Gas turbine engine communication gateway with internal sensors
A method of operating a communication adapter of a gas turbine engine of an aircraft includes receiving a plurality of time series data at the communication adapter from an engine control of the gas turbine engine. The method also includes recording a plurality of internal sensor data of an internal sensor system of the communication adapter. The method further includes correlating the time series data with the internal sensor data based on an alignment in time to form an enhanced data set and transmitting the enhanced data set from the communication adapter to an offboard system.
1. A method comprising:
receiving a plurality of time series data at a communication adapter of a gas turbine engine of an aircraft, the time series data received from an engine control of the gas turbine engine;
recording a plurality of internal sensor data of an internal sensor system of the communication adapter;
correlating the time series data with the internal sensor data based on an alignment in time to form an enhanced data set; and
transmitting the enhanced data set from the communication adapter to an offboard system.
2. The method of claim 1 , wherein the communication adapter comprises a housing having a plurality of mounts configured to couple the communication adapter to a fan case of the gas turbine engine.
3. The method of claim 2 , wherein the housing comprises at least one antenna configured to support wireless communication.
4. The method of claim 3 , wherein the at least one antenna comprises a global positioning system antenna.
5. The method of claim 1 , wherein the time series data comprises a combination of aircraft parameters and engine control parameters with at least one time stamp to establish a time base for correlation with the internal sensor data.
6. The method of claim 5 , wherein the aircraft parameters are received on an aircraft bus by the engine control and forwarded to the communication adapter along with the engine control parameters.
7. The method of claim 6 , wherein the alignment in time adjusts for varying delays from the engine control and/or the aircraft bus.
8. The method of claim 5 , wherein the aircraft parameters are received directly by the communication adapter.
9. The method of claim 1 , wherein the internal sensor system comprises a plurality of sensors within the communication adapter.
10. The method of claim 9 , wherein the sensors comprise two or more of: an accelerometer, a gyroscope, a barometer, and a magnetometer.
11. The method of claim 1 , wherein the internal sensor data provides one or more of: a position, an orientation, and a g-load coordinated with time stamping.
12. The method of claim 1 , wherein recording of the internal sensor data is performed until an end condition is met.
13. The method of claim 12 , wherein the end condition is determined based on an amount of data collected.
14. The method of claim 12 , wherein the end condition is determined based on a time period of data collection.
15. The method of claim 12 , wherein the end condition is determined responsive to a command.
16. The method of claim 1 , wherein transmitting the enhanced data set is performed based on a transmit condition.
17. The method of claim 16 , wherein the transmit condition is determined based on receiving a command.
18. The method of claim 16 , wherein the transmit condition is determined based on a message size limit.
19. The method of claim 1 , wherein the time series data is received at the communication adapter during operation of the gas turbine engine.