Embodiments are directed to a rotor-based remote flying vehicle platform such as a quadrotor, and to methods for controlling intra-flight dynamics of such rotor-based remote flying vehicles. In one case, a rotor-based remote flying vehicle platform is provided that includes a central frame. The central frame has a control center that is configured to control motors mounted to the vehicle platform. The central frame also has a communication port configured to interface with functionality modules. The communication port is communicably connected to the control center. The rotor-based remote flying vehicle platform further includes at least a first arm that is connected to the central frame and extends outward, as well as a first motor mounted to the first arm, where the first motor is in communication with the control center. The method for controlling intra-flight dynamics may be performed on such a rotor-based remote flying vehicle.

Embodiments are directed to a rotor-based remote flying vehicle platform such as a quadrotor, and to methods for controlling intra-flight dynamics of such rotor-based remote flying vehicles. In one case, a rotor-based remote flying vehicle platform is provided that includes a central frame. The central frame has a control center that is configured to control motors mounted to the vehicle platform. The central frame also has a communication port configured to interface with functionality modules. The communication port is communicably connected to the control center. The rotor-based remote flying vehicle platform further includes at least a first arm that is connected to the central frame and extends outward, as well as a first motor mounted to the first arm, where the first motor is in communication with the control center. The method for controlling intra-flight dynamics may be performed on such a rotor-based remote flying vehicle.

The rotor of a hybrid aerodyne for producing lift by rotating during a stage of vertical flight and then for being held stationary and stored longitudinally during a stage of cruising flight has at least one single-blade with a counterweight. The length of the active blade that generates lift of the rotor while rotating is significantly shorter than the length of the radius of the rotor. The portion that carries the active blade that makes the connection between the active blade and rotor mast is structurally rigid. The rigid portion that carries the active blade presents a cross-section optimized to provide zero or almost zero lift and very little aerodynamic drag while the rotor is rotating. The assembly is hinged about a transverse axis perpendicular to the vertical axis of the rotor and substantially on the vertical axis of the rotor mast.

The rotor of a hybrid aerodyne for producing lift by rotating during a stage of vertical flight and then for being held stationary and stored longitudinally during a stage of cruising flight has at least one single-blade with a counterweight. The length of the active blade that generates lift of the rotor while rotating is significantly shorter than the length of the radius of the rotor. The portion that carries the active blade that makes the connection between the active blade and rotor mast is structurally rigid. The rigid portion that carries the active blade presents a cross-section optimized to provide zero or almost zero lift and very little aerodynamic drag while the rotor is rotating. The assembly is hinged about a transverse axis perpendicular to the vertical axis of the rotor and substantially on the vertical axis of the rotor mast.

An unmanned aerial vehicle (UAV) includes lift rotors and control rotors. The lift rotors are mounted to the UAV and oriented to provide a first vertical thrust to the UAV. The control rotors are mounted to the UAV outboard of the lift rotors and oriented to provide a second vertical thrust to the UAV. The control rotors are each smaller than any of the lift rotors.

A rotor blade assembly connectable to a rotor hub configured to rotate about a center axis includes a torsional pitch member coupled to the rotor hub, a torque tube coupled to the torsional pitch member, wherein the torsional pitch member extends away from the center axis through a portion of the torque tube, a blade coupled to the torque tube, and a pitch control member coupled to the torque tube and configured to control a pitch angle of the blade, wherein the torsional pitch member includes a first curvilinear channel and a second curvilinear channel each having a front side and a back side, wherein the first curvilinear channel and the second curvilinear channel are disposed adjacent to each other, such that the back side of the first curvilinear channel faces the back side of the second curvilinear channel.

A rotor blade assembly connectable to a rotor hub configured to rotate about a center axis includes a torsional pitch member coupled to the rotor hub, a torque tube coupled to the torsional pitch member, wherein the torsional pitch member extends away from the center axis through a portion of the torque tube, a blade coupled to the torque tube, and a pitch control member coupled to the torque tube and configured to control a pitch angle of the blade, wherein the torsional pitch member includes a first curvilinear channel and a second curvilinear channel each having a front side and a back side, wherein the first curvilinear channel and the second curvilinear channel are disposed adjacent to each other, such that the back side of the first curvilinear channel faces the back side of the second curvilinear channel.

An exemplary aircraft includes a wing positioned below a vertical rotor, the wing extending to an outboard end, and an anhedral winglet extending from the outboard end through an angular transition to a tip, the anhedral winglet having an external surface exposed to the rotor downwash and the external surface is contoured to generate local wing lift in response to the rotor downwash.

An exemplary aircraft includes a wing positioned below a vertical rotor, the wing extending to an outboard end, and an anhedral winglet extending from the outboard end through an angular transition to a tip, the anhedral winglet having an external surface exposed to the rotor downwash and the external surface is contoured to generate local wing lift in response to the rotor downwash.

A method for calculating torque through a rotor mast of a propulsion system of a tiltrotor aircraft includes receiving the torque being applied through a quill shaft of the rotorcraft. The quill shaft is located between a fixed gearbox and a spindle gearbox, and the spindle gearbox is rotatable about a conversion access. The torque through the rotor mast is determined by using the torque through the quill shaft and the efficiency loss value between the quill shaft and the rotor mast.