Abstract: A hybrid engine installation (200) includes drive element (204) suitable for driving a mechanical element (BTP, BTA) in rotation. In addition, the hybrid engine installation is remarkable in that it includes at least one gas turbine (253, 254) and at least one electric motor (201) mechanically linked to the drive element (204) to drive it in rotation.

Abstract: A buoyancy system (2) comprising at least one float (3) and deployment means (30) for deploying said float (3), said buoyancy system (2) having engagement means (5) for activating the deployment means (30) of said float (3), said buoyancy system (2) including at least two immersion sensors (20) for issuing an order for automatic deployment of said float (3) to the deployment means (30). Said engagement means (5) are activated only manually, said deployment means (30) are provided with a memory (31) containing a pre-established list of events, and said deployment means (30) deploy each float (3) when a predetermined event occurs.

Abstract: The present invention relates to a method and an associated device for automatically jettisoning an external load (4) that is reversibly suspended from a release-hook (12) of an aircraft fuselage (2) by a sling (13), which method comprises: measuring the angle (?) between said sling (13) and a vertical axis in elevation of the aircraft; and activating automatic jettisoning when firstly said angle (?) exceeds an upper limit (LSUP), and secondly said sling (13) is directed towards the rear (4?) of the aircraft, thereby making it possible, optionally, to proceed with jettisoning said external load (4).

Abstract: Apparatus for regulating the flow rate of fuel to a turboshaft engine in acceleration or in deceleration, the engine having a free turbine and a core engine, the apparatus comprising sensors transmitting information to regulator means, said information relating: to a first speed of rotation NTL of said free turbine; to a second speed of rotation Ng of said engine's gas generator; to an internal temperature T4 of the gas at the inlet to the free turbine; to the external pressure; and to the external temperature. The apparatus further comprises control means activated by said regulator means to actuate a fuel metering system of the engine. In addition, the regulator means evaluates the flow rate of fuel to be supplied to the engine in acceleration or in deceleration on the basis of at least one optimum regulation relationship, said regulation relationship determining a main modulated flow rate as a function of a modulated speed of rotation.

Abstract: The present invention relates to a power plant (10) having a single engine (13) together with both a main gearbox (MGB) suitable for driving the rotary wing (3) of a helicopter (1) and a tail gearbox (TGB) suitable for driving an anti-torque rotor (4) of a helicopter (1). The power plant (10) also includes a first electric motor (11) mechanically connected to said main gearbox (MGB) in order to be capable of driving said main gearbox (MGB), and a second electric motor (12) mechanically connected to said tail gearbox (TGB) in order to be capable of driving said tail gearbox (TGB).

Abstract: A method and a device for obtaining a predictive vertical speed of a rotorcraft, the device constituting a predictive vertical speed indicator (1) that includes at least: first elements (1?) for measuring the instantaneous vertical speed v of a rotorcraft; second elements (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; and third elements (3) for calculating the predictive vertical speed vAP of a rotorcraft, the third elements being connected firstly to the first and second elements via respective first and second connections (l1, l2) and containing in memory predetermined values for the minimum-power speed VY and a characteristic constant k that are constants relating to the rotorcraft of a given type of rotorcraft.

Abstract: A method and a device (D) for detecting and signaling the approach to a vortex domain by a rotorcraft, the device includes: first elements (1) for measuring the instantaneous vertical speed v of a rotorcraft; second elements (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; third elements (3) constituting a database BDD relating to representing at least one instantaneous vortex domain; fourth elements (4) connected via first, second, and third connections (l1, l2, l3) respectively to the first, second, and third elements, the fourth elements being designed to detect the approach to a vortex domain by the rotorcraft; and fifth elements (5) for signaling the approach to a vortex domain by the rotorcraft, the fifth elements being connected to the fourth elements (4) via a connection (l4).

Abstract: The present invention relates to a method and an associated device for automatically jettisoning an external load (4) that is reversibly suspended from a release-hook (12) of an aircraft fuselage (2) by a sling (13), which method comprises: measuring the angle (?) between said sling (13) and a vertical axis in elevation of the aircraft; and activating automatic jettisoning when firstly said angle (?) exceeds an upper limit (LSUP), and secondly said sling (13) is directed towards the rear (4?) of the aircraft, thereby making it possible, optionally, to proceed with jettisoning said external load (4).

Abstract: A hybrid engine installation (200) includes drive element (204) suitable for driving a mechanical element (BTP, BTA) in rotation. In addition, the hybrid engine installation is remarkable in that it includes at least one gas turbine (253, 254) and at least one electric motor (201) mechanically linked to the drive element (204) to drive it in rotation.

Abstract: Apparatus for regulating the flow rate of fuel to a turboshaft engine in acceleration or deceleration, the engine having a free turbine and a core engine, the apparatus including sensors transmitting information to regulator elements, the information relating: to a first speed of rotation NTL of the free turbine; to a second speed of rotation Ng of the engine's gas generator; to an internal temperature T4 of the gas at the inlet to the free turbine; to the external pressure; and to the external temperature. The apparatus further includes control elements activated by the regulator to actuate a fuel metering system of the engine. The regulator evaluates the flow rate of fuel to be supplied to the engine in acceleration or deceleration on the basis of at least one optimum regulation relationship, which determines a main modulated flow rate as a function of a modulated speed of rotation.

Abstract: The invention relates to a rotorcraft (10) having a main rotor (11), a turbine engine (13), and a transmission mechanism (MGB) coupled to the rotor and to the engine to enable the engine to drive the rotor. The engine has a free turbine (132) connected to the transmission mechanism (MGB) by a shaft (15, 15a, 15b, 16, 18). The rotorcraft includes an external compressor (19) arranged to be driven by the free turbine (132) or by an electric motor, together with an air-transport duct (21) connecting the external compressor (19) to the engine so as to deliver the air that has been compressed by the external compressor to the inlets (22) of the engine.

Abstract: The present invention relates to a method and a device for obtaining a predictive vertical speed of a rotorcraft, the device constituting a predictive vertical speed indicator (1) that comprises at least: first means (1?) for measuring the instantaneous vertical speed v of a rotorcraft; second means (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; and third means (3) for calculating the predictive vertical speed vAP of a rotorcraft, the third means being connected firstly to the first and second means via respective first and second connections (l1, l2) and containing in memory predetermined values for the minimum-power speed VY and a characteristic constant k that are constants relating to said rotorcraft of a given type of rotorcraft.

Abstract: A method and a device (D) for detecting and signaling the approach to a vortex domain by a rotorcraft, the device includes: first elements (1) for measuring the instantaneous vertical speed v of a rotorcraft; second elements (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; third elements (3) constituting a database BDD relating to representing at least one instantaneous vortex domain; fourth elements (4) connected via first, second, and third connections (l1, l2, l3) respectively to the first, second, and third elements, the fourth elements being designed to detect the approach to a vortex domain by the rotorcraft; and fifth elements (5) for signaling the approach to a vortex domain by the rotorcraft, the fifth elements being connected to the fourth elements (4) via a connection (l4).

Abstract: Apparatus for regulating the flow rate of fuel to a turboshaft engine in acceleration or in deceleration, the engine having a free turbine and a core engine, the apparatus comprising sensors transmitting information to regulator means, said information relating: to a first speed of rotation NTL of said free turbine; to a second speed of rotation Ng of said engine's gas generator; to an internal temperature T4 of the gas at the inlet to the free turbine; to the external pressure; and to the external temperature. The apparatus further comprises control means activated by said regulator means to actuate a fuel metering system of the engine. In addition, the regulator means evaluates the flow rate of fuel to be supplied to the engine in acceleration or in deceleration on the basis of at least one optimum regulation relationship, said regulation relationship determining a main modulated flow rate as a function of a modulated speed of rotation.

Abstract: The present invention provides a device enabling the collective pitch of the blades of the main rotor of a single-engined rotorcraft to be reduced automatically in the event of an engine failure. The device comprises an actuator which increases the collective pitch of the blades above a predefined threshold, and which decreases the collective pitch below the predefined threshold. The actuator is arranged on a bell crank of the mixing unit of the rotorcraft.

Abstract: The present invention relates to a pilot indicator for a rotorcraft provided with a main rotor and at least one gas turbine engine. The indicator has first and second sensors delivering information relating respectively to a first speed of rotation Nr corresponding to said main rotor, and a second speed of rotation NTL corresponding to the free turbine of said engine. The indicator is also provided with display means provided with a display screen for displaying the first and second present values respectively for the first and second speeds of rotation Nr and NTL. In addition, said processor means determines an estimated value for the first speed of rotation Nr.

Abstract: A pilot indicator is provided for an aircraft provided with at least one gas turbine engine. The indicator includes a set of sensors delivering information relating to different monitoring parameters of the engine, namely: the speed of rotation Ng of the gas generator, the temperature T4 of the gas at the inlet of the free turbine, and the torque Cm. The indicator is also provided with a processor for processing information from the sensors, and a display provided with a display screen. In addition, the processor determines an estimated value of a limiting parameter, where the limiting parameter is that one of the monitoring parameters that is closest to its limit.

Abstract: The present invention relates to a pilot indicator for a rotorcraft provided with a main rotor and at least one gas turbine engine. The indicator has first and second sensors delivering information relating respectively to a first speed of rotation Nr corresponding to said main rotor, and a second speed of rotation NTL corresponding to the free turbine of said engine. The indicator is also provided with display means provided with a display screen for displaying the first and second present values respectively for the first and second speeds of rotation Nr and NTL. In addition, said processor means determines an estimated value for the first speed of rotation Nr.

Abstract: A pilot indicator is provided for an aircraft provided with at least one gas turbine engine. The indicator includes a set of sensors delivering information relating to different monitoring parameters of the engine, namely: the speed of rotation Ng of the gas generator, the temperature T4 of the gas at the inlet of the free turbine, and the torque Cm. The indicator is also provided with a processor for processing information from the sensors, and a display provided with a display screen. In addition, the processor determines an estimated value of a limiting parameter, where the limiting parameter is that one of the monitoring parameters that is closest to its limit.

Abstract: Apparatus for regulating the flow rate of fuel to a turboshaft engine in acceleration or deceleration, the engine having a free turbine and a core engine, the apparatus including sensors transmitting information to regulator elements, the information relating: to a first speed of rotation NTL of the free turbine; to a second speed of rotation Ng of the engine's gas generator; to an internal temperature T4 of the gas at the inlet to the free turbine; to the external pressure; and to the external temperature. The apparatus further includes control elements activated by the regulator to actuate a fuel metering system of the engine. The regulator evaluates the flow rate of fuel to be supplied to the engine in acceleration or deceleration on the basis of at least one optimum regulation relationship, which determines a main modulated flow rate as a function of a modulated speed of rotation.