Engine control system
Certain examples disclose and describe apparatus and methods to reprogram all electronic engine control system processors through a single external network interface to an aircraft data loader. In such examples, a main processor that interfaces to an aircraft communication network is to operate as both a data loader and a loadable device. Distributed electronic engine control processors are reprogrammable from a single network interface, rather than requiring separate, direct access to each controller.
1. An electronic engine control system comprising:
a first processor positioned at a first location in an aircraft engine under an engine cowl, in communication with an aircraft data loader, and programmable by the aircraft data loader according to a file;
a second processor positioned at a second location apart from the first location in the aircraft engine under the engine cowl and programmable by the first processor according to the file; and
a wired connection between the first processor and the second processor, the wire connection to transfer the file between the first processor and the second processor without opening the engine cowl.
2. The system of claim 1 , wherein the first processor is a main processor and the second processor is a distributed processor, wherein the distributed processor is not in communication with the aircraft data loader.
3. The system of claim 1 , further including the aircraft data loader.
4. The system of claim 1 , further including an aircraft network interface to transfer the file between the aircraft data loader and the first processor.
5. The system of claim 1 , wherein the first processor is configured to operate as a loadable device in a first mode and to operate as a data loader in a second mode.
6. The system of claim 1 , wherein the first processor is configured to operate as both a loadable device and as a data loader while in a programming mode.
7. The system of claim 1 , further including a maintenance interface for the second processor, the maintenance interface accessible through the engine cowl.
8. The system of claim 1 , wherein the first processor is to program the second processor while the first processor is being programmed by the aircraft data loader.
9. The system of claim 1 , wherein the first processor is to trigger a reboot of the second processor to place the second processor in a programming mode to install the file.
10. The system of claim 1 , further including the aircraft engine in which the first processor, the second processor, and the wired connection are arranged.
11. A non-transitory computer readable medium comprising machine-readable instructions that, when executed, cause at least a first processor to at least:
receive, from an aircraft data loader, files for installation on the first processor, the first processor positioned at a first location in an aircraft engine under an engine cowl;
trigger a reboot of a second processor positioned at a second location apart from the first location in the aircraft engine under the engine cowl; and
while installing the files on the first processor, transfer the files to the second processor via a wired connection to facilitate installation of the files on the second processor without opening the engine cowl.
12. The computer readable medium of claim 11 , wherein the instructions, when executed, configure the first processor to operate as both a loadable device and as a data loader while in a programming mode.
13. The computer readable medium of claim 11 , wherein the first processor is to program the second processor while the first processor is being programmed by the aircraft data loader.
14. The computer readable medium of claim 11 , wherein the first processor is to trigger the reboot of the second processor to place the second processor in a programming mode to install the files.
15. The computer readable medium of claim 11 , wherein the instructions, when executed, are to trigger the first processor to enter a programming mode to receive the files and exit the programming mode after the files are installed.
16. A method for programming an engine control system, the method comprising:
receiving, from an aircraft data loader, files for installation on a first processor, the first processor positioned at a first location in an aircraft engine under an engine cowl;
triggering a reboot of a second processor positioned at a second location apart from the first location in the aircraft engine under the engine cowl; and
while installing the files on the first processor, transferring the files to the second processor via a wired connection to facilitate installation of the files on the second processor without opening the engine cowl.
17. The method of claim 16 , further including configuring the first processor to operate as both a loadable device and as a data loader while in a programming mode.
18. The method of claim 16 , wherein the first processor is programming the second processor while the first processor is being programmed by the aircraft data loader.
19. The method of claim 16 , wherein triggering the reboot of the second processor includes placing the second processor in a programming mode to install the files.
20. The method of claim 16 , further including triggering the first processor to enter a programming mode to receive the files and to exit the programming mode after the files are installed.
21. The systea of claim 5 , wherein the first processor is configured to operate as the loadable device to be at least one of programmed or reprogrammed in the first mode, and wherein the first processor is configured to operate as the data loader to at least one of program or reprogram the second processor in the second mode.