Method and system for integrating engine control and flight control system

• US 8,634,972 B2
• Filed: 08/30/2011
• Issued: 01/21/2014
• Est. Priority Date: 08/30/2011
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Mathews, Harry Kirk Jr., Adibhatla, Sridhar, Bult, Jeffrey Russell
• Primary Examiner(s): Cheung, Mary
• Assistant Examiner(s): BERNS, MICHAEL ANDREW
• Application Number:
  US13/221,102
• Publication Number:
  US 20130054055A1
• Time in Patent Office: 875 Days
• Field of Search: 701/3
• US Class Current: 701/3
• CPC Class Codes: B64C 19/00 Aircraft control not otherwise provided for
• CPC Class Codes: B64D 31/06 actuated automatically
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: H04B 7/18506 Communications with or from aircraft, i.e. aeronautical mobile service

Abstract

A method and system of operating an aircraft system are provided. The aircraft system includes an integrated aircraft flight control system that includes an engine control system configured to generate engine performance and health information. The integrated aircraft flight control system also includes a flight control system configured to generate flight information and trajectory intent information. The integrated aircraft flight control system further includes a communications channel communicatively coupled between the engine control system and the flight control system, where the engine control system is configured to transmit the generated engine performance and health information to the flight control system using the communications channel and the flight control system is configured to transmit the generated flight information and trajectory intent information to the engine control system using the communications channel.

Claims

1. An integrated aircraft flight control system comprising:

an engine control system associated with an engine, said engine control system comprising a processor and a memory communicatively coupled to said processor, said engine control system configured to receive engine information from a plurality of sensors associated with the engine and to control a current operation of the engine using the received engine information and to generate engine performance and health information;

a flight control system associated with the aircraft, said flight control system comprising a processor and a memory communicatively coupled to said processor, said flight control system configured to receive aircraft information from a plurality of aircraft sensors associated with the aircraft and flight planning information from offboard the aircraft and to generate flight information and trajectory intent information; and

a communications channel communicatively coupled directly to said engine control system and said flight control system, wherein said communications channel facilitates transmission of the generated engine performance and health information from said engine control system to said flight control system, wherein said flight control system is configured to modify the operation of the aircraft based on the engine performance and health information generated by the engine control system, wherein said communications channel facilitates transmission of the generated flight information and trajectory intent information from said flight control system to said engine control system, and wherein said engine control system is configured to modify the operation of the engine based on the flight information and the trajectory intent information generated by the flight control system.

2. An integrated aircraft flight control system in accordance with claim 1, wherein said engine control system comprises a full authority digital engine control (FADEC).

3. An integrated aircraft flight control system in accordance with claim 1, wherein said communications channel comprises at least one of a two-way communications channel and a first one-way communications channel and a second one-way communications channel.

4. An integrated aircraft flight control system in accordance with claim 1, wherein communications between said engine control system and said flight control system occurs autonomously from commands external to said integrated aircraft flight control system.

5. An integrated aircraft flight control system in accordance with claim 1, wherein said integrated aircraft flight control system further comprises a separate flight control center positioned offboard said aircraft and communicatively coupled to said flight control system, said flight control center is configured to receive at least one of the engine performance and health information generated by the engine control system and the flight information and trajectory intent information generated by the flight control system.

6. An integrated aircraft flight control system in accordance with claim 5, wherein said flight control center is configured to:

process the received at least one of the engine performance and health information generated by the engine control system and the flight information and trajectory intent information generated by the flight control system; and

transmit at least one of commands and data generated using the processed information to said flight control system.