ABSTRACT The invention relates to an emergency beacon (10) comprising a housing (11) fitted with a connector (12) for connecting the beacon to an antenna (13, 14) that is external to the housing. Inside the housing, the beacon comprises an incident sensor (15), a transmitter (16), and a detection and control member...

The invention relates to a method of inspecting the integrity of an avionics system(1) installed in an aircraft, said method consisting in inspecting the integrity in terms of electrical installation and data acquisition and transmission, wherein the method consists in: using an Ethernet network (4) connecting the...

The invention relates to a method of detecting and identifying a defect or an adjustment error of a rotorcraft rotor using an artificial neural network (ANN), the rotor having a plurality of blades and a plurality of adjustment members associated with each blade; the network (ANN) is a supervised competitive learnin...

The invention applies to a vibrator comprising two pairs (A, B) of unbalanced rotors (10 to 13) driven in synchronous rotation by a first motor, and a second motor arranged to drive a phase shifter mechanism so as to adjust a phase difference between the first pair of rotors and the second pair of rotors; the system...

This invention relates to a rotorcraft (21) comprising a fuselage (22) and an undercarriage (20) having skids (24, 25) interconnected by at least one cross-member (26, 27) together with connection means for connecting the cross-member to the fuselage and presenting angular stiffness that varies with varying sinking ...

The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body (20) of the engine (8) having a first end (21) opening out into the ambient atmosphere in front of the engine, and a second ...

The present invention relates to a blade with a swept-back tip for the rotary wings of an aircraft, the blade being formed of successive elemental cross sections. According to the invention, subdividing said blade (1) into different regions, the chord length L and the offset y'f of the center of pressure from the p...

The invention relates to a method of determining the position of an aircraft by combining inertial data with range data between the aircraft and satellites, in which: a) the range data is stored in a FIFO memory so as make delayed range data available at the output from the memory; b) the delayed range data is com...

The present invention relates to a method of flying safely and at low altitude in an aircraft, in which method unsafe relief (RO) of terrain is determined as is the position of at least one high point (4, 5) representing an obstacle (4", 5") overlying said unsafe relief (RO) . A main volume (VO) is added to said uns...

The present invention relates to a method of controlling and regulating a rotorcraft presenting a speed of advance that is high and stabilized, the rotorcraft including at least a main lift rotor (10), at least one variable pitch propulsion propeller (6) , and at least one power plant for driving the main rotor (s) ...

ABSTRACT The present invention relates to a foldable step unit (10) for a rotorcraft, the step unit being provided with a bottom step (16) and a stationary support (11) that is secured to the structure of the rotorcraft (2). The step unit (10) comprises a left side beam (14) and a right beam (15) hinged on said sta...