Method and system for variable flight data collection

• US 6,628,995 B1
• Filed: 08/11/2000
• Issued: 09/30/2003
• Est. Priority Date: 08/11/2000
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Korson, Shannon Lee, Golding, Mary Beth, Velleca, Packey Pasquale, Schings, Bruce Gunter
• Primary Examiner(s): PATEL, RAMESH B
• Application Number:
  US09/637,441
• Time in Patent Office: 1,145 Days
• Field of Search: 700/38, 700/39, 700/74, 700/73, 700/67, 700/52, 700/53, 700/34, 700/46, 342/25, 342/62, 342/194, 342/419, 345/581, 345/427, 434/43, 434/44, 434/45, 702/48, 702/56, 702/100, 702/144, 702/199, 244/3.21, 244/163, 244/164, 244/46, 244/964
• US Class Current: 700/74
• CPC Class Codes: G01D 9/005 Solid-state data loggers

Abstract

Aircraft flight data collection is enhanced by changing the data sampling rate as a function of an operational condition of the aircraft, such as its flight phase. An algorithm is used to determine the flight phase. Then, the data is collected at a first sampling rate when the flight phase is one of a first set of flight phases and collected at a second sampling rate when the flight phase is one of a second set of flight phases. The second sampling rate is greater than the first sampling rate to maximize the data storage capacity of the system. Generally, the higher sampling rate is used with transient flight phases such as takeoff and thrust reverse.

Claims

1. A method for collecting flight data from an aircraft capable of flying at various operational conditions, said method comprising:

determining the operational condition of said aircraft;

collecting data at a first sampling rate when said operational condition is one of a first set of operational conditions; and

collecting data at a second sampling rate when said operational condition is one of a second set of operational conditions, wherein said second sampling rate is greater than said first sampling rate.

2. The method of claim 1 wherein operational conditions are the flight phases of said aircraft and said first set of operational conditions comprises non-transient flight phases and said second set of operational conditions comprises transient flight phases.

4. The method of claim 1 wherein said second sampling rate is at least 5-10 times greater than said first sampling rate.

5. The method of claim 1 wherein a first set of data parameters is collected when collecting data at said first sampling rate and a second set of data parameters is collected when collecting data at said second sampling rate.

6. The method of claim 1 further comprising:

monitoring said aircraft for anomalous events; and

collecting data at a third sampling rate when an anomalous event is detected, wherein said third sampling rate is greater than said first sampling rate.

7. The method of claim 6 wherein said third sampling rate is equal to said second sampling rate.

3. The method of 2 wherein said first set of flight phases comprises cruise phase and said second set of flight phases comprises engine start, takeoff and thrust reverse phases.

8. A method for collecting flight data from an aircraft capable of flying at various flight phases and having at least one engine and a corresponding engine controller, said method comprising:

determining the flight phase of said aircraft;

collecting data from said engine controller at a first sampling rate when said flight phase is one of a first set of flight phases; and

collecting data from said engine controller at a second sampling rate when said flight phase is one of a second set of flight phases, wherein said second sampling rate is greater than said first sampling rate.

9. The method of claim 8 wherein said first set of flight phases comprises non-transient flight phases and said second set of flight phases comprises transient flight phases.

11. The method of claim 8 wherein said second sampling rate is at least 5-10 times greater than said first sampling rate.

12. The method of claim 8 wherein a first set of data parameters is collected when collecting data at said first sampling rate and a second set of data parameters is collected when collecting data at said second sampling rate.

13. The method of claim 12 wherein said first set of data parameters includes data parameters that are used for control of said engine and data parameters that are used for diagnostic purposes and said second set of data parameters only comprises data parameters that are used for control of said engine.

14. The method of claim 12 wherein said engine controller has first and second communication channels, and wherein a first subset of said first set of data parameters is collected from said first channel and a second subset of said first set of data parameters is collected from said second channel, and a first subset of said second set of data parameters is collected from said first channel and a second subset of said second set of data parameters is collected from said second channel.

15. The method of claim 8 further comprising:

monitoring said engine for anomalous events; and

collecting data at a third sampling rate when an anomalous event is detected, wherein said third sampling rate is greater than said first sampling rate.

16. The method of claim 15 wherein said third sampling rate is equal to said second sampling rate.

10. The method of 9 wherein said first set of flight phases comprises cruise phase and said second set of flight phases comprises engine start, takeoff and thrust reverse phases.

17. A system for collecting flight data from an aircraft capable of flying at various flight phases and having at least one engine and a corresponding engine controller, said system comprising:

means for determining the flight phase of said aircraft; and

means for collecting data from said engine controller, wherein data is collected at a first sampling rate when said flight phase is one of a first set of flight phases and at a second sampling rate when said flight phase is one of a second set of flight phases, said second sampling rate being greater than said first sampling rate.

18. The system of claim 17 wherein said first set of flight phases comprises non-transient flight phases and said second set of flight phases comprises transient flight phases.

19. The system of claim 18 wherein said first set of flight phases comprises cruise phase and said second set of flight phases comprises engine start takeoff and thrust reverse phases.

20. The system of claim 17 wherein said second sampling rate is at least 5-10 times greater than said first sampling rate.

21. The system of claim 17 wherein said means for collecting data collects a first set of data parameters when collecting data at said first sampling rate and a second set of data parameters when collecting data at said second sampling rate.

22. The system of claim 21 wherein said first set of data parameters includes data parameters that are used for control of said engine and data parameters that are used for diagnostic purposes and said second set of data parameters only comprises data parameters that are used for control of said engine.

23. The system of claim 17 wherein said engine controller has first and second communication channels, and said means for collecting data collects a first set of data parameters from said first channel and a second set of data parameters from said second channel.

24. The system of claim 17 further comprising means for monitoring said engine for anomalous events, wherein said means for collecting data collects data at a third sampling rate when an anomalous event is detected, said third sampling rate being greater than said first sampling rate.

25. The system of claim 24 wherein said third sampling rate is equal to said second sampling rate.

26. The system of claim 17 further comprising sensors for sensing engine and aircraft conditions, said sensors supplying signals to said means for collecting data.