System for establishing a primary function display in an electrical vertical takeoff and landing aircraft

Patent metadata

Field	Value
Publication number	US-12492007-B2
Application number	US-202418773379-A
Country	US
Kind code	B2
Filing date	Jul 15, 2024
Priority date	Jan 13, 2022
Publication date	Dec 9, 2025
Grant date	Dec 9, 2025

Abstract

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.

First claim

What is claimed is:

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.

Assignees

• Beta Air Llc

Inventors

• Ferrier Lochie

Classifications

• H02J2105/32

  for aircrafts · CPC title

• H02J7/82

  Control of state of charge [SOC] · CPC title

• B64D27/34

  All-electric aircraft · CPC title

• B64D27/357

  using batteries · CPC title

• B64U2101/30

  for imaging, photography or videography · CPC title