An aircraft is described comprising a transmission unit with a first module and a lubrication system; the first module comprises a casing and a movable member; the lubrication system comprises a header, a nozzle fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing of the first module, a collection tank for the lubricating fluid injected by the nozzle, and recirculation means designed to cause the recirculation of the lubricating fluid from the collection tank to the feed header; the first module comprises a valve available in a first configuration, in which it enables the outflow of said lubricating fluid from said module to the recirculation means when the pressure of the lubricating fluid inside the header is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module from the recirculation means when the pressure of the lubricating fluid inside the header is less than the threshold value.

A VTOL with a redundant propulsion system, the redundant propulsion system comprising two independent groups of rotors, and each group of rotors are driven by an independent engine. When any failure is detected in the first group of rotors or in its connecting parts, the second group of rotors will be accelerated to take over the first group of rotors to supply flying thrust, or vice versa. The VTOL is quiet, low cost, easy to maneuver and highly reliable, and can be used in future personal transportation.

A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative $\left(\frac{dN2i}{dt}\right)”,$
and automatically stopping the engine when the current derivative $\left(\frac{dN2i}{dt}\right)$
changes sign.

An electric aircraft comprises a single passenger seat, vertical takeoff and landing capable rotorcraft with an amphibious undercarriage for ground or water landing and takeoff. An electrical power system includes an independent battery for each motor with quick-swap mechanism to enable drained batteries to be easily removed for external charging and swapped for a charged replacement battery. A ballistic recovery system may be deployed to safely land the aircraft in the event of an emergency and may be manually deployed in response to the passenger activating a deployment mechanism integrated into handles within the cockpit. An on-board flight control system includes an automated flight controller that places constraints on flight maneuvers, and a manual flight controller provides a passenger with a limited level of control over the flight.

A method of analyzing a vibratory signal derived from rotation of at least one moving part belonging to a rotary mechanism forming all or part of a drive train for transmitting drive torque, the rotary mechanism being fitted to an aircraft and the method comprising at least one first measurement step including measuring vibration in at least one direction and generating a vibratory signal representative of the operation of the rotary mechanism as a function of time, the first measurement step being performed by means of at least one vibration sensor; and at least one second measurement step including measuring an angular position of the moving part, the moving part having at least one degree of freedom to move in rotation about a respective axis of rotation Z. Such an analysis method makes it possible to determine at least one usable range for the vibratory signal.

An aircraft with a safety distance display apparatus that is configured to display a visual indication on an obstacle for representing a current distance between the aircraft and the obstacle, wherein the safety distance display apparatus comprises a first light source that emits a first light signal in a first predefined direction, and a second light source that emits a second light signal in a second predefined direction, and wherein the first light signal crosses the second light signal at a predetermined safety distance from the aircraft.

A system for detecting and neutralizing a target aerial vehicle comprises a counter-attack unmanned aerial vehicle (UAV) comprising a flight body and a flight control system supported about the flight body operable to facilitate flight of the UAV, and an aerial vehicle countermeasure supported by the flight body. The system can comprise an aerial vehicle detection system comprising at least one detection sensor operable to detect a target aerial vehicle while in-flight, and operable to provide command data to the counter-attack UAV to facilitate interception of the target aerial vehicle by the counter-attack UAV. Upon interception of the target aerial vehicle, the counter-attack UAV is operable to disrupt operation of the detected target aerial vehicle with the aerial vehicle capture countermeasure, thereby neutralizing the target aerial vehicle. The counter-attack UAV and systems may be autonomously operated. Associated systems and methods are provided.

Systems and methods for printed multifunctional skins are disclosed herein. In one embodiment, an aerodynamic apparatus includes an aerodynamic structure having a first surface exposed to an outside environment, and a second surface exposed to an inside environment. A printed sensor is carried by the first surface of the aerodynamic structure, electronic components are carried by the second surface of the aerodynamic structure, and at least one printed conductive trace is carried by the first surface and the second surface. The printed conductive trace electrically connects the printed sensor with the electronics.

A method of operating an electrically powered rotorcraft of the type having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N≥4, under a failure condition preventing ordinary operation of the rotorcraft. The method includes entering a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled. The method also includes using electrical braking associated with a selected group of the rotors to control yaw of the rotorcraft.

Methods and systems are configured to store user data and control access to the user data, wherein the data is stored remotely from the user (such as external to a user's computing device) and the user's data is maintained anonymously. Content is stored in association with a user identifier and access by third parties is controlled by linked third party identifiers.