This application is a National Stage application of PCT/US17/53666, filed Sep. 27, 2017, which is incorporated by reference in its entirety herein.
Detecting, localizing and quantifying airframe structural damage is important to understand current structural capability. Manual inspections are routinely done to check for damage to ensure safety of flight. Airframes include numerous mechanical fasteners which can require significant time to inspect fully. Further, detection of loose, broken and missing fasteners as well as elongated fastener holes, especially in hard to see areas is a challenge, making assessment of fastener health difficult. Additionally, such time consuming procedures reduce the availability of the aircraft. Undetected unhealthy fasteners may also lead to more damage and hence more maintenance time and costs as higher loads are now carried by the fasteners adjacent to the unhealthy fasteners.
According to an embodiment, a fastener health monitoring system includes a structure including a first component and a second component, one or more fasteners securing the first component to the second component, and an optical fiber arranged adjacent to the one or more fasteners. The fiber is configured to detect strain on the structure from the one or more fasteners. Strain patterns are derivable from sensed data from the optical fiber, and any deviation in strain value greater than a threshold value at a particular fiber position along the optical fiber is indicative of a missing, damaged, or loosened fastener amongst the one or more of fasteners corresponding to that particular fiber position.
In addition to one or more of the features described above, or as an alternative, in further embodiments the optical fiber is arranged adjacent to a plurality of the fasteners.
In addition to one or more of the features described above, or as an alternative, in further embodiments, an interrogation system is further provided including an interrogator, the interrogator including a light source and a receiver configured to analyze reflected light from the fiber as the sensed data.
In addition to one or more of the features described above, or as an alternative, in further embodiments the interrogation system is disposed with the structure for continuous monitoring of the one or more fasteners.
In addition to one or more of the features described above, or as an alternative, in further embodiments the interrogation system is provided separately from the structure and connectable to the structure when an interrogation is to be made.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the structure is a portion of an aircraft.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the fiber is disposed within a shadow of each fastener in the one or more fasteners, the shadow defining an area surrounding each fastener where strain is detectable from each fastener.
In addition to one or more of the features described above, or as an alternative, in further embodiments, each component includes a fastener hole for each respective fastener in the plurality of fasteners, and the shadow of each fastener extends radially outside of a fastener head of each fastener.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the fiber is disposed within layers of a composite material for one or both of the first and second components.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the structure includes a groove and the fiber is disposed within the groove.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the fiber is adhered within the groove.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the fiber is adhered to a surface of the structure.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the structure further includes a part attached to at least one of the first and second components, the part prohibiting direct visualization of at least one of the one or more fasteners.
According to another embodiment, a method of detecting a missing or malfunctioning fastener in a structure includes arranging an optical fiber along one or more fasteners connecting a first component to a second component of the structure; directing a light down the fiber; receiving reflected light from the fiber; analyzing the reflected light to determine a strain pattern along the fiber; monitoring a strain pattern to detect any deviations in strain greater than a threshold amount; and, interpreting a distance along the fiber having any deviations in strain greater than a threshold amount as a fastener that requires maintenance.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the structure is an aircraft.
In addition to one or more of the features described above, or as an alternative, in further embodiments, arranging the fiber includes arranging the fiber along an area of the aircraft that is not directly accessible by a maintainer.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the method further includes connecting an interrogator to the fiber when light is to be directed down the fiber, the interrogator provided separately from the structure.
In addition to one or more of the features described above, or as an alternative, in further embodiments, directing a light down the fiber includes using an interrogator disposed with the structure.
In addition to one or more of the features described above, or as an alternative, in further embodiments, arranging the fiber along the set of one or more fasteners connecting the first component to the second component includes at least substantially strain-locking the fiber to the structure.
In addition to one or more of the features described above, or as an alternative, in further embodiments, the fiber is disposed within a shadow of each fastener in the one or more fasteners, the shadow defining an area of the structure surrounding each fastener where strain is detectable from each fastener.
The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. However, it should be understood that the following description and drawings are intended to be exemplary in nature and non-limiting.
Various features will become apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiments. The drawings that accompany the detailed description can be briefly described as follows:
With reference now to
The fiber optic strain sensor assembly 34 includes one or more optical fibers 50. It should be understood that a diameter of the optical fiber 50 may be quite thin relative to the fasteners 40, and may be, but is not limited to, less than 0.010 inch diameter. Each fiber 50 is arranged adjacent one or more of the fastener holes 42. In some embodiments, such as in a large structure 32, the fiber or fibers 50 may be selectively placed along one or more subsets of the fasteners 40 as it may not be necessary to monitor all of the fasteners 40 in the entire structure 32. For example, some fasteners 40 may be easily accessible and monitored and therefore incorporating the fiber 50 may not be necessary. In some embodiments, the incorporation of the fiber 50 may be limited to areas which are inaccessible or inconvenient to access, such as within an area where removal of one or more parts, for example part 39 in
With additional reference to
The fiber 50 includes a first end 56 and a second end 58 (
One embodiment for securing the fiber 50 to the structure 32 is shown in
Another embodiment for securing the fiber 50 to the structure 32 is shown in
Yet another embodiment for securing the fiber 50 to the structure 32 is shown in
With reference again to
Analysis of the strain pattern may further include a compensation for temperature, in order to separate the temperature effects from the mechanically induced strain effects. In some areas of a structure 32, the strain effect from temperature will affect a majority of the fiber 50, and therefore the temperature gradients may be the same or substantially the same across the fiber 50. However, if a structure 32 is exposed to heat, such as engine heat or the sun, then some areas of the structure 32 may be hotter than other areas and temperature effects will have to be compensated for. Optical fiber which is free from mechanically induced strain/stresses can be used as a temperature sensor. Thermocouples or a reference optical fiber not bonded to the structure will respond to the temperature and not the mechanical strain and hence may be additionally included within the fiber optic strain sensor assembly 34 to correct for temperature.
The fastener 40 preloads the structure 32 to squeeze the first and second components 36, 38 together. The applied load produces a strain in the shadow 54 of the fasteners 40 and the fiber 50 measures the strain. As shown in
Embodiments of the fiber 50 in the fiber optic strain sensor assembly 34 may take hundreds of strain measurements per meter of the fiber 50, with only a single required connection 76 (
While different structures 32 may incorporate the fastener health monitoring system 30, the fastener health monitoring system 30 is particularly useful when the structure 32 is a portion of a vehicle, and in particular an aircraft. Design of airframes may be such that certain areas are difficult to access, and aircraft can undergo large stresses and strains, must withstand pressurization, de-pressurization, and G-Forces (loads from extreme maneuvers), and may hold large and variable cargo loads, making the monitoring of fastener health particularly important.
In some embodiments where weight of the fastener health monitoring system 30 is a concern, such as in some embodiments of the aircraft 10, and if continuous monitoring of the fastener health is not necessary, the structure 32 may include the fiber 50 of the fiber optic strain sensor assembly 34, but the interrogator 70, controller 72, and monitor 74 of the interrogation system 71 may be provided separately from the structure 32 and then connected to the fiber when an interrogation is to be made. The fiber 50 itself is very light and does not add significant weight to the structure 32 by having it on board at all times.
If continuous monitoring of the fasteners 40 is desired, such as, but not limited to in-flight measurements, then the interrogator 70, controller 72, and monitor 74 may be attached to the structure 32 such as on the airframe 14 or otherwise on board and in connection with the fiber 50, and carried with the structure 32. In such an embodiment, in-flight responses could be recorded but the pilot may or may not be informed of changes in the strain pattern, depending on the criticality of the fasteners 40 or the number of fasteners 40 experiencing a strain disparity from the baseline. Data could be examined and the fasteners 40 dealt with when landed. Alternatively, although reducing the workload on the pilot is desirable, in some embodiments an algorithm could determine if there is a certain strain pattern that is deficient at a predetermined number of fasteners 40 which the pilot may need to be aware of during flight. For example, a certain number of faulty fasteners 40 could elicit a warning to the pilot and indicate a need to adjust the maneuvering of the aircraft 10 to avoid loading that area of the aircraft 10, or even indicate a necessity to land depending on the severity of the condition of the fasteners 40.
Autonomously detecting and localizing structural damage with respect to fasteners 40 will reduce scheduled inspections and thereby maintain high levels of availability of the structure 32, and detection of loose, broken and missing fasteners 40 as well as elongated fastener holes 42, especially in hard to see areas will benefit by automated detection methods. The fastener health monitoring system 30 can readily detect and locate loose, broken, and/or missing fasteners 40 without visual inspection and hence can significantly contribute to reducing manual inspection burden and frequency of such inspections. In embodiments where the structure 32 is an aircraft 10, additional benefits may include increasing safety of flight and aircraft availability.
While the disclosure has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the disclosure is not limited to such disclosed embodiments. Rather, the disclosure can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the disclosure. Additionally, while various embodiments of the disclosure have been described, it is to be understood that aspects of the disclosure may include only some of the described embodiments. Accordingly, the disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
This invention was made with Government support under Agreement No. W911W6-13-2-0006 for the Army ASTRO-Structures program. The Government has certain rights in the invention.
Filing Document | Filing Date | Country | Kind |
---|---|---|---|
PCT/US2017/053666 | 9/27/2017 | WO |
Publishing Document | Publishing Date | Country | Kind |
---|---|---|---|
WO2019/066800 | 4/4/2019 | WO | A |
Number | Name | Date | Kind |
---|---|---|---|
4654520 | Griffiths | Mar 1987 | A |
5012679 | Haefner | May 1991 | A |
5223675 | Taft | Jun 1993 | A |
5250802 | Runner | Oct 1993 | A |
5293039 | Mongiols | Mar 1994 | A |
5343035 | Egalon | Aug 1994 | A |
5581019 | Minor | Dec 1996 | A |
5723857 | Underwood | Mar 1998 | A |
6354152 | Herlik | Mar 2002 | B1 |
8683869 | Herley et al. | Apr 2014 | B2 |
9279666 | Balasubramaniam | Mar 2016 | B1 |
20040129868 | Kilmartin | Jul 2004 | A1 |
20070006653 | Kim | Jan 2007 | A1 |
20100050778 | Herley | Mar 2010 | A1 |
20100329602 | Shah | Dec 2010 | A1 |
20110135476 | Olesen | Jun 2011 | A1 |
20120154821 | Koste | Jun 2012 | A1 |
20120321243 | Younge | Dec 2012 | A1 |
20130058616 | Cote | Mar 2013 | A1 |
20140224033 | Froggatt | Aug 2014 | A1 |
20180195856 | Reaves | Jul 2018 | A1 |
Number | Date | Country |
---|---|---|
0640824 | Mar 1995 | EP |
2213992 | Aug 2010 | EP |
2213992 | Apr 2013 | EP |
2993656 | Jan 2014 | FR |
2465577 | May 2010 | GB |
2536962 | Oct 2016 | GB |
3586611 | Nov 2004 | JP |
9506237 | Mar 1995 | WO |
Entry |
---|
EP2213992B1, 2013, English translation, downloaded from the Internet on Nov. 11, 2011 (Year: 2013). |
EP-2213992-A1, 2013, English translation, downloaded from the Internet on Nov. 11, 2011 (Year: 2013). |
EP-2213992-A1, 2013, English translation, downloaded from the Internet on Nov. 11, 2011 (Year: 2013) (Year: 2013). |
JP-3586611B2, 2004, English translation, downloaded from the Internet on Jul. 27, 2022 (Year: 2004) (Year: 2004). |
Akiyama et al., Strain detection method and strain detection system using optical fiber, 2004, JP3586611B2, downloaded from Espacenet on Dec. 27, 2022 (Year: 2004). |
Extended European Search Report for EP Application No. 17926346.2, dated Apr. 8, 2021; 8 pages. |
Number | Date | Country | |
---|---|---|---|
20200271542 A1 | Aug 2020 | US |