An aircraft frame includes a fuselage, at least one boom and a wing structure including a first lifting surface having a first root portion located proximate the at least one boom and a first tip portion where at least a portion of the first tip portion is located forwardly from at least a portion of the first root portion, a second lifting surface having a second root portion located proximate the fuselage, and a second tip portion located spaced from the first tip portion where at least a portion of the second tip portion is located rearwardly from at least a portion of the second root portion, and a connector surface extending between the first and second tip portions.

Aerial vehicles may be configured to control their attitudes by changing one or more physical attributes. For example, an aerial vehicle may be outfitted with propulsion motors having repositionable mounts by which the motors may be rotated about one or more axes, in order to redirect forces generated by the motors during operation. An aerial vehicle may also be outfitted with one or more other movable objects such as landing gear, antenna and/or engaged payloads, and one or more of such objects may be translated in one or more directions in order to adjust a center of gravity of the aerial vehicle. By varying angles by which forces are supplied to the aerial vehicle, or locations of the center of gravity of the aerial vehicle, a desired attitude of the aerial vehicle may be maintained irrespective of velocity, altitude and/or forces of thrust, lift, weight or drag acting upon the aerial vehicle.

A VTOL aircraft is provided with a fuselage, a pair of first thrust units, a pair of second thrust units, and a pair of first wings. The first thrust units and the second thrust units are tiltably mounted on the fuselage. The first wings are securely mounted on the fuselage, and each first wing has a root end and an outer end. The longitudinal length of the outer end is larger than that of the root end. Thus, when the VTOL aircraft is landing or taking off, the airflow can pass around the root ends of the first wings; when the VTOL aircraft is cruising or gliding, the wings can provide lift, so that the first thrust units and the second thrust units can operate in a low mode, which makes the VTOL aircraft save energy and land safely even when the thrust units are broken.

An aircraft is provided that is convertible in flight between a rotary wing configuration and a fixed wing configuration. In its fixed wing configuration the aircraft resembles a Blended Wing Body (BWB) having a swept wing angle . Conversions from the fixed wing configuration to the rotary wing configuration, and vice versa, are accomplished by flipping an outboard portion of one wing through 180 to reorient the leading edge of the outboard portion by an angle of 2 to establish a reverse sweep. In its rotary configuration, the entire aircraft is rotated.

In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.

Described is an aircraft, in particular a drone, with a supporting body (2) and at least two propulsion arrangements (4, 8) arranged at a distance from one another on the supporting body (2), which are designed to generate a propulsive thrust in a direction of propulsion (8b). According to a first aspect of the invention, the propulsion arrangements (4, 8) on the supporting body (2) are each mounted so as to be pivotable independently of one another about a first axis of pivoting (6) extending at an angle to the direction of propulsion (8b) and a first actuating drive (10) is provided and designed to pivot the propulsion arrangements (4, 8) independently of one another about the first axis of pivoting (6). According to a second aspect of the invention, in which a trunk body (20) is provided, this trunk body (20) is mounted on the supporting body (2) so as to be pivotable about a second axis of pivoting (22) and a second actuating drive (24) is provided and designed to pivot the supporting body (2) relative to the trunk body (20).

An electric aircraft is capable of vertically taking off and landing. The aircraft includes a fuselage, front and rear power units, power pods, main wings, ailerons, front landing gears, a tail wing and a rear landing gear. The power units include first and second electric duct groups. The first electric duct group includes two electric duct fans symmetrically and connected to two sides of a front portion of the fuselage respectively. The second electric duct group includes two electric duct fans symmetrically provided at two sides of a rear portion of the fuselage respectively. The power pods are configured to connect the fuselage to the first electric duct group. The two main wings are symmetrically and foldably connected to two sides of the fuselage respectively. The two ailerons are symmetrically connected to front ends of the two main wings respectively.

An amphibious vertical takeoff and landing (VTOL) unmanned device is provided. The amphibious VTOL unmanned device includes a modular and expandable waterproof body, an outer body shell, a gimbaled swivel propulsion system comprising a plurality of VTOL jet engines and VTOL ducted fans, a processor, electronic speed controllers, a two-way telemetry device, a video transmitter, a radio control receiver, a power distribution board, an electrical machine, an onboard electricity generator comprising a plurality of solar cells, a light detection and ranging device, an ultrasonic radar sensor, a plurality of sensors, a tail configured to stabilize the amphibious VTOL unmanned device, a head VTOL ducted fan adapted for VTOL, a plurality of wheels, a plurality of foldable wings configured to create a pressure difference and creating a lift, a plurality of parachutes configured to safely land the amphibious VTOL unmanned device in an emergency.

The claimed versions belong to tilt rotors nonexpendable aircrafts. In general, the convertiplane has a fuselage, a wing and engine groups. In one embodiment each engine group is designed in the form of at least one engine positioned with the possibility to turn, provided that the engines in groups are designed in view of the condition of thrust change relative to each other and/or groups and engine groups are positioned at the tip of corresponding wing at front fuselage and tail fuselage. In a second embodiment the wing is designed combined in the form of forward-swept wing and aft-swept wing, each engine group is designed in the form of at least one engine positioned with the possibility to turn, provided that the engines in groups are designed in view of the condition of thrust change relative to each other and/or groups and groups are positioned at the tip of corresponding wing. The claimed versions allow simplification and weight reduction of AC structure, increasing of its maneuvering ability at every flight stage, improvement of its aerodynamic quality such as stability and aerodynamic efficiency.

The vertical takeoff and landing unmanned aerial vehicle includes a pair of selectively rotatable ducted fans and a selectively rotatable thrust vectoring nozzle providing vertical takeoff and landing for an unmanned aerial vehicle or a similar type of aircraft. A pair of fixed forward-swept wings are mounted on a rear portion of a fuselage, and a pair of canards are mounted on a top end of a forward portion of the fuselage. The pair of ducted fans are respectively mounted on free ends of the pair of canards, and are selectively rotatable about an axis parallel to a pitch axis of the fuselage. An engine is mounted in the rear portion of the fuselage, and a thrust vectoring nozzle is mounted on the rear portion of the fuselage for directing thrust exhaust from the engine. The thrust vectoring nozzle is selectively rotatable about an axis parallel to the pitch axis.