An aerial system includes an energy source arranged to power a propulsion unit to operate the system at a flight level, wherein the propulsion unit is in communications with a control device arranged to detect an aerodynamic interaction between the system and a surface proximate to the flight level and control the propulsion unit by use of the detected aerodynamic interaction.

An aerodynamic blade is provided and includes a blade body and a light module. The blade body includes an inboard end and a tip outboard of the inboard end. The blade body is connectable with a hub at the inboard end such that rotations of the hub drive rotations of the tip about a rotational axis. The light module is disposed in the tip and configured to activate in response to the rotations of the tip about the rotational axis to emit light visible at an exterior of the blade body.

An aerodynamic blade is provided and includes a blade body and a light module. The blade body includes an inboard end and a tip outboard of the inboard end. The blade body is connectable with a hub at the inboard end such that rotations of the hub drive rotations of the tip about a rotational axis. The light module is disposed in the tip and configured to activate in response to the rotations of the tip about the rotational axis to emit light visible at an exterior of the blade body.

A drone having a deployment device, which is configured such that the same can fly both in a folded mode and in a deployed mode. A platform 300 is arranged in the middle of the drone body 400, a deployment device 200 is arranged on the radial outer side of the platform 300, a fixed support table 230 extends outwardly from the radial outer surface of the platform 300, a rotating support table 210 is coupled to an outer free end of the fixed support table 230, and the rotating support table 210 is rotatably coupled to/supported on the outer free end of the fixed support table 230. Multiple propellers 100 are mounted on the radial outer ends of the rotating support table 210, respectively, a landing structure 600 is coupled to the body 400, and a holder 500 is mounted on the landing structure 600.

A rotor mast including an outer member defining a channel therethrough and an inner member disposed in the channel through the outer member, wherein the inner member is configured to apply a compressive force to the outer member.

A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.

An embodiment rotorcraft includes a main rotor, one or more flight controls connected to the main rotor and operational to control flight characteristics of the main rotor by pitching a nose of the rotorcraft upward, and a flight control computer (FCC) operable to determine an attitude command and to generate an adjusted attitude command by adjusting a magnitude of the attitude command according to an above ground level (AGL) altitude of the rotorcraft. The FCC is further operable to control a flight characteristic of the rotorcraft by sending the adjusted attitude command to one or more flight controls.

A method and a system for anticipating entry of a rotorcraft into a vortex domain, the rotorcraft having a main rotor with blades. After previously determining a specific frequency characterizing the proximity of a vortex domain, measurements are acquired of at least one parameter serving to characterize variation of the flow of air in the environment of the main rotor. Thereafter, the measurements are analyzed in order to isolate frequencies characteristic of the variation of each parameter, and the presence of the specific frequency is detected among the characteristic frequencies. Where appropriate, an alarm can then be issued in order to inform a pilot of the rotorcraft of the proximity of the vortex domain.

Provide is an agricultural chemical spraying drone with improved safety. An acceleration sensor and a contact detection sensor are combined to detect contact of a drone with an obstacle. In a case where the contact is detected, a retreat action such as hovering is taken. In addition, a message may be displayed on a control terminal, a warning sound may be generated, and a warning light may be turned on. Further, a structure capable of minimizing finger insertion accidents and minimizing interference with a rotor even in collision is adopted as a propeller guard.

Multi-rotor rotorcraft (10) comprise a fuselage (12), and at least four rotor assemblies (14) operatively supported by and spaced-around the fuselage (12). Each of the at least four rotor assemblies (14) defines a spin volume (24) and a spin diameter (26). Some multi-rotor rotorcraft (10) further comprise at least one rotor guard (50) that is fixed relative to the fuselage (12), that borders the spin volume (24) of at least one of the at least four rotor assemblies (14), and that is configured to provide a visual indication of the spin volume (24) of the at least one of the at least four rotor assemblies (14). Various configurations of rotor guards (50) are disclosed.