Abstract: A method of managing the braking of an aircraft having landing gear with wheels fitted with friction brakes and with auxiliary brakes that enable energy to be dissipated by other than friction. The method comprises the steps of, (1) when braking is requested, testing the braking parameters to determine whether the aircraft is in a braking situation for which the friction brakes are not essential for providing the requested braking, and (2) performing the requested braking by giving priority to actuating the auxiliary brakes so long as the aircraft remains within the braking situation, and actuating the friction brakes only if the aircraft departs from the braking situation.

Abstract: A method manages energy of a power unit of a hybrid vehicle. The power unit includes at least one internal combustion engine and an electric drive machine, coupled to wheels of the vehicle by a transmission with discrete ratios. The method includes minimizing, at each operating point of the energy, an energy criterion linked to a sum of consumption of the internal combustion engine and an electrical consumption of the electrical machine multiplied by an equivalence factor weighting a supply of energy from the internal combustion engine and a supply of energy of electrical origin. The minimized criterion is a mixed criterion which is a sum of an energy criterion and a discomfort criterion linked to management of kinematic modes of the transmission.

Abstract: A method of determining an equivalence energy factor representing weighting applied between an infeed of energy of thermal origin and an infeed of energy of electrical origin, to minimize on an operating point overall energy consumption of a hybrid motor propulsion plant for an automotive vehicle including a heat engine and at least one electric motor powered by a battery. This factor is controlled in a discrete manner as a function of an instantaneous state of energy of the battery, and of an energy target, and as a function of the vehicle running conditions.

Abstract: A method manages energy of a power unit of a hybrid vehicle. The power unit includes at least one internal combustion engine and an electric drive machine, coupled to wheels of the vehicle by a transmission with discrete ratios. The method includes minimizing, at each operating point of the energy, an energy criterion linked to a sum of consumption of the internal combustion engine and an electrical consumption of the electrical machine multiplied by an equivalence factor weighting a supply of energy from the internal combustion engine and a supply of energy of electrical origin. The minimized criterion is a mixed criterion which is a sum of an energy criterion and a discomfort criterion linked to management of kinematic modes of the transmission.

Abstract: A method of estimating temperature at a core of a module of a traction battery of an electric or hybrid vehicle in which is packaged a plurality of electric charge accumulating elements, the method including: measuring a temperature at a level of an exterior wall of the battery module; and calculating an estimation of the temperature at the core of the battery module on the basis of the measurement of the temperature.

Abstract: A method of determining an equivalence energy factor representing weighting applied between an infeed of energy of thermal origin and an infeed of energy of electrical origin, to minimize on an operating point overall energy consumption of a hybrid motor propulsion plant for an automotive vehicle including a heat engine and at least one electric motor powered by a battery. This factor is controlled in a discrete manner as a function of an instantaneous state of energy of the battery, and of an energy target, and as a function of the vehicle running conditions.

Abstract: 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: estimating at each instant during the turning movement: an instantaneous total power developed by all of the independent drive devices in response to the commands; and an instantaneous mean angular acceleration for all of the wheels; and adapting the commands to the independent drive devices such that the total instantaneous power developed by all of the independent drive devices is minimized, while conserving the mean angular acceleration.

Abstract: A method of estimating temperature at a core of a module of a traction battery of an electric or hybrid vehicle in which is packaged a plurality of electric charge accumulating elements, the method including: measuring a temperature at a level of an exterior wall of the battery module; and calculating an estimation of the temperature at the core of the battery module on the basis of the measurement of the temperature.

Abstract: A method of controlling a yawing movement of an aircraft running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels. The method comprises the steps of (1) on the basis of a yaw rate setpoint {dot over (?)}c, determining a wheel-steering prepositioning angle ?p; and (2) using closed-loop control which as its input has the yaw rate setpoint and which generates a command to steer the bottom part in order to steer it through a steering angle ?c equal to the sum of this prepositioning angle ?p and of an angle ?z which is determined taking account of an error between the yaw rate setpoint {dot over (?)}c and the measured yaw rate {dot over (?)}m when the steerable bottom part is steered by the steering angle ?c.

Abstract: The present disclosure relates to an pneumatic hybrid internal combustion engine with at least one combustion chamber composed of a cylinder in which a piston is arranged mechanically interconnected to a crank shaft via a piston rod. An inlet valve and an exhaust valve are both mechanically interconnected via a valve gear to the crank shaft. The engine further includes at least one charge valve which is actuated by a charge valve actuator in a fully variable manner such that the engine can be operated in a four stroke hybrid mode.

Abstract: The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels.

Abstract: The invention provides a method of managing the braking of an aircraft having a plurality of brakes comprising friction elements, the method comprising the following steps for at least one group of brakes: estimating an energy level (?E) to be dissipated by the brakes of the group; and estimating individual braking setpoints (Fi) for each of the brakes of the group so that the individual braking setpoints make it possible, at least under normal operating conditions of the brakes, to implement braking that dissipates said energy level, the individual braking setpoints also being determined so as to satisfy at least one other given operating objective.

Abstract: A braking control method that includes: (1) regularly updating a grip model representative of a relationship between a coefficient of friction and a wheel slip rate; (2) determining, with an iterative calculation process including a plurality of calculation cycles a variation of a braking setpoint in a given prediction horizon, the variation of the braking setpoint in the given prediction horizon being established using the regularly updated grip model and its characteristic shape and so that the variation of the braking setpoint in the given prediction horizon complies with the braking order and complies with a given calculation constraint which is function of the wheel slip rate; and (3) retaining as the generated braking setpoint a value of the braking setpoint in the given prediction horizon which corresponds to a first calculation cycle of the plurality of calculation cycles of the iterative calculation process.

Abstract: The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels.

Abstract: The invention relates to a method of controlling a yawing movement of an aircraft running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels. According to the invention, the method comprises the steps of: on the basis of a yaw rate setpoint {dot over (?)}c, determining a wheel-steering prepositioning angle ?p; using closed-loop control which as its input has the yaw rate setpoint and which generates a command to steer the bottom part in order to steer it through a steering angle ?c equal to the sum of this prepositioning angle ?p and of an angle ?z which is determined taking account of an error between the yaw rate setpoint {dot over (?)}c and the measured yaw rate {dot over (?)}m when the steerable bottom part is steered by the steering angle ?c.

Abstract: 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: estimating at each instant during the turning movement: an instantaneous total power developed by all of the independent drive devices in response to the commands; and an instantaneous mean angular acceleration for all of the wheels; and adapting the commands to the independent drive devices such that the total instantaneous power developed by all of the independent drive devices is minimized, while conserving the mean angular acceleration.

Abstract: The invention relates to a method of managing the braking of an aircraft having landing gear with wheels fitted with friction brakes and with auxiliary brakes that enable energy to be dissipated by means other than friction, the method comprising the steps of: when braking is requested, testing the braking parameters to determine whether the aircraft is in a braking situation for which the friction brakes are not essential for providing the requested braking; and performing the requested braking by giving priority to actuating the auxiliary brakes so long as the aircraft remains within said braking situation, and actuating the friction brakes only if the aircraft departs from said braking situation.

Abstract: The present disclosure relates to an pneumatic hybrid internal combustion engine with at least one combustion chamber composed of a cylinder in which a piston is arranged mechanically interconnected to a crank shaft via a piston rod. An inlet valve and an exhaust valve are both mechanically interconnected via a valve gear to the crank shaft. The engine further includes at least one charge valve which is actuated by a charge valve actuator in a fully variable manner such that the engine can be operated in a four stroke hybrid mode.

Abstract: A method of distribution braking between the brakes of an aircraft. The method includes a first step of estimating a braking force objective and a steering torque objective to be achieved by the brakes of the aircraft. It also includes the steps of defining at least two groups of brakes (12, 13) and determining, for each group, a braking level that is to be achieved by the group. The braking levels being calculated in such a manner that braking performed in application of the braking levels is, at least under normal operating conditions of the brakes, in compliance with a braking force objective and with a steering torque objective.

Abstract: A method of distribution braking between the brakes of an aircraft. The method includes a first step of estimating a braking force objective and a steering torque objective to be achieved by the brakes of the aircraft. It also includes the steps of defining at least two groups of brakes (12, 13) and determining, for each group, a braking level that is to be achieved by the group. The braking levels being calculated in such a manner that braking performed in application of the braking levels is, at least under normal operating conditions of the brakes, in compliance with a braking force objective and with a steering torque objective.