Messier-bugatti-dowty

Safran Landing Systems

Other

Messier-bugatti Inc.

Safran Electronics & Defense

David Frank

David Lemay

Yann Chamaillard

Michel Basset

Joël Zabulon

Jean-Baptiste Vaney

Dominique Onfroy

Jean-Pierre Garcia

François Bonigen

Joel Zabulon

Thierry Bickard

Arnaud Jacquet

Raphael Pierra

Jerome Fraval

Jérôme Fraval

Aurélien Doux

Emmanuel Brun

Gérard Léon Gissinger

Jean-Baptiste Lestage

Guillaume Fallet

Xavier Gallerand

Vincent Pavoine

Donny Warint

Jérôme Mehez

Raphaël Pierra

Jean-Luc Belleval

Jerome Mehez

Gerard Leon Gissinger

Joêl Zabulon

A strut for an aircraft landing gear is provided. The strut includes a casing configured to absorb landing forces applied to the aircraft landing gear. The casing includes a cavity in which an energy accumulator is housed. The energy accumulator can be a removable cartridge which can be inserted in the cavity. An aircraft landing gear comprising such a strut is also provided. An aircraft comprising at least one such landing gear having such a strut is also provided. A method for emergency deployment of such a landing gear, using energy stored in the energy accumulator integrated in the strut of the landing gear to deploy the landing gear is also provided.

Strut for aircraft landing gear equipped with an accumulator, landing gear comprising such a strut, and aircraft comprising at least one such landing gear

An aircraft wheel and brake assembly includes a wheel, a brake configured to brake the wheel, and a measurement device configured to measure the speed of rotation of the wheel. The brake includes at least one friction member, an actuator support, and at least one brake actuator carried by the actuator support and configured to exert a braking force selectively on the friction member. The measurement device includes a target and a sensing component for producing a measurement signal representative of the speed of rotation of the target. The aircraft wheel and brake assembly is configured in such a manner that, when assembled, the target is constrained to rotate with the wheel and the sensing component is mounted on the actuator support. The target and the sensing component is configured in such a manner that the sensing component detects rotation of the target.

Aircraft wheel and brake assembly

The invention relates to a device for braking a wheel, the device comprising: According to the invention, the control system is arranged to interrupt control of the first actuator or control of the second actuator in the event of the braking torque measured by the first sensor exceeding a predetermined braking torque limit.

Wheel braking device

An emergency braking method for aircraft, comprising using a progressing parking brake controlled by a lever () that can be actuated by the pilot between a '0%' position in which the brakes are connected to the return pressure of the aircraft, and a '100%' position in which the brakes are connected to the feed pressure of the aircraft, the lever being blockable in the 100% position in order to provide parking braking when the aircraft is stationary. According to the invention, the emergency braking method being characterized in that it comprises:

Emergency braking method for an aircraft

A measurement method for measuring the position of a movable body that is movable relative to a fixed body, the measurement method making use of a measurement device comprising a fixed portion for securing to the fixed body and a movable portion for securing to the movable body, the fixed portion including a first printed circuit () having formed thereon first tracks () defining at least one emission pattern () and also a plurality of measurement patterns (), the movable portion including a second printed circuit () having formed thereon second tracks () defining at least one reception pattern () and also at least one target pattern (), the first and second printed circuits being coupled together electromagnetically in such a manner that, when the emission pattern is excited by an excitation signal, an induced signal is received by the reception pattern and is then re-emitted by the target pattern, the measurement patterns then picking up measurement signals that are representative of the position of the target pattern, and thus also of the second printed circuit, of the movable portion, and of the movable body.

Method of measuring a position of a movable body relative to a fixed body

A measurement device for measuring speeds of rotation of at least two wheels of an aircraft undercarriage includes a measurement unit and a processor unit associated with each wheel. The measurement unit of each wheel is configured to transform the speed of rotation of the wheel into an electrical magnitude. The processor unit of each wheel is configured to acquire the electrical magnitudes produced by at least two measurement units in order to transform the electrical magnitudes into digital measurement signals representative of the speeds of rotation of at least two wheels, and in order to transmit the digital measurement signals to external equipment.

Device for measuring the speeds of rotation of at least two wheels of an aircraft undercarriage

The invention relates to a hydraulic circuit for operating an aircraft landing gear comprising: According to the invention, the depressurization valve is returned () in a stable manner to the depressurization position, and is moved into the open position only in response to the presence of supply pressure downstream of the general valve.

Hydraulic circuit for operating an aircraft landing gear

An aircraft braking system comprising: a first group (Ga) of actuators and a second group (Gb) of actuators. A first control module () is adapted, in a nominal mode, to control the first group, and in a reconfigured mode, to control the first group and the second group. A second control module () is adapted, in a nominal mode, to control the second group, and in a reconfigured mode, to control the first group and the second group. A monitoring unit adapted is adapted to monitor the first control module and the second control module, and to put the first control module into the reconfigured mode of operation when the monitoring unit detects a failure of the second control module, and to put the second control module into the reconfigured mode when the monitoring unit detects a failure of the first control module.

Aircraft braking system having a high level of availability

A method for measuring the rotation speed of a wheel including the steps of: acquiring an analog measurement signal (Sma) generated by a magnetic tachometer and containing a useful signal the frequency of which is representative of the rotation speed of the wheel; digitizing in real-time the analog measurement signal (Sma) in order to obtain a time-dependent digital measurement signal (Smnt); calculating a Fourier transform of the time-dependent digital measurement signal (Smnt) in order to obtain a frequency-dependent digital measurement signal (Smnf); and carrying out a frequency analysis in order to identify by a search for peaks a useful spectral line () so as to obtain the frequency of the useful signal and therefore the rotation speed of the wheel.

Method for measuring the rotation speed of a vehicle wheel

The invention relates to an aircraft undercarriage comprising: a strut () for connecting to the aircraft, a slide rod () slidably engaged in leaktight manner in the strut via the bottom opening, which rod carries at least one wheel at its bottom end, a diaphragm () carried by a support () attached to the top wall of the strut to cooperate in leaktight manner with an inside wall of the slide rod so as to define a first chamber (C) under the diaphragm inside the rod and completely filled with hydraulic fluid, and a second chamber (C) above the diaphragm and partially filled with hydraulic fluid, a throttle needle () secured to the slide rod and penetrating into a calibrated orifice () in the diaphragm so as to define a calibrated fluid passage between the first and second chambers, and angular connection means for imposing an angular position on the slide rod relative to the strut. According to the invention, the undercarriage includes at least one vane () fastened to the end of the throttle needle in order to extend inside a portion of the second chamber that is filled with hydraulic fluid.

Aircraft undercarriage with shimmy-damping means

The invention relates to a method for managing the braking of an aircraft fitted with undercarriages () bearing braked wheels (), the method comprising the step of generating braking commands by means of a braking computer () for each of the braked wheels as a function of longitudinal speed information representative of a longitudinal movement of the wheels in question, characterized in that there is placed at the bottom of the undercarriage, close to the braked wheels, a sensor adapted for generating a signal that can be used for generating the longitudinal speed information used for generating the braking commands.

Method for managing the braking of an aircraft with speed measurement close to the braked wheels

An aircraft landing gear comprising an axle () intended to receive a wheel () comprising a rim () mounted to rotate on the axle () by means of at least one rolling bearing (). The rolling bearing () comprises an inner ring () mounted around the axle () and an outer ring () rotationally secured to the rim () of the wheel (). The landing gear further comprising a measurement device () intended to perform measurements of at least one operating parameter of the landing gear. The measurement device () is incorporated in the rolling bearing () by being secured to one of the inner or outer rings of the rolling bearing ().

Aircraft landing gear

The invention relates to a management method for managing a turning movement of an aircraft taxiing on the ground, the aircraft having wheels each fitted with an independent drive device, in which method commands are generated for the independent drive devices so that at least some of those devices contribute to the turning movement. According to the invention, the method comprises the steps of:

Method of managing a turning movement of an aircraft taxiing on the ground

A method of managing the braking of an aircraft, the aircraft having a plurality of wheels R, . . . , R, each fitted with a brake F, . . . , Fadapted to generate a braking force in response to brake pedalsbeing depressed. The management method comprising the steps of: distributing the wheels fitted with respective brakes in at least two distinct groups G1, G2, G3, G'1, G&#x2032;2, G&#x2032;3; allocating respective relationships to each of the groups of wheels for determining how braking force varies as a function of the depression of the brake pedals; and modifying the distribution of the wheels in response to a predetermined event occurring.

Method of managing the braking of an aircraft

A method of managing the braking of an aircraft, the aircraft having a plurality of wheels R, . . . , R, each fitted with a brake F, . . . , Fadapted to generate a braking force in response to brake pedalsbeing depressed. The management method comprising the steps of (1) distributing the wheels fitted with respective brakes in at least two distinct groups G, G, G, G', G&#x2032;, G&#x2032;; (2) allocating respective braking relationships to each of the groups of wheels for determining how braking force varies as a function of the depression of the brake pedals; and (3) acting at predetermined intervals to permutate the allocation of the relationships to the groups in application of a predefined permutation relationship. The method also includes a step of modifying the permutation relationship in response to the occurrence of a predetermined event.

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Paris, France

David Frank