Systems and methods for flight control on an electric aircraft. The system includes a propulsor configured to generate lift to propel an electric aircraft, a pilot input mechanically coupled to the electric aircraft, a sensor communicatively connected to the pilot input, and a flight controller communicatively connected to the sensor. Sensor is configured to detect an input datum from the pilot input and convert the input datum into a command datum for the propulsor as a function of input mapping. Input mapping is determined as a function of the phase of flight.

The novel wing design disclosed herein has a cambered, swept wing design for aircraft application that can achieve steady state flight via the integration of an electric motor driven lift-thrust system that can provide both vertical thrust for take-off and horizontal thrust for flight propulsion by the selective use of fan blades connected to the motor.

The novel wing design disclosed herein has a cambered, swept wing design for aircraft application that can achieve steady state flight via the integration of an electric motor driven lift-thrust system that can provide both vertical thrust for take-off and horizontal thrust for flight propulsion by the selective use of fan blades connected to the motor.

An aircraft, in particular a personal air mobility aircraft or a drone, having one or more annular propellers, with one or more blades extending radially from a rotor ring body towards the axis of the rotor ring, and one or more belt transmissions, which connect the rotor ring of each annular propeller with the output shaft of a motor unit including an electric motor. Various aircraft configurations include a vertical take-off and horizontal flight configuration. The aircraft surfaces are covered by groups of photovoltaic solar cells connected to a main battery pack for powering the electric motors that drive the annular propellers, and to an auxiliary electric battery for powering the on-board electrical circuit.

An aircraft, in particular a personal air mobility aircraft or a drone, having one or more annular propellers, with one or more blades extending radially from a rotor ring body towards the axis of the rotor ring, and one or more belt transmissions, which connect the rotor ring of each annular propeller with the output shaft of a motor unit including an electric motor. Various aircraft configurations include a vertical take-off and horizontal flight configuration. The aircraft surfaces are covered by groups of photovoltaic solar cells connected to a main battery pack for powering the electric motors that drive the annular propellers, and to an auxiliary electric battery for powering the on-board electrical circuit.

A cooling system includes a plurality of heat exchanger assemblies corresponding to a plurality of battery packs and a fluid conveyance assembly. Each heat exchanger assembly includes a first heat exchanger inlet-outlet and a second heat exchanger inlet-outlet configured to receive a heat transfer fluid or discharge the heat transfer fluid. The fluid conveyance assembly is coupled to the heat exchanger assemblies and configured to circulate the heat transfer fluid in parallel to the heat exchanger assemblies in a U-flow scheme with an inlet and an outlet of the heat transfer fluid arranged at the same location. The fluid conveyance assembly includes a plurality of flow restrictors configured to balance the heat transfer fluid flowing into the heat exchanger assemblies. The heat transfer fluid flows through the corresponding flow restrictor before flowing into the corresponding heat exchanger assembly of the battery pack.

An aircraft capable of carrying at least 400 pounds of payload, has four rotors systems, each of the rotor systems being independently driven by an electric motor or other torque-producing source. Each of the rotor systems provide sufficient thrust such that the aircraft is capable of controlled vertical takeoff and landing, even if one of the variable pitch rotor is inoperable. An electronic control system is configured to control the rotational speed and pitch of at least one of the rotor systems in each of the first and second rotor pairs. The rotors may be arranged in coaxial stacks or may be otherwise configured.

Aspects of this present disclosure relate to flight control of electric aircrafts and other vehicles. In one embodiment, an aircraft is disclosed comprising: a fuselage; two wings; a plurality of lift propellers, the lift propellers disposed aft of the wings during forward flight; plurality of tilt propellers that are tiltable between vertical lift and forward propulsion configurations, the tilt propellers disposed forward of the wings during forward flight; a plurality of tilt propellor actuators that tilt propellers between vertical lift and forward propulsion configurations, the tilt propellor actuators on opposite sides of the fuselage; and a plurality of electrical buses coupled to a flight control computer; wherein the flight control computer is configured to provide control signals for at least one of the lift propellers mounted to one of the wings and one of the tilt propellers mounted to the other wing via the same electrical bus.

An electrical propulsion assembly that includes: a propeller that has a rotation axis, at least two electric motors offset relative to one another in a longitudinal direction parallel to the rotation axis of the propeller, a main drive shaft parallel to the rotation axis of the propeller to which the electric motor are coupled, a transmission system including an output shaft connected to the propeller and an input shaft connected to the main drive shaft. Also an aircraft including at least one such electrical propulsion assembly.

An electrical propulsion assembly that includes: a propeller that has a rotation axis, at least two electric motors offset relative to one another in a longitudinal direction parallel to the rotation axis of the propeller, a main drive shaft parallel to the rotation axis of the propeller to which the electric motor are coupled, a transmission system including an output shaft connected to the propeller and an input shaft connected to the main drive shaft. Also an aircraft including at least one such electrical propulsion assembly.