A multirotor aircraft is provided. The multirotor aircraft comprises a body comprising a main body and a camera assembly with a camera coupled to the main body; a frame connected to the body, comprising a multirotor propulsion system; and a drive system coupled with the body and the frame, for driving the body to rotate against the frame. With the multirotor aircraft, full unobstructed 360 yaw field of view of the camera in the upper or lower hemisphere can be obtained and the camera is in a safe position at takeoff and landing.

A contextual presentation system is disclosed. The contextual presentation system may include a communication device. Further, the communication device may be configured for receiving the at least one presentation content from an external content providing device. Further, the contextual presentation system may include a storage device configured for storing each of at least one presentation content and at least one presentation criteria. Further, the contextual presentation system may include at least one sensor configured for sensing at least one contextual data associated with the contextual presentation system. Further, the contextual presentation system may include a processing device communicatively coupled with each of the communication device, the storage device and the at least one sensor. Further, the contextual presentation system may include at least one presentation device configured for presenting the at least one presentation content based on the analyzing.

An airfoil profile for an aircraft, such as an unmanned aerial system. The airfoil profile includes a leading edge portion and a trailing edge portion that are spaced apart along a chordwise direction, an airfoil centroid; and an upper airfoil surface and a lower airfoil surface. The airfoil surfaces are shaped such that the pressure center of the lifting force is arranged at the same chord location as the airfoil centroid or closer to the trailing edge portion along the chordwise direction than the airfoil centroid. With this, a pitch-down momentum is generated that urges the leading edge portion towards a lower angle of attack.

A propeller for an aircraft includes at least two blades, arranged about a central hub, which is coupled to at least one motor, driven by a power source. At least one blade is attached to at least one sleeve member, configured for being in an outer sliding connection to a first cylindrical element of the hub. An inner surface of each of the at least one sleeve member includes at least one projecting element, configured to be in a sliding connection with a corresponding at least one first recessed guide path, arranged in an outer surface of the first cylindrical element. Each of the at least one first recessed guide path circles at least partly around the first cylindrical element from a first position to a second position. Each of the at least one sleeve member positions its blade in an operational position when its, at least one, projecting element is positioned in its corresponding first position in its designated first recessed guide path of the first cylindrical element. Each of the at least one sleeve member positions its blade in a storage position when its, at least one, projecting element is positioned in its corresponding second position in its designated first recessed guide path of the first cylindrical element. A rotation of the first cylindrical element moves each of the at least one sleeve member thereabout along their first recessed guide path. An arrangement includes the propeller and a compartment configured to accommodate the propeller. An aircraft includes at least one wing and at least one propeller.

A propeller for an aircraft includes at least two blades, arranged about a central hub, which is coupled to at least one motor, driven by a power source. At least one blade is attached to at least one sleeve member, configured for being in an outer sliding connection to a first cylindrical element of the hub. An inner surface of each of the at least one sleeve member includes at least one projecting element, configured to be in a sliding connection with a corresponding at least one first recessed guide path, arranged in an outer surface of the first cylindrical element. Each of the at least one first recessed guide path circles at least partly around the first cylindrical element from a first position to a second position. Each of the at least one sleeve member positions its blade in an operational position when its, at least one, projecting element is positioned in its corresponding first position in its designated first recessed guide path of the first cylindrical element. Each of the at least one sleeve member positions its blade in a storage position when its, at least one, projecting element is positioned in its corresponding second position in its designated first recessed guide path of the first cylindrical element. A rotation of the first cylindrical element moves each of the at least one sleeve member thereabout along their first recessed guide path. An arrangement includes the propeller and a compartment configured to accommodate the propeller. An aircraft includes at least one wing and at least one propeller.

A cargo transportation system includes a cargo platform having an upper surface and a perimeter. A propulsion system is disposed about the perimeter of the cargo platform. The propulsion system includes a plurality of propulsion assemblies, each including a propulsion unit disposed within a housing defining an airflow channel having an air inlet for incoming air and an air outlet for outgoing air such that the outgoing air is operable to generate at least vertical lift. A power system disposed within the cargo platform provides energy to drive the propulsion system. A flight control system operably associated with the propulsion system and the power system controls flight operations of the cargo transportation system.

A method for facilitating the design and manufacturing of a tiltrotor aircraft, including the steps of: determining a compatible mission data set; identifying lift propulsion module components for the compatible mission data set; determining compatible specifications; and generating a design for a lift propulsion module; wherein the lift propulsion module is configured to be connected to at least two different fuselages. There is also a method of designing a tiltrotor aircraft, comprising the step of modularizing a lift propulsion system, wherein the lift propulsion system is configured to be connected to at least two different fuselages. In another aspect, there is a tiltrotor aircraft including a fuselage; and a lift propulsion module, the lift propulsion module including a mounting surface; wherein the lift propulsion module is coupled to the fuselage on the mounting surface. Also included are methods of assembling and systems including a lift propulsion module.

A modular Unmanned Aerial System (UAS) includes an Unmanned Aerial Vehicle (UAV) parent module and UAV child modules. A main wing extends from a respective fuselage of the modules. The UAS includes docking mechanisms coupled to wingtips of the main wings. The child modules dock with the wingtips of the parent or an adjacent child module. Docking forms a linked-flight configuration, with undocking and separation from the parent or adjacent child module achieving an independent-flight configuration. The modules have booms arranged transverse to the main wings and parallel to the longitudinal axis, as well as front and rear rotors/propellers. The front and rear propellers have axes of rotation that are normal to a plane of the longitudinal axis in a vertical takeoff and landing (VTOL) configuration, with the axis of rotation of the rear propellers parallel to the longitudinal axis in a forward-flight configuration.

As one aspect of this multicopter, the multicopter flies on the basis of information from a flight controller and is provided with the following: a main body section; a plurality of propulsion units having rotating rotary wing, the propulsion units being attached to the main body section; motors installed in the main body section or the propulsion units; at least one first detection unit that detects motor information; and a wireless transmission unit that wirelessly transmits, to the outside, the motor information detected by the first detection unit.

As one embodiment of this motor, the motor is mounted in a multicopter and is provided with: a rotating section that rotates around a rotation axis that extends in one direction; a stationary section that is attached to a main body section of the multicopter; at least one first detection unit that detects motor information; and an output unit that outputs, to the outside, the motor information detected by the first detection unit.