The present disclosure relates to a flight control apparatus, a system including the same, and a method thereof. An example embodiment of the present disclosure provides a flight control apparatus, including: at least one processor, and memory storing instructions that, when executed by the at least one processor, cause the flight control apparatus to determine, based on environmental information and based on variations of a parameter for each operation mode of an aerial vehicle, a flight path among at least one candidate path associated with a destination for the aerial vehicle.

Techniques for drone device control are provided. In one example, the technique includes monitoring, by a drone device operatively coupled to a processor and allocated to a vehicle in operation, one or more conditions associated with the vehicle. The technique also includes, in response to identifying, by the drone device, a defined condition of the one or more conditions: moving, by the drone device, to a position relative to the vehicle and determined based on the defined condition; and performing, by the drone device, an indication operation determined based on the defined condition.

The invention relates to a vector control for an aerial vehicle drive wherein a rotor shaft (16) which is suspended from a frame (19) via a. pivot bearing (18). A rotor (14) is mounted rotatably relative to the rotor shalt (16). A motor (20) is configured to set the rotor (14) in rotation. An actuator (21, 22) which extends between the frame (19) and the rotor shaft (.16) is configured to change the orientation of the rotor shaft (16). The invention also concerns a method for controlling a helicopter drive.

Techniques for drone device control are provided. In one example, the technique includes monitoring, by a drone device operatively coupled to a processor and allocated to a vehicle in operation, one or more conditions associated with the vehicle. The technique also includes, in response to identifying, by the drone device, a defined condition of the one or more conditions: moving, by the drone device, to a position relative to the vehicle and determined based on the defined condition; and performing, by the drone device, an indication operation determined based on the defined condition.

Systems and associated methods for rapid integration and control of payloads carried by a multi-mode unmanned vehicle configured to accommodate a variety of payloads of varying size, shape, and interface and control characteristics. Mechanical, power, signal, and logical interfaces to a variety of payloads operate to enable environmental protection, efficient placement and connection to the vehicle, and control of those payloads in multiple environmental modes as well as operational modes (including in air, on the surface of water surface, and underwater).

In some embodiments, an apparatus includes a fuselage of an unmanned aircraft that includes a first section removably coupled to a second section, and a third section removably coupled to the second section such that the second section is disposed between the first section and the third section in a vertical direction. The first section includes a first rotor and a second rotor disposed at a non-zero spaced distance in the vertical direction from each other. The first rotor and the second rotor share a common and aligned rotational axis defined along a longitudinal centerline of the fuselage defined in the vertical direction. The second section is configured to contain a selected payload, and the third section includes a control system. A plurality of legs are coupled to the third section and serve as landing gear for the unmanned aircraft.

There is disclosed a multicopter vertical takeoff and landing (VTOL) aircraft. The aircraft comprises am airframe with spatial design, a pilot seat, a cockpit, controls, engine units, engine compartment, control system, remote control system. The airframe consists of a central section and, at least, two peripheral sections, wherein peripheral sections can be folded up or down, or be retracted under the central section. The central section and peripheral sections of the airframe have spatial design. Each of the peripheral sections comprises at least three standard engine compartments which are connected to each other. Inside each engine compartment there is an engine unit which comprises at least one engine and at least one horizontally rotating propeller together with the control hardware. Each engine unit is an autonomous member of the distributed control system (DCS).

A fuel cell system includes a fuel cell and a fuel system. The fuel cell includes a housing and a fuel cell stack positioned in the housing. The fuel cell stack is configured to produce an electrochemical reaction from a fuel and air to output electricity. The fuel system includes a fuel source, a fuel vaporizer, and fuel lines through which fuel flows from the fuel source to the fuel vaporizer and from the fuel vaporizer to the fuel cell stack. The fuel vaporizer includes a conductive tube through which the fuel flows, the conductive tube being in contact with the housing to conduct heat from the housing to the fuel to vaporize the fuel.

A fuel cell system includes a fuel cell and a fuel system. The fuel cell includes a housing and a fuel cell stack positioned in the housing. The fuel cell stack is configured to produce an electrochemical reaction from a fuel and air to output electricity. The fuel system includes a fuel source, a fuel vaporizer, and fuel lines through which fuel flows from the fuel source to the fuel vaporizer and from the fuel vaporizer to the fuel cell stack. The fuel vaporizer includes a conductive tube through which the fuel flows, the conductive tube being in contact with the housing to conduct heat from the housing to the fuel to vaporize the fuel.

An aircraft includes an airframe having a fixed-wing section and a plurality of articulated electric rotors, at least some of which are variable-position rotors having different operating configurations based on rotor position. A first operating configuration is a vertical-flight configuration in which the rotors generate primarily vertical thrust for vertical flight, and a second operating configuration is a horizontal-flight configuration in which the rotors generate primarily horizontal thrust for horizontal fixed-wing flight. Control circuitry independently controls rotor thrust and rotor orientation of the variable-position rotors to provide thrust-vectoring maneuvering. The fixed-wing section may employ removable wing panels so the aircraft can be deployed both in fixed-wing and rotorcraft configurations for different missions.