Methods and apparatus for monitoring and fixing holes in composite aircraft

• US 9,586,699 B1
• Filed: 01/29/2014
• Issued: 03/07/2017
• Est. Priority Date: 08/16/1999
• Status: Active Grant

• Current Assignee: Smart Drilling and Completion, Inc.
• Original Assignee: Smart Drilling and Completion, Inc.
• Inventors: Skerl, Tomislav, Vail, William Banning III
• Primary Examiner(s): West, Paul
• Application Number:
  US14/167,766
• Time in Patent Office: 1,133 Days
• US Class Current: 1/1
• CPC Class Codes: B29C 2035/0811 using induction
• CPC Class Codes: B29C 73/10 using patches sealing on the surface of the article B29C73/14 takes precedence
• CPC Class Codes: B29C 73/24 Apparatus or accessories not otherwise provided for
• CPC Class Codes: G01M 11/083 by using an optical fiber in contact with the device under test [DUT]
• CPC Class Codes: G01M 11/085 the optical fiber being on or near the surface of the DUT
• CPC Class Codes: G01M 5/0083 by measuring variation of impedance, e.g. resistance, capacitance, induction

Abstract

Methods and apparatus are described for repairing a damaged area of an airplane fuselage made from fiber-reinforced composite material. In one embodiment, an intelligent patch is provided comprising a first electronic communication device to communicate information from at least one sensor regarding the presence of compression induced microfractures within the patch.

Claims

1. An intelligent patch for repairing a damaged area of the fuselage of an airplane made of a fiber-reinforced composite material, said intelligent patch comprising first electronic sensor to measure, monitor, and determine the condition of said intelligent patch and said repaired area of said fuselage and wherein said first electronic sensor comprises a second selected electronic sensor that measures and determines the onset of compression induced microfractures within said intelligent patch and said repaired area of said fuselage, and first electronic communication means to communicate information from said first electronic sensor to at least one location.

2. The intelligent patch in claim 1 wherein said first electronic sensor comprises a third selected electronic sensor that measures and determines the evolution of said microfractures to detect the condition of swarming of said compression induced microfractures prior to catastrophic failure of said specific damaged area of said fuselage.

3. The intelligent patch in claim 2 wherein said first electronic communication means is used to issue an alarm signal to said at least one location to indicate the condition of swarming of the compression induced microfractures within said damaged area during flight of said airplane.

4. The intelligent patch in claim 2 wherein said third selected sensor comprises sensors to measure the electronic signals from a phased array of acoustic sensors disposed within the intelligent patch covering said damaged area of the fuselage.

5. The intelligent patch in claim 2 wherein said third selected sensor comprises sensors to measure the electronic signals from fiber optic sensors disposed within the intelligent patch covering said damaged area of the fuselage.

6. The intelligent patch in claim 1 wherein said second selected sensor comprises sensors to measure the resistance between an array of electrodes disposed within the intelligent patch covering said damaged area of the fuselage.

7. The intelligent patch in claim 1 comprising a fourth electronic sensor to measure small imperfections in the condition of said intelligent patch and said repaired area of said fuselage, and fifth electronic sensor to measure larger imperfections in the condition of said intelligent patch and said repaired area of said fuselage, wherein said small imperfections have dimensions of 0.0010 inch or smaller and wherein said larger imperfections have dimensions of 0.0011 inch or larger.

8. An intelligent patch to cover a specific damaged area of the fuselage of an airplane to repair said specific damaged area, said fuselage made of a fiber-reinforced composite material, said intelligent patch comprising at least one of a first sensor selected from the group comprising an electrical resistance sensor means, phased array acoustic sensor means, phased array ultrasonic sensor means, phased array shearography sensors, phased array acoustic resonance sensors, phased array thermography sensors, X-ray sensors and fiber-optic sensors for detecting imperfections of a first size, and a second sensor selected from the group comprising acoustic sensors, ultrasonic sensor, shearography sensors, acoustic resonance sensors, thermography sensors, thermography sensor means, and thermal wave guide sensors for detecting imperfections of a second size, where the second size is larger than the first size.

9. An intelligent patch to cover a specific damaged area of the fuselage of an airplane to repair said specific damaged area, said fuselage made of carbon fiber-reinforced polymer material, said intelligent patch comprising a carbon fiber filament having a transparent component, wherein the transparent component is adapted to carry an optical signal and is also used as an element of a fiber-optic system to measure, monitor, and determine the condition of the fiber reinforced material.

10. The intelligent patch of claim 9, wherein the transparent component is one of an outer coating applied to the carbon fiber filament or a transparent filament with a woven carbon fiber outer layer.

11. An intelligent patch to cover a specific damaged area of the fuselage of an airplane to repair said specific damaged area, said fuselage made of carbon fiber-reinforced polymer material, said intelligent patch comprising a distribution of pre-determined different densities of carbon fiber materials that forms waveguides for trapped acoustic waves, which material is also used as an element of an acoustic sensor system to measure, monitor, and determine the condition of the new type of fiber-reinforced material.