that allow the fault cues to be grouped together on the basis of their respective indicators for making a determination as to the origin of the fault. The system aide in the diagnosis and correction of a fault in a complex system, which are involved in locating and repairing such faults.