Abstract: Example methods and systems for coupling and controlling transport of cargo using an unmanned aerial vehicle (UAV) are provided, comprising coupling at least one electronically-controllable attachment device positioned on an underside of the UAV to a sling cable, the sling cable being secured to the cargo. The UAV flies to a predetermined area above the cargo, and responsive to determining that the UAV is positioned within the predetermined area, the UAV elevates above the initial operating height to lift the cargo and navigates to a target location.

Abstract: An unmanned aerial vehicle including a frame elongated along a frame axis, the frame has a leading side and an aft side, the frame further includes a left end portion and a right end portion, a first forward rotor assembly connected to the left end portion of the frame, a second forward rotor assembly connected to the right end portion of the frame, the first forward rotor assembly and the second forward rotor assembly being positioned on the leading side of the frame, a compartment connected to the frame, the compartment having a leading side, and a curved leading-edge fairing disposed on the frame, wherein a portion of the curved leading-edge fairing extends to cover the leading side of the compartment, and wherein the curved leading-edge fairing reduces drag during flight in a forward direction to enable a substantially level flight profile.

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

Abstract: Example methods and systems for coupling and controlling transport of cargo using an unmanned aerial vehicle (UAV) are provided, comprising coupling at least one electronically-controllable attachment device positioned on an underside of the UAV to a sling cable, the sling cable being secured to the cargo. The UAV flies to a predetermined area above the cargo, and responsive to determining that the UAV is positioned within the predetermined area, the UAV elevates above the initial operating height to lift the cargo and navigates to a target location.

Abstract: In an example, a system is described. The system comprises an unmanned aerial vehicle (UAV) having a UAV control system to control flight of the UAV. The system also comprises a steerable parachute system for parachute-assisted landing. The steerable parachute system comprises (i) a deployable parachute having steerable parachute cables, (ii) steering actuators, each steering actuator coupled to, and movable to adjust, a respective steerable parachute cable, (iii) a steerable parachute controller, and (iv) one or more parachute system sensors communicatively coupled to the steerable parachute controller and configured to detect physical characteristics of a reachable landing zone for the UAV. The steerable parachute controller is configured to (i) select a safe landing location within the reachable landing zone based on the physical characteristics and (ii) control movement of the steering actuators to steer the parachute to land the UAV at the safe landing location.

Abstract: In an example, a system is described. The system comprises an unmanned aerial vehicle (UAV) having a UAV control system to control flight of the UAV. The system also comprises a steerable parachute system for parachute-assisted landing. The steerable parachute system comprises (i) a deployable parachute having steerable parachute cables, (ii) steering actuators, each steering actuator coupled to, and movable to adjust, a respective steerable parachute cable, (iii) a steerable parachute controller, and (iv) one or more parachute system sensors communicatively coupled to the steerable parachute controller and configured to detect physical characteristics of a reachable landing zone for the UAV. The steerable parachute controller is configured to (i) select a safe landing location within the reachable landing zone based on the physical characteristics and (ii) control movement of the steering actuators to steer the parachute to land the UAV at the safe landing location.

Abstract: Example methods and systems for coupling and controlling transport of cargo using an unmanned aerial vehicle (UAV) are provided, comprising coupling at least one electronically-controllable attachment device positioned on an underside of the UAV to a sling cable, the sling cable being secured to the cargo. The UAV flies to a predetermined area above the cargo, and responsive to determining that the UAV is positioned within the predetermined area, the UAV elevates above the initial operating height to lift the cargo and navigates to a target location.

Abstract: Example methods and systems for coupling and controlling transport of cargo using an unmanned aerial vehicle (UAV) are provided, comprising coupling at least one electronically-controllable attachment device positioned on an underside of the UAV to a sling cable, the sling cable being secured to the cargo. The UAV flies to a predetermined area above the cargo, and responsive to determining that the UAV is positioned within the predetermined area, the UAV elevates above the initial operating height to lift the cargo and navigates to a target location.

Abstract: An unmanned aerial vehicle including a frame elongated along a frame axis, the frame has a leading side and an aft side, the frame further includes a left end portion and a right end portion, a first forward rotor assembly connected to the left end portion of the frame, a second forward rotor assembly connected to the right end portion of the frame, the first forward rotor assembly and the second forward rotor assembly being positioned on the leading side of the frame, a compartment connected to the frame, the compartment having a leading side, and a curved leading-edge fairing disposed on the frame, wherein a portion of the curved leading-edge fairing extends to cover the leading side of the compartment, and wherein the curved leading-edge fairing reduces drag during flight in a forward direction to enable a substantially level flight profile.

Abstract: 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.