The present invention relates to a method for controlling a rotorcraft (1), said rotorcraft (1) comprising at least two combustion engines (2, 3), at least one control system (13) and a transmission system (4), said at least two engines (2, 3) being mechanically connected to said transmission…
The present invention relates to an aircraft (1) equipped with at least one exhaust duct (30) for ejecting gases from an engine (10), the exhaust duct (30) being partially housed in an internal housing (25) of the aircraft (1), the housing (25) being separated from an external environment (EXT)…
A control unit (46, 46') for an aircraft (1, 1') capable of hovering or for a flight simulation system of the aircraft (1, 1') is described; the control unit (46, 46') is programmed to: - receive in input a plurality of data associated with equipment (15) and/or kits (25) actually installed or…
La présente invention concerne un procédé d'optimisation du bruit généré par une installation motrice (10) d'un giravion (1) en vol, ladite installation motrice hybride (10) entraînant en rotation un rotor principal (2) dudit giravion (1) et étant munie d'au moins un moteur thermique (11), d'une…
A helicopter 10 includes a mast 14, a main rotor 16, an engine 32, a radiator 34 and a body cover 24. The engine 32 and the radiator 34 are housed in the body cover 24. The body cover 24 has an opening 66 penetrated by the mast 14; an opening 84 which is at a more forward position than the opening…
The method involves identifying a necessary speed (NR) of a swing drive of a main rotor (1) by a control unit (10). The necessary speed is calculated by application of a calculation rule integrating a set of calculation parameters. Another calculation rule integrates a third calculation parameter…
An exhaust system (100, 150, 170) for reducing infrared emissions of a rotary wing aircraft (10) includes a duct assembly having an inlet portion (102, 152, 172) and an outlet portion (104, 154, 174); the inlet portion configured to receive exhaust from an engine (E) of the aircraft; and the outlet…
The method involves selecting an idling mode for operation of a turbomotor (3) during a selection phase. The idling mode of operation is implemented during a regulation phase, where the idling operation mode is implemented according to hierarchical and operational conditions either through a…
The method involves operating a two-position selector to stop an engine i.e. turbomotor (3), or to set the engine into operation, during a selection step. The engine is controlled automatically to implement an idling mode of operation if collective pitch of blades (301) is less than a threshold…
The method involves defining two levels of performance of an aircraft (1), and determining a power margin based on a rotational speed of a gas generator (2'). Another power margin is determined based on a temperature of the gas. Each power margin is compared to a threshold to determine whether a…
The powerplant has a determination unit (10) determining three distinct use envelopes applied during a takeoff flight phase, a cruising flight phase and a landing flight phase, respectively. The determination unit communicates with a control unit (5) to indicate its use to the envelopes during…
The method involves activating an assisted piloting mode. A monitoring parameter e.g. gas ejection temperature, is maintained below a predetermined threshold when a limit indicator (10) is no longer in a position to display information. The monitoring parameter is maintained below a predetermined…
A system is disclosed for determining the total torque required at the main and tail rotors of a helicopter for use in feed-forward rotor torque anticipation which includes a polynomial neural network adapted and configured to predict the aerodynamic torque at the main and tail rotors with the…