ELECTRONIC ENGINE CONTROL SOFTWARE RECONFIGURATION FOR DISTRIBUTED EEC OPERATION

• US 20120095662A1
• Filed: 10/14/2010
• Published: 04/19/2012
• Est. Priority Date: 10/14/2010
• Status: Abandoned Application

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Inventors: Roy, Kevin P., Zebrowski, Thaddeus J.
• Application Number:
  US12/904,757
• Publication Number:
  US 20120095662A1
• Time in Patent Office: Days
• US Class Current: 701/99
• CPC Class Codes: B64D 31/00 Power plant control systems; Arrangement of power plant control systems in aircraft
• CPC Class Codes: G05B 19/0426 Programming the control sequence
• CPC Class Codes: G05B 2219/23349 Pluggable pin module, fits in corresponding female receptacle, coded plug
• CPC Class Codes: G05B 2219/25114 Jumpers
• CPC Class Codes: G05B 2219/25232 DCS, distributed control system, decentralised control unit
• CPC Class Codes: G05B 2219/25296 Identification module, type connected I-O, device

Abstract

A system for configuring a full authority digital engine controller (FADEC) for use with an engine and an airframe combination. The system includes the FADEC and a data entry plug. The FADEC includes an electronic engine controller (EEC) attached to the engine, an airframe data concentrator (ADC) attached to the airframe, and a digital bus electrically connecting the ADC to the EEC. The ADC includes a data storage device and a data entry plug socket. The data entry plug includes electrical components configured for the engine and the airframe combination. The data entry plug is inserted into the data entry plug socket to direct the ADC to recall configuration data from the data storage device for the engine and the airframe combination and send the configuration data over the digital bus to the EEC.

Claims

1. A system for configuring a full authority digital engine controller (FADEC) for use with an engine and an airframe combination, the system comprising:

the FADEC comprising;

an electronic engine controller (EEC) attached to the engine;

an airframe data concentrator (ADC) attached to the airframe, the ADC comprising;

a data entry plug socket; and

a data storage device; and

a digital bus electrically connecting the ADC to the EEC; and

a data entry plug inserted into the data entry plug socket to direct the ADC to recall configuration data from the data storage device for the engine and the airframe combination and send the configuration data over the digital bus to the EEC;

the data entry plug comprising electrical components configured for the engine and the airframe combination.

2. The system of claim 1, wherein the data entry plug electrical components comprise at least one of discrete jumper connectors and a non-volatile memory device.

3. The system of claim 1, wherein the configuration data is formatted as a set of look-up tables and constants in the data storage device.

4. The system of claim 1, wherein the configuration data is formatted as a set of look-up tables, constants, and software code in the data storage device.

5. The system of claim 1, wherein the data storage device is solid-state non- volatile memory device.

6. A method of configuring a full authority digital engine controller (FADEC) for use with an engine and an airframe combination, the method comprising:

receiving a data entry plug configured for the engine and the airframe combination into an airframe data concentrator (ADC) attached to the airframe;

directing the ADC to recall configuration data from a data storage device within the ADC, the configuration data corresponding to the engine and the airframe combination of the data entry plug;

recalling the configuration data from the data storage device as directed by the data entry plug;

transmitting the recalled configuration data from the ADC over a digital bus to an electronic engine controller (EEC), the EEC being attached to the engine; and

configuring the EEC using the transmitted configuration data.

7. A system for configuring and controlling an aircraft engine attached to an airframe, the system comprising:

a plurality of airframe sensors attached to the airframe to produce airframe sensor signals;

an airframe data concentrator (ADC) attached to the airframe and electrically connected to the plurality of airframe sensors to convert the airframe sensor signals to airframe sensor digital data, the ADC comprising;

a data entry plug socket; and

a data storage device; and

a fuel metering unit (FMU) attached to the engine, the FMU comprising;

an effector; and

an electronic engine controller (EEC);

an engine sensor;

a digital bus connecting the ADC to the EEC; and

a data entry plug inserted into the data entry plug socket to direct the ADC to recall configuration data from the data storage device for the engine and the airframe combination and send the configuration data over the digital bus to the EEC;

the data entry plug comprising electrical components configured for the engine and the airframe combination;

wherein the engine sensor is electrically connected to the EEC to provide an engine sensor signal to the EEC;

the effector is electrically connected to the EEC to adjust a rate of fuel flowing into the engine in response to a control signal sent from the EEC; and

the control signal sent from the EEC is responsive to the airframe sensor digital data sent by the ADC over the digital bus and the engine sensor signal.

8. The system of claim 7, wherein the data entry plug electrical components comprise at least one of discrete jumper connectors and a non-volatile memory device.

9. The system of claim 7, wherein the configuration data is formatted as a set of look-up tables and constants in the data storage device.

10. The system of claim 7, wherein the configuration data is formatted as a set of look-up tables, constants, and software code in the data storage device.

11. The system of claim 7, wherein the data storage device comprises a non-volatile memory device.

12. The system of claim 7, wherein the FMU is contained within a single housing.

13. The system of claim 7, wherein the FMU further comprises a cooling plate in thermal contact with the EEC.

14. The system of claim 7, comprising a cockpit display connected to the ADC for displaying engine sensor digital data, wherein the EEC converts the engine sensor signal to the engine sensor digital data and sends the engine sensor digital data to the ADC over the digital bus.

15. The system of claim 7, wherein the engine sensor comprises at least one of a pressure sensor, a temperature sensor, a position sensor, and a rotational speed sensor.

16. The system of claim 7, wherein the effector comprises at least one of a solenoid valve, a stepper motor, a torque motor, and an electric motor.

17. The system of claim 7, wherein the plurality of airframe sensors comprise at least one of a pressure sensor, a temperature sensor, a position sensor, and a rotational speed sensor.