SYSTEMS AND METHODS FOR IN-FLIGHT OPERATIONAL ASSESSMENT
A method of in-flight operational assessment for an electric aircraft comprising detecting by a sensor an electrical parameter of an energy source. The method further includes receiving by a controller the electrical parameter from the sensor and determining a power-production capability of the energy source, using the electrical parameter. The method further includes calculating, by the controller, a projected power-consumption need of the electric aircraft and comparing the determined power-production capability of the energy source to the projected power-consumption need. The method further includes displaying, by a graphical user interface, an element of the power-production capability of the energy source.
1 . A system for in-flight operational assessment, the system comprising:
an energy source mechanically coupled to an electric aircraft, wherein the energy source is configured to power at least a portion of the electric aircraft;
a sensor mechanically coupled to the electric aircraft, wherein the sensor is configured to detect an electrical parameter of the energy source;
a controller communicatively connected to the sensor, wherein the controller is designed and configured to:
receive the electrical parameter of the energy source from the sensor;
determine, using the electrical parameter, a power-production capability of the energy source;
calculate a projected power-consumption need of the electric aircraft; and
compare the determined power-production capability of the energy source to a projected power-consumption need;
a graphical user interface communicatively connected to the controller, wherein the graphical user interface is designed and configured to:
display at least an element of the power-production capability of the energy source based upon the comparison of the power-production capability and the projected power-consumption need.
2 . The system of claim 1 , wherein the electric aircraft further comprises a vertical takeoff and landing aircraft.
3 . The system of claim 1 , wherein the at least an energy source further comprises a plurality of energy sources connected in series.
4 . The system of claim 1 , wherein the at least a sensor further includes:
a voltage sensor;
a current sensor; and
an environmental sensor.
5 . The system of claim 4 , wherein the voltage sensor is configured to detect the voltage of the energy source.
6 . The system of claim 4 , wherein the current sensor is configured to detect the current of the energy source. The system of claim 4 , wherein the environmental sensor is configured to detect at least an element of environmental data.
8 . The system of claim 7 , wherein environmental data may include:
geospatial data;
ambient air temperature data;
barometric pressure data; and
turbulence data.
9 . The system of claim 1 , wherein determining the power-production capability of the energy source further comprises comparing the electrical parameter to a curve, wherein the curve represents a projected evolution over time of the energy source.
10 . The system of claim 9 , wherein comparing the electrical parameter to a curve further comprises modifying the curve as a function of the electrical parameter.
11 . The system of claim 1 , wherein the projected power-consumption need of the electric aircraft is calculated as function of a flight plan for the electric aircraft.
12 . A method of in-flight operational assessment, the method comprising:
detecting, by a sensor, an electrical parameter an energy source of an electric aircraft;
receiving, by a controller, the electrical parameter of the energy source from the sensor;
determining, by the controller, a power-production capability of the energy source, using the electrical parameter;
calculating, by the controller, a projected power-consumption need of the electric aircraft;
comparing, by the controller, the determined power-production capability of the energy source to a projected power-consumption need;
displaying, by a graphical user interface, at least an element of the power-production capability of the energy source based upon the comparison of the power-production capability and the projected power-consumption need.
13 . The method of claim 9 , wherein detecting the electrical parameter further comprises detecting, by a voltage sensor, a voltage level.
14 . The method of claim 9 , wherein detecting the electrical parameter further comprises detecting, by a current sensor, a current level.
15 . The method of claim 9 , wherein detecting the electrical parameter further comprises detecting, by an environmental sensor, an element of environmental data.
16 . The method of claim 9 , wherein determining the power-production capability further comprises comparing the electrical parameter to a curve, wherein the curve represents a projected evolution over time of the energy source.
17 . The method of claim 13 , wherein comparing the electrical parameter to a curve further comprises modifying the curve as a function of the electrical parameter.
18 . The method of claim 9 , wherein determining the power-production capability of the energy source further comprises:
determining the power-production capability of each energy source of a plurality of energy sources.
19 . The method of claim 15 , wherein determining the power-production capability of each energy source of a plurality of energy sources further comprises:
determining a plurality of component energy capabilities representing the energy capabilities of each energy source of the plurality of energy sources;
identifying a lowest component energy capability of the plurality of component energy capabilities; and
determining the delivery capability of the energy source as a function of the lowest component energy capability.
20 . The method of claim 9 , wherein calculating the projected power-consumption need of the electric aircraft is performed as a function of a flight plan for the electric aircraft.