Integrated system for aircraft crack detection

• US 5,065,630 A
• Filed: 06/12/1990
• Issued: 11/19/1991
• Est. Priority Date: 06/12/1990
• Status: Expired due to Fees

• Current Assignee: Vought Aircraft Industries, Inc. (Triumph Group, Inc.)
• Original Assignee: Grumman Aerospace Corporation (Northrop Grumman Corporation)
• Inventors: Chipman, Richard R., Chance, Richard F., Hadcock, Richard N., Horn, Michael
• Primary Examiner(s): RAEVIS, ROBERT R
• Application Number:
  US07/536,808
• Time in Patent Office: 525 Days
• Field of Search: 73/577, 73/583, 73/587, 73/801, 73/802, 73/799
• US Class Current: 73/802
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: G01M 5/0016 of aircraft wings or blades
• CPC Class Codes: G01M 5/0033 by determining damage, crack or wear
• CPC Class Codes: G01M 5/0066 by exciting or detecting vibration or acceleration vibration testing of structures G01M7/00
• CPC Class Codes: G01M 5/0075 by means of external apparatus, e.g. test benches or portable test systems G01M5/005 takes precedence
• CPC Class Codes: G01M 5/0091 by using electromagnetic excitation or detection
• CPC Class Codes: G01N 2291/2694 Wings or other aircraft parts
• CPC Class Codes: G01N 29/14 using acoustic emission techniques echo of particles G01N29/046; measuring mechanical vibrations or acoustic waves in solids in general G01H1/00

Abstract

An automated system is disclosed for rapidly inspecting a complete aircraft and detecting cracks in the airframe. For inspecting the aircraft fuselage, the system incorporates a framework disposed over the fuselage and extending along a major portion of the length of the fuselage. Beams having suction devices and acoustic sensors are movably attached to the framework and are moved into a position adjacent to the outer surface of the fuselage when the aircraft has been located within the framework. The suction devices attach the beams to the fuselage surface along fuselage panel joints or other areas to be inspected. Several acoustic sensors, located on each beam, are connected to a device for analyzing and recording or visually displaying the signals generated by the sensors upon the detection of noise generated by the formation or propagation of cracks. In order to simulate the loads on the fuselage encountered during flight, the interior of the fuselage is pressurized via the aircraft engines or an external pressurization source. The system according to the invention may also be used to inspect the aircraft wings by placing inflatable bags beneath the wing and inflating them so as to exert upward loads on the wing. Additional inflatable bags are placed between the fuselage and a framework extending over the aircraft fuselage such that, when inflated, they exert downward loads on the upper surface of the aircraft fuselage. The fuselage is pressurized to prevent collapse. Mounting beams having acoustic sensors are attached via suction devices to the aircraft wing at joints, or other areas to be inspected.

Claims

1. A method for detecting cracks in a completed aircraft on the ground wherein the aircraft has a fuselage and a wing comprising the steps of:

a) placing the completed aircraft within a framework such that the framework extends over a majority of the length of the fuselage;

b) mounting a plurality of sensors on the framework such that they are movable between positions in contact with and displaced away from an outer surface of the fuselage;

c) placing the plurality of sensors in operative position with respect to a surface of the aircraft to be tested, the sensors having means to generate a signal upon detecting a crack in the aircraft airframe;

d) applying loads to the aircraft simulating the loads encountered by the aircraft during flight; and

,

e) analyzing signals generated by the plurality of sensors during the application of the loads to detect and locate any cracks in the airframe under test.

2. The method according to claim 1 wherein the loads are applied by pressurizing the interior of the fuselage.

3. The method according to claim 1, wherein the mounting of the plurality of sensors on the framework comprises the steps of:

a) movably attaching a plurality of beams to the framework such that the beams extend generally parallel to a longitudinal axis of the fuselage and are movable between positions in contact with and displaced from the fuselage;

b) mounting a plurality of suction devices on each of the beams such that the suction devices contact an exterior surface of the fuselage when the beams are in position adjacent to the fuselage;

c) attaching at least one sensor to each beam; and

,

d) placing the sensor in contact with the exterior surface of the fuselage.

4. The method according to claim 1 wherein the sensors are acoustic emission sensors which generate an output signal upon sensing the noise generated by the formation or propagation of a crack.

5. The method according to claim 1 comprising the further steps of:

a) mounting the sensors on at least one mounting beam; and

,

b) attaching the at least one mounting beam to a surface of the wing.

6. The method according to claim 5 comprising the additional steps of mounting suction devices on the at least one mounting beam to hold the at least one mounting beam on the wing surface.

7. The method according to claim 5 wherein the load is applied by the steps of:

a) placing at least one first inflatable bag member beneath the wing; and

,

b) inflating the first bag member such that it contacts a lower surface of the wing and exerts upward loads on the wing.

8. The method according to claim 7 comprising the additional steps of:

a) placing at least one second inflatable bag member between the framework and an upper portion of the fuselage; and

,

b) inflating the second bag member so as to contact the framework and the upper portion of the fuselage so as to exert downward loads on the fuselage.

9. The method according to claim 8 comprising the additional step of pressurizing the interior of the fuselage.

10. A system for detecting cracks in a completed aircraft on the ground wherein the aircraft has a fuselage and a wing comprising:

a) a framework disposed about the fuselage and extending over a majority of the length of the fuselage;

b) support means supporting a plurality of sensors in operative position with respect to a surface of the aircraft to be tested, the sensors having means to generate a signal upon detecting a crack in the aircraft, the support means comprising;

i) at least one mounting beams;

ii) mounting means to mount the plurality of sensors on the at least on mounting beam; and

,

iii) attaching means to attach the at least one mounting beam to a surface of the wing;

c) means for applying loads to the aircraft simulating the loads encountered by the aircraft during flight comprising at least one first inflatable bag member located beneath the wing such that, when the at least one bag member is inflated it contacts a lower surface of the wing to exert upward loads thereon;

d) at least one second inflatable bag member located between the support framework and an upper portion of the fuselage such that, when the at least one second bag member is inflated, it exerts downward loads on the fuselage; and

,

e) means to analyze the signals generated by the sensors during the application of the loads to detect any crack in the aircraft.

14. The system according to claim 10 wherein the sensors are acoustic emission sensors which generate an output signal upon sensing the noise generated by the formation, propagation or presence of a crack.

15. The system according to claim 10 wherein the attaching means comprises suction devices mounted on the at least one mounting beam.

16. The system according to claim 10 further comprising means to pressurize the interior of the fuselage.

11. The system according to claim 11 wherein the mounting means comprises means to mount the plurality of sensors on the framework such that they are movable between positions adjacent to and displaced from an outer surface of the fuselage.

12. The system according to claim 11 wherein the means to apply the loads further comprises means to pressurize the interior of the fuselage.

13. The system according to claim 11 wherein the support means further comprises:

a) a plurality of beams;

b) attaching means attaching the plurality of beams to the framework such that they are movable between positions adjacent to and displaced away from the fuselage;

c) a plurality of suction devices mounted on each beam such that the suction devices contact an exterior surface of the fuselage when the beams are in their position adjacent to the fuselage; and

,

d) means to mount at least one sensor to each beam.

17. A method for detecting cracks in a completed aircraft on the ground wherein the aircraft has a fuselage and a wing comprising the steps of:

a) placing the completed aircraft within a framework such that the framework extends over a majority of the length of the fuselage;

b) placing a plurality of sensors in operative position with respect to a surface of the aircraft to be tested, the sensors having means to generate a signal upon detecting a crack in the aircraft airframe by the steps of;

i) mounting the sensors on at least one mounting beam; and

,

ii) attaching the at least one mounting beam to a surface of the wing;

c) applying loads to the aircraft simulating the loads encountered by the aircraft during flight by the steps of;

i) placing at least one first inflatable bag member beneath the wing; and

,

ii) inflating the first bag member such that it contacts a lower surface of the wing and exerts upward loads on the wing;

d) placing at least one second inflatable bag member between the framework and an upper portion of the fuselage;

e) inflating the second bag member so as to contact the framework and the upper portion of the fuselage so as to exert downward loads on the fuselage; and

,

f) analyzing signals generated by the plurality of sensors during the application of the loads to detect and locate any cracks in the airframe under test.

18. The method according to claim 17 comprising the additional step of mounting the plurality of sensors on the at least one mounting beam such that they are movable between positions in contact with and displaced away from an outer surface of the fuselage.

19. The method according to claim 17 comprising the additional steps of pressurizing the interior of the fuselage when applying loads to the aircraft.

20. The method according to claim 17 wherein the placing of the plurality of sensors in operative position comprises the additional steps of:

a) movably attaching a plurality of beams to the framework such that the beams extend generally parallel to a longitudinal axis of the fuselage and are movable between positions in contact with and displaced from the fuselage;

b) mounting a plurality of suction devices on each of the beams such that the suction devices contact an exterior surface of the fuselage when the beams are in position adjacent to the fuselage;

c) attaching at least one sensor to each beam; and

,

d) placing the sensor in contact with the exterior surface of the fuselage.

21. The method according to claim 17 wherein the sensors are acoustic emission sensors which generate an output signal upon sensing the noise generated by the formation or propagation of a crack.

22. The method according to claim 17 comprising the additional steps of mounting suction devices on the at least one mounting suction devices on the at least one mounting beam to hold the at least one mounting beam on the wing surface.