The invention relates to a method for controlling at least one vehicle (k) comprising a propulsion system (102), motorised directional control members (103) and a computer control unit (107) connected to the motorised directional control members (102, 103) in order to control said members and guide the vehicle along a reference course, on the basis of a speed correction (in order to maintain a first minimum distance between the vehicle and any obstacle along the reference course) transformed into a position correction. The position correction is estimated over a prediction horizon in order to determine a course to be followed over the prediction horizon. The commands are determined so as to follow the course to be followed by applying an avoidance constraint corresponding to a second minimum distance between the vehicle and any obstacle along the course to be followed over the prediction horizon, the second minimum distance being shorter than the first minimum distance.
The present invention relates to a method for verifying the presence of equipment (E) on board an aircraft, the method comprising the following steps:—during a flight of the aircraft, implementing (102) radio communication tests by means of a device (2) on board the aircraft so as to determine an in-flight list of equipment consisting of any equipment having a quality of radio link with the radio communication device (2) higher than a first predetermined quality threshold;—after the flight, implementing (104) radio communication tests by means of the device (2) so as to determine a post-flight list of equipment consisting of any equipment having a quality of radio link with the radio communication device (2) higher than a second predetermined threshold after the flight;—generating (108) an alert when an item of equipment is present on the in-flight list and absent from the post-flight list.
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
B64C 13/10 - Initiating means actuated personally comprising warning devices
G05G 5/03 - Means for enhancing the operator's awareness of the arrival of the controlling member at a command or datum positionProviding feel, e.g. means for creating a counterforce
4.
Method for automatically assisting with the landing of an aircraft
The present invention relates to a method for automatically assisting with the landing of an aircraft on a runway from a return point (A) to a completion point (D), at which the aircraft touches the runway, by means of a data-processing device on-board said aircraft, which device is configured to be connected to an altimeter and a deviation meter, the method including: a return-navigation assistance phase including guidance of the aircraft, on the basis of measurements of the azimuth deviation of the aircraft relative to a reference direction linking said return point (A) and the position of the deviation meter (E) transmitted by said deviation meter, from the return point (A) towards the position of the deviation meter (E), determination of the position of the aircraft at a predetermined capture point (B) that is aligned with the return point (A) and the position of the deviation meter (E), and guidance of the aircraft along a predetermined path from the capture point (B) to a predetermined holding point (C), which is approximately aligned with the axis of the runway, on the basis of altitude data provided by the altimeter and heading and speed data relating to the aircraft, a landing assistance phase including guidance from the holding point (C) to the completion point (D).
calculation (105) of a second control signal to be generated during a second period on the basis of the first control signal and the relative-positioning data, the second control signal being chosen in such a way as to minimize an average of accumulated angular errors in the angular measurements acquired by the gyroscope during the entirety of the first and second period, the angular errors being expressed in the platform coordinate system.
G01C 25/00 - Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
G01C 19/567 - Turn-sensitive devices using vibrating masses, e.g. vibratory angular rate sensors based on Coriolis forces using the phase shift of a vibration node or antinode
G01C 19/5776 - Signal processing not specific to any of the devices covered by groups
G01C 19/56 - Turn-sensitive devices using vibrating masses, e.g. vibratory angular rate sensors based on Coriolis forces
The present invention concerns a method for switching, by a local processing unit (1,2) of a flight control system of an aircraft, configured to control at least one local actuator, connected to at least one local sensor and connected via at least one link (3,4) to an opposite processing unit (2,1) configured to control at least one opposite actuator and be connected to at least one opposite sensor, said local processing unit (1,2) being further configured to be connected to backup communication means (13,14) enabling data exchanges between the local processing unit (1,2) and the opposite processing unit (2,1) in the case of failures of the links connecting same (3,4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14), comprising steps of: •—sending, to the opposite processing unit (2,1), acquisition data relative to the at least one local sensor and actuator data relative to the at least one local actuator, •—receiving, from the opposite processing unit (2,1), acquisition data relative to the at least one opposite sensor and actuator data relative to the at least one opposite actuator, •—receiving an item of opposite health data and determining an item of local health data, •—switching said local processing unit (1,2) from a first state to a second state chosen from an active state (15), a passive state (16) and a slave state (18), depending on the opposite health data received and the local health data determined.
G06F 11/20 - Error detection or correction of the data by redundancy in hardware using active fault-masking, e.g. by switching out faulty elements or by switching in spare elements
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
7.
Method for manufacturing a part out of a metal matrix composite material, and related device
A method (S) for manufacturing a part (1) out of a metal matrix composite material, including the following steps: opening (S1) a device (10) that includes a supporting portion (14) and a molding portion (14); placing (S2) a fibrous reinforcement into the device (10); sealably closing (S3) the device (10) by providing a space between the fibrous reinforcement (2) and the device portions; feeding (S4) the molten metal matrix (3) into the device (10) such as to fill the space between the fibrous reinforcement (2) and the device portions (13, 14); and applying (S5) a force onto the equipment (10) such as to impregnate the fibrous reinforcement (2) with the metal matrix (3).
B22D 19/02 - Casting in, on, or around, objects which form part of the product for making reinforced articles
B22D 19/14 - Casting in, on, or around, objects which form part of the product the objects being filamentary or particulate in form
B22D 18/02 - Pressure casting making use of mechanical pressing devices, e.g. cast-forging
B22D 18/06 - Vacuum casting, i.e. making use of vacuum to fill the mould
B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedureSelection of compositions therefor
B22D 25/06 - Special casting characterised by the nature of the product by its physical properties
B22D 27/11 - Treating the metal in the mould while it is molten or ductile by using pressure making use of mechanical pressing devices
C22C 47/06 - Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element
C22C 49/14 - Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
D06M 11/83 - Treating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with inorganic substances or complexes thereofSuch treatment combined with mechanical treatment, e.g. mercerising with metalsTreating fibres, threads, yarns, fabrics or fibrous goods made from such materials, with inorganic substances or complexes thereofSuch treatment combined with mechanical treatment, e.g. mercerising with metal-generating compounds, e.g. metal carbonylsReduction of metal compounds on textiles
8.
Landing gear for an aircraft comprising an obstacle detector
The invention relates to an actuator (4) for controlling a horizontal stabilizer (3) of an aircraft, including: a primary channel including a screw (6) and a primary nut (7), the primary nut (7) being suitable for engaging with the screw (6), such that a rotation of the screw (6) relative to the primary nut (7) about a rotation axis (X) causes the primary nut (7) to translate relative to the screw (6) along the axis (X), such as to move the horizontal stabilizer (3); a secondary channel including a secondary part (25, 28), and a housing (23, 26), the secondary part (25, 28) being mounted in the housing (23, 26) with play between the secondary part and the housing, in which the secondary channel also includes a play take-up device (27), configured to, in the event of a breakdown of the primary channel causing the secondary part (25, 28) to move relative to the housing, eliminate the play between the secondary part (25, 28) and the housing (23, 26) such as to keep the secondary part (25, 28) in contact with the housing (23, 26).
B64C 13/50 - Transmitting means with power amplification using electrical energy
G01D 5/14 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage
patents
