System for establishing a primary function display in an electrical vertical takeoff and landing aircraft
A system for establishing a primary function display for an electrical vertical takeoff and landing aircraft. The system further includes a plurality of sensors that detects at least a metric and generates at least a datum based on the at least a metric. Specifically, state of charge is at least generated based on the performance metric of an energy source. The system further includes a display to show the at least a datum. The system further includes a controller that receives the at least a datum and generates a visual to the pilot.
1 . A method comprising:
determining, by a controller, a power-production capability of at least one energy source based at least in part on at least one electrical parameter;
calculating, by the controller, at least a projected power-consumption need of an electric aircraft;
comparing, by the controller, the power-production capability of the at least one energy source to the projected power-consumption need; and
displaying at least an element of the power-production capability compared to the projected power-consumption need.
2 . The method of claim 1 , wherein determining the power-production capability includes determining a state of charge (SOC) of the at least one energy source and modifying an SOC curve as a function of the at least one electrical parameter.
3 . The method of claim 1 , wherein determining the projected power-consumption need includes determining an energy cost associated with performing one or more maneuvers associated with a flight plan.
4 . The method of claim 3 , wherein the one or more maneuvers include at least one of a landing according to a landing protocol or traveling a distance while cruising.
5 . The method of claim 1 , wherein determining the projected power-consumption need includes determining at least one condition of flight including at least one of a speed of wind, a direction of wind, air density, degree of turbulence, or exterior temperature.
6 . The method of claim 1 , wherein the element of the power-production capability includes an indication of a remaining time able to use rotor-based flight based on the at least one energy source.
7 . The method of claim 1 , wherein the at least one electrical parameter includes torque datum and the element includes indication of a torque value require for power-production capability.
8 . 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:
determining, by a controller, a power-production capability of at least one energy source based at least in part on at least one electrical parameter;
calculating, by the controller, at least a projected power-consumption need of an electric aircraft;
comparing, by the controller, the power-production capability of the at least one energy source to the projected power-consumption need; and
displaying at least an element of the power-production capability compared to the projected power-consumption need.
9 . The computing device of claim 8 , wherein determining the power-production capability includes determining a state of charge (SOC) of the at least one energy source and modifying an SOC curve as a function of the at least one electrical parameter.
10 . The computing device of claim 8 , wherein determining the projected power-consumption need includes determining an energy cost associated with performing one or more maneuvers associated with a flight plan.
11 . The computing device of claim 10 , wherein the one or more maneuvers include at least one of a landing according to a landing protocol or traveling a distance while cruising.
12 . The computing device of claim 8 , wherein determining the projected power-consumption need includes determining at least one condition of flight including at least one of a speed of wind, a direction of wind, air density, degree of turbulence, or exterior temperature.
13 . The computing device of claim 8 , wherein the element of the power-production capability includes an indication of a remaining time able to use rotor-based flight based on the at least one energy source.
14 . The computing device of claim 8 , wherein the at least one electrical parameter includes torque datum and the element includes indication of a torque value require for power-production capability.
15 . An arial vehicle comprising:
a processor; and
memory storing computer readable instructions causing the processor to perform one or more operations including:
determining, by a controller, a power-production capability of at least one energy source based at least in part on at least one electrical parameter;
calculating, by the controller, at least a projected power-consumption need of an electric aircraft;
comparing, by the controller, the power-production capability of the at least one energy source to the projected power-consumption need; and
displaying at least an element of the power-production capability compared to the projected power-consumption need.
16 . The arial vehicle of claim 15 , wherein determining the power-production capability includes determining a state of charge (SOC) of the at least one energy source and modifying an SOC curve as a function of the at least one electrical parameter.
17 . The arial vehicle of claim 15 , wherein determining the projected power-consumption need includes determining an energy cost associated with performing one or more maneuvers associated with a flight plan.
18 . The arial vehicle of claim 17 , wherein the one or more maneuvers include at least one of a landing according to a landing protocol or traveling a distance while cruising.
19 . The arial vehicle of claim 15 , wherein determining the projected power-consumption need includes determining at least one condition of flight including at least one of a speed of wind, a direction of wind, air density, degree of turbulence, or exterior temperature.
20 . The arial vehicle of claim 15 , wherein the element of the power-production capability includes an indication of a remaining time able to use rotor-based flight based on the at least one energy source.