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Propulsion prognostics apparatus and systems for an unmanned aerial vehicle (UAV) are provided. One propulsion prognostics apparatus comprises a prognostics module configured to generate prognostics data and a power output sensor configured to be coupled to the engine system and configured to genera

Propulsion prognostics apparatus and systems for an unmanned aerial vehicle (UAV) are provided. One propulsion prognostics apparatus comprises a prognostics module configured to generate prognostics data and a power output sensor configured to be coupled to the engine system and configured to generate power output data representing an actual power output of the engine system. The propulsion prognostics apparatus further comprises a processor coupled to the prognostics module and the power output sensor. The processor is configured to receive the prognostics data and the power output data, compare the prognostics data and the power output data, and determine the airworthiness of the UAV based on the comparison. A propulsion prognostics system includes a UAV having an engine system and the above propulsion prognostics apparatus coupled to the UAV.

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1. A propulsion prognostics apparatus for an unmanned aerial vehicle (UAV) having an engine system, comprising: a prognostics module configured to generate prognostics data;a power output sensor configured to be coupled to the engine system and configured to generate power output data representing a

1. A propulsion prognostics apparatus for an unmanned aerial vehicle (UAV) having an engine system, comprising: a prognostics module configured to generate prognostics data;a power output sensor configured to be coupled to the engine system and configured to generate power output data representing an actual power output of the engine system; anda processor coupled to the prognostics module and the power output sensor, the processor configured to: receive the prognostics data and the power output data,compare the prognostics data and the power output data, anddetermine the airworthiness of the UAV based on the comparison. 2. The propulsion prognostics apparatus of claim 1, wherein the prognostics module comprises: a tachometer configured to be coupled to the engine system;a throttle position sensor configured to be coupled to the engine system; anda barometric pressure sensor. 3. The propulsion prognostics apparatus of claim 2, further comprising memory coupled to the processor, the memory comprising a look-up table storing a plurality of expected power outputs for the engine system, each expected power output represents an amount of power the engine system should be producing for a particular set of a given rotational speed of the engine system, a given throttle command, and a given barometric pressure condition. 4. The propulsion prognostics apparatus of claim 3, wherein the processor is further configured to: determine an expected power output of the plurality of expected power outputs based on a rotational speed of the engine system detected by the tachometer, a throttle position detected by the throttle position sensor, and a barometric pressure detected by the barometric pressure sensor; andcompare the expected power output with the actual power output in determining the airworthiness of the UAV. 5. The propulsion prognostics apparatus of claim 1, wherein the prognostics module comprises: a tachometer configured to be coupled to the engine system;a throttle position sensor configured to be coupled to the engine system;a barometric pressure sensor; anda vertical rate of climb sensor. 6. The propulsion prognostics apparatus of claim 5, further comprising memory coupled to the processor, the memory comprising a look-up table storing a plurality of expected power outputs for the engine system, each expected power output represents an amount of power the engine system should be producing for a particular set of a given rotational speed of the engine system, a given throttle command, a given barometric pressure condition, and a given vertical rate of climb. 7. The propulsion prognostics apparatus of claim 6, wherein the processor is further configured to: determine an expected power output of the plurality of expected power outputs based on a rotational speed of the engine system detected by the tachometer, a throttle position detected by the throttle position sensor, a barometric pressure detected by the barometric pressure sensor, and a vertical rate of climb detected by the vertical rate of climb sensor; andcompare the expected power output with the actual power output in determining the airworthiness of the UAV. 8. The propulsion prognostics apparatus of claim 1, wherein the prognostics module comprises a pre-flight module and an in-flight module. 9. The propulsion prognostics apparatus of claim 8, wherein the pre-flight module comprises: a tachometer configured to be coupled to the engine system,a throttle position sensor configured to be coupled to the engine system, anda barometric pressure sensor; andwherein the in-flight module comprises:the tachometer,the throttle position sensor,the barometric pressure sensor, anda vertical rate of climb sensor. 10. The propulsion prognostics apparatus of claim 9, further comprising memory coupled to the processor, the memory comprising: a first look-up table storing a plurality of first expected power outputs for the engine system, each first expected power output represents an amount of pre-flight power the engine system should be producing for a particular set of a given rotational speed of the engine system, a given throttle command, and a given barometric pressure condition; anda second look-up table storing a plurality of second expected power outputs for the engine system, each second expected power output represents an amount of in-flight power the engine system should be producing for a particular set of a given rotational speed of the engine system, a given throttle command, a given barometric pressure condition, and a given vertical rate of climb. 11. The propulsion prognostics apparatus of claim 10, wherein the processor is further configured to: determine a first expected power output of the plurality of expected power outputs based on a first rotational speed of the engine system detected by the tachometer, a first throttle position detected by the throttle position sensor, and a first barometric pressure detected by the barometric pressure sensor;compare the first expected power output with a first actual power output in determining the airworthiness of the UAV prior to flight;determine a second expected power output of the plurality of expected power outputs based on a second rotational speed of the engine system detected by the tachometer, a second throttle position detected by the throttle position sensor, a second barometric pressure detected by the barometric pressure sensor, and a vertical rate of climb detected by the vertical rate of climb sensor; andcompare the second expected power output with a second actual power output during flight in determining the airworthiness of the UAV during flight. 12. A system, comprising: an unmanned aerial vehicle (UAV) including an engine system; anda propulsion prognostics apparatus coupled to the UAV, the propulsion prognostics apparatus comprising: a prognostics module configured to generate prognostics data,a power output sensor coupled to the engine system and configured to generate power output data representing an actual power output of the engine system, anda processor coupled to the prognostics module and the power output sensor, the processor configured to: receive the prognostics data and the power output data,compare the prognostics data and the power output data, anddetermine the airworthiness of the UAV based on the comparison. 13. The system of claim 12, wherein the prognostics module comprises a pre-flight module and an in-flight module. 14. The system of claim 13, wherein the pre-flight module comprises: a tachometer configured to be coupled to the engine system,a throttle position sensor configured to be coupled to the engine system, anda barometric pressure sensor; andwherein the in-flight module comprises:the tachometer,the throttle position sensor,the barometric pressure sensor, anda vertical rate of climb sensor. 15. The system of claim 14, further comprising memory coupled to the processor, the memory comprising: a first look-up table storing a plurality of first expected power outputs for the engine system, each first expected power output represents an amount of pre-flight power the engine system should be producing for a particular set of a given rotational speed of the engine system, a given throttle command, and a given barometric pressure condition; anda second look-up table storing a plurality of second expected power outputs for the engine system, each second expected power output represents an amount of in-flight power the engine system should be producing for a particular set of a given rotational speed of the engine system, a given throttle command, a given barometric pressure condition, and a given vertical rate of climb. 16. The system of claim 15, wherein the processor is further configured to: determine a first expected power output of the plurality of expected power outputs based on a first rotational speed of the engine system detected by the tachometer, a first throttle position detected by the throttle position sensor, and a first barometric pressure detected by the barometric pressure sensor;compare the first expected power output with a first actual power output in determining the airworthiness of the UAV prior to flight;determine a second expected power output of the plurality of expected power outputs based on a second rotational speed of the engine system detected by the tachometer, a second throttle position detected by the throttle position sensor, a second barometric pressure detected by the barometric pressure sensor, and a vertical rate of climb detected by the vertical rate of climb sensor; andcompare the second expected power output with a second actual power output during flight in determining the airworthiness of the UAV during flight. 17. The system of claim 13, wherein the pre-flight module comprises: a tachometer coupled to the engine system;a throttle position sensor coupled to the engine system; anda barometric pressure sensor. 18. The system of claim 17, further comprising memory coupled to the processor, the memory comprising a look-up table storing a plurality of expected power outputs for the engine system, each expected power output represents an amount of power the engine system should be producing for a particular set of a given rotational speed of the engine system, a given throttle command, and a given barometric pressure condition, wherein the processor is further configured to: determine an expected power output of the plurality of expected power outputs based on a rotational speed of the engine system detected by the tachometer, a throttle position detected by the throttle position sensor, and a barometric pressure detected by the barometric pressure sensor, andcompare the expected power output with the actual power output in determining the airworthiness of the UAV prior to flight. 19. The system of claim 13, wherein the in-flight module comprises: a tachometer coupled to the engine system;a throttle position sensor coupled to the engine system;a barometric pressure sensor; anda vertical rate of climb sensor. 20. The system of claim 19, further comprising memory coupled to the processor, the memory comprising a look-up table storing a plurality of expected power outputs for the engine system, each expected power output represents an amount of power the engine system should be producing for a particular set of a given rotational speed of the engine system, a given throttle command, a given barometric pressure condition, and a given vertical rate of climb, wherein the processor is further configured to: determine an expected power output of the plurality of expected power outputs based on a rotational speed of the engine system detected by the tachometer, a throttle position detected by the throttle position sensor, a barometric pressure detected by the barometric pressure sensor, and a vertical rate of climb detected by the vertical rate of climb sensor, andcompare the expected power output with the actual power output in determining the airworthiness of the UAV during flight.