Abstract: The invention relates to a liquid recovery system for a motor vehicle where such a recovery system includes at least one liquid intake that communicates with a tank, which is designed to store liquid from the liquid intake, and is designed with an arrangement below the motor vehicle's beltline.

Abstract: The invention relates to a liquid recovery system for a motor vehicle and to a vehicle including such a recovery system that that includes at least one liquid intake that communicates with a tank and is referred to as the first tank, which is designed to store liquid from the liquid intake and where the liquid intake is arrangeably designed below the vehicle's beltline.

Abstract: An end joining piece (4) for a windscreen wiper for a glazed surface of a motor vehicle is disclosed. The end piece has at least a receipt receptacle (410) for receiving an end part of a longitudinal vertebra (20), and at least one flexible tongue (6a, 6b) which is configured to go from a first, position of rest, to a second, retracted position, by displacement in a first direction (F2a, F2b) during the insertion of the longitudinal vertebra in the receipt receptacle (410), the flexible tongue including an engagement ramp along which the vertebra is made to thrust, to provide the tongue with its second, retracted position. The engagement ramp (620a, 620b) has an inclination which is configured to exert on the longitudinal vertebra a force which tends to displace this vertebra in a second direction (F3a, F3b), which, together with the first direction of displacement, forms a non-zero angle.

Abstract: The invention relates to a liquid recovery system for a motor vehicle and to a vehicle including such a recovery system that that includes at least one liquid intake that communicates with a tank and is referred to as the first tank, which is designed to store liquid from the liquid intake and where the liquid intake is arrangeably designed below the vehicle's beltline.

Abstract: An end joining piece (4) for a windscreen wiper for a glazed surface of a motor vehicle is disclosed. The end piece has at least a receipt receptacle (410) for receiving an end part of a longitudinal vertebra (20), and at least one flexible tongue (6a, 6b) which is configured to go from a first, position of rest, to a second, retracted position, by displacement in a first direction (F2a, F2b) during the insertion of the longitudinal vertebra in the receipt receptacle (410), the flexible tongue including an engagement ramp along which the vertebra is made to thrust, to provide the tongue with its second, retracted position. The engagement ramp (620a, 620b) has an inclination which is configured to exert on the longitudinal vertebra a force which tends to displace this vertebra in a second direction (F3a, F3b), which, together with the first direction of displacement, forms a non-zero angle.

Abstract: Device for locking a windshield wiper (10) to a drive arm (12), characterized in that it comprises electrical means (4) able to drive a reversible movement of at least one locking element (5) secured to the arm (12) or to the wiper (10), said at least one locking element (5) moving relative to the arm (12) or to the wiper (10) to which it is secured between an unlocked position in which said at least one locking element (5) is secured only to the arm (12) or to the wiper (10) and a locked position in which said at least one element (5) is secured to the arm (12) and to the wiper (10).

Abstract: A method for monitoring degradation of an onboard device of an aircraft, implemented by a computer, the degree of degradation of the onboard device being defined by an abnormality score formed by the counting of occurrences of abnormalities noted by a control system of the device, the monitoring method comprising a step of comparing an abnormality score obtained for an observation sequence of given length (n, t) with a decision threshold (ks) and a step of issuing an alarm in the event of the decision threshold (ks) being reached or exceeded, the decision threshold (ks) being determined automatically for a given probability of alarm Pa, corresponding to the probability that an alarm will be issued during the monitoring method whereas the onboard device is sound, by means of the following steps: a step of obtaining an abnormality score (r) on at least one reference sequence corresponding to flights of the aircraft without degradation and with a length (m, tc) equal to a plurality of lengths (n, t) of observ

Abstract: A method for monitoring degradation of an onboard device of an aircraft, implemented by a computer, the degree of degradation of the onboard device being defined by an abnormality score formed by the counting of occurrences of abnormalities noted by a control system of the device, the monitoring method comprising a step of comparing an abnormality score obtained for an observation sequence of given length (n, t) with a decision threshold (ks) and a step of issuing an alarm in the event of the decision threshold (ks) being reached or exceeded, the decision threshold (ks) being determined automatically for a given probability of alarm Pa, corresponding to the probability that an alarm will be issued during the monitoring method whereas the onboard device is sound, by means of the following steps: a step of obtaining an abnormality score (r) on at least one reference sequence corresponding to flights of the aircraft without degradation and with a length (m, tc) equal to a plurality of lengths (n, t) of observ

Abstract: A method for monitoring a degradation in an on-board device of an aircraft, comprising a step of comparing an abnormality score obtained for a given flight of said aircraft with a decision threshold (S) and a step of transmitting an alert in the event of said decision threshold (S) being exceeded, said decision threshold (S) being automatically determined for a given probability of alert Pa, corresponding to the probability of an alert being transmitted during the monitoring method when said on-board device is healthy, by means of a plurality of steps, including a step of reading the antecedent of the continuous adjusted division function for the value 1?Peac, said antecedent corresponding to said decision threshold (S), with Peac being the elementary probability of exceeding the threshold for confirmation per k exceedances of threshold during n consecutive flights and being a function of the probability of alert Pa.

Abstract: A method for monitoring degradation of an on-board device of an aircraft includes comparing an abnormality score obtained for a given aircraft flight to a decision threshold and emitting an alarm when the decision threshold is exceeded.

Abstract: A method monitoring a servo-control loop, including: estimating monitoring parameters from operating data of the servo-control loop; obtaining indicators from the monitoring parameters; determining at least one signature from values of at least some of the indicators; and detecting and locating a degradation affecting the servo-control loop as a function of the at least one determined signature.

Abstract: A method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine, the control device supplying a control current to a servo valve in order to modify the position of the fuel metering valve. The method includes determining the position of the fuel metering valve during a flight of the aircraft, determining the travelling speed of the fuel metering valve, and determining the control current when the travelling speed of the fuel metering valve is zero. A mean control current is calculated when the travelling speed of the fuel metering valve is zero, the mean control current forming an indicator of deterioration of the control device. The deterioration indicator is compared with a reference base of indicators with deterioration so as to infer the type of deterioration from it, and an abnormality score is calculated for the deterioration indicator.

Abstract: A method for monitoring degradation of an on-board device of an aircraft includes comparing an abnormality score obtained for a given aircraft flight to a decision threshold and emitting an alarm when the decision threshold is exceeded.

Abstract: A method for monitoring a degradation in an on-board device of an aircraft, comprising a step of comparing an abnormality score obtained for a given flight of said aircraft with a decision threshold (S) and a step of transmitting an alert in the event of said decision threshold (S) being exceeded, said decision threshold (S) being automatically determined for a given probability of alert Pa, corresponding to the probability of an alert being transmitted during the monitoring method when said on-board device is healthy, by means of a plurality of steps, including a step of reading the antecedent of the continuous adjusted division function for the value 1?Peac, said antecedent corresponding to said decision threshold (S), with Peac being the elementary probability of exceeding the threshold for confirmation per k exceedances of threshold during n consecutive flights and being a function of the probability of alert Pa.

Abstract: A method for monitoring a servo-control loop (3) of an actuator system (2) for actuating variable-geometry components of a turbojet, said method comprising: an estimation step of estimating a plurality of monitoring parameters from operating data of the servo-control loop (2); an evaluation step of evaluating a plurality of indicators from the monitoring parameters; an evaluation step for evaluating at least one signature matrix, each signature matrix being representative of the values of at least some of the indicators; and a detection and location step of detecting and locating a degradation affecting the servo-control loop as a function of said at least one signature matrix.

Abstract: A process for monitoring a machine including moving pieces, a lubrication system and an electromagnetic sensor fitted with a magnet and two electrodes is disclosed. The sensor is capable of collecting particles present in the lubrication system between the electrodes. The monitoring process includes a step for obtaining measurements of resistance between the electrodes of the sensor, taken during an operating period of the machine; a step for determining from said measurements a first autoregressive mathematical model characterizing the resistance; a step for comparison between the first model and a predetermined reference model; and a step for working out an opinion on maintenance of the machine as a function of the comparison result.

Abstract: A method monitoring a servo-control loop, including: estimating monitoring parameters from operating data of the servo-control loop; obtaining indicators from the monitoring parameters; determining at least one signature from values of at least some of the indicators; and detecting and locating a degradation affecting the servo-control loop as a function of the at least one determined signature.

Abstract: The method of the invention for monitoring a thrust reverser of a turbojet having an actuator controlled by an electric motor consists in determining a maintenance notice from a weighted combination of provisional notices, each provisional notice relating to a category of parameters associated with at least one phase of an operating cycle of the reverser, the category being selected from a category of parameters representative of a duration of said phase, of an energy seen by the motor during said phase, of a torque seen by the motor at a predefined instant of said phase, and of a duration during which the setpoint speed of rotation and the measured speed of rotation of the motor differ during said phase, each provisional notice being generated by analyzing values obtained during at least one cycle for at least one parameter of said category relative to a degradation threshold.

Abstract: A line replaceable unit for aircraft, the line replaceable unit including: a measuring device configured to measure useful data to define the status of the line replaceable unit, a predictive monitoring device configured to calculate indicators of potential breakdown of the line replaceable unit from useful data to define the status of the line replaceable unit, a communication interlace capable of forwarding indicators of potential breakdown to a central unit.

Abstract: The invention relates to monitoring a redundant measurement system of an aeroengine by means of an electronic unit. The monitoring comprises a step of obtaining first measurements of a physical magnitude measured in said engine, and a step of obtaining second measurements of said physical magnitude. According to the invention, the method includes a step of calculating detection residues as a function of differences between the first and second measurements, a step of determining a mean-jump flag, a step of determining a variance-jump flag, a step of determining a change-of-slope flag, and a step of generating a diagnostic notice as a function of said mean-jump flag, of said variance-jump flag, and of said change-of-slope flag.