Building block approach for fatigue spectra generation

• US 6,125,333 A
• Filed: 11/06/1997
• Issued: 09/26/2000
• Est. Priority Date: 11/06/1997
• Status: Expired due to Term

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: Northrop Grumman Corporation
• Inventors: Pun, Adarsh Kumar
• Primary Examiner(s): Callahan, Timothy P.
• Assistant Examiner(s): NGUYEN, LINH M
• Application Number:
  US08/965,599
• Time in Patent Office: 1,055 Days
• Field of Search: 395/500.28, 73/802, 244/117 R, 702/42, 702/33, 702/34, 702/43, 702/35
• US Class Current: 702/42
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems

Abstract

The present invention is embodied in an apparatus and method for generating fatigue spectra on a chosen aircraft for which a Finite element model is available and for which a library of external load summations at key interfaces and key fundamental parameters are available from an aeroelastic analysis. The fatigue spectra generation system of the present invention represents a profile of stresses endured by the aircraft due to numerous events, such as ground and maneuver events, occurring during the life of the aircraft. The system calculates a total stress based on load and unit conditions associated with outside events by factoring up the unit conditions to derive individual stresses for each event and by summing all unit conditions.

Claims

1. An evaluation system for generating fatigue spectra representing a predicted amount of stress that an aircraft will be subjected to for each of a plurality of events that are expected to occur during the life of the aircraft, the evaluation system comprising:

a host computer having a digitally readable medium, wherein digital data representing the expected events and aircraft load and unit condition parameters corresponding thereto reside on said digitally readable medium;

a generator operating on said computer and having access to said digital data for generating fatigue spectra of the aircraft representing a profile of predicted stresses to which the aircraft will be subjected due to the plurality of events expected to occur during the life of the aircraft; and

wherein said generator is preprogrammed to calculate a total stress for each of the events based on said load and unit condition parameters associated therewith by factoring said unit condition parameters to derive individual stresses and summing all the individual stresses.

2. The evaluation system of claim 1, wherein said events are at least one of ground events and maneuver events.

3. The evaluation system of claim 1, wherein said loads are at least one of internal loads and external loads.

4. The evaluation system of claim 1, wherein said digital data is an event tape.

5. The evaluation system of claim 1, further comprising a remote computer system coupled to said host computer.

6. The evaluation system of claim 1, wherein said event tape is comprised of a spectrum of stored events including a sequence of given events that said aircraft endures in a representative block of a set number of flight hours.

7. The evaluation system of claim 1, further comprising a graphical user interface coupled to said computer for interfacing a user with said computer.

8. The evaluation system of claim 2, wherein said maneuver events comprise symmetric maneuvers and asymmetric maneuvers.

14. The evaluation system of claim 1, wherein said event tape is comprised of a spectrum of stored events.

9. A computer-readable medium for causing a computer to function as a fatigue spectra generation system which predicts an amount of stress that an aircraft will be subjected to for each of a plurality of events that are expected to occur during the life of the aircraft, the medium comprising:

a computer-readable storage medium having digital data representing the expected events and aircraft load and unit condition parameters corresponding thereto; and

a computer program stored on said medium and including a generator having access to the digital data stored on said computer-readable medium and operative to generate fatigue spectra of an aircraft representing a profile of predicted stresses to which said aircraft will be subjected due to the plurality of events expected to occur during the life of said aircraft;

wherein said generator is preprogrammed to calculate a total stress for each of the events based on said load and unit condition parameters associated therewith by factoring said unit condition parameters to derive individual stresses and summing all the individual stresses.

10. The evaluation system of claim 9, wherein said events are at least one of ground events and maneuver events.

11. The evaluation system of claim 9, wherein said loads are at least one of internal loads and external loads.

12. The evaluation system of claim 9, wherein said digital data is an event tape.

13. The evaluation system of claim 9, further comprising a remote computer system coupled to said host computer.

15. The evaluation system of claim 9, further comprising a graphical user interface coupled to said computer for interfacing a user with said computer.

16. The evaluation system of claim 10, wherein said maneuver events comprise symmetric maneuvers and asymmetric maneuvers.

17. A process for generating fatigue spectra representing a predicted amount of stress that an aircraft will be subjected to during the life of the aircraft, comprising the steps of:

(a) defining data representing aircraft load and unit condition parameters of the aircraft;

(b) associating events which are expected to occur during the life of the aircraft with said data;

(c) calculating a total stress based on said load and unit condition parameters by,

(1) factoring said unit condition parameters to derive individual stresses for each event, and

(2) summing all the individual stresses; and

(d) using said total stress to define a fatigue model representing a profile of predicted stresses to which the aircraft will be subjected due to said events which are expected to occur during the life of the aircraft.

18. The evaluation system of claim 17, wherein said events are at least one of ground events and maneuver events.

19. The process of claim 18, wherein said loads are at least one of internal loads and external loads and said maneuver events comprise symmetric maneuvers and asymmetric maneuvers.

20. The process of claim 18, wherein said data is an event tape defining how an aircraft will be used.