Systems and methods for an electric vertical takeoff and landing aircraft braking system

1. A braking system for an electric vertical takeoff and landing aircraft, the system comprising:

a wheel configured to allow rolling motion of the aircraft on the ground, wherein the wheel is a part of the aircraft, the wheel comprising a first wheel and a second wheel;

a skid component at an undercarriage of the aircraft and configured to support the aircraft on the ground, wherein the skid component comprises a skid tube comprising:

a recess, wherein the recess houses the wheel and is configured to allow the wheel to rotate freely; and

a biasing mechanism, wherein the biasing mechanism is configured to generate an elastic recoil force to allow the wheel to extend or retract in the recess; and

a brake configured to resist rotation of the wheel, the brake comprising a first brake configured to resist rotation of the first wheel and a second brake configured to resist rotation of the second wheel;

a pilot control device, the pilot control device configured to:

detect a measured pilot input, the measured pilot input comprising selective braking by the first brake to steer the aircraft while the aircraft is in motion on the ground; and

generate a pilot datum as a function of the measured pilot input;

a controller communicatively connected to the aircraft and the pilot control device, the controller configured to:

receive the pilot datum from the pilot control device;

generate an action command based on the pilot datum; and

transmit an action command to at least a control surface, the at least a control surface comprises a caliper, wherein a pressure sensor is used to determine a force applied by the caliper to the brake pad and the caliper interacts with the brake pad to resist rotation of a wheel, the first brake, and a rudder of the aircraft, wherein transmitting the action command comprises:

controlling operation of the caliper of the first brake to resist rotation of the first wheel to steer the aircraft on the ground; and

controlling operation of the rudder to control yaw of the aircraft to steer the aircraft on the ground.

2. The system of claim 1 , wherein the at least a control surface comprises at least an actuator.

3. The system of claim 1 , wherein the at least a control surface comprises a propulsor.

4. The system of claim 1 , wherein the at least a control surface comprises a rudder.

5. The system of claim 1 , wherein the pilot control device comprises a brake pedal.

6. The system of claim 1 , wherein the pilot control device comprises a rudder pedal.

7. The system of claim 1 , wherein the pilot control device comprises a sensor configured to at least detect a position of a pedal.

8. The system of claim 7 , wherein the sensor comprises an accelerometer.

9. The system of claim 1 , wherein the aircraft comprises a sensor configured to at least detect a geospatial location of the aircraft, wherein the geospatial location includes a ground location and an airborne location.

10. The system of claim 9 , wherein the sensor is further configured to determine an orientation of the aircraft relative to a reference frame or point including ground and gravity vector.

11. The system of claim 1 , wherein the wheel comprises a sensor configured to detect pressure on the wheels.

12. The system of claim 1 , wherein the wheel comprises at least the first wheel on a first side of the aircraft and at least the second wheel on a second side of the aircraft.

13. The system of claim 12 , wherein the brake allows for steering of the aircraft through selective braking of the wheels.

14. The system of claim 13 , wherein selective braking of the wheels comprises only engaging the brake on either the at least a first wheel or the at least a second wheel.

15. The system of claim 1 , wherein the brake includes a regenerative brake configured to generate electrical energy.

16. The system of claim 1 , wherein the controller controls the at least a control surface when the aircraft is on the ground.

17. The system of claim 1 , wherein the controller controls the at least a control surface when the aircraft is airborne.

18. The system of claim 1 , wherein the controller activates braking when forward rolling motion above a predetermined threshold is detected.

19. The system of claim 1 , wherein the controller activates braking when backward rolling motion above a predetermined threshold is detected.