An aircraft with increased crash robustness including a fuselage with a forward end, an opposite rear end, a ventral surface, and a dorsal surface. The aircraft further including a longitudinal axis running from the rear end to the forward end and a dorsoventral axis orthogonal to the longitudinal axis and running from the dorsal surface to the ventral surface. The aircraft also including at least a battery module located within the fuselage comprising a plurality of battery cells, each battery cell includes an axial axis positioned orthogonally to each of the longitudinal axis and the dorsoventral axis, and each battery cell has a plurality of radial axes orthogonal to the axial axis, wherein the plurality of radial axes includes a first radial axis aligned with the longitudinal axis and a second radial axis aligned with the dorsoventral axis.

An embodiment is an aircraft, including at least a fuselage, a tail rotatably coupled to the fuselage, the tail coupled at an aft of the fuselage, and a tail actuator coupled to the fuselage and the tail, the tail actuator to transition the tail between an extended position and a retracted position.

An embodiment is an aircraft, including at least a fuselage, a tail rotatably coupled to the fuselage, the tail coupled at an aft of the fuselage, and a tail actuator coupled to the fuselage and the tail, the tail actuator to transition the tail between an extended position and a retracted position.

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 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 High Altitude Pseudo Satellite (HAPS) aircraft is disclosed, the aircraft including at least one aeroelastic span loaded fixed wing, an aspect ratio greater than 15 and wing loading less than 6 kg/m.sup.2, where the at least one wing has a plurality of spoilers distributed across the span of the wing and each spoiler being chordwise located adjacent the centre of pressure of the wing. The HAPS aircraft further includes a control system for controlling the spoilers, sensors which allow at least one of the quantity or quantities selected from the group comprising the amount of lift at points or regions along the wing span the pitch and roll at points or regions along the wing span, the bending and torsional strain at points or regions along the wing span, or the net speed and roll and pitch angle of the wing to be determined by the control system, and the spoiler being activatable to reduce the lift experienced by the wing in the location of the spoiler in response to the quantities determined by control system.

This disclosure provides a monitoring system, a base station, and a control method of drones. The drone includes a battery that supplies electric power for the drone and that connects with a charging connector. The base station includes a charging device, and the charging device includes a power supply connector, a power supply, and a power controller. The power supply connector is used for connecting to the charging connector. The power supply provides electric power. The power controller is coupled to the power supply and the power supply connector. The power controller is used to determine the battery specification of the battery and charge the battery from the power supply according to the battery specification. Thereby, the charging efficiency can be improved and the charging abnormality can be avoided.

An aircraft having a fuselage and a front landing gear; both sides of the rear bottom of the fuselage are fixedly connected with the rear landing gear; one end of the front landing gear is rotatably connected to the front bottom of the fuselage. When the front landing gear rotates to the first position, the second position and the third position, the connecting line between the end of the front landing gear away from the fuselage and the end of the rear landing gear away from the fuselage intersects with the plane, where the fuselage is located, on the side close to the front of the fuselage, parallel to and intersect on the side close to the rear of the fuselage.

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 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.