CA2490059C - Methods and systems for inspecting aircraft fuselage frames - Google Patents
Methods and systems for inspecting aircraft fuselage frames Download PDFInfo
- Publication number
- CA2490059C CA2490059C CA2490059A CA2490059A CA2490059C CA 2490059 C CA2490059 C CA 2490059C CA 2490059 A CA2490059 A CA 2490059A CA 2490059 A CA2490059 A CA 2490059A CA 2490059 C CA2490059 C CA 2490059C
- Authority
- CA
- Canada
- Prior art keywords
- detector
- collision avoidance
- proximity sensor
- avoidance system
- inspection system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N23/00—Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups G01N3/00 – G01N17/00, G01N21/00 or G01N22/00
- G01N23/02—Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups G01N3/00 – G01N17/00, G01N21/00 or G01N22/00 by transmitting the radiation through the material
- G01N23/04—Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups G01N3/00 – G01N17/00, G01N21/00 or G01N22/00 by transmitting the radiation through the material and forming images of the material
Abstract
A method for inspecting an aircraft fuselage (10) using an inspection system (12) including a moveable detector (14), wherein the method includes coupling a collision avoidance system (20) to the inspection system detector, monitoring the collision avoidance system during operation of the inspection system, and controlling operation of the inspection system with the collision avoidance system.
Description
METHODS AND SYSTEMS FOR INSPECTING AIRCRAFT FUSELAGE
FRAMES
BACKGROUND OF THE INVENTION
This invention relates generally to aircraft fuselage frames, and more particularly to methods and systems for non-destructive inspection of aircraft fuselage frames.
In order to facilitate performing high-speed digital radiography for defect detection on passenger aircraft fuselage frames in both a timely and cost efficient manner, speed of data collection is primary. Speed can be addressed by rapid image acquisition, which can be accomplished through the synchronous motion of the energy source and the detector. In order to achieve adequate image quality, the detector must be located close to and along the outside of the aircraft fuselage to reduce the effects of magnification.
The proximity of the inspection system to the aircraft fuselage increases the potential for collision and damage to both the aircraft and the inspection system. To facilitate preventing collision and damage, at least some method of avoidance and protection is required.
BRIEF DESCRIPTION OF THE INVENTION
In one aspect, a method for inspecting an aircraft fuselage using an inspection system that includes a moveable detector is provided. The method includes coupling a collision avoidance system to the inspection system detector, monitoring the collision avoidance system during operation of the inspection system, and controlling operation of the inspection system with the collision avoidance system.
In another aspect, an apparatus for inspecting an aircraft fuselage is provided. The apparatus includes a moveable detector, and a collision avoidance system in electrical communication with the moveable detector to control the moveable detector for inspecting the aircraft fuselage.
In another aspect, an inspection system for inspecting an aircraft fuselage is provided.
The system includes a moveable detector, at least one proximity sensor electrically coupled to the moveable detector, and a collision avoidance system in electrical communication with the moveable detector and the at least one proximity sensor for controlling the moveable detector during the inspection of the aircraft fuselage.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 is an illustration of an aircraft fuselage; and Figure 2 is a block diagram of a collision avoidance system coupled to an inspection system for use with an aircraft fuselage.
DETAILED DESCRIPTION OF THE INVENTION
Figure 1 is an illustration of an aircraft fuselage 10 of a passenger jet.
Figure 2 is block diagram of an inspection system 12 for use with an aircraft fuselage, such as, aircraft fuselage 10 in Figure 1. Inspection system 12 can detect defects in the aircraft fuselage, such as cracks, corrosion, delaminations, disbonds, etc. Inspection system 12 may also be used with other types of aircraft fuselages, structural components, and materials that include these types of defects. More specifically, inspection system 12 includes a moveable detector 14 coupled in synchronous motion with an energy source (not shown). In one embodiment, inspection system 12 is a high-speed digital radiography system, such as the DXR-500 available from General Electric Inspection Technology, Cincinnati, Ohio. However, as will be appreciated by those in the art, other systems can be used within the scope of the present invention.
In operation, inspection system 12 rapidly passes close to and along fuselage 10. A
collision avoidance system (CAS) 20 is coupled to inspection system 12 in order to prevent contact between inspection system 12 and fuselage 10 during the inspection process. CAS 20 includes at least one proximity sensor 22, at least one protection device 24, and a collision monitor 26. Proximity sensor 22 is electrically coupled to detector 14. In one embodiment, proximity sensor 22 is remotely coupled to detector 14. In one embodiment, proximity sensor 22 is a single sensor that includes at least an infrared sensor, an air-filled bladder sensor, or an accelerometer. In another embodiment, proximity sensor 22 is a group of sensors that includes a combination of at least an infrared sensor, an air-filled bladder sensor, or an accelerometer. An infrared sensor allows for measuring distance between detector 14 and fuselage 10.
An air-filled bladder allows for monitoring changes in pressure and provides damage prevention. An accelerometer allows for measuring detector speed In operation, proximity sensor 22 generates signals during the operation of detector 14 and transmits those signals to collision monitor 26. 'If during the inspection process proximity sensor 22 detects an imminent collision, then a signal is transmitted to collision monitor 26. Monitor 26 is configured to send an imminent collision signal to an inspection system stopping mechanism 28. Stopping mechanism 28 is configured to iW mediately halt the motion of detector 14 and facilitate preventing a collision between detector 14 and fuselage 10. In one embodiment, stopping mechanism 28 is a manipulator that moves detector 14 away from fuselage 10.
A protection device 24 is coupled to inspection system 12. In one embodiment, protection device 24 includes, but is not limited to, one or a combination of at least an air-filled bladder, a balloon, or an airbag system. In another embodiment, protection device 24 includes other devices capable of protecting detector 14 as described herein.
Protection device 24 is in electrical communication with stopping mechanism 28 such that during operation, when stopping mechanism 28 receives an imminent collision signal from monitor 26, protection device 24 is deployed. Accordingly, detector 14 does not contact fuselage 10. In an alternative embodiment, protection device 24 is in electrical communication with proximity sensor 22 such that when proximity sensor 22 detects an imminent collision, protection device 24 is deployed and prevents contact between detector 14 and fuselage 10.
The above-described collision avoidance system 22 for an aircraft fuselage inspection system 12 is both cost-effective and highly reliable. The inspection system receives input from at least one proximity sensor coupled to the collision avoidance system to facilitate the prevention of contact between the movable detector and the aircraft fuselage. Furthermore, the collision avoidance system allows non-destructive inspections of aircraft fuselage frames. As a result, the inspection system can perfornl high-speed digital) radiography on aircraft fuselages in close proximity without concern of damage to the detector or the fuselage or loss of image quality.
While the invention has been described in terms of various specific embodiments, those skilled in the art will recognize that the invention can be practiced with modification within the spirit and scope of the claims.
FRAMES
BACKGROUND OF THE INVENTION
This invention relates generally to aircraft fuselage frames, and more particularly to methods and systems for non-destructive inspection of aircraft fuselage frames.
In order to facilitate performing high-speed digital radiography for defect detection on passenger aircraft fuselage frames in both a timely and cost efficient manner, speed of data collection is primary. Speed can be addressed by rapid image acquisition, which can be accomplished through the synchronous motion of the energy source and the detector. In order to achieve adequate image quality, the detector must be located close to and along the outside of the aircraft fuselage to reduce the effects of magnification.
The proximity of the inspection system to the aircraft fuselage increases the potential for collision and damage to both the aircraft and the inspection system. To facilitate preventing collision and damage, at least some method of avoidance and protection is required.
BRIEF DESCRIPTION OF THE INVENTION
In one aspect, a method for inspecting an aircraft fuselage using an inspection system that includes a moveable detector is provided. The method includes coupling a collision avoidance system to the inspection system detector, monitoring the collision avoidance system during operation of the inspection system, and controlling operation of the inspection system with the collision avoidance system.
In another aspect, an apparatus for inspecting an aircraft fuselage is provided. The apparatus includes a moveable detector, and a collision avoidance system in electrical communication with the moveable detector to control the moveable detector for inspecting the aircraft fuselage.
In another aspect, an inspection system for inspecting an aircraft fuselage is provided.
The system includes a moveable detector, at least one proximity sensor electrically coupled to the moveable detector, and a collision avoidance system in electrical communication with the moveable detector and the at least one proximity sensor for controlling the moveable detector during the inspection of the aircraft fuselage.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 is an illustration of an aircraft fuselage; and Figure 2 is a block diagram of a collision avoidance system coupled to an inspection system for use with an aircraft fuselage.
DETAILED DESCRIPTION OF THE INVENTION
Figure 1 is an illustration of an aircraft fuselage 10 of a passenger jet.
Figure 2 is block diagram of an inspection system 12 for use with an aircraft fuselage, such as, aircraft fuselage 10 in Figure 1. Inspection system 12 can detect defects in the aircraft fuselage, such as cracks, corrosion, delaminations, disbonds, etc. Inspection system 12 may also be used with other types of aircraft fuselages, structural components, and materials that include these types of defects. More specifically, inspection system 12 includes a moveable detector 14 coupled in synchronous motion with an energy source (not shown). In one embodiment, inspection system 12 is a high-speed digital radiography system, such as the DXR-500 available from General Electric Inspection Technology, Cincinnati, Ohio. However, as will be appreciated by those in the art, other systems can be used within the scope of the present invention.
In operation, inspection system 12 rapidly passes close to and along fuselage 10. A
collision avoidance system (CAS) 20 is coupled to inspection system 12 in order to prevent contact between inspection system 12 and fuselage 10 during the inspection process. CAS 20 includes at least one proximity sensor 22, at least one protection device 24, and a collision monitor 26. Proximity sensor 22 is electrically coupled to detector 14. In one embodiment, proximity sensor 22 is remotely coupled to detector 14. In one embodiment, proximity sensor 22 is a single sensor that includes at least an infrared sensor, an air-filled bladder sensor, or an accelerometer. In another embodiment, proximity sensor 22 is a group of sensors that includes a combination of at least an infrared sensor, an air-filled bladder sensor, or an accelerometer. An infrared sensor allows for measuring distance between detector 14 and fuselage 10.
An air-filled bladder allows for monitoring changes in pressure and provides damage prevention. An accelerometer allows for measuring detector speed In operation, proximity sensor 22 generates signals during the operation of detector 14 and transmits those signals to collision monitor 26. 'If during the inspection process proximity sensor 22 detects an imminent collision, then a signal is transmitted to collision monitor 26. Monitor 26 is configured to send an imminent collision signal to an inspection system stopping mechanism 28. Stopping mechanism 28 is configured to iW mediately halt the motion of detector 14 and facilitate preventing a collision between detector 14 and fuselage 10. In one embodiment, stopping mechanism 28 is a manipulator that moves detector 14 away from fuselage 10.
A protection device 24 is coupled to inspection system 12. In one embodiment, protection device 24 includes, but is not limited to, one or a combination of at least an air-filled bladder, a balloon, or an airbag system. In another embodiment, protection device 24 includes other devices capable of protecting detector 14 as described herein.
Protection device 24 is in electrical communication with stopping mechanism 28 such that during operation, when stopping mechanism 28 receives an imminent collision signal from monitor 26, protection device 24 is deployed. Accordingly, detector 14 does not contact fuselage 10. In an alternative embodiment, protection device 24 is in electrical communication with proximity sensor 22 such that when proximity sensor 22 detects an imminent collision, protection device 24 is deployed and prevents contact between detector 14 and fuselage 10.
The above-described collision avoidance system 22 for an aircraft fuselage inspection system 12 is both cost-effective and highly reliable. The inspection system receives input from at least one proximity sensor coupled to the collision avoidance system to facilitate the prevention of contact between the movable detector and the aircraft fuselage. Furthermore, the collision avoidance system allows non-destructive inspections of aircraft fuselage frames. As a result, the inspection system can perfornl high-speed digital) radiography on aircraft fuselages in close proximity without concern of damage to the detector or the fuselage or loss of image quality.
While the invention has been described in terms of various specific embodiments, those skilled in the art will recognize that the invention can be practiced with modification within the spirit and scope of the claims.
Claims (9)
1. A method for inspecting an aircraft fuselage (10) using an inspection system (12) including a moveable detector (14), said method comprising:
coupling a collision avoidance system (20) to the inspection system detector;
monitoring the collision avoidance system during operation of the inspection system; and controlling operation of the inspection system with the collision avoidance system;
wherein said collision avoidance system (20) comprises at least one protection device (24), at least one proximity sensor (22) and a collision monitor (26), said proximity sensor (22) comprising a group of sensors that includes at least an infrared sensor and an accelerometer.
coupling a collision avoidance system (20) to the inspection system detector;
monitoring the collision avoidance system during operation of the inspection system; and controlling operation of the inspection system with the collision avoidance system;
wherein said collision avoidance system (20) comprises at least one protection device (24), at least one proximity sensor (22) and a collision monitor (26), said proximity sensor (22) comprising a group of sensors that includes at least an infrared sensor and an accelerometer.
2. A method in accordance with Claim 1 wherein coupling a collision avoidance system (20) comprises coupling the at least one proximity sensor (22) to the inspection system detector (14) such that the collision avoidance system receives signals from the proximity sensor during operation of the inspection system.
3. A method in accordance with Claim 1 wherein coupling a collision avoidance system (20) comprises coupling at least one of an air-filled bladder sensor and an accelerometer to the inspection system detector (14).
4. An apparatus for inspecting an aircraft fuselage (10) comprising:
a moveable detector (14);
a collision avoidance system (20) in electrical communication with said moveable detector to control said moveable detector for inspecting the aircraft fuselage; and wherein said collision avoidance system (20) comprises at least one protection device (24), at least one proximity sensor (22) and a collision monitor (26), said proximity sensor (22) comprising a group of sensors that includes at least an infrared sensor and an accelerometer.
a moveable detector (14);
a collision avoidance system (20) in electrical communication with said moveable detector to control said moveable detector for inspecting the aircraft fuselage; and wherein said collision avoidance system (20) comprises at least one protection device (24), at least one proximity sensor (22) and a collision monitor (26), said proximity sensor (22) comprising a group of sensors that includes at least an infrared sensor and an accelerometer.
5. An apparatus in accordance with Claim 4 wherein said at least one proximity sensor (22) is electrically coupled to said collision avoidance system (20) such that said collision avoidance system receives a signal from said at least one proximity sensor (22) during operation of said moveable detector (14).
6. An apparatus in accordance with Claim 4 wherein said at least one proximity sensor (22) comprises at least one of an infrared sensor, an air-filled bladder sensor, and an accelerometer.
7. An apparatus in accordance with Claim 4 wherein said moveable detector (14) is controlled based on input received by said at least one proximity sensor (22) during the inspection of the airplane fuselage (10).
8. An apparatus in accordance with Claim 4 further comprising a stopping mechanism (28) coupled to said moveable detector (14) and configured to receive an imminent collision signals from said at least one proximity sensor (22) to facilitate preventing contact between said moveable detector and the aircraft fuselage (10) frame.
9. An apparatus in accordance with Claim 4 wherein said protection device (24) comprises at least one of air-filled bladder, a balloon, and an airbag system.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/064,291 US6662088B1 (en) | 2002-06-28 | 2002-06-28 | Methods and systems for inspecting aircraft fuselage frames |
| US10/064,291 | 2002-06-28 | ||
| PCT/US2003/020953 WO2004003530A1 (en) | 2002-06-28 | 2003-06-26 | Methods and systems for inspecting aircraft fuselage frames |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2490059A1 CA2490059A1 (en) | 2004-01-08 |
| CA2490059C true CA2490059C (en) | 2010-12-07 |
Family
ID=29709240
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2490059A Expired - Fee Related CA2490059C (en) | 2002-06-28 | 2003-06-26 | Methods and systems for inspecting aircraft fuselage frames |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US6662088B1 (en) |
| EP (1) | EP1520167B1 (en) |
| JP (1) | JP4520850B2 (en) |
| AU (1) | AU2003253788A1 (en) |
| BR (1) | BR0312401A (en) |
| CA (1) | CA2490059C (en) |
| SG (1) | SG173935A1 (en) |
| WO (1) | WO2004003530A1 (en) |
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| DE102005007094B4 (en) * | 2005-02-16 | 2007-03-29 | Siemens Ag | Digital flat detector for the detection of X-rays |
| US7266174B2 (en) * | 2005-03-07 | 2007-09-04 | General Electric Company | Radiographic inspection of airframes and other large objects |
| US20080061940A1 (en) * | 2006-08-03 | 2008-03-13 | Kimberly-Clark Worldwide, Inc. | Smart antenna system for reading data tags |
| CN102119023B (en) * | 2008-07-03 | 2014-04-09 | 弗吉尼亚大学专利基金会 | Unit dosage of apadenoson |
| US8886388B2 (en) * | 2009-06-29 | 2014-11-11 | The Boeing Company | Embedded damage detection system for composite materials of an aircraft |
| US8693613B2 (en) * | 2010-01-14 | 2014-04-08 | General Electric Company | Nuclear fuel pellet inspection |
| US8983172B2 (en) * | 2012-12-28 | 2015-03-17 | Modern Technology Solutions, Inc. | Visual inspection apparatus, secure one-way data transfer device and methods therefor |
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-
2002
- 2002-06-28 US US10/064,291 patent/US6662088B1/en not_active Expired - Lifetime
-
2003
- 2003-06-26 SG SG2010012854A patent/SG173935A1/en unknown
- 2003-06-26 EP EP03762327.9A patent/EP1520167B1/en not_active Expired - Fee Related
- 2003-06-26 JP JP2004518231A patent/JP4520850B2/en not_active Expired - Fee Related
- 2003-06-26 WO PCT/US2003/020953 patent/WO2004003530A1/en active Search and Examination
- 2003-06-26 AU AU2003253788A patent/AU2003253788A1/en not_active Abandoned
- 2003-06-26 BR BRPI0312401-0A patent/BR0312401A/en not_active Application Discontinuation
- 2003-06-26 CA CA2490059A patent/CA2490059C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| SG173935A1 (en) | 2011-09-29 |
| US20040002797A1 (en) | 2004-01-01 |
| JP4520850B2 (en) | 2010-08-11 |
| EP1520167A1 (en) | 2005-04-06 |
| EP1520167B1 (en) | 2013-09-11 |
| JP2005531773A (en) | 2005-10-20 |
| WO2004003530A1 (en) | 2004-01-08 |
| BR0312401A (en) | 2007-06-19 |
| CA2490059A1 (en) | 2004-01-08 |
| AU2003253788A1 (en) | 2004-01-19 |
| US6662088B1 (en) | 2003-12-09 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20170627 |