An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.

A propeller for an aircraft having a fuselage and a pair of fixed wings includes a mounting member secured to at least one wing. At least one blade is rotatably connected to each mounting member and has an airfoil shape. The at least one blade is in a locked condition during take-off and landing of the aircraft extending parallel to a leading edge of the wing and in an unlocked, rotating condition during flight for propelling the aircraft.

Embodiments provide a propeller ground stop mechanism configured to keep an unpowered propeller of an aircraft (e.g. when the aircraft is on the ground and not operating) static. The propeller is prevented from rotating due to external forces (e.g. an air flow caused by wind, manual rotation of the propeller). When the propeller is powered, and the propeller is providing thrust, the propeller ground stop mechanism automatically disengages and does not provide any drag. Among various benefits, the propeller ground stop mechanism provides added safety to the ground support personnel.

A rotary wing aircraft has a nacelle, at least one rotor provided with at least one blade, a braking device to stop the rotation of the rotor, an emergency parachute provided with a canopy and with a rope, a rocket to start the extraction of the canopy from the nacelle, two operating devices to operate the braking device and the rocket, respectively, and a single actuator device to operate both the operating devices.

Disclosed is a drone having at least one rotor. The at least one rotor comprises a mast and at least two blades having a proximal end and a distal end. The at least two blades are arranged in connection with the mast by their proximal ends. The at least one of the blades comprises an electrically conductive element extending a distance D between its distal end and its proximal end. The electrically conductive element is electrically coupled with means for stopping the blades, thus forming an electrical circuit. The means for stopping the blades is arranged to be actioned when at least one electrical property of the electrical circuit change.

Systems and methods for delivering packages via aerial vehicles are disclosed. The system can comprise a label that includes a parachute to enable the packages to be dropped from the aerial vehicle, yet land at the package's destination without damage. The system can include a self-adhesive backing, a plurality of parachute cords, a parachute, and a breakaway cover. The parachute cords can include a shock absorber to reduce the shock on the package of the parachute opening. The parachute and/or the breakaway cover can include graphics to provide address, velocity, or spin information for the package. The parachute cords can include a harness to separate the cords and reduce tangling of the cords and spinning of the parachute canopy with respect to the package.

A motor assembly that includes a motor (102) having a rotatable shaft, a hub coupled to the rotatable shaft, the hub having a propeller indexer to receive a propeller (104), when the propeller is present, a sensor trigger rotatable with the shaft (100) and positioned at a propeller offset angle .sub.PROP from the propeller indexer, and a sensor coupled to the motor and positioned to detect the sensor trigger so that the propeller indexer may be positioned at the propeller offset angle .sub.PROP from the sensor through rotation of the shaft so that said sensor is proximate to the sensor trigger.

Generally, a mechanically self-regulating propeller is described which may have a central hub unit disposed around a shaft member, at least two blades coupled to the central hub unit, at least one timing hub coupled to each of the at least two blades, and a hydraulic unit coupled to the at least one timing hub. The at least one timing hub is slidably engaged to the shaft member. When not in use the blades lay substantially parallel to the central hub unit. When the central hub unit is rotated the blades begin to open or fan out to a position that is substantially perpendicular to the central hub unit. The propeller may be used any number of implementations including vehicles, generators, and any other mechanism requiring a propeller or similarly structured device.

A motor assembly that includes a motor (102) having a rotatable shaft, a hub coupled to the rotatable shaft, the hub having a propeller indexer to receive a propeller (104), when the propeller is present, a sensor trigger rotatable with the shaft (100) and positioned at a propeller offset angle .sub.PROP from the propeller indexer, and a sensor coupled to the motor and positioned to detect the sensor trigger so that the propeller indexer may be positioned at the propeller offset angle .sub.PROP from the sensor through rotation of the shaft so that said sensor is proximate to the sensor trigger.

A propulsor brake lock system includes an aircraft propulsor, a reduction gear assembly, a brake shaft, and a brake assembly. The aircraft propulsor includes a propeller having a propeller input shaft coupled thereto. The reduction gear assembly includes at least an input gear and an output gear. The input gear and output gear are both rotatable with the propeller input shaft. The brake shaft is coupled to, and is rotatable with, the output gear. The brake assembly is coupled to the brake shaft and is moveable between a disengaged position, in which the brake shaft may rotate whenever the output gear rotates, and an engaged position, in which the brake shaft is prevented from rotating, thereby preventing rotation of the output gear, the input gear, and the propeller input shaft.