Systems and methods for the autonomous transition of an electric vertical takeoff and landing aircraft
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.
1. A system for flight control of an electric vertical takeoff and landing (eVTOL) aircraft, the system comprising:
a fuselage;
a plurality of laterally extending elements secured to the fuselage;
a plurality of propulsors attached to the plurality of laterally extending elements, wherein the plurality of propulsors are configured to rotate between a lift position to a forward thrust position;
a flight controller including a reconfigurable hardware platform, the reconfigurable hardware platform containing hardware circuitry configured to:
identify a flight transition point;
determine a segmentation boundary of a segmented control algorithm, wherein the segmentation boundary includes a boundary associated with an ability of a propulsor of the plurality of propulsors;
distribute a plurality of commands based on the flight transition point and the segmentation boundary to a cluster of flight controllers, wherein each flight controller of the cluster of flight controllers operates a propulsor of the plurality of propulsors;
perform a flight maneuver based on the plurality of commands, wherein performing a flight maneuver includes performing a flight transition, wherein the flight transition includes:
initiating rotation about an axis of the fuselage as a function of the flight transition point; and
terminating rotation about the axis of the fuselage once a desired flight angle is reached.
2. The system of claim 1 , further comprising a pilot override switch.
3. The system of claim 1 , wherein each propulsor of the plurality of propulsors is attached to the aircraft by a rotating actuator.
4. The system of claim 1 , wherein the plurality of laterally extending elements includes at least a wing.
5. The system of claim 1 , wherein the plurality of propulsors attached to the plurality of laterally extending elements are configured to generate a generally upward thrust for the eVTOL aircraft when in the lift position.
6. The system of claim 1 , wherein the rotation of the plurality of propulsors is configured to generate a generally forward thrust for the eVTOL aircraft when in the forward thrust position.
7. The system of claim 1 , wherein the flight controller comprises information of a preplanned trajectory from vertical flight of the eVTOL aircraft to horizontal flight of the eVTOL aircraft.
8. The system of claim 1 , wherein the segmentation boundary includes a first starting section and a first ending section.
9. The system of claim 1 , wherein the flight controller comprises a proportional-integral-derivative (PID) controller.
10. The system of claim 1 , wherein the segmented control algorithm creates an optimized signal communication as a function of the segmentation boundary, wherein the optimized signal communication includes identifying a discrete timing to transmit the segmentation boundary.
11. A method for flight control of an electric vertical takeoff and landing (eVTOL) aircraft, the method comprising:
identifying, by a flight controller having a reconfigurable hardware platform, the reconfigurable hardware platform containing reconfigurable hardware circuitry, wherein the flight controller is incorporated in an electric vertical takeoff and landing (eVTOL) aircraft having a plurality of propulsors configured to rotate between a lift position to a forward thrust position, a flight transition point;
determining a segmentation boundary of a segmented control algorithm, wherein the segmentation boundary includes a boundary associated with an ability of a propulsor of the plurality of propulsors;
distributing a plurality of commands based on the flight transition point and the segmentation boundary to a cluster of flight controllers, wherein each flight controller of the cluster of flight controllers operates a propulsor of the plurality of propulsors;
performing a flight maneuver based on the plurality of commands, wherein performing the flight maneuver includes performing a flight transition, wherein the flight transition includes:
initiating, by the flight controller, rotation about an axis of the fuselage as a function of the flight transition point; and
terminating, by the flight controller, rotation about the axis of the fuselage once a desired flight angle is reached, as a function of the flight transition point.
12. The method of claim 11 wherein the eVTOL aircraft further comprises a pilot override switch.
13. The method of claim 11 wherein each propulsor of the plurality of propulsors is attached to the aircraft by a rotating actuator.
14. The method of claim 11 wherein a plurality of laterally extending elements includes at least a wing.
15. The method of claim 11 , wherein the plurality of propulsors attached to a plurality of laterally extending elements are configured to generate a generally upward thrust for the eVTOL aircraft when in the lift position.
16. The method of claim 11 , wherein the rotation of the plurality of propulsors is configured to generate a forward thrust for the eVTOL aircraft when in the forward thrust position.
17. The method of claim 11 , wherein the flight controller comprises information of a preplanned trajectory from vertical flight of the eVTOL aircraft to horizontal flight of the eVTOL aircraft.
18. The method of claim 11 , wherein the segmentation boundary includes a first starting section and a first ending section.
19. The method of claim 11 , wherein the flight controller comprises a proportional-integral-derivative (PID) controller.
20. The method of claim 11 , wherein the segmented control algorithm creates an optimized signal communication as a function of the segmentation boundary, wherein the optimized signal communication includes identifying a discrete timing to transmit the segmentation boundary.