METHOD OF ANALYSIS OF EFFECTS OF CARGO FIRE ON PRIMARY AIRCRAFT STRUCTURE TEMPERATURES

• US 20100004891A1
• Filed: 03/07/2006
• Published: 01/07/2010
• Est. Priority Date: 03/07/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Ahlers, Mark F., Lewinski, Daniel F., Eshghi, Mel, Mazzone, Richard J.
• Granted Patent: US 7,690,837 B2
• Time in Patent Office: Days
• US Class Current: 702/130
• CPC Class Codes: G01M 99/002 Thermal testing flaw detection G01N25/72

Abstract

Embodiments provide systems and methods for analyzing effects of cargo fire on primary aircraft structure. A thermal profile of a suppressed fire in a cargo compartment of an aircraft is developed. The thermal profile is applied to a heat transfer model of structure of an aircraft, and structural integrity of the modeled structure is analyzed. The thermal profile may be developed by introducing a fire in a physical model of a cargo compartment instrumented with temperature sensors and determining profiles of temperature versus time. A heat transfer model of aircraft structure is built, boundary conditions are input into the heat transfer model, and the model is run. When analysis of the modeled structure determined structural integrity to be insufficient to satisfy flight certification requirements, structural parameters are modified, the thermal profile is applied to a heat transfer model of the modified structure, and the analysis is repeated.

Claims

1-9. -9. (canceled)

10. A method comprising:

developing a thermal profile of a suppressed fire in a physical model of a cargo compartment of an aircraft, wherein the physical model is built to enable the measurement of temperatures generated during ignition and suppression of a controlled cargo fire, wherein the thermal profile of the suppressed fire includes one or more profiles of temperature versus time for a plurality of locations in the physical model of the cargo compartment;

analyzing heat transfer resulting from applying the thermal profile of the suppressed fire to a structure of the aircraft surrounding the cargo compartment to determine a predicted temperature reached by one or more parts of the structure surrounding the cargo compartment as a result of the suppressed fire; and

generating an output at a display or other output device of a computer system, the output including the predicted temperature reached by the one or more parts of the structure surrounding the cargo compartment to facilitate analyzing whether the one or more parts of the structure surrounding the cargo compartment have sufficient strength after reaching the predicted temperature to safely land the aircraft.

11. The method of claim 10, wherein developing the thermal profile includes determining boundary locations for the heat transfer resulting from applying the thermal profile to the structure of the aircraft surrounding the cargo compartment.

12. The method of claim 11, wherein determining the boundary locations for the heat transfer includes selecting a predetermined number of the profiles of temperature versus time based on fires having highest energy levels, wherein an energy level of each of the profiles of temperature versus time is determined by an area under a curve of each of the profiles of temperature versus time.

14. The method of claim 11, wherein analyzing the heat transfer further includes building a heat transfer model of the structure surrounding the cargo compartment.

15. The method of claim 14, wherein analyzing the heat transfer further includes inputting the boundary conditions into the heat transfer model.

16. The method of claim 15, wherein the boundary conditions include predicted initial pre-fire air temperatures and surface temperatures in the cargo compartment and surface temperatures of the structure surrounding the cargo compartment.

17. The method of claim 15, wherein analyzing the heat transfer further includes executing the heat transfer model on a computing system and applying the heat transfer model to the thermal profile.

19. The method of claim 10, wherein analyzing whether the one or more parts of the structure surrounding the cargo compartment have sufficient strength after reaching the predicted temperature to safely land the aircraft includes determining whether the predicted temperature is less than a predetermined temperature for the structure surrounding the cargo compartment.

20. The method of claim 19, farther comprising modifying structural parameters of the structure surrounding the cargo compartment when it is determined that the predicted temperature results in the structure surrounding the cargo compartment not meeting flight certification requirements for structural integrity.

26. The method of claim 10, wherein the physical model of the cargo compartment is loaded with predetermined cargo compartment loads.

27. The method of claim 10, wherein enabling the measurement of temperatures generated during ignition and suppression of the controlled cargo fire in the physical model of the cargo compartment includes instrumenting the plurality of locations in the physical model of the cargo compartment with a plurality of temperature sensors.

28. The method of claim 27, wherein the plurality of locations in the physical model of the cargo compartment includes two or more of a ceiling of the cargo compartment, sidewalls of the cargo compartment, endwalls of the cargo compartment, and floors of the cargo compartment.

29. The method of claim 27, wherein developing the thermal profile of the suppressed fire includes:

introducing a fire in the physical model of the cargo compartment; and

suppressing the fire.

30. The method of claim 29, wherein the measurement of temperatures includes measuring, with the plurality of temperature sensors, air temperatures and surface temperatures in the physical model of the cargo compartment and of the structure surrounding the physical model of the cargo compartment.

31. The method of claim 30, wherein each of the one or more profiles of temperature versus time is determined from an output of one of the plurality of temperature sensors included in the thermal profile.

32. The method of claim 31, wherein the one or more profiles of temperature versus time include one or more profiles for air temperatures in the physical model of the cargo compartment.

33. The method of claim 31, wherein the one or more profiles of temperature versus time include one or more profiles for surface temperatures in the physical model of the cargo compartment.

34. The method of claim 10, wherein analyzing the heat transfer includes determining a heat transfer model of the structure surrounding the cargo compartment of the aircraft and generating the output utilizing the thermal profile of the suppressed fire.

35. The method of claim 10, wherein generating the output of the predicted temperature includes determining and providing surface temperatures of the structure surrounding the physical model of the cargo compartment.

36. The method of claim 12, wherein determining the predetermined number of the profiles of temperature versus time includes selecting the profiles of temperature versus time for the fires having the highest energy levels.

13. (canceled)

18. (canceled)

21-25. -25. (canceled)