Hybrid propulsion system cockpit interface
An example system includes a throttle control for managing power in a hybrid propulsion system that includes an electrical propulsion unit configured to operate using electrical energy sourced from an electrical energy storage system (ESS) and/or one or more electrical generators, the throttle control comprising: a control lever movable through a plurality of positions, the plurality of positions including: a regeneration position; an off position; a maximum electric only position; a maximum continuous dual source position; and a maximum non-continuous dual source position.
1 . An airframe comprising:
a plurality of electrical propulsion units configured to propel, via respective propulsors, the airframe using electrical energy sourced from an electrical energy storage system (ESS) and/or one or more electrical generators, the one or more electrical generators configured to operate using fuel;
a display; and
one or more processors configured to output, for display at the display, a graphical user interface (GUI) that indicates a respective operating state of each respective electrical propulsion unit of the plurality of electrical propulsion units, wherein the indication of the operating state indicates, for each respective electrical propulsion unit:
a respective amount of torque provided by the respective electrical propulsion unit, and
a respective representation of a source of electrical power used by the respective electrical propulsion unit to provide the respective amount of torque, wherein the representation of the source of electrical power indicates an amount of electrical power sourced by the respective electrical propulsion unit from the one or more electrical generators relative to an amount of electrical power sourced by the respective electrical propulsion unit from the ESS.
2 . The airframe of claim 1 , wherein the one or more processors are further configured to output, for display at the display, a GUI that indicates an operating state of the ESS and an operating state of the one or more electrical generators.
3 . The airframe of claim 1 , wherein the representation of the source of electrical power for a particular electrical propulsion unit of the plurality of electrical propulsion units comprises a bar having a total size that represents the amount of torque provided by the particular electrical propulsion unit, a first portion of the bar represents the amount of electrical power sourced from the one or more electrical generators by the particular electrical propulsion unit, a second portion of the bar represents the amount of electrical power sourced from the ESS by the particular electrical propulsion unit, the first portion having a different visual appearance than the second portion.
4 . The airframe of claim 1 , wherein the ESS is configured to charge using electrical power generated by one or both of the plurality of electrical propulsion units and the one or more electrical generators, and wherein the representation of the source of electrical power indicates whether the ESS is charging.
5 . The airframe of claim 4 , wherein, when the ESS is charging using electrical power generated by the plurality of electrical propulsion units, the GUI indicates a negative amount of torque provided by the respective electrical propulsion unit.
6 . The airframe of claim 1 , wherein the GUI further indicates a maximum amount of torque available to the respective electrical propulsion unit.
7 . The airframe of claim 1 , wherein the maximum amount of torque available to a particular electrical propulsion unit of the plurality of electrical propulsion units is different than the amount of torque provided by the particular electrical propulsion unit.
8 . A system comprising a plurality of electrical propulsion units configured to propel an airframe using electrical energy sourced from an electrical energy storage system (ESS) and/or one or more electrical generators that operate using fuel, the system further comprising:
a display; and
one or more processors configured to output, for display at the display, a graphical user interface (GUI) that indicates a respective operating state of each respective electrical propulsion unit of the plurality of electrical propulsion units, wherein the indication of the operating state indicates, for each respective electrical propulsion unit:
a respective amount of torque provided by the respective electrical propulsion unit, and
a respective representation of a source of electrical power used by the respective electrical propulsion unit, wherein the respective representation of the source of electrical power indicates an amount of electrical power sourced by the respective electrical propulsion unit from the one or more electrical generators relative to an amount of electrical power sourced by the respective electrical propulsion unit from the ESS.
9 . The airframe of claim 8 , wherein the one or more processors are further configured to output, for display at the display, a GUI that indicates an operating state of the ESS and an operating state of the one or more electrical generators.
10 . The airframe of claim 8 , wherein the representation of the source of electrical power for a particular electrical propulsion unit of the plurality of electrical propulsion units comprises a bar having a total size that represents the amount of torque provided by the particular electrical propulsion unit, a first portion of the bar represents the amount of electrical power sourced from the one or more electrical generators by the particular electrical propulsion unit, a second portion of the bar represents the amount of electrical power sourced from the ESS by the particular electrical propulsion unit, the first portion having a different visual appearance than the second portion.
11 . The airframe of claim 8 , wherein the ESS is configured to charge using electrical power generated by one or both of the plurality of electrical propulsion units and the one or more electrical generators, and wherein the representation of the source of electrical power indicates whether the ESS is charging.
12 . The airframe of claim 11 , wherein, when the ESS is charging using electrical power generated by the plurality of electrical propulsion units, the GUI indicates a negative amount of torque provided by the respective electrical propulsion unit.
13 . The airframe of claim 8 , wherein the GUI further indicates a maximum amount of torque available to the respective electrical propulsion unit.
14 . The airframe of claim 8 , wherein the maximum amount of torque available to a particular electrical propulsion unit of the plurality of electrical propulsion units is different than the amount of torque provided by the particular electrical propulsion unit.
15 . A non-transitory computer-readable storage medium storing instructions that, when executed, cause one or more processors of an aircraft to:
control a plurality of electrical propulsion units of the aircraft to propel, via respective propulsors, the aircraft using electrical energy sourced from an electrical energy storage system (ESS) and/or one or more electrical generators, the one or more electrical generators configured to operate using fuel; and
output, for display, a graphical user interface (GUI) that indicates a respective operating state of each respective electrical propulsion unit of the plurality of electrical propulsion units, wherein the indication of the operating state indicates, for each respective electrical propulsion unit:
a respective amount of torque provided by the respective electrical propulsion unit, and
a respective representation of a source of electrical power used by the respective electrical propulsion unit to provide the respective amount of torque, wherein the respective representation of the source of electrical power indicates an amount of electrical power sourced by the respective electrical propulsion unit from the one or more electrical generators relative to an amount of electrical power sourced by the respective electrical propulsion unit from the ESS.