CN115248222A

CN115248222A - X-ray tomography system and method for imaging aircraft parts

Info

Publication number: CN115248222A
Application number: CN202210187508.1A
Authority: CN
Inventors: D·D·小帕尔默; T·A·梅德
Original assignee: Boeing Co
Current assignee: Boeing Co
Priority date: 2021-04-28
Filing date: 2022-02-28
Publication date: 2022-10-28

Abstract

X-ray tomography systems and methods for imaging aircraft parts are disclosed herein. The system includes a part-positioning device configured to support an aircraft part. The system also includes an X-ray source configured to selectively emit X-rays and an X-ray detector configured to detect X-rays. The system further includes a support structure that operably supports the X-ray source and the X-ray detector such that X-rays emitted by the X-ray source travel along a beam path that is incident on the X-ray detector and passes through the aircraft part. The system also includes a rotational scanning structure configured to selectively rotate the support structure about the scanning axis, and a longitudinal scanning structure configured to selectively translate the support structure along the scanning axis. The methods include methods of using these systems.

Description

X-ray tomography system and method for imaging aircraft parts

Technical Field

The present disclosure relates generally to tomography systems and methods for imaging aircraft parts.

Background

Tomography has been used in industrial environments to image parts and/or components. While effective for certain parts and/or components, conventional tomography systems suffer from a number of significant drawbacks. As an example, conventional industrial tomography systems typically rotate components during their imaging, which may result in undesirable movement and/or flexing of the components during imaging. As another example, conventional industrial tomography systems are generally unable to image an entire part, or at least do so without moving the part, for example due to part size and/or configuration. Such movement of components may result in an undesirable reduction in the signal-to-noise ratio of the generated image and/or undesirable variability in the measurements. Furthermore, these motion problems are further compounded for large and/or flexible components, such as many common aircraft parts. Accordingly, there is a need for improved tomography systems and/or methods for imaging aircraft parts.

Disclosure of Invention

X-ray tomography systems and methods for imaging aircraft parts are disclosed herein. The system includes a part positioning device (fix) configured to support the aircraft part in a desired orientation. The system also includes an X-ray source configured to selectively emit X-rays and an X-ray detector configured to detect X-rays. The system further includes a support structure operably supporting the X-ray source and the X-ray detector such that X-rays emitted by the X-ray source travel along a beam path incident on the X-ray detector and passing through the aircraft part when the aircraft part is supported by the part positioning device. The system also includes a rotational scanning structure configured to selectively rotate the support structure about a scanning axis and a longitudinal scanning structure configured to selectively translate the support structure along the scanning axis.

The method includes supporting the aircraft part in a desired orientation with a part positioning device and scanning the aircraft part. Scanning includes selectively rotating a support structure supporting an X-ray source and an X-ray detector about a scan axis such that a beam path from the X-ray source to the X-ray detector passes through the aircraft part. The scanning further comprises selectively translating the support structure along a scanning axis.

Drawings

FIG. 1 is a schematic illustration of an aircraft that may include aircraft parts that may be imaged by a tomography system and/or method according to the present disclosure.

FIG. 2 is a schematic side view illustrating an example of a tomography system for imaging aircraft parts according to the present disclosure.

FIG. 3 is a schematic cross-sectional view of the tomography system of FIG. 2 taken along line 3-3 of FIG. 2.

FIG. 4 is a flow chart depicting an example of a method of imaging an aircraft part according to the present disclosure.

Detailed Description

Fig. 1-4 provide illustrative, non-exclusive examples of aircraft 10 including aircraft parts 12 that may be imaged by tomography system 30 and/or method 200 according to the present disclosure. Elements that serve a similar or at least substantially similar purpose are labeled with like numerals in each of fig. 1-4, and such elements may not be discussed in detail herein with reference to each of fig. 1-4. Similarly, not all elements may be labeled in each of fig. 1-4, but for consistency, reference numerals associated therewith may be used herein. Elements, components, and/or features discussed herein with reference to one or more of fig. 1-4 may be included in and/or used with any of fig. 1-4 without departing from the scope of the present disclosure.

In general, elements that may be included in a given (i.e., particular) embodiment are shown in solid lines, while optional elements for a given embodiment are shown in dashed lines. However, elements shown in solid lines are not required for all embodiments, and elements shown in solid lines may be omitted from a particular embodiment without departing from the scope of the disclosure.

Fig. 1 is a schematic illustration of an aircraft 10. In accordance with the present disclosure, the aircraft 10 includes a plurality of aircraft parts 12, and any suitable one and/or more of the aircraft parts 12 may be imaged by the tomography system 30 and/or using the method 200. This may include imaging the aircraft part 12 prior to assembly of the aircraft part 12 within the aircraft 10 and/or imaging the aircraft part 12 after assembly of the aircraft 10. Examples of aircraft parts 12 include aerodynamic surfaces 13 and/or edge structures 14 of the aircraft 10.

The edge structure 14 may also be referred to herein and/or may be an aircraft edge structure 14 and/or an advanced aircraft edge structure 14. Examples of edge structures 14 include a wing, a leading edge, a trailing edge, a tail, a leading edge of a tail, a trailing edge of a tail, a horizontal stabilizer, a leading edge of a horizontal stabilizer, a trailing edge of a horizontal stabilizer, a vertical stabilizer, a leading edge of a vertical stabilizer, and/or a trailing edge of a vertical stabilizer.

In some examples, the aircraft part 12 may include and/or be a composite aircraft part 12. Such composite aircraft parts 12, which may also be referred to herein as composite structures 12, may be formed and/or defined from fiber-reinforced composite materials. The fiber-reinforced composite material may include and/or may be defined by a plurality of fibers 16 and a resin material 18.

Fig. 2 is a schematic side view illustrating an example of a tomography system 30 for imaging an aircraft part 12 in accordance with the present disclosure, and fig. 3 is a schematic cross-sectional view of the tomography system 30 of fig. 2 taken along line 3-3 of fig. 2. The tomography system 30 may also be referred to herein as the system 30. As generally illustrated by fig. 2-3, the system 30 includes a part-positioning device 40 that may be configured to support or hold the aircraft part 12 in a desired orientation 20. In some instances, and as perhaps best illustrated in fig. 2, the desired orientation 20 may include and/or be a horizontal orientation. As a specific example, and with continued reference to fig. 2, the aircraft part 12 may include and/or be an elongate aircraft part 12, which may have and/or define an elongate axis 19. In such examples, the elongate shaft 19 may extend horizontally, or at least substantially horizontally.

Returning to fig. 2-3, the system 30 further includes an X-ray source 50 configured to selectively emit X-rays and an X-ray detector 60 configured to detect X-rays. The system 30 further includes a support structure 70 that operably supports the X-ray source 50 and the X-ray detector 60. This operative support causes the X-rays emitted by X-ray source 50 to travel along a beam path 52 incident on X-ray detector 60 and passing through aircraft part 12 when the aircraft part is supported by the part positioning device, as perhaps best illustrated by fig. 3.

The system 30 also includes a rotational scanning configuration 80 and a longitudinal scanning configuration 90. The rotational scanning structure 80 may be configured to selectively rotate the support structure 70 about the scan axis 110, and the longitudinal scanning structure 90 may be configured to selectively translate the support structure 70 along the scan axis 110. In some examples, the scan axis 110 may be horizontal, may be at least substantially horizontal, may be parallel to the elongated axis 19, may be at least substantially parallel to the elongated axis 19, and/or may extend coaxially with the elongated axis 19.

During operation or operational use of system 30, and as discussed in more detail herein with reference to method 200 of fig. 4, aircraft part 12 may be supported by part locating device 40, such as by being attached to the part locating device by one or more fasteners and/or by residing (rest) on the part locating device under the influence of gravity. Further, the X-ray source 50 may emit X-rays along a beam path 52, and the X-rays may travel through the aircraft part 12 and impinge on the X-ray detector 60. The aircraft part 12 may then be scanned and/or imaged by the system 30. By way of example, the rotational scanning structure 80 and/or the longitudinal scanning structure 90 may be used to selectively move the support structure 70 relative to the aircraft part 12, thereby selectively moving the X-ray source 50 and X-ray detector 60 relative to the aircraft part and/or selectively varying the region of the aircraft part through which the beam path 52 extends. The changes in the X-rays detected by the X-ray detector 60 may then be utilized to generate two-dimensional and/or three-dimensional images of the aircraft part 12, such as via tomographic reconstruction.

It is within the scope of the present disclosure that part locating device 40 may be configured to support and/or hold aircraft part 12 stationary, and/or motionless while the aircraft part is being imaged by system 30. This can provide significant benefits as compared to conventional industrial tomography systems that typically rotate the respective components during imaging thereof, as discussed herein. By way of example, the bending and/or flexing of the aircraft part 12 when imaged by the system 30 may be significantly reduced as compared to conventional industrial tomography systems, thereby allowing the system 30 to produce more detailed, more accurate, and/or higher resolution images of the aircraft part as compared to conventional industrial tomography systems.

Part locating device 40 may include any suitable structure that may be adapted, configured, designed and/or configured to support or operatively support aircraft part 12 as it is imaged by system 30. In some examples, and as discussed, part positioning device 40 may be adapted, configured, designed, and/or configured to hold aircraft part 12 fixed in space, stationary, and/or stationary, such as when rotating scanning structure 80 rotates support structure 70 about scanning axis 110 and/or when longitudinal scanning structure 90 translates support structure 70 along scanning axis 110. In this regard, the system 30 may be configured to scan at least a threshold fraction of the volume of the aircraft part 12 without moving the aircraft part. Examples of threshold fractions of the volume of the aircraft part 12 include at least 60%, at least 65%, at least 70%, at least 75%, at least 80%, at least 85%, at least 90%, at least 95%, at least 99%, 100%, at most 95%, at most 90%, at most 85%, and/or at most 80%.

In some examples, part positioning device 40 may be configured such that beam path 52 extends outside of the part positioning device while system 30 scans at least a threshold fraction of the volume of aircraft part 12. Examples of threshold fractions of the volume of the aircraft part include at least 60%, at least 65%, at least 70%, at least 75%, at least 80%, at least 85%, at least 90%, at least 95%, at least 99%, 100%, at most 95%, at most 90%, at most 85%, and/or at most 80%. Such a configuration may allow and/or facilitate scanning of aircraft part 12 without also scanning part positioning device 40, which may reduce the likelihood of artifacts and/or noise in the images of aircraft part 12 produced by system 30.

By way of example, and as illustrated in fig. 2, the aircraft part 12 may extend between a first part end region 22 and a second part end region 24. In some such examples, part locating device 40 may be configured to engage, attach to, secure to, and/or support first and second

part end regions

22, 24, or only first and second

part end regions

22, 24. In other words, in some such instances, part positioning device 40 may not support intermediate region 26 of aircraft part 12, and/or intermediate region 26 may not be supported by part positioning device 40.

As another example, and with continued reference to fig. 2, part locating apparatus 40 may include at least one intermediate support 46. The intermediate support 46, when present, may be configured to engage, attach to, secure to, and/or support the intermediate region 26, which intermediate region 26 may be positioned between the first part end region 22 and the second part end region 24. In some such examples, intermediate support 46 may be configured to move and/or remove during scanning of aircraft part 12 by system 30, thereby allowing and/or facilitating scanning of aircraft part 12 without also scanning intermediate support 46 of part positioning device 40.

In some examples, and with continued reference to fig. 2, part locating device 40 may extend along length 28 of aircraft part 12 or along the entire length 28 of aircraft part 12. This is shown in dashed lines in fig. 2 and indicated at 48. Such a configuration may provide additional support to the aircraft part 12, which may be advantageous for an elongated and/or flexible aircraft part 12. However, this configuration may also enable system 30 to image both aircraft part 12 and part locating device 40.

With this in mind, and in some examples, part positioning device 40 may include, may be defined by, and/or may be entirely defined by a positioning device material that is X-ray transparent, at least substantially X-ray transparent, and/or at least substantially X-ray transparent. In other words, the positioning device material of part positioning device 40 may be selected such that the X-rays do not interact or interact only minimally with the part positioning device, thereby reducing the likelihood of artifacts and/or noise being generated within the images generated by system 30 due to the presence of part positioning device 40. Examples of positioning device materials include non-metallic materials, composite materials, and/or fiberglass. In some examples, the positioning device material may have and/or define a dielectric constant within a threshold dielectric constant range. Examples of threshold dielectric constant ranges include a dielectric constant of at least 1.4, at least 1.6, at least 1.8, at least 2, at least 2.2, at least 2.4, at least 2.6, at most 5, at most 4.5, at most 4, at most 3.8, at most 3.6, at most 3.4, at most 3.2, at most 3, at most 2.8, at most 2.6, at most 2.4, and/or at most 2.2.

The X-ray source 50 may include any suitable structure that may be adapted, configured, designed and/or constructed to selectively emit X-rays, such as along a beam path 52. In some instances, and as generally illustrated by fig. 2-3, the X-ray source 50 can include an X-ray emitter 54 and a power source 56 that can be configured to power the X-ray emitter 54. In some such examples, the power supply 56 may be configured to power the X-ray emitter 54 at an emitter voltage, examples of which include voltages selected from: at least 200 kilovolts (kV), at least 250kV, at least 300kV, at least 350kV, at least 400kV, at least 450kV, at most 600kV, at most 550kV, at most 450kV, at most 400kV, and/or at most 350kV. Additionally or alternatively, the power source 56 may be configured to power the X-ray emitter 54 with an emitter current, examples of which include a current selected from the group consisting of: at least 1.0 milliamps (mA), at least 1.2mA, at least 1.4mA, at least 1.6mA, at least 1.8mA, at least 2.0mA, at least 2.2mA, at least 2.4mA, at least 2.6mA, at least 2.8mA, at least 3.0mA, at most 5.0mA, at most 4.8mA, at most 4.6mA, at most 4.4mA, at most 4.2mA, at most 4.0mA, at most 3.8mA, at most 3.6mA, at most 3.4mA, at most 3.2mA, and/or at most 3.0mA.

X-ray detector 60 may include any suitable structure that may be adapted, configured, designed and/or constructed to detect X-rays that may be incident thereon and/or to quantify any suitable property and/or characteristic of the X-rays. Examples of properties and/or characteristics of the X-rays include the frequency of the X-rays, the wavelength of the X-rays, the amplitude of the X-rays, the intensity of the X-rays, the phase of the X-rays, the polarization of the X-rays, and/or the changes in any of these parameters caused as the X-rays pass through the aircraft part. In some examples, the X-ray detector 60 may include and/or be a high resolution X-ray detector 60. In other words, the X-ray detector 60 may have a spatial resolution, or may allow and/or facilitate the generation of two-dimensional and/or three-dimensional images of the aircraft part 12 having the following spatial resolutions: at least 80 micrometers (μm), at least 90 μm, at least 100 μm, at least 110 μm, at least 120 μm, at least 130 μm, at least 140 μm, at least 150 μm, at least 160 μm, at least 170 μm, at least 180 μm, at least 190 μm, at least 200 μm, at most 300 μm, at most 280 μm, at most 260 μm, at most 240 μm, at most 220 μm, at most 200 μm, at most 190 μm, at most 180 μm, at most 170 μm, at most 160 μm and/or at most 150 μm.

The support structure 70 may include any suitable structure that may be adapted, configured, designed and/or constructed to support both the X-ray source 50 and the X-ray detector 60, to orient the X-ray source 50 and/or the X-ray detector such that the beam path 52 is incident on the X-ray detector 60 from the X-ray source 50, and/or to orient the X-ray source 50 and the X-ray detector 60 such that the beam path 52 extends through the aircraft part 12. In some examples, and as illustrated in fig. 3, support structure 70 may include and/or be a circular, at least substantially circular, and/or at least partially circular support structure 70.

In some examples, the support structure 70 may be configured to maintain a fixed, or at least substantially fixed, relative orientation between the X-ray source 50 and the X-ray detector 60. This may include maintaining a fixed relative orientation as the support structure 70 rotates about the scan axis 110 and/or translates along the scan axis 110. In this regard, the support structure 70 may include and/or be a rigid or at least substantially rigid support structure 70.

In some instances, and as perhaps best illustrated in fig. 3, the support structure 70 may include and/or may define an opening 72. In some such examples, the support structure 70 may extend around the opening 72, may extend circumferentially around the opening 72, may at least partially surround the opening 72, and/or may at least partially surround the opening 72. Opening 72 may be configured to receive aircraft part 12 such that beam path 52 extends through the aircraft part when the aircraft part is supported by part locating device 40. In other words, the aircraft part 12 may extend within the opening 72 as the system 30 scans and/or images the aircraft part. In still other words, beam path 52 may extend through or may span opening 72.

The rotational scanning structure 80 may include any suitable structure that may be adapted, configured, designed and/or constructed to selectively rotate the support structure 70 about the scan axis 110. In other words, the rotating scanning structure 80 may be configured to rotate, or selectively rotate, the support structure 70 in a plane of rotation that is perpendicular to the scanning axis 110, at least substantially perpendicular to the scanning axis 110, extends through the X-ray source 50, extends through the X-ray detector 60, and/or extends through the aircraft part 12. Examples of planes of rotation include the plane illustrated in FIG. 3 defined by line 3-3 of FIG. 2. Examples of the rotary scanning structure 80 include a rotary scanning motor 84, such as a stepper motor and/or a servo motor.

In some examples, the rotational scanning structure 80 may be adapted, configured, designed and/or constructed to allow and/or facilitate continuous rotation of the support structure 70 about the scanning axis 110. As an example, the rotating scanning structure 80 may be configured to facilitate rotation of the support structure 70 through a range of rotational motion of at least 360 degrees, at least 1 rotation, at least 2 rotations, at least 3 rotations, and/or an infinite or any desired number of rotations. In other words, the rotating scanning structure 80 may be configured to facilitate unrestricted rotation of the support structure 70 about the scan axis 110 and/or within a plane of rotation.

In some examples, and as illustrated in fig. 2, the rotational scanning structure 80 may include a rotational scanning controller 82. The rotational scan controller 82, when present, may be configured and/or programmed to control, regulate, and/or direct the rotation of the support structure 70 about the scan axis 110.

The longitudinal scanning structure 90 can comprise any suitable structure that can be adapted, configured, designed and/or constructed to selectively translate the support structure 70 along the scanning axis 110. In other words, the longitudinal scanning structure 90 may be configured to translate or selectively translate the support structure 70 in a direction perpendicular, or at least substantially perpendicular, to the plane of rotation. Examples of the longitudinal scanning structure 90 include a longitudinal scanning motor 94, such as a stepper motor and/or a servo motor.

In some examples, the longitudinal scanning structure 90 may be configured to allow and/or facilitate continuous translation of the support structure 70 along at least a threshold fraction of the length 28 of the aircraft part 12. Examples of threshold scores for length 28 include at least 60%, at least 65%, at least 70%, at least 75%, at least 80%, at least 85%, at least 90%, at least 95%, at least 99%, 100%, at most 95%, at most 90%, at most 85%, and/or at most 80%.

In some examples, the longitudinal scanning structure 90 may include a longitudinal scan controller 92. The longitudinal scan controller 92, when present, may be configured and/or programmed to control, adjust, and/or direct translation of the support structure 70 along the scan axis 110.

As illustrated by the dashed lines in fig. 2, the system 30 may include a scanning structure support frame 120. The scanning structure support frame 120, when present, may be configured to support the support structure 70, the rotational scanning structure 80, and/or the longitudinal scanning structure 90, constrain the motion of the support structure 70, the rotational scanning structure 80, and/or the longitudinal scanning structure 90, and/or guide the motion of the support structure 70, the rotational scanning structure 80, and/or the longitudinal scanning structure 90. By way of example, the longitudinal scanning structure 90 may be operably attached to the scanning structure support frame 120, may interface with the scanning structure support frame 120, and/or may operably translate the support structure 70 along the scanning structure support frame 120. An example of a scanning structure support frame 120 includes a track 122, which may be positioned below the aircraft part 12 and/or on the ground. Another example of a scanning structure support frame 120 includes a gantry 124, which may be positioned alongside and/or over the aircraft part 12.

As discussed and in some examples, the aircraft part 12 may include and/or be an elongated aircraft part 12. With this in mind, and in some examples, the length 28 of the aircraft part 12 may be at least 2 meters (m), at least 2.5m, at least 3m, at least 3.5m, at least 4m, at least 4.5m, at least 5m, at least 5.5m, at least 6m, at least 6.5m, at least 7m, at least 7.5m, at most 20m, at most 18m, at most 16m, at most 14m, at most 12m, at most 10m, at most 8m, and/or at most 6m. Additionally or alternatively, the part aspect ratio of the aircraft part 12 may be at least 2, at least 3, at least 4, at least 5, at least 6, at least 7, at least 8, at least 9, at least 10, at most 20, at most 18, at most 16, at most 14, at most 12, at most 10, and/or at most 8. The part aspect ratio may be defined as a ratio of the length 28 of the aircraft part 12 to a maximum transverse dimension, a ratio of the length 28 of the aircraft part 12 to a minimum transverse dimension, and/or a ratio of the length 28 of the aircraft part 12 to an average maximum transverse dimension.

As discussed, the system 30 may be configured to scan at least a threshold fraction of the volume of the aircraft part 12 without movement of the aircraft part. It is within the scope of the present disclosure that system 30 may scan a threshold fraction of the volume of aircraft part 12 during the scan period. Examples of the scanning period include the following periods: at least 5 minutes, at least 10 minutes, at least 15 minutes, at least 20 minutes, at least 25 minutes, at least 30 minutes, at least 35 minutes, at least 40 minutes, at least 45 minutes, at least 50 minutes, at least 55 minutes, at least 60 minutes, at most 120 minutes, at most 110 minutes, at most 100 minutes, at most 90 minutes, at most 80 minutes, at most 70 minutes, at most 60 minutes, at most 50 minutes, and/or at most 40 minutes.

In some examples, system 30 may be configured to allow and/or facilitate viewing of at least one area of aircraft part 12, part positioning device 40, X-ray source 50, X-ray detector 60, support structure 70, rotational scanning structure 80, and/or longitudinal scanning structure 90 as system 30 scans and/or images aircraft part 12. In this regard, system 30 may be devoid of an enclosure surrounding aircraft part 12, part positioning device 40, X-ray source 50, X-ray detector 60, support structure 70, rotary scanning structure 80, and/or longitudinal scanning structure 90.

As illustrated by the dashed lines in fig. 2, and in some examples, the system 30 may include a controller 100. The controller 100, when present, may be adapted, configured, designed, constructed and/or programmed to communicate with and/or control the operation of at least one other component of the system 30. As an example, the controller 100 may be programmed to communicate with and/or control the operation of the X-ray source 50, the X-ray detector 60, the rotating scanning structure 80, and/or the longitudinal scanning structure 90. In some such examples, the power source 56, the rotational scan controller 82, and/or the longitudinal scan controller 92 may form a portion of the controller 100 and/or may be integrated into the controller 100. In some examples, controller 100 may be programmed to direct system 30 to perform any suitable step and/or steps of method 200, which will be discussed in more detail herein.

FIG. 4 is a flow chart depicting an example method 200 of imaging an aircraft part, such as the aircraft part 12 of FIGS. 1-3, in accordance with the present disclosure. Method 200 may be performed by an X-ray tomography system, such as X-ray tomography system 30 of fig. 2-3. The method 200 includes supporting an aircraft part at 210 and scanning the aircraft part at 220.

Supporting the aircraft part at 210 may include supporting the aircraft part in a desired orientation and/or supporting the aircraft part with a part positioning device. Examples of desired orientations include horizontal or at least substantially horizontal orientations. Examples of part locating devices are disclosed herein with reference to part locating device 40. In some examples, the supporting at 210 may include keeping the aircraft part stationary, and/or motionless in space during the scanning at 220.

Scanning the aircraft part at 220 may include selectively rotating the support structure at 222 and/or selectively translating the support structure at 224. The support structure may support the X-ray source and/or the X-ray detector. Examples of support structures are disclosed herein with reference to support structure 70 of fig. 2-3. An example of an X-ray source is disclosed herein with reference to X-ray source 50 of fig. 2-3. Examples of X-ray detectors are disclosed herein with reference to X-ray detector 60 of fig. 2-3. The selective rotation at 222 may include selectively rotating the support structure about a scan axis and/or traversing a beam path from the X-ray source to the X-ray detector through the aircraft part. The selective translation at 224 may include selectively translating the support structure along the scan axis. Examples of scan axes are disclosed herein with reference to scan axis 110 of fig. 2-3. An example of a beam path is disclosed herein with reference to beam path 52 of fig. 3.

In some examples, method 200 may include supporting at 210 and/or scanning at 220 such that the beam path is external to or does not pass through the part positioning device during the scanning and/or during the scanning of at least a threshold fraction or total volume of the aircraft part. Examples of threshold fractions of volumes for aircraft parts are disclosed herein.

In some instances, the scan at 220 may include a scan during a scan time period. Examples of scan periods are disclosed herein.

In some examples, the rotation at 222 may include rotation within a plane of rotation. The rotation plane may be vertical, may be at least substantially vertical, and/or may extend perpendicular to the scan axis. The scan axis may be horizontal, or at least substantially horizontal. Additionally or alternatively, the scanning axis may extend parallel, at least substantially parallel and/or coaxial to a longitudinal or elongate axis of the aircraft part.

Illustrative, non-exclusive examples of the inventive subject matter according to this disclosure are described in the paragraphs listed below:

A1. an X-ray tomography system (30) for imaging an aircraft part (12) or an elongated aircraft part (12), the system (30) comprising:

a part positioning device (40) configured to support the aircraft part (12) in a desired orientation (20) or a horizontal orientation;

an X-ray source (50) configured to selectively emit X-rays;

an X-ray detector (60) configured to detect the X-rays;

a support structure (70) operably supporting the X-ray source (50) and the X-ray detector (60) such that the X-rays emitted by the X-ray source (50) travel along a beam path (52) incident on the X-ray detector (60) and passing through the aircraft part (12) when the aircraft part (12) is supported by the part positioning device (40);

a rotating scanning structure (80) configured to selectively rotate the support structure (70) about a scanning axis (110); and

a longitudinal scanning structure (90) configured to selectively translate the support structure (70) along the scanning axis (110).

A2. The system (30) according to paragraph A1, wherein the part positioning device (40) is configured to keep the aircraft part (12) fixed in space, optionally while the rotating scanning structure (80) rotates the support structure (70) about the scanning axis (110) and further optionally while the longitudinal scanning structure (90) translates the support structure (70) along the scanning axis (110).

A3. The system (30) of any of paragraphs A1-A2, wherein the aircraft part (12) extends between a first part end region (22) and a second part end region (24), and further wherein the part locating device (40) is configured to engage the first part end region (22) and the second part end region (24), and optionally engage only the first part end region (22) and only the second part end region (24).

A4. The system (30) of paragraph A3, wherein the part locating arrangement (40) further includes at least one intermediate support (46) configured to engage an intermediate region (26) of the aircraft part (12), the intermediate region (26) being located between the first part end region (22) and the second part end region (24).

A5. The system (30) of any of paragraphs A3-A4, wherein the part locating device (40) extends along a length (28) of the aircraft part (12) or along the entire length (28) of the aircraft part (12).

A6. The system (30) of any of paragraphs A1-A5, wherein the part locator (40) is defined by a locator material.

A7. The system (30) of paragraph A6, wherein the positioning device material is at least one of:

(i) At least substantially transmissive to the X-rays;

(ii) At least substantially transparent to said X-rays;

(iii) Is non-metallic;

(iv) Is a composite material; and

(v) Is a glass fiber.

A8. The system (30) of any of paragraphs A6-A7, wherein the positioning device material has a dielectric constant of at least one of:

(i) At least 1.4, at least 1.6, at least 1.8, at least 2, at least 2.2, at least 2.4, or at least 2.6; and

(ii) At most 5, at most 4.5, at most 4, at most 3.8, at most 3.6, at most 3.4, at most 3.2, at most 3, at most 2.8, at most 2.6, at most 2.4, or at most 2.2.

A9. The system (30) of any of paragraphs A1-A8, wherein the part-positioning device (40) is configured such that the beam path (52) extends outside of the part-positioning device (40) while the system (30) scans at least a threshold fraction of a volume of the aircraft part (12), optionally wherein the threshold fraction of the volume of the aircraft part (12) is at least one of:

(i) At least 60%, at least 65%, at least 70%, at least 75%, at least 80%, at least 85%, at least 90%, at least 95%, or at least 99%;

(ii) 100 percent; and

(iii) At most 100%, at most 95%, at most 90%, at most 85% or at most 80%.

A10. The system (30) according to any of paragraphs A1-A9, wherein the X-ray source (50) includes an X-ray emitter (54) and a power source (56) configured to power the X-ray emitter (54).

A11. The system (30) according to paragraph a10, wherein the power source (56) is configured to power the X-ray emitter (54) with an emitter voltage of at least one of:

(i) At least 200 kilovolts (kV), at least 250kV, at least 300kV, at least 350kV, at least 400kV, or at least 450kV; and

(ii) At most 600kV, at most 550kV, at most 450kV, at most 400kV or at most 350kV.

A12. The system (30) as in any of paragraphs a10-a11, wherein the power supply (56) is configured to power the X-ray emitter (54) with an emitter current of at least one of:

(i) At least 1.0 milliamps (mA), at least 1.2mA, at least 1.4mA, at least 1.6mA, at least 1.8mA, at least 2.0mA, at least 2.2mA, at least 2.4mA, at least 2.6mA, at least 2.8mA, or at least 3.0mA; and

(ii) At most 5.0mA, at most 4.8mA, at most 4.6mA, at most 4.4mA, at most 4.2mA, at most 4.0mA, at most 3.8mA, at most 3.6mA, at most 3.4mA, at most 3.2mA, or at most 3.0mA.

A13. The system (30) according to any of paragraphs A1-a12, wherein the X-ray detector (60) is configured to detect the X-rays with a spatial resolution of at least one of:

(i) At least 80 micrometers (μm), at least 90 μm, at least 100 μm, at least 110 μm, at least 120 μm, at least 130 μm, at least 140 μm, at least 150 μm, at least 160 μm, at least 170 μm, at least 180 μm, at least 190 μm, or at least 200 μm; and

(ii) At most 300 μm, at most 280 μm, at most 260 μm, at most 240 μm, at most 220 μm, at most 200 μm, at most 190 μm, at most 180 μm, at most 170 μm, at most 160 μm or at most 150 μm.

A14. The system (30) of any of paragraphs A1-a13, wherein the support structure (70) is a circular or at least substantially circular support structure (70).

A15. The system (30) according to any of paragraphs A1-a14, wherein the support structure (70) is configured to maintain a fixed relative orientation between the X-ray source (50) and the X-ray detector (60).

A16. The system (30) of any of paragraphs A1-a15, wherein the support structure (70) comprises an opening (72), the opening (72) being configured to receive the aircraft part (12) such that the light beam path (52) extends through the aircraft part (12) when the aircraft part (12) is supported by the part positioning device (40).

A17. The system (30) of paragraph a16, wherein the support structure (70) extends circumferentially around the opening (72).

A18. The system (30) according to any of paragraphs A1-a17, wherein the rotating scanning structure (80) is configured to selectively rotate the support structure (70) within a plane of rotation extending through both the X-ray source (50) and the X-ray detector (60).

A19. The system (30) of any of paragraphs A1-a18, wherein the rotating scanning structure (80) is configured to facilitate continuous rotation of the support structure (70) about the scanning axis (110) through a range of rotational motion of at least 360 degrees.

A20. The system (30) of any of paragraphs A1-a19, wherein the rotating scanning structure (80) is configured to facilitate unrestricted rotation of the support structure (70) about the scanning axis (110).

A21. The system (30) according to any of paragraphs A1-a20, wherein the rotating scanning structure (80) comprises a rotating scanning controller (82), the rotating scanning controller (82) configured to control rotation of the support structure (70) about the scanning axis (110).

A22. The system (30) of any of paragraphs A1-a21, wherein the rotary scanning structure (80) comprises a rotary scanning motor (84).

A23. The system (30) of any of paragraphs A1-a22, wherein the longitudinal scanning structure (90) is configured to facilitate continuous translation of the support structure (70) at least along a length (28)/a threshold fraction of the length (28) of the aircraft part (12).

A24. The system (30) of paragraph a23, wherein the threshold fraction of the length (28) of the aircraft part (12) includes at least one of:

(ii) 100 percent; and

(iii) At most 100%, at most 95%, at most 90%, at most 85% or at most 80%.

A25. The system (30) according to any of paragraphs A1-a24, wherein the longitudinal scanning structure (90) includes a longitudinal scanning controller (92), the longitudinal scanning controller (92) configured to control translation of the support structure (70) along the scanning axis (110).

A26. The system (30) of any of paragraphs A1-a25, wherein the longitudinal scanning structure (90) comprises a longitudinal scanning motor (94).

A27. The system (30) of any of paragraphs A1-a26, wherein the system (30) comprises the aircraft part (12).

A28. The system (30) of any of paragraphs A1-a27, wherein the aircraft part (12) comprises, is, or consists of at least one of:

(i) A composite structure; and

(ii) A fiber reinforced composite.

A29. The system (30) of any of paragraphs A1-a28, wherein the aircraft part (12) comprises a plurality of fibers (16) and a resin material (18).

A30. The system (30) of any of paragraphs A1-a29, wherein the aircraft part (12) includes or is at least one of:

(i) An aircraft edge structure (14);

(ii) An advanced aircraft edge structure (14); and

(iii) A aerodynamic surface (13) of the aircraft.

A31. The system (30) of any of paragraphs A1-a30, wherein the length (28)/the length (28) of the aircraft part (12) is at least one of:

(i) At least 2 meters (m), at least 2.5m, at least 3m, at least 3.5m, at least 4m, at least 4.5m, at least 5m, at least 5.5m, at least 6m, at least 6.5m, at least 7m, or at least 7.5m; and

(ii) At most 20m, at most 18m, at most 16m, at most 14m, at most 12m, at most 10m, at most 8m or at most 6m.

A32. The system (30) of any of paragraphs A1-a31, wherein the aircraft part (12) defines a part aspect ratio of at least one of:

(i) At least 2, at least 3, at least 4, at least 5, at least 6, at least 7, at least 8, at least 9, or at least 10; and

(ii) At most 20, at most 18, at most 16, at most 14, at most 12, at most 10, or at most 8.

A33. The system (30) of any of paragraphs A1-a32, wherein the system (30) is configured to scan at least a volume of the aircraft part (12)/a threshold fraction of the volume without movement of the aircraft part (12).

A34. The system (30) of paragraph a33, wherein the threshold fraction of the volume of the aircraft part (12) is at least one of:

(ii) 100 percent; and

(iii) At most 100%, at most 95%, at most 90%, at most 85% or at most 80%.

A35. The system (30) according to any of paragraphs a33-a34, wherein the system (30) is configured to scan a threshold fraction of the volume of the aircraft part (12) during a scan period of at least one of:

(i) At least 5 minutes, at least 10 minutes, at least 15 minutes, at least 20 minutes, at least 25 minutes, at least 30 minutes, at least 35 minutes, at least 40 minutes, at least 45 minutes, at least 50 minutes, at least 55 minutes, or at least 60 minutes; and

(ii) Up to 120 minutes, up to 110 minutes, up to 100 minutes, up to 90 minutes, up to 80 minutes, up to 70 minutes, up to 60 minutes, up to 50 minutes, or up to 40 minutes.

A36. The system (30) of any of paragraphs A1-a35, wherein the system (30) has no enclosure surrounding any of the X-ray source (50) and the X-ray detector (60).

A37. The system (30) according to any of paragraphs A1-a36, wherein the system (30) further comprises a controller (100) programmed to control operation of at least one other component of the system (30).

A38. The system (30) according to paragraph a37, wherein the controller (100) is programmed to control operation of at least one of:

(i) The X-ray source (50);

(ii) The X-ray detector (60);

(iii) The rotary scanning structure (80); and

(iv) The longitudinal scanning structure (90).

A39. The system (30) of any of paragraphs a37-a38, wherein the controller (100) is programmed to direct the system (30) to perform any suitable step of any of the methods (200) of any of paragraphs B1-B8.

B1. A method (200) of imaging an aircraft part (12) or an elongated aircraft part (12) with an X-ray tomography system (30), the method (200) comprising:

supporting (210) the aircraft part (12) in a desired orientation (20) or a horizontal orientation with a part positioning device (40); and

scanning (220) the aircraft part (12) by:

(i) Selectively rotating (222) a support structure (70) supporting an X-ray source (50) and an X-ray detector (60) about a scanning axis (110) such that a beam path (52) from the X-ray source (50) to the X-ray detector (60) passes through the aircraft part (12); and

(ii) Selectively translating (224) the support structure (70) along the scan axis (110).

B2. The method (200) according to paragraph B1, wherein the supporting (210) includes keeping the aircraft part (12) fixed in space during the scanning (220).

B3. The method (200) of any of paragraphs B1-B2, wherein the beam path (52) is external to the part-positioning device (40) during the scanning at least a threshold fraction of a volume of an aircraft part (12).

B4. The method (200) of paragraph B3, wherein the threshold fraction of the volume of the aircraft part (12) is at least one of:

(ii) 100 percent; and

(iii) At most 100%, at most 95%, at most 90%, at most 85% or at most 80%.

B5. The method (200) of any of paragraphs B1-B4, wherein the scanning (220) comprises scanning during a scanning period of at least one of:

B6. The method (200) according to any of paragraphs B1-B5, wherein the selectively rotating (222) comprises selectively rotating in a vertical or at least substantially vertical plane of rotation.

B7. The method (200) of any of paragraphs B1-B6, wherein the scan axis (110) is at least substantially horizontal.

B8. The method (200) according to any of paragraphs B1-B7, wherein the method (200) comprises performing the method (200) with any suitable structure of any of the systems (30) of any of paragraphs A1-a 39.

As used herein, the terms "selective" and "selectively," when used in reference to an action, movement, configuration, or other activity that modifies one or more components or characteristics of a device, mean that the particular action, movement, configuration, or other activity is the direct or indirect result of a user manipulating an aspect of the device or one or more components of the device.

As used herein, the terms "adapted" and "configured" mean that an element, component, or other subject matter is designed and/or intended to perform a given function. Thus, use of the terms "adapted" and "configured" should not be construed to mean that a given element, component, or other subject matter is simply "capable" of performing a given function, but rather that element, component, and/or other subject matter is specifically selected, created, implemented, utilized, programmed, and/or designed for the purpose of performing that function. It is within the scope of the present disclosure that elements, components, and/or other recited subject matter recited as being adapted to perform a particular function may additionally or alternatively be described as being configured to perform that function, and vice versa. Similarly, subject matter recited as being configured to perform a particular function may additionally or alternatively be described as being operative to perform that function.

As used herein, the phrase "at least one of" in reference to a list of one or more entities should be understood to mean at least one entity selected from any one or more of the entities in the list of entities, but not necessarily including at least one of each of the entities specifically listed in the list of entities, and not excluding any combinations of entities in the list of entities. This definition also allows that entities other than the entities specifically identified in the list of entities referred to by the phrase "at least one" may optionally be present, whether related or unrelated to those specifically identified entities. Thus, as a non-limiting example, "at least one of a and B" (or, equivalently, "at least one of a or B," or, equivalently, "at least one of a and/or B") can refer, in one embodiment, to at least one (optionally including more than one) a, with no B present (and optionally including an entity other than B); in another embodiment, refers to at least one (optionally including more than one) B, no a is present (and optionally including entities other than a); in yet another embodiment, refers to at least one (optionally including more than one) a and at least one (optionally including more than one) B (and optionally including other entities). In other words, the phrases "at least one," "one or more," and/or "are open-ended expressions that are both operably linked and operably separated. For example, "at least one of a, B, and C", "at least one of a, B, or C", "one or more of a, B, and C", "one or more of a, B, or C", and "a, B, and/or C" may mean a alone, B alone, C alone, a and B together, a and C together, B and C together, a, B, and C together, and optionally any of the foregoing in combination with at least one other entity.

The various elements of the apparatus and method steps disclosed herein are not required for all apparatus and methods according to the present disclosure, and the present disclosure includes all novel and non-obvious combinations and subcombinations of the various elements and steps disclosed herein. Further, one or more of the various elements and steps disclosed herein may define independent inventive subject matter that is separate and apart from the entirety of the disclosed apparatus or method. Accordingly, such inventive subject matter need not be associated with the particular apparatus and methods explicitly disclosed herein, and such inventive subject matter may find utility in apparatus and/or methods not explicitly disclosed herein.

As used herein, the phrase "for example," the phrase "as an example" and/or simply the term "example" when referring to one or more components, features, details, structures, embodiments, and/or methods in accordance with the present disclosure is intended to convey that the described components, features, details, structures, embodiments, and/or methods are illustrative, non-exclusive examples of components, features, details, structures, embodiments, and/or methods in accordance with the present disclosure. Thus, the described components, features, details, structures, embodiments, and/or methods are not intended to be limiting, required, or exclusive/exhaustive; and other components, features, details, structures, embodiments, and/or methods, including structurally and/or functionally similar and/or equivalent components, features, details, structures, embodiments, and/or methods, are also within the scope of the present disclosure.

As used herein, "at least substantially" when modifying a degree or relationship may include not only the recited "substantial" degree or relationship, but also the full range of the recited degree or relationship. A substantial amount of a recited degree or relationship may include at least 75% of the recited degree or relationship. For example, an object that is at least substantially formed from a material includes at least 75% of objects formed from the material, and also includes objects that are entirely formed from the material. As another example, a first length that is at least substantially as long as a second length includes the first length within 75% of the second length and also includes the first length as long as the second length.

Claims

1. An X-ray tomography system (30) for imaging an aircraft part (12), the system (30) comprising:

a part-positioning device (40) configured to support the aircraft part (12) in a desired orientation (20);

an X-ray source (50) configured to selectively emit X-rays;

an X-ray detector (60) configured to detect the X-rays;

2. The system (30) in accordance with claim 1, wherein the part-positioning device (40) is configured to keep the aircraft part (12) fixed in space (110) while the rotating scanning structure (80) rotates the support structure (70) about the scanning axis (110) and while the longitudinal scanning structure (90) also translates the support structure (70) along the scanning axis (110).

3. The system (30) of claim 1, wherein the aircraft part (12) extends between a first part end region (22) and a second part end region (24), and further wherein the part locating device (40) is configured to engage the first part end region (22) and the second part end region (24).

4. The system (30) of claim 3, wherein the part-locating device (40) is configured to engage only the first part end region (22) and only the second part end region (24).

5. The system (30) of claim 1, wherein the part locator (40) is defined by a locator material, wherein the locator material is at least one of:

(i) At least substantially transmissive to the X-rays;

(ii) At least substantially transparent to said X-rays;

(iii) Is non-metallic;

(iv) Is a composite material; and

(v) Is a glass fiber.

6. The system (30) of any of claims 1-5, wherein the part-positioning device (40) is configured such that the beam path (52) extends outside of the part-positioning device (40) when the system (30) scans at least 75% of a volume of the aircraft part (12).

7. The system (30) according to any one of claims 1-5, wherein the X-ray detector (60) is configured to detect the X-rays with a spatial resolution of at least one of at least 80 micrometers (μm) and at most 300 μm.

8. The system (30) according to any one of claims 1-5, wherein the support structure (70) includes an opening (72), the opening (72) configured to receive the aircraft part (12) such that the beam path (52) extends through the aircraft part (12) when the aircraft part (12) is supported by the part positioning device (40).

9. The system (30) according to any one of claims 1-5, wherein the rotating scanning structure (80) is configured to facilitate unrestricted rotation of the support structure (70) about the scanning axis (110).

10. A method (200) of imaging an aircraft part (12) with an X-ray tomography system (30), the method (200) comprising:

supporting (210) the aircraft part (12) in a desired orientation (20) with a part positioning device (40); and

scanning (220) the aircraft part (12) by:

(i) Selectively rotating (222) a support structure (70) supporting an X-ray source (50) and an X-ray detector (60) about a scan axis (110) such that a beam path (52) from the X-ray source (50) to the X-ray detector (60) passes through the aircraft part (12); and