Systems and methods for data verification at start up
Embodiments of the systems and methods disclosed herein describe a data verification of electrical electric components and software systems electronically or mechanically coupled to the electric aircraft by a novel process which starts an electric aircraft and receives physical and software information for each aircraft component or system and determines the status of the health of each of those components or systems. An embodiment may further include a monitoring system configured to measure a plurality of data from each aircraft component and a flight controller communicatively coupled to the monitoring system, wherein the data verification can be performed by the flight controller. Further embodiments may include the flight controller generating an output datum from the assessment produced by the data verification and displaying it to a pilot via an output device.
1 . A system comprising:
a plurality of software systems associated with an electric aircraft;
a sensor configured to detect an operational datum from an electric component of the electric aircraft;
a display; and
a processor communicably coupled to the plurality of software systems and the display, at startup of the electric aircraft, the processor configured to:
identify a software datum of each software system of the plurality of software systems;
receive the operational datum from the sensor;
retrieve a historical performance datum of the electric component from a previous flight;
determine a plurality of software status datum by determining, for each software system of the plurality of software systems, a respective software status datum based on a comparison of the respective software datum to an acceptance criterion and further based on an assessment of the operational datum relative to an operational threshold, wherein the assessment of the operational datum relative to an operational threshold includes a rate of degradation determined based on a comparison of the operational datum to the historical performance datum; and
initiate display of an output datum in a graphical form via the display, the output datum including the plurality of software status datum.
2 . The system of claim 1 , wherein the assessment of the operational datum relative to an operational threshold includes comparing the operational datum to a physical value or state representing an ideal or sufficient operability status or threshold for the electric component.
3 . The system of claim 1 , wherein the operational datum includes an operating state of the electric component, a torque value of the electric component, a lifecycle value for the electric component, or an energy efficiency value for the electric component.
4 . The system of claim 1 , wherein the operational datum includes a performance of the electric component during a most recent flight of the electric aircraft.
5 . The system of claim 1 , wherein the operational datum includes an indication of remaining power of an electric energy source associated with the electric component.
6 . The system of claim 1 , wherein the electric component includes a radio-frequency identification system, a gyroscope, a motion sensor, an inertial measurement unit, a propulsor, an electric energy source, or a landing gear.
7 . The system of claim 1 , wherein the plurality of software systems include a flight navigation system, a flight communication system, or a flight control system.
8 . The system of claim 1 , wherein the display includes a heads-up display in a pilot headwear.
9 . The system of claim 1 , wherein the software datum for a software system of the plurality of software systems includes a current software version of the software system.
10 . A method comprising:
receiving an operational datum from a sensor configured to detect the operational datum from an electric component of an electric aircraft at start-up of the electric aircraft;
receiving a software datum from a software system associated with the electric aircraft;
retrieving a historical performance datum of the electric component from a previous flight;
determining a software status datum based on a comparison of the software datum to an acceptance criterion and further based on an assessment of the operational datum relative to an operational threshold, wherein the assessment of the operational datum relative to an operational threshold includes a rate of degradation determined based on a comparison of the operational datum to the historical performance datum; and
initiating display of an output datum in a graphical form via a display, the output datum including the software status datum.
11 . The method of claim 10 , wherein the operational datum includes a state of health of the electric component.
12 . The method of claim 10 , wherein the electric component includes a radio-frequency identification system, and
the operational datum includes a serial number.
13 . The method of claim 10 , wherein the software datum includes a current software version of the software system, and
the software status datum includes a software version state indicating a comparison of the current software version for the software system with a software version table.
14 . The method of claim 13 , wherein the output datum further includes a signal representing the software version state.
15 . The method of claim 10 , wherein the assessment of the operational datum relative to an operational threshold includes comparing the operational datum to a physical value or state representing an ideal or sufficient operability status or threshold for the electric component.
16 . The method of claim 10 , wherein the operational datum includes an indication of remaining power of an electric energy source associated with the electric component.
17 . The system of claim 1 , wherein, at startup of the electric aircraft, the processor is further configured to select the acceptance criterion from a plurality of acceptance criteria based on the assessment of the operational datum relative to the operational threshold.
18 . The system of claim 1 , wherein the operational datum includes a hardware identifier of the electric component, and
at startup of the electric aircraft, the processor is further configured to:
determine the acceptance criterion by retrieving a software configuration associated with the hardware identifier, and
determine the software status datum by verifying that the software datum satisfies the software configuration.