Abstract: A navigation method based on satellite positioning data and non-satellite positioning data includes the following steps of: computing a first reference navigation that is hybridised on the basis of non-satellite positioning data and satellite positioning data, the first reference navigation being reset on the satellite positioning data; performing a statistical analysis of the positional corrections provided by the first reference navigation and deducing therefrom the existence or the absence of a deception operation of the satellite signal receiver. A navigation system for implementing this method is disclosed.

Abstract: A system including a coupling device and a data processing device designed to supply an excitation signal (SE) so that an internal signal (?) occurs in the coupling device, this internal signal (?) having a deformation resulting from the current to be measured (I0), obtain a measured signal (Sm) for a variable (Vm) sensitive to the deformation, supply a compensation signal (Sc) in order to cancel out the deformation, and evaluate the current to be measured (I0) based on the compensation signal (Sc). The data processing device is furthermore designed to analyse the measured signal (Sm) and to detect a fault on the trans-mission line based on this analysis.

Abstract: A system couples a driving shaft and a driven shaft in rotation and without play. The driving shaft includes a tubular end with at least one internal longitudinal groove receiving the driven shaft and having at its end a projecting cylindrical transverse pin configured to engage in the groove. A return spring for the pin urges the pin without play against a longitudinal edge of the groove. The spring includes a first helical section for fastening to the driven shaft and threaded by screwing through the pin. A second section of the spring bears on the pin, and a third elastic return section of the spring acts elastically on the second section.

Abstract: The invention relates to a force application device for an aircraft control stick, in which the computer is configured: a) for an angle (ANG1) smaller than or equal to a prescribed virtual stop threshold (S1, S2), to control the motor so that it applies a resistive force (EFF1) to the lever, according to the angle (ANG1), and to deactivate the brake; b) for an angle (ANG1) which is increasing beyond the prescribed threshold (S1, S2), to control the motor and activate the brake so that they apply a resistive force (EFF2) to the lever that is higher than the value (V1); c for an angle (ANG1) which is decreasing while being higher than the prescribed virtual stop threshold (S1, S2), to control the motor so that it applies a return force (EFF3) to the lever according to the angle (ANG1) and to deactivate the brake.

Abstract: The invention relates to an anti-jamming antenna device comprising: an antenna having a uniform radiation pattern; a mesh structure (3) covering the antenna, said mesh structure being configured to modify the radiation pattern of the antenna so as to generate and to orient at least one lobe and/or gain slot in at least one direction of interest.

Abstract: This aircraft flight trim system comprises a friction module that has variable friction and is coupled on one side to a drive shaft and on the other side to an output shaft via a kinematic chain. The aircraft flight trim system has a control circuit which controls the friction module on the basis of an angular displacement value of the output shaft provided by a position sensor and on the basis of a force feedback control signal provided by a flight control computer.

Abstract: A control stick for a vehicle comprising a control lever connected to a mechanical chain, a cup and a locking device, the control lever being oriented relative to a pivot point of the control stick, the locking device further comprising a frame, a lower jaw and an upper jaw which are movable between a locking position of the cup between the jaws and a free position, the lower jaw and the upper jaw being rigidly attached to the frame.

Abstract: A force application device for an aircraft control stick in provided. The device includes a mechanical joint, a force motor, a rheological brake, and a control device. The mechanical joint receives a lever of an aircraft pilot stick and is rotatably movable. The force motor includes a motor shaft extending along a third axis, the rotation of the motor shaft being linked to the rotation of the mechanical joint. The force motor exerts a resistive torque on the motor shaft. The rheological brake includes two facing parts, and has a volume delimited by the two facing parts, the volume being adapted to contain a rheological material. One of the parts is arranged on the motor shaft and rotatably movable about the third axis relative to the other of the parts. The control device applies an electromagnetic field within the volume so as to vary shear strength of the rheological material.

Abstract: A system for controlling actuators in an aircraft. The system including at least a first actuator and a second actuator. Each of the actuators including a movement member, at least one measurement sensor, and a computing member internally connected to the movement member and configured to be connected to at least one electronic computer of the aircraft. The computing member having a function for controlling the movement member, the measurement sensor of the first actuator being externally connected to the computing member of the second actuator, the computing member of the second actuator also having a monitoring function for monitoring the movement member of the first actuator.

Abstract: A control device includes a mechanical seal which guides a rotation of a control lever relative to a frame about two pivot connections of orthogonal axes. The mechanical seal includes, for one or both of the pivot connections, a device that returns a movable part into a neutral position relative to a stationary part. The return device includes one or more elastic members including two branches each extending orthogonally to an axis of the pivot connection from a finger of one of the movable and stationary parts as far as a free end. Each elastic member prevents the free ends from moving towards one another. The elastic member is inserted, in a transverse direction orthogonal to a bisector of an angle between the two branches, between a stationary pin which is secured to the stationary part and a movable pin which is secured to the movable part.

Abstract: This method for monitoring the integrity of a plurality of pseudorange measurements acquired by a navigation system from signals transmitted by a constellation of satellites includes: a first calculation, for each satellite of the constellation, of a first innovation (Inno) reflecting the deviation between the measured pseudorange from said satellite and a value of said pseudorange estimated after the event, produced by a Kalman filter; a first update of each first innovation (Inno); a second calculation of a first group of first test values (CM); maintaining the set of measured pseudoranges so as to calibrate the Kalman filter if all of the first test values (CM) are less than a first predetermined threshold, otherwise implementing a processing step.

Abstract: This method for processing an infrared image captured by an infrared camera comprises the following steps: a step of duplicating the infrared image to form a first image and a second image; a step of applying a local processing operation to the first image; a step of applying a global processing operation to the second image; a step of colourising at least one region of the second image, by means of a lookup table correlating greyscale levels and a colour computer coding format; and a step of fusing the first image with the second image to form a final image.

Abstract: A device for detecting, by a drone, at least one manned aircraft, the manned aircraft emitting at least one positioning message comprising at least one altitude data, the detection device having a receiver to receive the positioning message and to measure its reception strength, a calculator configured to compare an altitude difference with a first threshold to activate a first state of vigilance in case of exceedance, compare the reception strength with a second threshold to activate a second vigilance state in case of exceedance, and generate at least one collision warning signal if the first vigilance signal and the second vigilance signal are active simultaneously.

Abstract: Said method for determining aircraft landing runway conditions comprises the steps of: acquiring a set of data groups of different types (D1, D2) for evaluating and monitoring runway degradation conditions; deriving weighting coefficients (Ki) from each data group; filtering the data; determining, for each data group, a partial runway condition; modifying the weighting coefficients of each data group; and combining the partial runway conditions to derive a runway condition coefficient (RWYCC) associated with a confidence index (C1) derived from the modified weighting coefficients.

Abstract: A self-adaptive shielding device is suitable for a lens or a window of a piece of equipment provided with an electrically conductive enclosure containing an optical or RF sensor. The device includes a shielding screen having a switchable RF shielding mesh of micrometric pitch at least partially surrounded by a border of insulator-metal transition material arranged between the mesh and an electrically conductive envelope. A susceptor element is arranged facing the insulator-metal transition material and transforms incident electromagnetic energy (RFH) into activation heat for the insulator-metal transition material. The susceptor element causes a transition to the conductive state of the insulator-metal transition material under the action of the electromagnetic energy so as to electrically connect the mesh to the electrically conductive envelope when the incident electromagnetic energy exceeds a given threshold.

Abstract: A navigation method and device for an aircraft, and associated system, aircraft, computer program and information medium. The proposed method is wherein a navigation module determines navigation data of said aircraft and in that it includes: during a landing phase of said aircraft, a step of determining said first navigation data based on data from an inertial measurement unit and from images captured by said aircraft; and during a taxiing phase, a step of determining said first navigation data based on data from the inertial measurement unit and from an odometer.

Abstract: A position sensor including a supporting structure bearing two elements capable of translational movement relative to one another in a first direction, namely a magnetic-field-emitting element for generating a magnetic field, and a magnetic-field-detecting element. The magnetic-field-emitting element is arranged in such a way that an orientation of the magnetic field, which orientation is considered in a first plane orthogonal to the first direction, changes as a function of a distance separating the first plane from a first end of the magnetic-field-emitting element. The magnetic-field-detecting element is configured to produce a signal indicative of the orientation of the magnetic field. A brake and an aircraft are equipped with the position sensor.

Abstract: A navigation method based on satellite and inertial positioning data includes the following steps of computing: a first reference navigation, that is hybridised on the basis of inertial positioning data with positional corrections determined on the basis of satellite positioning data; a second reference navigation, that is hybridised on the basis of inertial positioning data; an emergency navigation on the basis of the second reference navigation, reset on the operational navigation then corrected by means of the positional corrections provided by the first reference navigation. A navigation system for implementing this method is also disclosed.

Abstract: A navigation method of a vehicle equipped with a star tracking device, a first inertial measurement device and a satellite positioning device, the star tracking device and the first inertial measurement device being connected to a single support. The method includes controlling movements of the support; simultaneously with these movements, calculating, in a horizontal plane, first positions of the vehicle, and second positions of the vehicle; calculating first deviations between the first positions and the second positions corresponding to each tracking heading and depicting them in a polar reference frame as a function of the corresponding heading and the values of the first deviations; carrying out a circular regression on said first deviations to determine, in this polar reference frame, a first circle; and determining a radius of the circle and a second deviation between a centre of the first circle and an origin of the polar reference frame.

Abstract: This parachute comprising a canopy having a leading edge and a trailing edge opposite the leading edge, suspension lines each having a first end attached to the leading edge and a second end that is designed to bear a load, and a slider having through-elements for the suspension lines to pass through, said elements being connected to one another by attachment means, each of said through-elements being passed through by one of the suspension lines and being free to move in translation relative thereto, the slider being designed to slide along the suspension lines that pass through the through-elements in the direction from the first ends of said suspension lines towards their second ends under the effect of gravity and the force generated by the suspension lines spreading apart when the parachute starts a descent, tightening and spreading apart the suspension lines as the canopy inflates.