Sealant analysis system

• US 9,303,983 B2
• Filed: 04/02/2012
• Issued: 04/05/2016
• Est. Priority Date: 04/02/2012
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Georgeson, Gary Ernest, Edwards, William Talion
• Primary Examiner(s): ZHAO, XIAO SI
• Application Number:
  US13/437,355
• Publication Number:
  US 20130260016A1
• Time in Patent Office: 1,464 Days
• Field of Search: 427/9
• US Class Current: 1/1
• CPC Class Codes: G01B 11/0616 of coating
• CPC Class Codes: G01B 21/08 for measuring thickness

Abstract

A method and apparatus for inspecting sealant on an object. First data is generated for a first geometry of a first surface of the object prior to sealing the object. Second data is generated for a second geometry of a second surface of the object after the sealant has been applied to the object. A difference is identified between the first data and the second data. The difference indicates a thickness of the sealant on the object.

Claims

1. A method for inspecting sealant on an object, the method comprising:

generating first data for a first geometry of a first surface of the object prior to sealing the object, wherein generating the first data for the first geometry of the first surface of the object comprises using a model of the object in a database in combination with scanning the first surface of the object, wherein portions of the first surface cannot be scanned due to an occlusion caused by a line of sigh obstruction to a portion of the first surface, and wherein data from the model of the object in the database is used to fill in the portions not scanned to generate the first data for the first geometry of the first surface of the object;

generating second data for a second geometry of a second surface of the object after the sealant has been applied to the object; and

identifying a difference between the first data and the second data to determine a thickness of the sealant on the object.

2. The method of claim 1 further comprising:

applying the sealant to the object to form the second surface of the object.

3. The method of claim 1 further comprising:

applying additional sealant to a portion of the surface with the sealant having an insufficient thickness.

4. The method of claim 1 further comprising:

determining whether the thickness of the sealant on the object is a desired thickness for the sealant.

5. The method of claim 4, wherein the desired thickness is the thickness at which a number of desired performance parameters is met.

6. The method of claim 1 further comprising:

generating a map identifying the thickness of the sealant on different parts of the object.

7. The method of claim 1, wherein scanning the first surface of the object generates data about locations on the first surface of the object.

8. The method of claim 7, wherein the data is a point cloud of the object.

9. The method of claim 1, wherein generating the second data for the second geometry of the second surface of the object comprises:

scanning the second surface of the object to generate data about locations on the second surface of the object.

10. The method of claim 1, wherein the object is selected from one of a fastener, a rivet, a bolt with a nut engaged with the bolt, a reinforcing strip, a stiffener, a lap joint, a bracket, a tie bar, a spar, a fuel tank, a wing, a composite barrel for a fuselage, and a wing box.

11. The method of claim 1, wherein the object is inside of a fuel tank.

12. The method of claim 1, wherein the object is in a platform selected from one of a mobile platform, a stationary platform, a land-based structure, an aquatic-based structure, a space-based structure, an aircraft, a surface ship, a tank, a personnel carrier, a train, a spacecraft, a space station, a satellite, a submarine, an automobile, a power plant, a dam, a manufacturing facility, and a building.

13. A method for inspecting an interior of a wing of an aircraft, the wing including a composite fuel tank with fasteners, wherein the fasteners are in the interior of the wing, wherein portions of the fasteners extend into the composite fuel tank, and wherein a corresponding sealant covers each of the fasteners, the method comprising:

generating first data for a first geometry of a first surface of the interior of the wing prior to sealing the fasteners, wherein generating the first data for the first geometry of the first surface of the interior of the wing comprises using a model of the wing in a database in combination with scanning the first surface of the interior of the wing, wherein portions of the interior of the wing cannot be scanned by a scanner system due to an occlusion caused by a line of sight obstruction to a portion of the first surface, and wherein data from the model of the wing in the database is used to fill in the portions not scanned by the scanner system to generate the first data for the first geometry of the first surface of the interior of the wing;

generating second data for a second geometry of a second surface of the interior of the wing after the corresponding sealant has been applied to the fasteners; and

identifying a difference between the first data and the second data to determine a thicknesses of the corresponding sealant for the fasteners.

14. The method of claim 13, wherein the first surface and the second surface are inside the composite fuel tank.

15. The method of claim 13 further comprising:

for each fastener having an amount of the corresponding sealant less than a desired amount, adding additional sealant to the each fastener.

16. The method of claim 15 further comprising:

storing the first data, the second data, and the difference; and

analyzing the first data, the second data, and the difference to determine whether a trend is present for repeated areas in which the corresponding sealant is not as thick as desired.

17. The method of claim 16 further comprising:

changing a spraying process for subsequent applications based on the trend.