A vertical takeoff and landing (VTOL) aircraft, including: a vehicle controller circuit programmed to operate the VTOL aircraft without an onboard human operator; a rotor system; an airframe; and an external cargo coupling to receive an external payload of at least approximately 300 pounds beneath the airframe.

One embodiment is an aircraft including first and second fuselages; a wing assembly connecting the first and second fuselages, wherein the first and second fuselages are parallel to one another; first and second forward propulsion systems tiltably attached to forward ends of the first and second fuselages; and first and second aft propulsion systems fixedly attached proximate aft ends of the first and second fuselages.

A ground marker for use in identifying a location associated with a mission performed by an aerial vehicle includes a visible surface with aspects that are positioned at different vertical heights or elevations. The vertical variation in the aspects of the visible surface enhances a level of visibility of the ground marker within images captured by cameras provided aboard the aerial vehicle, resulting in more accurate estimations of ranges to such markers (e.g., altitudes) determined from such images. The visible surface includes one-dimensional or two-dimensional bar codes, alphanumeric characters and symbols thereon and is provided on or within rigid or flexible frames that are adapted to be placed on ground surfaces at the location associated with the mission.

In an aspect, a system for a guidance interface for a vertical take-off and landing (VTOL) aircraft comprises a plurality of flight components that are mechanically coupled to the VTOL aircraft. The VTOL aircraft also comprises an output device that is configured to present a display of the outside environment. The output device may overlay the display with a datum, a focal point, and a guidance symbol. The datum may be associated with the flight components of the VTOL aircraft. The focal point may be indicative of a desired landing location for the VTOL aircraft. The focal point may be determined by at least a predetermined flight plan. The guidance symbol may be a symbol that includes an optimal flight path to the focal point.

Aerial vehicles may be selectively transitioned between a fixed wing flight configuration and a vertical takeoff and landing (VTOL) configuration. In the fixed wing flight configuration, a forward propeller may rotate in a first forward plane, whereas in the VTOL configuration, the forward propeller may be tilted to rotate in a second forward plane. A forward landing arm may extend downward in the VTOL configuration and be configured to be tilted to a stowed position when the aerial vehicle is in the fixed wing flight configuration. The forward landing arm may be coupled to the forward propeller such that tilting of the forward propeller causes corresponding tilting of the forward landing arm. In some examples, a plurality of such landing arms and propellers are tilted during transitioning of the aerial vehicle, such as one or more forward propellers and landing arms and/or one or more aft propellers and landing arms.

A long-distance drone having a main body, a left hind wing, a right hind wing, a left forewing, and a right forewing. There is a left linear support connecting the left forewing to the left hind wing, and a right linear support connecting the right forewing to the right hind wing. A plurality of propellers are disposed on the left and the right linear supports.

A tandem tiltrotor aircraft in which the tiltrotor assemblies are operably coupled at the forward and aft ends of the fuselage of the aircraft is disclosed. The tiltrotor assemblies are capable of rotating between a vertical lift position and a horizontal flight position. The in-line location of the tiltrotor assemblies allow the aircraft to have the vertical take-off and landing capabilities, and, in combination with the at least one wing, can be used in horizontal flight. The aft rotor assembly can assume a horizontal flight position that places the rotor blades forward of a vertical fin of the aircraft. In another embodiment, a winged triple tiltrotor aircraft is disclosed. In another embodiment, a winged quad tiltrotor aircraft is disclosed.

A vehicle comprises a propulsion assembly that includes a rotor system configured to swivel about a pivot axis and a flight control system in communication with the propulsion assembly. In one embodiment, the pivot axis is fixedly oriented at an angle relative to a lateral axis of the vehicle in a plane defined by a longitudinal axis of the vehicle. The flight control system is configured to activate a particular operational mode of the propulsion assembly, in which the rotor system is configured to swivel about the pivot axis to move a rotor axis of the rotor system from a first gimbal angle to a second gimbal angle. In various embodiments, the gimbal angle is configured to change a center of gravity, or direction of thrust vectors, or attitude of the vehicle. The operational mode may comprise a one engine inoperative (OEI) mode in an example embodiment.

A system can include a flight controller for an aircraft that includes an electric motor that drives blades with a variable pitch, where the flight controller receives a command to change a flight characteristic of the aircraft and creates a torque command and a revolutions per minute (RPM) command. The system can also include a propulsion assembly, where the propulsion assembly creates a current command based at least in part on the torque command and the RPM command, creates a blade pitch command based at least in part on the torque command and the RPM command, communicates the current command to the electric motor to change a mechanical output of the electric motor, and communicates the blade pitch command to blade actuators to control the pitch of the blades. The current command and the blade pitch command cause the blades of the aircraft to rotate at a predetermined RPM.

An aircraft includes a fuselage airframe and a wing airframe that is subject to flight loads. The fuselage airframe includes fore/aft floor beams having a plurality of floor intercostals laterally extending therebetween and fore/aft roof beams with a plurality of roof intercostals laterally extending therebetween. Each of a plurality of cabin frames extends generally vertically between respective floor and roof beams. The wing airframe includes forward and aft wing spars with a plurality of wing ribs extending therebetween. At least one fuel tank, that is configured to contain a pressurized fuel such as pressurized hydrogen fuel, integrally forms at least a portion of one of the beams, the intercostals, the frames, the spars and/or the ribs such that the fuel tank is subject to the flight loads.