An aircraft includes a short-range radar that is configured to detect a trajectory, which is specified based on a position detection of the aircraft by a ground station.

A cargo transporting system for a tailsitter aircraft includes a cargo receptacle rotatably coupled to an underside of a wing and a cargo assembly selectively coupled to the cargo receptacle. By rotating the cargo receptacle, the cargo transporting system can transition between a deployed position and a retracted position. In the deployed position, the cargo receptacle is substantially perpendicular to the wing, and accommodates ground personnel charged with connecting or removing the cargo assembly from the cargo transporting system. In the retracted position, the cargo receptacle is substantially parallel to the wing, and positioned for flight operations.

An unmanned aircraft capable of vertical takeoff, vertical landing, and/or flight in a hovering orientation is presented; its fixed-wing is positively-swept and of low aspect-ratio with suitable airfoils. The unmanned aircraft includes a thruster comprising two contra-rotating motors and propellers forward of the fixed-wing's leading-edge and a rudderless fin aft of the center-of-mass, all of which lie on the aircraft's plane-of-symmetry. Two elevons provide pitch and roll control. The unmanned aircraft can stand upright on its feet. A control system for aircraft with at least one wing is also presented. The control system includes a mount and attached thruster which lie on the plane-of-symmetry forward of the fixed-wing's leading-edge. A hinge axis approximately perpendicular to the aircraft's horizontal plane passes through the mount. The thruster rotates about the hinge axis for aircraft yaw control.

A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight trust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

An aerial vehicle is programmed or configured to respond to reports of events or conditions within spaces of a facility. The aerial vehicle travels to a location of a reported event or condition and captures data using onboard sensors. The aerial vehicle independently determines whether the reported event or condition is occurring, or is otherwise properly addressed by resources that are available at the location, using images or other data captured by the onboard sensors. Alternatively, the aerial vehicle transmits a request for additional resources to be provided at the location, where necessary. A map of the location generated based on images or other data captured by the onboard sensors may be utilized for any purpose, such as to make one or more recommendations of products that are appropriate for use at the facility.

In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.

Systems, devices, and methods for an aircraft having a fuselage (110); a wing (120) extending from both sides of the fuselage; a first pair of motors (132b, 133b) disposed at a first end of the wing; and a second pair of motors (142b, 143b) disposed at a second end of the wing; where each motor is angled (381, 382, 391, 392) to provide a component of thrust by a propeller (134, 135, 144, 145) attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.

A VTOL aircraft (1), including: a fuselage (2) for transporting passengers and/or load; a front wing (3) attached to the fuselage (2); an aft wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF); a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the aft wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two propulsion units (6) on each one of the connecting beams (5a, 5b). The propulsion units (6) include at least one propeller (6b, 6b′) and at least one motor (6a) driving the propeller (6b, 6b′), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z).

A base station is disclosed that is configured for use with a UAV. The base station includes: an enclosure with an outer housing that defines a roof section and an inner housing that is connected to the outer housing; one or more heating elements that are supported by the enclosure and which are configured to heat the roof section; one or more fiducials that are supported by the enclosure; an illumination system that is supported by the enclosure and which is configured to illuminate the one or more fiducials; and a visualization system that is supported by the enclosure.