Identification module for turbine engine or auxiliary power unit with extended data storage capacity
Examples described herein provide an aircraft that includes an auxiliary power unit, a controller, and an identification module. The identification module includes a plurality of digital potentiometers to store information about the auxiliary power unit and readable by the controller.
1 . An aircraft comprising:
an auxiliary power unit;
a controller; and
an identification module comprising a connector and a plurality of digital potentiometers, the identification module configured to store information about the auxiliary power unit and readable by the controller,
wherein the connector is configured to electrically connect the identification module to the auxiliary power unit, and to program the plurality of digital potentiometers with a desired resistance value via the controller to store analog coded identification (ID) information of the auxiliary power unit and binary coded information indicative of a serial number of the auxiliary power unit, and
wherein the analog coded ID information is generated as a resistance-based coded value that is produced in response to programing at least one digital potentiometer among the plurality of digital potentiometers with the desired resistance value.
2 . The aircraft of claim 1 , wherein the plurality of digital potentiometers are arranged in a parallel configuration.
3 . The aircraft of claim 1 , wherein the plurality of digital potentiometers are arranged in a series configuration.
4 . The aircraft of claim 1 , wherein the plurality of digital potentiometers comprises a first subset of digital potentiometers connected in parallel with each other and a second subset of potentiometers connected in series with each other wherein the first subset is connected in parallel with the second subset.
5 . The aircraft of claim 1 , wherein at least one of the plurality of digital potentiometers is a reprogrammable digital potentiometer, and wherein at least one other of the plurality of digital potentiometers is a fusible digital potentiometer.
6 . The aircraft of claim 1 , wherein at least one of the plurality of digital potentiometers stores the serial number of the auxiliary power unit, and wherein at least one other of the plurality of digital potentiometers stores dynamic information associated with the auxiliary power unit.
7 . The aircraft of claim 6 , wherein the dynamic information associated with the auxiliary power unit comprises an exhaust gas temperature trim or a torque trim.
8 . A system comprising:
a turbine engine of an aircraft;
a controller; and
an identification module comprising a plurality of digital potentiometers, the identification module configured to store information about the turbine engine of the aircraft and readable by the controller,
wherein a connector is configured to electrically connect the identification module to the turbine engine, and to program the plurality of digital potentiometers with a desired resistance value via the controller,
wherein the connector is configured to electrically connect the identification module to the turbine engine, and to program the plurality of digital potentiometers via the controller to store analog coded identification (ID) information the turbine engine and binary coded information indicative of a serial number of the turbine engine, and
wherein the analog coded ID information is generated as a resistance-based coded value that is produced in response to programing at least one digital potentiometer among the plurality of digital potentiometers with the desired resistance value.
9 . The system of claim 8 , wherein the plurality of digital potentiometers are arranged in a parallel configuration.
10 . The system of claim 8 , wherein the plurality of digital potentiometers are arranged in a series configuration.
11 . The system of claim 8 , wherein the plurality of digital potentiometers comprises a first subset of digital potentiometers connected in parallel with each other and a second subset of potentiometers connected in series with each other wherein the first subset is connected in parallel with the second subset.
12 . The system of claim 8 , wherein at least one of the plurality of digital potentiometers is a reprogrammable digital potentiometer, and wherein at least one other of the plurality of digital potentiometers is a fusible digital potentiometer.
13 . The system of claim 8 , wherein at least one of the plurality of digital potentiometers stores the serial number of the turbine engine.
14 . The system of claim 8 , wherein at least one of the plurality of digital potentiometers stores dynamic information associated with the turbine engine.
15 . The system of claim 14 , wherein the dynamic information associated with the turbine engine comprises an exhaust gas temperature trim or a torque trim.