Engine gateway with engine data storage

1. An engine gateway of a gas turbine engine of an aircraft, the engine gateway comprising:

a communication interface configured

to wirelessly communicate with an offboard system; and

to communicate with an engine control of the gas turbine engine using both a first communication bus and a second communication bus; wherein the first communication bus is distinct from the second communication bus;

a memory system;

a data storage system separate from the memory system; and

processing circuitry configured to:

provide communication with the engine control on attic first communication bus;

provide communication between the engine control and the data storage system on the second communication bus;

provide wireless communication with the onboard system using system credential authentication; and

update the data storage system by receiving an update from the offboard system following system credential authentication of the onboard system, communicating the update to the engine control on the first communication bus, and receiving the update from the engine control on the second communication bus.

2. The engine gateway of claim 1 , wherein the second communication bus provides electrical power from the engine control to the data storage system.

3. The engine gateway of claim 1 , wherein the data storage system comprises a controller and one or more non-volatile memory devices.

4. The engine gateway of claim 3 , wherein the controller is configured to manage the one or more updates using a buffer that enables reversion to a previous state of one or more data records based on detecting an error condition.

5. The engine gateway of claim 1 , wherein the data storage system is physically separated from the memory system.

6. The engine gateway of claim 1 , wherein communication with the engine control is performed using system credential authentication.

7. An engine gateway of a gas turbine engine of an aircraft, the engine gateway comprising:

a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine;

a memory system;

a data storage system isolated from the memory system, the data storage system comprising a controller and one or more non-volatile memory devices; and

processing circuitry configured to:

establish communication with the engine control on a first communication bus using system credential authentication;

establish communication between the engine control and the data storage system on a second communication bus;

establish wireless communication with the offboard system using system credential authentication;

provide access from the offboard system through the engine gateway, from the engine gateway through the engine control, and from the engine control to the data storage system to enable one or more updates of the data storage system by the offboard system based on service credential authentication; and

communicate with the controller in a maintenance mode based on determining that the engine control is disconnected from the engine gateway, wherein the maintenance mode is enabled based on one or more of: a discrete input, a keycode, and a connection between the first communication bus and the second communication bus.

8. The engine gateway of claim 1 , wherein user credential authentication is performed in combination with system credential authentication and service credential authentication.

9. The engine gateway of claim 1 , wherein the engine gateway is mounted on a fan case of the gas turbine engine, and the engine gateway is physically separated from the engine control.

10. A method comprising:

providing communication between an engine control of a gas turbine engine of an aircraft and an engine gateway on a first communication bus;

providing communication between the engine control and a data storage system of the engine gateway on a second communication bus, wherein the data storage system is separate from a memory system of the engine gateway, and the first communication bus is distinct from the second communication bus;

providing wireless communication between the engine gateway and an offboard system using system credential authentication; and

updating the data storage system by receiving an update from the offboard system following system credential authentication of the offboard system, communicating the update to the engine control on the first communication bus, and receiving the update from the engine control on the second communication bus.

11. The method of claim 10 , further comprising:

receiving electrical power on the second communication bus at the data storage system from the engine control.

12. The method of claim 10 , wherein the data storage system comprises a controller and one or more non-volatile memory devices.

13. The method of claim 12 , further comprising:

managing, by the controller, the one or more updates using a buffer that enables reversion to a previous state of one or more data records based on detecting an error condition.

14. The method of claim 12 , wherein further comprising:

communicating between the engine gateway and the controller in a maintenance mode based on determining that the engine control is disconnected from the engine gateway, wherein the maintenance mode is enabled based on one or more of: a discrete input, a keycode, and a connection between the first communication bus and the second communication bus.

15. The method of claim 10 , wherein user credential authentication is performed in combination with system credential authentication and service credential authentication.

16. The method of claim 10 , wherein the engine gateway is mounted on a fan case of the gas turbine engine, and the engine gateway is physically separated from the engine control.

17. A gas turbine engine of an aircraft, the gas turbine engine comprising:

a fan section comprising a fan case;

an engine control mounted on the fan case, the engine control configured to monitor and control operation of the gas turbine engine in real-time; and

an engine gateway mounted on the fan case, the engine gateway comprising:

a communication interface configured

to wirelessly communicate with an offboard system; and

to communicate with an engine control of the gas turbine engine using both a first communication bus and a second communication bus, wherein the first communication bus is distinct from the second communication bus;

a memory system

a data storage system separate from the memory system; and

processing circuitry configured to:

provide communication with the engine control on the first communication bus;

provide communication between the engine control and the data storage system on the second communication bus;

provide wireless communication with the offboard system using system credential authentication; and

update the data storage system by receiving an update from the offboard system following system credential authentication of the offboard system, communicating the update to the engine control on the first communication bus, and receiving the update from the engine control on the second communication bus.

18. The gas turbine engine of claim 17 , wherein the second communication bus provides electrical power from the engine control to the data storage system.

19. The gas turbine engine of claim 17 , wherein the data storage system comprises a controller and one or more non-volatile memory devices.

20. The gas turbine engine of claim 19 , wherein the controller is configured to manage the one or more updates using a buffer that enables reversion to a previous state of one or more data records based on detecting an error condition.

21. The gas turbine engine of claim 19 , wherein the processing circuitry is further configured to:

communicate with the controller in a maintenance mode based on determining that the engine control is disconnected from the engine gateway, wherein the maintenance mode is enabled based on one or more of: a discrete input, a keycode, and a connection between the first communication bus and the second communication bus.

22. The gas turbine engine of claim 17 , wherein user credential authentication is performed in combination with system credential authentication and service credential authentication.