Safran

Safran Aircraft Engines

Safran Power Units

Safran Landing Systems

Bruno Thoraval

Nicolas Claude Parmentier

Pierre Froment

Jean-François Rideau

Jean-Francois Rideau

René Meunier

Pierre-Yves Liegeois

Clélia Level

Christophe Maury

An electric propulsion architecture for a multi-rotor vertical take-off and landing aircraft includes four electric generators; and four pairs of rotors. For each rotor, a first electric motor is configured to operate in an active mode, and a second electric motor is configured to be in a standby mode and being able to operate in an active mode in a breakdown situation. A propeller is coupled to the electric motors, wherein, for each pair of rotors, one of the electric generators powers the first electric motors, and another of the electric generators powers the second electric motors. The rotors form counter-rotors and for each counter-rotor, the electric motors are each powered by one of the four electric generators so that the four electric generators power the electric motors of the rotors of each counter-rotor.

Electric propulsion architecture for a multi-rotor vertical take-off and landing aircraft and method for controlling such an architecture

A method for securing an aircraft landing gear wheel drive actuator in an open position of the wheel, the drive actuator being movably mounted on the landing gear between said open position in which it is remote from the wheel and an engaged position in which it cooperates with the wheel to ensure its rotational drive, a displacement actuator being coupled to the drive actuator to move same between the two positions, and a locking member being provided to lock the drive actuator in the open position. The method includes holding the controlled displacement actuator to move the drive actuator to the open position, while the drive actuator is locked in the open position.

Method for securing an aircraft wheel drive actuator in an open position

An aircraft turboprop engine has at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the means for supplying air has at least one compressor of which the rotor is coupled to the low-pressure body. The compressor has an air inlet connected to means for bleeding air from an air inlet duct of the turboprop engine.

Supply of air to an air-conditioning circuit of an aircraft cabin from its turboprop engine

An aircraft turboprop engine includes at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the supply means has at least one compressor borne by the gearbox and of which the rotor is coupled to the low-pressure body by means of the gearbox.

An aircraft turboprop engine () including at least a low-pressure body () and a high-pressure body (), possibly also an intermediate-pressure body. At least one of the bodies includes a compressor. The low-pressure body drives a first gearbox () The turboprop engine also includes at least one load compressor () for supplying air to an air-conditioning circuit of an aircraft cabin. A rotor () of the load compressor is coupled to the low-pressure body. The load compressor () includes an air inlet () connected to a conduit () to bleed air from the compressor of the turboprop engine when all of the aforementioned bodies include only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies include at least two compressors.

Growing community of inventors

Moissy Cramayel, France

Bruno Thoraval