Systems and methods for displaying a pilot display for an aircraft
In an aspect of the present disclosure a pilot display system for an aircraft includes a sensor configured to measure an aircraft position and generate a position datum based on the aircraft position, a display incorporated in the aircraft, and a computing device communicatively connected to the sensor and the display, the computing device configured to receive a flight path including a transition point, determine, from the position datum, the aircraft position relative to the transition point, and command the display to display a visual representation of the aircraft position relative to the transition point.
1 . A pilot display system for an aircraft, the system comprising:
a sensor configured to measure an aircraft position and generate a position datum based on the aircraft position;
a display incorporated in the aircraft; and
a computing device communicatively connected to the sensor and the display, the computing device configured to:
receive a flight path including a transition point;
determine, based at least in part on the position datum, the aircraft position relative to the transition point; and
command the display to display a visual representation of the aircraft position relative to the transition point, wherein the transition point represents a location along the flight path where the aircraft is transitioning between fixed-wing flight and vertical rotor-based flight or between vertical rotor-based and fixed-wing flight.
2 . The system of claim 1 , wherein the display is a heads-up display.
3 . The system of claim 1 , wherein the visual representation comprises:
a location of the visual representation relative to a horizon during a style in flight transition; and
a corresponding degree of correction for pitch of the aircraft.
4 . The system of claim 1 , wherein:
the transition point comprises a first altitude,
the position datum comprises a second altitude, and
determining, based at least in part on the position datum, the aircraft position relative the transition point further comprises comparing the first altitude and the second altitude.
5 . The system of claim 1 , wherein the visual representation is configured to represent the transition in style of flight, wherein the visual representation further comprises a location of the visual representation relative to a horizon during a style in flight transition and a corresponding degree of correction for pitch of the aircraft.
6 . The system of claim 1 , wherein the display comprises a visual representation of a horizon, wherein the visual representation positioned on the horizon signifies that the aircraft is in the flight path.
7 . The system of claim 1 , wherein the aircraft is an electric vertical takeoff and landing (eVTOL) aircraft comprising at least a vertical propulsor.
8 . The system of claim 7 , wherein the eVTOL comprises at least a forward propulsor.
9 . The system of claim 1 , wherein the transition point comprises a first altitude, the position datum comprises a second altitude, and determining, from the position datum, the aircraft position relative the transition point further comprises comparing the first altitude and the second altitude.
10 . A method for displaying a pilot display for an aircraft, the method comprising:
receiving a flight path including a transition point;
determining, based at least in part on position datum, an aircraft position relative to the transition point; and
commanding a display to display a visual representation of the aircraft position relative to the transition point, wherein the transition point represents a location along the flight path where the aircraft is transitioning between fixed-wing flight and vertical rotor-based flight or between vertical rotor-based and fixed-wing flight.
11 . The method of claim 10 , wherein the display is a heads-up display.
12 . The method of claim 10 , wherein the visual representation is configured to represent the transition in style of flight, wherein the visual representation further comprises a location of the visual representation relative to a horizon during the style in flight transition and a corresponding degree of correction for pitch of the aircraft.
13 . The method of claim 10 , wherein the display comprises a visual representation of a horizon, wherein the visual representation positioned on the horizon signifies that the aircraft is in the flight path.
14 . The method of claim 10 , wherein the flight path is based on a flight plan.
15 . The method of claim 10 , wherein the aircraft is an electric vertical takeoff and landing (eVTOL) aircraft comprising at least a vertical propulsor.
16 . The method of claim 15 , wherein the display comprises a visual representation of a horizon eVTOL comprises at least a forward propulsor.
17 . The method of claim 10 , further comprising receiving the flight path from another computing device transition point comprises a first altitude, the position datum comprises a second altitude, and determining, from the position datum, the aircraft position relative the transition point further comprises comparing the first altitude and the second altitude.
18 . A computing device comprising:
one or more processors; and
one or more non-transitory computer-readable media storing computer-executable instructions that, when executed, cause the one or more processors to perform operations comprising:
receive a flight path that includes a transition point;
determine, based at least in part on position datum, an aircraft position relative to the transition point; and
command a display to display a visual representation of the aircraft position relative to the transition point, wherein the transition point represents a location along the flight path where the aircraft is transitioning between fixed-wing flight and vertical rotor-based flight or between vertical rotor-based and fixed-wing flight.
19 . The computing device of claim 18 , wherein the computing device is further configured to command the display to display an image of at least an arrow to indicate a corrective maneuver of an aircraft as a function of a degree of deviation of the aircraft position from the flight path.
20 . The computing device of claim 18 , wherein the flight path is based on at least a state of charge of a battery.