A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a fuselage, a plurality of laterally extending elements, a plurality of propulsors, a flight controller, and a pilot override switch. The plurality of laterally extending elements are attached to the fuselage. The plurality of propulsors is attached to the plurality of laterally extending elements. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a flight transition point, initiate rotation about an axis of the fuselage a as function of the flight transition point, and terminate rotation once the desired flight angle is reached.

A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a fuselage, a plurality of laterally extending elements, a plurality of propulsors, a flight controller, and a pilot override switch. The plurality of laterally extending elements are attached to the fuselage. The plurality of propulsors is attached to the plurality of laterally extending elements. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a flight transition point, initiate rotation about an axis of the fuselage a as function of the flight transition point, and terminate rotation once the desired flight angle is reached.

An automatic aircraft powerplant control system includes a throttle servo for adjusting a throttle valve via a throttle control linkage. A throttle control lever provides a user input to the throttle servo, and a throttle controller controls the throttle servo for controlling a throttle valve. A propeller servo may be provided for adjusting a propeller governor setting of an engine. A propeller control lever provides a user input to the propeller servo, and a propeller controller controls the propeller servo. A full-authority digital engine control (FADEC) controller is used to automatically control mixing of fuel and air via a fuel-air mixture device. The FADEC controller may be used to automatically provide propeller control.

A hover and thrust control assembly for dual-mode aircraft including a plurality of flight components mechanically coupled to an aircraft includes a support structure attached to an aircraft frame of an aircraft having a control stick coupled to the support structure. The control stick may include a length and radius and configured to be manipulated along a plurality of axes, wherein the manipulation of the control stick produces an electronic signal, wherein the control stick is further configured to be manipulated rotationally about the length of the control stick. A first interface device disposed on the control stick may be configured to receive an interaction and adjust a lift of the dual-mode aircraft as a function of the interaction. A second interface device may be configured to receive an interaction and adjust the lift of the dual-mode aircraft as a function of the interaction.

An aircraft having reverse thrust capabilities includes a fuselage, a plurality of flight components, a pilot control located within the fuselage, a sensor attached to the pilot control configured to detect an aircraft datum from the pilot control, and a flight controller, located within the fuselage, the flight controller configured to receive the aircraft datum from the sensor, and initiate a reverse torque command of a flight component of the plurality of flight components as a function of the aircraft datum.

An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

A land-and-air vehicle configured to switch between a first form to be taken during ground traveling and a second form to be taken during flight includes a main body, a main wing unit, an operation unit, and a controller. The controller is configured to control, on the basis of an operation performed on the operation unit by an operator, a behavior of the land-and-air vehicle during the ground traveling and during the flight. The operation unit includes a handle and a step. The handle of the operation unit includes a throttle unit. The controller is configured to control, both during the ground traveling and during the flight, yawing of the land-and-air vehicle in response to an operation performed on the handle, and to control thrust for the land-and-air vehicle during the flight in response to an operation performed on the throttle unit.

A land-and-air vehicle configured to switch between a first form to be taken during ground traveling and a second form to be taken during flight includes a main body, a main wing unit, an operation unit, and a controller. The controller is configured to control, on the basis of an operation performed on the operation unit by an operator, a behavior of the land-and-air vehicle during the ground traveling and during the flight. The operation unit includes a handle and a step. The handle of the operation unit includes a throttle unit. The controller is configured to control, both during the ground traveling and during the flight, yawing of the land-and-air vehicle in response to an operation performed on the handle, and to control thrust for the land-and-air vehicle during the flight in response to an operation performed on the throttle unit.

Methods, apparatus, systems and a vertical take-off and landing (VTOL) vehicle are provided. The VTOL vehicle includes: a fuselage having longitudinally a front section, a central section and a rear section; a first lifting surface comprising two wings respectively secured to opposite sides of the rear section of the fuselage; a second lifting surface comprising two wings respectively secured to opposite sides of the front section of the fuselage; where each wing comprises at least one engine module, each of the engine modules being pivotally coupled to the wing and each engine module being independently controlled for transitioning between a vertical mode of flight and a horizontal mode of flight.