Abstract: A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

Abstract: A flight control system includes at least one actuator for a mobile flight surface of an aircraft, and a flight control module in communication with the actuator. The module includes a first and a second computer. Each computer calculates a control command established according to at least one predetermined law for control of the flight surface. The first computer, known as validating computer, comprises logic means adapted for comparing its control command with that of the second computer, known as master computer, and for transmitting the result of the comparison to the actuator. The actuator comprises logic means adapted for deciding, on the basis of the result, to execute or not to execute the command of the master computer. An aircraft comprising such a system is also disclosed.

Abstract: The flight control system comprises: at least one actuator (13) for a mobile surface of the said aircraft; a flight control module (12) in communication with the said actuator (13), the said module comprising at least a first and a second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), each computer being adapted for calculating a control command established according to at least one predetermined law for control of the said flight surface; the said actuator (13) comprising logical means (18, 19) adapted for comparing the commands of the said computers (14-1, 14-2, 14-3, 15-1, 15-2, 15-3) and for determining on the basis of these commands the action to be executed on the said mobile surface. The aircraft comprises such a system.

Abstract: An aircraft control system in which a plurality of elementary control systems, corresponding to different aircraft functions, can share one or more sensors due to a common AFDX network. The transmission of commands is carried out via AFDX messages sent to network-subscribed actuators. Advantageously, the computers of the different elementary control systems installed in the avionics bay include generic computers hosting software specific to execution of respective functions thereof (IMA architecture).

Abstract: A flight control system for an aircraft, controlling a plurality of actuators adapted to actuate control surfaces of the aircraft, including: at least one communications bus; at least one computer situated in the avionics bay of the aircraft, and adapted to calculate flight commands and to transmit them over the bus in the form of command messages; and at least a first remote terminal connected to the bus, adapted to control a control surface actuator, and to acquire the state of the actuator from information provided by at least a first sensor, the first terminal receiving command messages from the computer and transmitting electrical orders to the actuator as a function of the command messages received in this way, and also transmitting messages to the computer, at its request, relating to the state of the actuator as a function of the information provided by the first sensor.

Abstract: The invention relates to a method for the transmission of data relating to the actuation of a member used to operate a vehicle, in which code words are transmitted along the length of a given channel, each of said code words resulting from the channel coding of a block of information symbols that is representative of the aforementioned data. According to the invention, at least two such successive blocks of information symbols are coded using two different codes. The invention also relates to a data transmission system that is used to implement said method.

Abstract: A method and device for detecting oscillatory faults relating to an aircraft airfoil slaving chain. The device includes units that count the number of overshoots of a threshold value by the current value of a quantity related to the positional slaving of an airfoil. Oscillatory fault is detected based on the number of overshoots of the threshold value being greater than the current value by a predetermined number.

Abstract: An aircraft control system in which a plurality of elementary control systems, corresponding to different aircraft functions, can share one or more sensors due to a common AFDX network. The transmission of commands is carried out via AFDX messages sent to network-subscribed actuators. Advantageously, the computers of the different elementary control systems installed in the avionics bay include generic computers hosting software specific to execution of respective functions thereof (IMA architecture).

Abstract: A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

Abstract: A flight control system for an aircraft, controlling a plurality of actuators adapted to actuate control surfaces of the aircraft, including: at least one communications bus; at least one computer situated in the avionics bay of the aircraft, and adapted to calculate flight commands and to transmit them over the bus in the form of command messages; and at least a first remote terminal connected to the bus, adapted to control a control surface actuator, and to acquire the state of the actuator from information provided by at least a first sensor, the first terminal receiving command messages from the computer and transmitting electrical orders to the actuator as a function of the command messages received in this way, and also transmitting messages to the computer, at its request, relating to the state of the actuator as a function of the information provided by the first sensor.

Abstract: The flight control system comprises: at least one actuator (13) for a mobile surface of the said aircraft; a flight control module (12) in communication with the said actuator (13), the said module comprising at least a first and a second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), each computer being adapted for calculating a control command established according to at least one predetermined law for control of the said flight surface; the said actuator (13) comprising logical means (18, 19) adapted for comparing the commands of the said computers (14-1, 14-2, 14-3, 15-1, 15-2, 15-3) and for determining on the basis of these commands the action to be executed on the said mobile surface. The aircraft comprises such a system.

Abstract: The flight control system comprises: at least one actuator (13) for a mobile flight surface of the said aircraft; a flight control module (12) in communication with the said actuator (13), the said module comprising a first and a second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), each computer being adapted for calculating a control command established according to at least one predetermined law for control of the said flight surface; the said first computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), known as validating computer, comprising logic means adapted for comparing its control command with that of the said second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), known as master computer, and for transmitting the result of the said comparison to the said actuator (13), the said actuator (13) comprising logic means (18, 19) adapted for deciding, on the basis of this result, to execute or not to execute the command of the master computer. The aircraft comprises such a system.

Abstract: Method and device for detecting oscillatory faults relating to an aircraft airfoil slaving chain. The device (1) comprises means for carrying out a counting of all the overshoots of a threshold value by the current value of a quantity related to the positional slaving of an airfoil (3), and for detecting an oscillatory fault as soon as the number resulting from said counting becomes greater than a predetermined number.

Abstract: The invention relates to a method for the transmission of data relating to the actuation of a member used to operate a vehicle, in which code words are transmitted along the length of a given channel, each of said code words resulting from the channel coding of a block of information symbols that is representative of the aforementioned data. According to the invention, at least two such successive blocks of information symbols are coded using two different codes. The invention also relates to a data transmission system that is used to implement said method.

Abstract: A method for testing or measuring electric elements uses at least one electron-discharging electrode, at least one electron-collecting electrode and at least one source of a beam of particles. The method includes ejecting electrons present in the discharging electrode by use of the beam of particles and injecting into an element the electrons supplied by the discharging electrode, and ejecting electrons present in an element by means of the beam of particles and collecting by the collecting electrode the electrons ejected from the element. The ejection of electrons present in the discharging electrode includes the application to the discharging electrode of a reflected beam of particles resulting from the reflection of an incident beam of particles on at least one element.

Abstract: A machine for welding rail comprises a rail vehicle with at least one energy generator set, a programmable automatic control unit and a raised chassis disposed between the bogies of the vehicle. The chassis supports at least one welding unit, grinders, two workbench units, each comprising a beam equipped with grippers for gripping, lifting and holding the rails in a working position, a set of grippers at the ends of the vehicle, and position sensors.

Abstract: A microlaser having input and output mirrors defining a microlaser cavity, a solid active dielectric medium disposed in the microlaser cavity, and a pumping mechanism which pumps the microlaser and which includes at least one vertical cavity semiconductor laser. The microlaser may also include a microoptical focusing device, passive and/or active cavity switches. A plurality of such microlasers can be assembled to form a bidimensional network.

Abstract: A self-aligned, monolithic, solid microlaser with passive switching by a saturable absorber and a production process therefor. The cavity for the microlaser has a solid active medium, a saturable absorber, an entrance mirror and an exit mirror, wherein the saturable absorber is a thin film of saturable absorbent material directly deposited on the solid active medium.

Abstract: Mixed lanthanide-magnesium aluminates and lasers using monocrystals of these aluminates. These lasers in particular incorporate two flash lamps for longitudinally pumping a monocrystalline rod of a magnetoplumbito-aluminate emitting visible or infrared light, amplified between a mirror, a polarizing prism being used for passing to the outside of the laser the amplified light beam. The aluminate is of formula: (La.sub.1-x Tr.sub.x).sub.1-y-v Mg.sub.1-z-t Al.sub.11-u+y+2Z/3 Cr.sub.u O.sub.19-t-3v/3 in which Tr represents (a) at least one single trivalent substance chosen from among lanthanides, Y.sup.3+, Sc.sup.3+, or (b) at least one pair of lanthanides formed from a divalent element and a trivalent element, while retaining the electrical neutrality by adding aluminum or oxygen deficiencies, or any combination of (a) and (b); x is a number such that 0.ltoreq.x<1; y and v are numbers such that 0.ltoreq.y+v.ltoreq.0.4; z and t are numbers such that 0.ltoreq.z+t<1, provided that when z=t=O, y+v is .noteq.

Abstract: Mixed lathanum-magnesium aluminates, their production process and lasers using these aluminates.These lasers comprise two flash lamps for longitudinally pumping a bar of an aluminate of formula La.sub.1-x Nd.sub.x Mg.sub.Y Al.sub.11 O.sub.18+y, x and y being numbers such that O<x.ltoreq.0.2 and O<y<1, preferably with y ranging from 0.5 to 0.55, emitting in the infrared, mirrors for amplifying the light emitted by the bar and a polarizing prism for passing the amplified light beam outside the laser.