Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

An aircraft for capturing drones includes an airframe having a drone channel with first and second wings extending outboard thereof. A two-dimensional distributed thrust array includes a plurality of propulsion assemblies coupled to each of the first and second wings such that the rotor disc of each propulsion assembly is outboard of the drone channel. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A mesh bag is coupled to the drone channel forming a drone capture net. The aircraft is configured to convert between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft is also configured to overtake a drone during flight in the biplane orientation such that the drone passes through the drone channel into the mesh bag, thereby capturing the drone in the drone capture net.

A rotor system is provided in one example embodiment and may include a first pair of rotor blades comprising a first pitch and a first diameter; and a second pair of rotor blades comprising a second pitch and a second diameter, wherein the first pitch of the first pair of rotor blades and the second pitch of the second pair of rotor blades are different.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

An unmanned aerial vehicle (UAV) includes a central body and a plurality of arms extending from the central body. Each of the plurality of arms supports one or more propulsion units. At least one arm of the plurality of arms is configured to transform between (1) a flight configuration that provides lift while the UAV is in flight and (2) a landing configuration in which the at least one arm is configured to function as a landing support that bears weight of the UAV while the UAV is not in flight. The at least one arm is configured to transform between the flight configuration and the landing configuration in response to operation of the one or more propulsion units supported by the at least one arm.

A flying machine includes a flying machine body including a rotor blade; a frame including a frame body supporting the flying machine body, and a pressing section that is pressed against a target object at least at two locations separated along a direction orthogonal to a width direction of the frame body; and a detector fixed to the frame, and having a detection direction that is a direction orthogonal to a direction joining the two locations together and facing toward the target object.

A vehicle includes a fuselage having a longitudinal axis and a propulsion system that is coupled to the fuselage. The vehicle also includes a pair of articulated appendages that is coupled to the fuselage. Each one of the articulated appendages includes a plurality of airfoil segments and is moveable between a ground configuration, in which each one of the pair of articulated appendages supports the vehicle during takeoff or landing of the vehicle, and a flight configuration, in which each one of the pair of articulated appendages produces lift during flight of the vehicle.

Aerial vehicles are provided with one or more transformable arms (110, 310, 410, 510, 910). The one or more transformable arms (110, 310, 410, 510, 910) may support one or more propulsion units, and transform between a flight configuration where the propulsion units of the arms effect flight of the aerial vehicle, and a landing configuration, wherein the transformable arms (110, 310, 410, 510, 910) are used as a landing support that bears weight of the aerial vehicle when the aerial vehicle is not in flight. Using the transformable arms (110, 310, 410, 510, 910) as legs when the UAV is in a landed state permits the UAV to reduce weight and reduce obstruction to a payload carried by the UAV when the UA is in flight.