An aircraft has an airframe with a two-dimensional distributed thrust array attached thereto having a plurality of propulsion assemblies that are independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto that is operable to tilt about first and second axes responsive to first and second actuators. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector. Responsive to a thrust vector error of a first propulsion assembly, the flight control system commands at least a second propulsion assembly, that is symmetrically disposed relative to the first propulsion assembly, to counteract the thrust vector error, thereby providing redundant directional control for the aircraft.

A plurality of landing gear are rotatable between a flight position and a landing position under the control of a control system on a vertical takeoff and landing aircraft. The plurality of landing gear may be separately and selectably rotatable to accommodate uneven or sloping terrain. The landing gear may include flight control surfaces and the degree of deployment of the landing gear controls the flight control surfaces. The flight control surfaces may include separately controllable elements. The aircraft may be a flight module of a modular and morphable air vehicle.

A control device 200 includes at least one memory configured to store a program code, and at least one processor configured to access the program code and operate as instructed by the program code. The program code includes an acquisition code configured to cause the at least one processor to acquire a request for requesting determination as to whether or not a target area is usable for a predetermined purpose, and a control code configured to cause the at least one processor to perform control to cause a first flying object to fly to the target area. The acquisition code is configured to cause the at least one processor to further acquire sensing data that is data obtained by optical sensing of the target area by the first flying object. The program code further comprises a determination code configured to cause the at least one processor to determine, based on the acquired sensing data, whether or not the target area is usable for the predetermined purpose.

A vertical landing of an aircraft is performed using the first battery where the aircraft is unoccupied when the vertical landing is performed, the unoccupied aircraft includes the first battery, and the unoccupied aircraft excludes a second, removable battery. In response to detecting that the second, removable battery is detachably coupled to the aircraft, a power source for the aircraft is switched from the first battery to the second, removable battery. After switching the switch power source, a vertical takeoff of the aircraft is performed using the second, removable battery, wherein the aircraft is occupied when the vertical takeoff is performed.

The battery thermal management system includes a battery pack, a circulation subsystem, and a heat exchanger. The system can optionally include a cooling system, a reservoir, a de-ionization filter, a battery charger, and a controller.

Multi-rotor aerial vehicle (1, 1, 1, 1, 1, 1, 1) comprising, at least a first, second and third rotor 10, 20, 30, each rotatable by a dedicated first second and third hydraulic motor 11, 21, 31, a power unit 2, at least a first, second and third hydraulic pump 12, 22, 32 dedicated to the respective first, second and third hydraulic motor 11, 21, 31, wherein each hydraulic pump 12, 22, 32 is arranged to provide pressurized fluid to each hydraulic motor 11, 21, 31 for powering the hydraulic motor 11, 21, 31 and thereby rotating the respective rotor 10, 20, 30, a control unit 6 for controlling the operation of the multi-rotor aerial vehicle (1, 1, 1, 1, 1, 1, 1), wherein the control of the multi-rotor aerial vehicle (1, 1, 1, 1, 1, 1, 1) is arranged to be performed by altering the flow of pressurized fluid distributed to each respective hydraulic motor 11, 21, 31, wherein, wherein the flow of pressurized fluid provided to each hydraulic motor 11, 21, 31 is individually controllable by means of at least one control valve 13, 23, 33 configured to control the flow of pressurized fluid from each hydraulic pump 12, 22, 32 to its dedicated hydraulic motor 11, 21, 31.

A hybrid VTOL vehicle having an envelope configured to provide hydrostatic buoyancy, a fuselage attached to the envelope and having at least one pair of wings extending from opposing sides thereof to produce dynamic lift through movement, and a thrust generation device on each wing and configured to rotate with each wing about an axis that is lateral to a longitudinal axis of the envelope to provide vertical takeoff or landing capabilities. Ideally, the envelope provides negative hydrostatic lift to enhance low-speed and on-the-ground stability. A vehicle comprising a first lift device capable of providing hydrostatic lift; a second lift device capable of providing dynamic lift through movement; and a system structured to generate thrust coupled to the second lift device, the second lift device and the thrust generation system capable of rotating together about an axis that is lateral to a longitudinal axis of the vehicle at angles at least in the range of 90 degrees to and including 180 degrees.

Rotorcraft including a fuselage and at least three rotor system arms each having a rotor system. Each rotor system includes a mast having at least two rotor blades and an electric rotor motor. At least one rotor system arm includes a support mechanism for pivotally supporting a floating mast about at least one pivot axis whereby the floating mast is tillable relative to a fiducial tilt position. The floating mast has a controllable cyclic rotor blade pitch. A mast tilt measurement mechanism provides a mast tilt feedback signal regarding a measured tilt position of a floating mast relative to its fiducial tilt position. A flight control system continuously controls the at least three electric rotor motors and the floating masts cyclic rotor blade pitch in response to a desired input maneuver and its mast tilt feedback signal.

Rotorcraft including a fuselage and at least three rotor system arms each having a rotor system. Each rotor system includes a mast having at least two rotor blades and an electric rotor motor. At least one rotor system arm includes a support mechanism for pivotally supporting a floating mast about at least one pivot axis whereby the floating mast is tillable relative to a fiducial tilt position. The floating mast has a controllable cyclic rotor blade pitch. A mast tilt measurement mechanism provides a mast tilt feedback signal regarding a measured tilt position of a floating mast relative to its fiducial tilt position. A flight control system continuously controls the at least three electric rotor motors and the floating masts cyclic rotor blade pitch in response to a desired input maneuver and its mast tilt feedback signal.

The present invention relates to a hybrid-powered unmanned vehicle, comprising: a fuel engine (10), a permanent magnet brushless DC motor (20), a rechargeable battery component (30), an startup control circuit (40), an electronic speed regulator, a flight controller, and a propeller. The startup control circuit (40) supplies power from the chargeable battery assembly to the permanent magnet brushless DC motor such that the permanent magnet brushless DC motor drives an operation of the fuel engine. The power generated by the permanent magnet brushless DC motor can charge the rechargeable battery component. When compared to using a battery as sole power supply device, the use of hybrid-power provides greater energy density of up to 1,000-1,500 Wh/kg.