Hard Landing Report Based on Sink Rate Algorithm

• US 20110276217A1
• Filed: 05/10/2010
• Published: 11/10/2011
• Est. Priority Date: 05/10/2010
• Status: Abandoned Application

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Anderson, John D., McIntyre, Melville D.W., Kattouw, Maarten, Lee, Amy H., Evans, Monte R., Sim, Daniel T., Hagelin, Jack S.
• Application Number:
  US12/776,464
• Publication Number:
  US 20110276217A1
• Time in Patent Office: Days
• US Class Current: 701/29
• CPC Class Codes: B64D 2045/008 Devices for detecting or indicating hard landing
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G07C 5/085 using electronic data carriers

Abstract

A system and a method for detecting a hard landing or other high load event of an aircraft and then automatically triggering a report of such hard landing event. A sink rate algorithm is used to estimate the altitude rate of a main gear. The sink rate algorithm uses a plurality of flight parameters to estimate the main gear altitude rate, preferably including at least the following: pitch altitude, radio altitude, vertical acceleration, body pitch rate and vertical speed. This invention has the potential to reduce the number of unnecessary structural inspections, and may also limit the scope of any such required inspections.

Claims

1. A method for reporting data concerning a landing of an aircraft, comprising:

receiving a respective set of data samples for each of a set of flight parameters, the data samples in each data sample set being received at different times during a time interval that starts prior to and ends subsequent to touchdown of said aircraft;

deriving a series of main gear sink rate values from data sample sets of a subset of said flight parameters during said time interval, each main gear sink rate value being a function of the data samples for said subset of said flight parameters corresponding to a respective time;

determining whether a trigger event has occurred;

collecting at least said data sample sets of said subset of said flight parameters acquired during said time interval and said main gear sink rate values derived during said time interval in response to occurrence of said trigger event; and

sending said collected data sample sets and main gear sink rate values to an output device in a report format.

2. The method as recited in claim 1, wherein said trigger event is touchdown of said aircraft.

3. The method as recited in claim 1, wherein said trigger event is that the gross weight of said aircraft at touchdown exceeds a threshold amount.

4. The method as recited in claim 1, wherein said trigger event is that a set of trigger preconditions have been satisfied.

5. The method as recited in claim 4, wherein said set of trigger preconditions are that, at the time of aircraft touchdown, the roll angle and roll rate of said aircraft lie within respective predefined ranges and the current or preceding main gear sink rate value exceeds a threshold amount.

6. The method as recited in claim 4, wherein said set of trigger preconditions are that, at the time of aircraft touchdown, the roll angle and/or roll rate of said aircraft lie outside respective predefined ranges and the current or preceding main gear sink rate value exceeds a threshold amount.

7. The method as recited in claim 1, wherein said deriving step is initiated when said aircraft reaches a predefined radio altitude.

8. The method as recited in claim 1, wherein said subset of said flight parameters comprises vertical acceleration, pitch attitude, pitch attitude rate, and radio altitude.

9. A system for reporting data concerning a landing of an aircraft, comprising an output device and a computer capable of communicating with said output device, said computer being programmed to perform the following operations:

receiving a respective set of data samples for each of a set of flight parameters, the data samples in each data sample set being received at different times during a time interval that starts prior to and ends subsequent to touchdown of said aircraft;

deriving a series of main gear sink rate values from data sample sets of a subset of said flight parameters during said time interval, each main gear sink rate value being a function of the data samples for said subset of said flight parameters corresponding to a respective time;

determining whether a trigger event has occurred;

collecting at least said data sample sets of said subset of said flight parameters acquired during said time interval and said main gear sink rate values derived during said time interval in response to occurrence of said trigger event; and

sending said collected data sample sets and main gear sink rate values to said output device in a report format.

10. The system as recited in claim 9, wherein said trigger event is touchdown of said aircraft.

11. The system as recited in claim 9, wherein said trigger event is that the gross weight of said aircraft at touchdown exceeds a threshold amount.

12. The system as recited in claim 9, wherein said trigger event is that a set of trigger preconditions have been satisfied.

13. The system as recited in claim 12, wherein said set of trigger preconditions are that, at the time of aircraft touchdown, the roll angle and roll rate of said aircraft lie within respective predefined ranges and the current or preceding main gear sink rate value exceeds a threshold amount.

14. The system as recited in claim 12, wherein said set of trigger preconditions are that, at the time of aircraft touchdown, the roll angle and/or roll rate of said aircraft lie outside respective predefined ranges and the current or preceding main gear sink rate value exceeds a threshold amount.

15. The system as recited in claim 9, wherein said deriving step is initiated when said aircraft reaches a predefined radio altitude.

16. The system as recited in claim 9, wherein said subset of said flight parameters comprises vertical acceleration, pitch attitude, pitch attitude rate, and radio altitude.

17. An airplane comprising a computer, a radio altimeter, an air data inertial reference unit (ADIRU), and an output device, said computer being programmed to perform the following operations:

receiving radio altitude data samples from said radio altimeter during a time interval that starts prior to and ends subsequent to touchdown of said aircraft;

receiving vertical acceleration data samples, pitch attitude data samples, and pitch attitude rate data samples from said ADIRU during said time interval;

deriving main gear sink rate values based at least partly on said received data samples during said time interval, each main gear sink rate value being a function of the data samples corresponding to a respective time during said time interval;

determining whether a trigger event has occurred;

collecting at least said received data samples and said derived main gear sink rate values in response to occurrence of said trigger event; and

sending said collected data samples and main gear sink rate values to said output device in a report format.

18. The system as recited in claim 17, wherein said trigger event is that a main landing gear truck has transitioned from a tilted state to a less-tilted state.

19. The system as recited in claim 17, wherein said trigger event is that the gross weight of said aircraft at touchdown exceeds a threshold amount.

20. The system as recited in claim 17, wherein said trigger event is that at aircraft touchdown, the roll angle and roll rate of said aircraft lie within respective predefined ranges and the current or preceding main gear sink rate value exceeds a threshold amount.

21. The system as recited in claim 17, wherein said trigger event is that at aircraft touchdown, the roll angle and roll rate of said aircraft lie outside respective predefined ranges and the current or preceding main gear sink rate value exceeds a threshold amount.