An aircraft includes a fuselage, a wing disposed above the fuselage, a pylon connecting the wing to the fuselage, and a plurality of internal combustion engines housed in the fuselage. The pylon vertically traverses the fuselage and is fixed to an upper portion and a lower portion of the fuselage. Among the plurality of internal combustion engines, a first internal combustion engine and a second internal combustion engine are disposed bilaterally symmetrically about the pylon and are fixed to the pylon.

The present disclosure relates to the technical field of air vehicles, and in particular, an air vehicle with a double-layer rotor wing structure, including a cabin in which a power device is arranged, the power device includes a drive assembly, a crankwheel, and a connecting link; the connecting link is fixed on the crankwheel; the drive assembly drives the crankwheel to rotate; the top of the cabin is provided with a flying device that includes a first flying unit and a second flying unit; the first flying unit includes a sleeve, a rotating bearing II, and lower-layer rotor wings symmetrically fixed on two sides of the rotating bearing II; the rotating bearing II is fixed to the sleeve which is fixed to the cabin; the second flying unit includes a transmission rod, a rotating bearing I, and upper-layer rotor wings symmetrically fixed on two sides of the rotating bearing I.

Embodiments are directed to boosting aircraft engine performance for takeoff and critical mission segments by reducing airflow used for cooling exhaust gases. The airflow is reduced by stopping an accessory blower or by closing an external air vent Eliminating the cooling airflow to the exhaust has the effect of lowering the backpressure on the engine, which thereby increases maximum engine power.

Embodiments are directed to boosting aircraft engine performance for takeoff and critical mission segments by reducing airflow used for cooling exhaust gases. The airflow is reduced by stopping an accessory blower or by closing an external air vent Eliminating the cooling airflow to the exhaust has the effect of lowering the backpressure on the engine, which thereby increases maximum engine power.

In an aspect the current disclosure may describe a electric charging station for an electric vehicle. The electric charging station may include a charging cable, wherein the charging cable is configured to carry electricity and an energy source, wherein the energy source is electrically connected to the charging cable. The charging station may further include a temperature sensor, wherein the temperature sensor is configured to generate temperature datum and a computing device. A computing device may be communicatively connected to the plurality of temperature regulating elements and the temperature sensor. The computing device may further be configured to receive the battery datum and regulate battery temperature and cabin temperature using the plurality of temperature regulating elements as a function of the temperature datum.

In an embodiment, a method includes: collecting usage and maintenance data for a rotorcraft at a computer of the rotorcraft; sending the usage and maintenance data to a fleet management server; generating individualized equipment data for the rotorcraft according to the usage and maintenance data at the fleet management server, the individualized equipment data including a lightweight digital representation of the rotorcraft and technical publications for the rotorcraft, the lightweight digital representation including mesh-based 3D visualizations of each component of the rotorcraft, the technical publications having views referencing the mesh-based 3D visualizations; sending the individualized equipment data to the computer of the rotorcraft; and persisting the individualized equipment data at the computer of the rotorcraft.

In an embodiment, a method includes: collecting usage and maintenance data for a rotorcraft at a computer of the rotorcraft; sending the usage and maintenance data to a fleet management server; generating individualized equipment data for the rotorcraft according to the usage and maintenance data at the fleet management server, the individualized equipment data including a lightweight digital representation of the rotorcraft and technical publications for the rotorcraft, the lightweight digital representation including mesh-based 3D visualizations of each component of the rotorcraft, the technical publications having views referencing the mesh-based 3D visualizations; sending the individualized equipment data to the computer of the rotorcraft; and persisting the individualized equipment data at the computer of the rotorcraft.

A rotorcraft including a first power plant, at least one main rotor participating at least in providing lift for the rotorcraft in the air, and at least one tail rotor carried by a tail boom, the first power plant including at least one engine. In accordance with the invention, the rotorcraft includes: at least one pusher or puller propeller independent from the at least one main rotor, the at least one pusher or puller propeller participating at least in providing propulsion or traction for the rotorcraft; a second power plant including at least one electric motor; and at least one control member configured to generate a control setpoint or instruction for controlling the at least one electric motor.

A rotorcraft including a first power plant, at least one main rotor participating at least in providing lift for the rotorcraft in the air, and at least one tail rotor carried by a tail boom, the first power plant including at least one engine. In accordance with the invention, the rotorcraft includes: at least one pusher or puller propeller independent from the at least one main rotor, the at least one pusher or puller propeller participating at least in providing propulsion or traction for the rotorcraft; a second power plant including at least one electric motor; and at least one control member configured to generate a control setpoint or instruction for controlling the at least one electric motor.

A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.