A flying vehicle propulsion system including a propulsor, a drive system and a heat exchanger. The drive system is arranged to drive the propulsor and the heat exchanger is arranged to thermally regulate at least part of the drive system. The propulsor is arranged to move fluid, thereby producing a propulsor fluid flow having a main direction. The system is arranged such that in a first operation configuration, at least part of the propulsor fluid flow is incident on the heat exchanger, thereby thermally regulating the at least part of the drive system.

An abnormality warning system provides an abnormality warning for multiple motor systems that drive a motor used correspondingly to each of multiple rotors included in an electric aircraft. The abnormality warning system includes an abnormality determination unit and a warning level setting unit. The abnormality determination unit determines an abnormal one of the motor systems. The warning level setting unit sets a warning level to warn abnormality, based on at least position information of the rotor in the electric aircraft or the usage of the rotor corresponding to a motor system determined to be abnormal by the abnormality determination unit.

A system for automated flight correction is an electric aircraft that includes an input control configured to receive a user input and generate a control datum as a function of the user input, at least a sensor connected to the electric aircraft that is configured to detect a status datum and transmit the status datum to a flight controller, a flight controller communicatively connected to the input control and the at least a sensor configured to receive the control datum from the input control, receive the status datum from the flight controller and determine a command datum as a function of the control datum and status datum, and an actuator connected to the flight controller configured to receive the command datum from the flight controller and command at least a flight component as a function of the command datum.

A system for estimating flight range of an electric aircraft. The system generally includes at least a sensor and a flight controller. The at least a sensor is communicatively connected to at least a flight component. The at least a sensor is configured to detect a performance datum of the at least a flight component. The flight controller is communicatively connected to the at least a sensor. The flight controller is configured to receive the performance datum from the at least a sensor, determine an energy performance datum from the performance datum, determine a flight performance datum from the performance datum, generate a projected flight range datum as a function of the energy performance datum and the flight performance datum, and display the projected flight range datum. A method for estimating flight range of an electric aircraft is also provided.

An aircraft includes a short-range radar that is configured to detect a trajectory, which is specified based on a position detection of the aircraft by a ground station.

Winged tilt-rotor vertical take-off and landing (VTOL) aircraft and related methods are disclosed. Aircraft comprise an airframe comprising one or more wings; one or more tilt-adjustable rotors positioned forward of the one or more wings; and one or more fixed-tilt rotors positioned behind at least one of the one or more wings. Methods comprise tilting only one or more forward rotors positioned in front of one or more wings of the aircraft, and not tilting one or more rearward rotors positioned behind at least one of the one or more wings.

A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight trust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

A multi-axis amphibious copter for flying and cruising at high speeds. The multi-axis amphibious copter includes six propulsion points i.e., four propellors oriented vertically, a coaxial rotor oriented vertically, and a mini turbine thruster on the rear of the aircraft body and configured to propel the multi-axis amphibious copter forward. The multi-axis amphibious copter can land and take off vertically from congested places and can fly at cruising speeds.

A ducted fan of an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan radially at the outside and that defines a flow channel for air flowing via the fan. The stator-side duct has an inner wall facing toward the fan, an outer wall averted from the fan, and at least one stiffening strut that runs within the flow channel. The stiffening strut, at one respective end, extends through the duct and protrudes radially relative to the outer wall of the duct. At the respective end of the stiffening strut, a fastening device is formed. The fastening device is configured to mount the ducted fan on a structural component of the aircraft. The fastening device has an insert composed of a fiber-reinforced plastic and laminated into the respective end of the stiffening strut.

Systems and methods to control gain of an electric aircraft are provided in this disclosure. The system may include gain scheduling to provide stability of the electric aircraft at various dynamic states of operation. The system may include a sensor to obtain measurement datum of an operating state. The system may further include a controller that adjusts a control gain of the electric aircraft as a function of the measurement datum. The gain control may be determined by a gain schedule generated by the controller.