METHOD AND SYSTEM FOR DETERMINING AND CHECKING THE CANVAS ORIENTATION OF A COMPOSITE LAMINATE

专利摘要:
METHOD AND SYSTEM FOR DETERMINING AND CHECKING THE CANVAS ORIENTATION OF A COMPOSITE LAMINATE. A method (66) for determining and verifying the canvas orientation (98) of composite laminates (28) includes performing a first scan (104) of a prepared edge (92a) of a composite laminate (28) using an inclined light source off-axis (106) directing light (108) at a first acute angle (110) to a first area (112) on the prepared edge (92a) to produce a first scanned image (116); rotate an orientation (117) of the tilted light source off-axis (106) in relation to the prepared edge (92a), so that the tilted light source off-axis (106) directs light at a second acute angle ( 130) symmetrically opposite the first acute angle (110); and performing a second scan (126) of the prepared edge (92a) using the tilted light source off-axis (106) directing light (108) at the second acute angle (130) to the first area (112) on the prepared edge (92a) to produce a second scanned image (128). Method (66) includes comparing the first and second scanned images (116, 128) to determine a canvas orientation (98) for each canvas (94), and checking the canvas orientation (98) against a reference canvas orientation (99).
公开号:BR102015000999B1
申请号:R102015000999-2
申请日:2015-01-15
公开日:2020-09-15
发明作者:Thomas J. Gonze；James R. Kendall；David C. Jackson
申请人:The Boeing Company；
IPC主号:

专利说明:

FUNDAMENTALS 1) Description field
[001] The description generally refers to methods and systems for analyzing composite structures, and more particularly, methods and systems for determining and verifying the canvas orientation of composite laminates used in composite structures, such as composite aircraft structures. 2) Description of the Related Art
[002] Composite structures can be used in a wide variety of applications, including in the manufacture of aircraft, space vehicle, helicopter, vessel, automobiles, and other vehicles and structures, due to their high strength-to-weight ratios, corrosion resistance and other favorable properties. In particular, in aircraft construction, composite structures can be used to form the tail, wings, fuselage and other component parts of the aircraft.
[003] Composite laminates used to form composite structures can be manufactured by laying or stacking multiple layers or "tarps" together and curing the laid structure. A single layer or canvas typically consists of reinforcing fibers in a matrix material. Composite laminates can be stacked with tarpaulins of different tarpaulin orientations in a defined sequence for design and / or quality requirements to optimize performance, such as load-bearing capacity. For example, canvas orientations can typically include 0o (zero degree) canvas orientation, 90 ° (ninety degree) canvas orientation, + 45 ° (plus forty-five degree) / -45 ° canvas orientation ( minus forty-five degrees), or another suitable canvas orientation. The determination of the canvas orientation of composite laminates is important in optimizing composite laminate designs, as well as in meeting the requirements for composite laminate design and / or quality.
[004] In addition, during the manufacturing process of composite laminate, inconsistencies may occur during the laying or stacking of the tarpaulins, such as, for example, wrongly oriented tarpaulins, interstices, overlaps, or other inconsistencies. Methods and systems for determining and checking the canvas orientation can be used to analyze the composite laminates for any possible inconsistencies and to ensure that the composite laminates manufactured by the laying or stacking process meet the design and / or quality requirements related to the orientation of canvas.
[005] There are known methods and systems for determining and verifying the canvas orientation. However, such known methods and systems may require an extensive and time-consuming polishing process on an edge or portion of a sample laminated composite to be analyzed. Such a polishing process may be necessary to obtain sufficient visibility of the fiber orientation of the composite laminate sheets. The polishing process may require mounting the sample on an epoxy resin material, or similar material, so that the sample can be held in place during the polishing process. Such an assembly process can be difficult with large samples that require polishing.
[006] Furthermore, such known methods and systems for determining and verifying the orientation of the canvas may require the use of a high amplification microscope, that is, 100x or higher, to observe the individual fibers of the composite laminate canvas of the sample. If the sample to be analyzed is larger than the microscope's field of view, this may require obtaining multiple images of the composite laminate sheets and editing the images together with known photo editing software to obtain a continuous view of the sample under the microscope. This image preparation process can be time-consuming and labor-intensive.
[007] In addition, such known methods and systems for determining and verifying the orientation of the canvas may require additional cutting, polishing, and image processing steps to analyze the fibers of the sample composite laminate having a canvas orientation of + 45 ° (plus forty-five degrees) and a canvas orientation of -45 ° (minus forty-five degrees). To sufficiently distinguish between a + 45 ° canvas orientation (plus forty-five degrees) and a -45 ° canvas orientation (less than forty-five degrees), a second cut and a second composite laminate cut may need to be made and the assembly, polishing, and image processing processes may need to be performed for both cuts of the + 45 ° canvas orientation (plus forty-five degrees) and the -45 ° canvas orientation (minus forty-five degrees) . The additional work required to analyze +/- 45 ° (plus / minus forty-five degrees) tarps can increase overall time and manufacturing costs.
[008] Thus, such known methods and systems for determining and verifying the orientation of canvas can be very time-consuming, labor-intensive, and tedious, and can, in turn, result in high manufacturing time and costs. For example, a known process for determining and verifying the orientation of the canvas that includes the steps of assembly, polishing, and image processing can take several days to complete.
[009] Consequently, there is a need in the art for an improved method and system for determining and verifying the canvas orientation of a composite laminate that provides advantages over known methods and systems. SUMMARY
[0010] Example implementations of the present description provide an improved method and system for determining and verifying the canvas orientation of a composite laminate to overcome the laborious nature of existing solutions. As discussed in the detailed description below, improved method and system modalities for determining and verifying the canvas orientation of a composite laminate can provide significant advantages over existing methods and systems.
[0011] In one embodiment of the description, a method is provided to determine and verify the canvas orientation of a composite laminate. The method comprises the step of carrying out a first scan of a prepared edge of the composite laminate using a light source inclined off a geometrical axis directing light at a first angle to a first area on the edge prepared to produce a first scanned image. The method further comprises the step of rotating an orientation of the light source inclined off-axis relative to the prepared edge. The method further comprises the step of carrying out a second scan of the prepared edge using the light source tilted off the geometric axis directing light at a second angle to the first area on the prepared edge to produce a second scanned image.
[0012] The method further comprises the step of comparing the first scanned image and the second scanned image to determine a canvas orientation of each canvas of the composite laminate. The orientation of the canvas is preferably determined based on reflections from the light source of the slanted light source off-axis. Preferably, the steps of performing the first scan of the prepared edge and carrying out the second scan of the prepared edge comprise using an scanning device having an optical resolution of 1,200 dpi (dots per inch) or higher. More preferably, the step of comparing the first scanned image and the second scanned image to determine the canvas orientation comprises using a manual visual comparison of the light source reflections from the first scanned image and the second scanned image. The method further comprises the step of checking the canvas orientation of the composite laminate against a reference canvas orientation of a reference composite laminate. Preferably, the step of checking the canvas orientation of the composite laminate comprises verifying that a plurality of canvas of the composite laminate is properly seated as intended by the design.
[0013] In another embodiment of the description, a method is provided to determine and verify the canvas orientation of a composite laminate of a composite aircraft structure. The method comprises the step of preparing an edge of the composite laminate to obtain a prepared edge. The method further comprises the step of carrying out with an scanning device having at least one light source tilted off the axis a first scan of the prepared edge using at least one light source tilted off the axis to direct light in a first angle to a first area on the edge prepared to produce a first scanned image. The method further comprises the step of rotating an orientation of at least one light source inclined off-axis 180 degrees relative to the prepared edge by 180 degrees. The method further comprises the step of carrying out with the scanning device a second scan of the prepared edge using at least one light source inclined off-axis to direct light at a second angle to the first area over the prepared edge to produce a second image explored.
[0014] The method further comprises the step of transferring the first scanned image and the second scanned image from the scanning device to a processing device for processing. The method further comprises the step of comparing the first scanned image and the second scanned image to determine a canvas orientation of each canvas of the composite laminate. Preferably, the step of comparing the first scanned image and the second scanned image to determine the canvas orientation comprises using at least one of a manual visual comparison and an automatic comparison with a process software of the reflections of the light source of the first image explored and the second image explored. The canvas orientation is preferably determined based on reflections from the light source of the at least one light source tilted outside the geometric axis. Preferably, the steps of carrying out the first scan (104) of the prepared edge (92a) and carrying out the second scan (126) of the prepared edge (92a) comprise carrying out with the scanning device (102) having a light source (106a) 45 (forty-five degrees) and an optical resolution (122) of 1,200 dpi (dots per inch) or higher. The method further comprises the step of preparing a reference matrix comprising a reference canvas orientation of a reference composite laminate of the aircraft's composite structure. The method further comprises the step of checking the canvas orientation of the composite laminate against the reference canvas orientation of the reference matrix. Preferably, the step of comparing the first scanned image and the second scanned image to determine the canvas orientation comprises determining the canvas orientation based on reflections from the light source comprising light / dark transition reflections at +/- 45 ° (more / minus forty-five) degrees plies to a cross-sectional surface of the prepared edge, dark reflections for normal plies to the cross-sectional surface of the prepared edge, and clear reflections for plies parallel to the cross-sectional surface of the prepared edge.
[0015] In another embodiment of the description, a system is provided to determine and verify the canvas orientation of a composite laminate. The system comprises a composite laminate which is cured and comprises at least one prepared edge and a plurality of tarps, each tarpaulin having a tarpaulin orientation.
[0016] The system additionally comprises an exploration set. The scanning array comprises an scanning device having at least one light source tilted off-axis configured to direct light at a first angle to a first area over the prepared edge of the composite laminate to illuminate and capture a first scanned image. The at least one light source tilted off the geometric axis is further configured to direct light at a second angle to the first area on the edge prepared to illuminate and capture a second scanned image. The scanning set further comprises a processing device coupled to the scanning device. The processing device is configured to receive and process the first scanned image and the second scanned image from the scanning device. Preferably, the composite laminate is a fiber-reinforced composite laminate, composed of continuous fibers, and the scanning device has an optical resolution of 1,200 dpi (dots per inch) or higher. The scanning set further comprises a reference matrix comprising a reference canvas orientation of a composite reference laminate.
[0017] The system provides a canvas orientation determination of each composite laminate canvas based on reflections from the light source of at least one light source tilted off the axis and a comparison of the first scanned image and the second scanned image . The system also provides a canvas orientation check of the composite laminate using the reference matrix. Preferably, the processing device comprises a computer having process software for processing the first scanned image and the second scanned image to allow comparison of the first scanned image and the second scanned image against each other and against the reference matrix.
[0018] The characteristics, functions, and advantages, which have been discussed, can be obtained independently in various modalities of the description, or can be combined in still other modalities, other details of which can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] The description can be better understood with reference to the following detailed description, taken in conjunction with the accompanying drawings, which illustrate preferred and exemplary modalities, but which are not necessarily drawn without scale, in which: figure 1 is a illustration of a perspective view of an aircraft having one or more composite structures that can be explored and verified using modalities of a method and a description system; figure 2 is an illustration of a flow chart of a modality of an aircraft manufacturing and maintenance method; figure 3 is an illustration of a functional block diagram of an aircraft modality; Figure 4A is a flow chart illustration of one of the modalities of a method for determining and verifying the canvas orientation of a composite laminate of the description; Figure 4B is a flow chart illustration of one of the modalities of a method for determining and verifying the canvas orientation of a composite laminate of an aircraft composite structure of the description; Figure 5 is an illustration of a functional block diagram of an embodiment of a system for determining and verifying the canvas orientation of a composite laminate of the description; Figure 6A is a schematic illustration of a side view of an embodiment of a system for determining and verifying the canvas orientation of a composite laminate, where the composite laminate is being subjected to a first scan; Figure 6B is a schematic illustration of a side view of the system for determining and verifying the canvas orientation of the composite laminate of Figure 6A, where the composite laminate is being subjected to a second scan; figure 7 is a schematic illustration of images explored side by side from first explored images, taken by first explorations, and second explored images, taken by second explorations, from a prepared edge of a composite laminate, obtained using one of the methods of a method and a description system; and, figure 8 is an illustration of a modality of a reference matrix that can be used in one of the modalities of a method and a system for determining and verifying the canvas orientation of the composite laminate of the description. DETAILED DESCRIPTION
[0020] The described modalities will now be described more fully hereinafter with reference to the attached drawings, in which some modalities, but not all of the described modalities, are shown. In fact, several different modalities can be provided and should not be interpreted as limited to the modalities described here. On the contrary, these modalities are provided in such a way that this description will be concise and will fully convey the scope of the description to those skilled in the art.
[0021] Now, with reference to the figures, figure 1 is an illustration of a perspective view of an aircraft 10 having one or more composite structures 12. As shown further in figure 1, aircraft 10 comprises a fuselage 14, a nose 16, wings 18, engines 20, and a warp 22 comprising horizontal stabilizers 24 and a vertical stabilizer 26. As shown in figure 1, the one or more composite structures 12 may comprise a composite laminate 28. Preferably, the composite laminate 28 ( see figure 1), discussed in more detail below, is cured and is in the form of a fiber-reinforced composite laminate 28a (see figure 1).
[0022] Description modalities, discussed in detail below, provide a method 66 (see figure 4A) to determine and verify the canvas orientation of the composite laminate 28 (see figures 1, 5), provide a method 80 (see the figure 4B) to determine and verify the canvas orientation of the composite laminate 28 of the composite structure of the aircraft 12, and provide a system 90 (see figure 5) to determine and verify the canvas orientation of the composite laminate 28 (see figures 1 , 5).
[0023] Figure 2 is an illustration of a flow chart of a modality of an aircraft manufacturing and maintenance method 30. Figure 3 is an illustration of a functional block diagram of an aircraft modality 50. With reference to the Figures 2 to 3, modalities of the description can be described in the context of the aircraft manufacturing and maintenance method 30, as shown in figure 2, and aircraft 50, as shown in figure 3. During pre-production, the manufacturing method and aircraft maintenance 30, for example, (see figure 2), may include specification and design 32 (see figure 2) of aircraft 50 (see figure 3) and material acquisition 34 (see figure 2). During manufacturing, the manufacture of components and subassemblies 36 (see figure 2) and systems integration 38 (see figure 2) of aircraft 50 (see figure 3) take place. After that, the aircraft 50 (see figure 3) can go through certification and delivery 40 (see figure 2) in order to be put into service 42 (see figure 2). While in service 42 (see figure 2) by a customer, aircraft 50 (see figure 3) can be scheduled for routine maintenance and service 44 (see figure 2), which may also include modification, reconfiguration, remodeling, and other suitable services.
[0024] Each of the aircraft manufacturing and maintenance method processes 30 (see figure 2) can be performed or executed by a systems integrator, a third party, and / or an operator (for example, a customer). For the purposes of this description, a systems integrator may include, without limitation, any number of aircraft manufacturers and subcontractors of the main systems; a third party may include, without limitation, any number of vendors, subcontractors, and suppliers; and an operator may include an airline, leasing company, military organization, service organization, and other suitable operators.
[0025] As shown in figure 3, the aircraft 50 produced by the aircraft manufacturing and maintenance method 30, for example, can include a fuselage 52 with a plurality of systems 54 and an interior 56. As shown in figure 3, examples systems 54 may include one or more of a propulsion system 58, an electrical system 60, a hydraulic system 62, and an environmental system 64. Any number of other systems may be included. Although an example aerospace example is shown, the principles of the description can be applied to other industries, such as the automotive industry.
[0026] The methods and systems incorporated here can be used during any one or more of the stages of the aircraft manufacturing and maintenance method 30 (see figure 2). For example, components or subassemblies corresponding to the manufacture of components and subassemblies 36 (see figure 2) can be manufactured or produced in a similar manner to the components or subassemblies produced while aircraft 50 (see figure 3) is in service 42 (see figure 2). Also, one or more device modalities, method modalities, or a combination thereof, can be used during the manufacture of components and subassemblies 36 (see figure 2) and systems integration 38 (see figure 2), for example , by substantially speeding up the assembly of, or reducing the cost of, aircraft 50 (see figure 3). Similarly, one or more of the apparatus modalities, the method modalities, or a combination thereof, may be used while aircraft 50 (see figure 3) is in service 42 (see figure 2), for example, and without limitation, for maintenance and service 44 (see figure 2).
[0027] With reference to figure 4A, in one embodiment of the description, a method 66 is provided to determine and verify the canvas orientation 98 (see figure 5) of composite laminate 28 (see figures 1, 5). Figure 4A is an illustration of a flow chart of one of the modalities of method 66 to determine and verify the canvas orientation 98 (see figure 5) of composite laminate 28 (see figure 5).
[0028] With reference to figure 4B, in another embodiment of the description, a method 80 is provided to determine and verify the canvas orientation 98 (see figure 5) of composite laminate 28 (see figures 1, 5) of the composite structure of aircraft 12 (see figures 1, 5). Figure 4B is an illustration of a flowchart of one of the modalities of method 80 to determine and verify the canvas orientation 98 (see figure 5) of composite laminate 28 (see figure 5) of the composite structure of aircraft 12 (see figures 1, 5).
[0029] With reference to figure 5, in another embodiment of the description, a system 90 is provided for determining and verifying the canvas orientation 98 of the composite laminate 28. Figure 5 is an illustration of a functional block diagram of a modality of the system 90 to determine and verify the canvas orientation 98 of the composite laminate 28.
[0030] In the discussion below method 66 shown in figure 4A, reference will be made to the various components of the related system 90 in figure 5. Similarly, in the discussion below method 80 shown in figure 4B, reference will be made to the various components of the related system. 90 of figure 5.
[0031] As shown in figure 4A, method 66 comprises an optional step 68 of preparing an edge 92 (see figure 5) of composite laminate 28 (see figure 5) to obtain a prepared edge 92a (see figure 5) . During the manufacture of composite laminate 28 (see figure 5), one or more edges 92 (see figure 5) of composite laminate 28 (see figure 5) can become rough and may require one or more preparation treatments 93 ( see figure 5), in order to obtain a prepared edge 92 a (see figure 5) that is smooth or polished before being subjected to the exploration steps of method 66 (see figure 4A), discussed below. Preferably, preparation treatments 93 (see figure 5) comprise one or more procedures, such as smoothing, polishing, abrasion, finishing, cleaning, or other suitable preparation treatment for edge 92a (see figure 5) of composite laminate 28 (see figure 5). Preparation treatments 93 (see figure 5) can be carried out through a manual process, for example, manually by sanding the edge 92 (see figure 5) with sandpaper or another abrasion device, with the polishing or cleaning solution or device, or with another suitable manual preparation treatment. Alternatively, preparation treatments 93 (see figure 5) can be carried out through an automatic process, or through a combination of manual and automatic processes.
[0032] Step 68 of preparing edge 92 (see figure 5) can be carried out in a short period of time, and preferably, in about ten (10) minutes to thirty (30) minutes, and more preferably, in about ten (10) minutes. This short preparation treatment time to prepare the edge 92 (see figure 5) is advantageous in comparison to the assembly and polishing processes required in the known methods for determining and checking the canvas orientation, which can take hours to be completed. completed.
[0033] The composite laminate 28 (see figures 1, 5) is preferably in the form of a fiber-reinforced composite laminate 28a (see figures 1.5), composed of a plurality of canvas 94 (see figure 5). The preparation of the edge 92 (see figure 5) of the composite laminate 28 (see figures 1, 5) to obtain the prepared edge 92a (see figure 5) preferably facilitates the visibility of the plurality of sheets 94 (see figure 5) at the prepared edge 92a (see figure 5), in the images explored from the prepared edge 92a, after the prepared edge 92a has been explored, as discussed below.
[0034] The plurality of canvas 94 (see figure 5) preferably comprises continuous fibers 96 (see figure 5) in a resin matrix material 97 (see figure 5). Continuous fibers 96 (see figure 5) are preferred over staple or chopped fibers. With continuous fibers 96 (see figure 5), few, if any, breaks in the reinforcements can occur, and continuous fibers 96 can provide better performance properties of composite laminate 28 (see figure 5).
[0035] The continuous fibers 96 (see figure 5) comprising the plurality of tarpaulins 94 (see figure 5) preferably comprise reinforcing or high strength fibers, made from one or more materials, such as carbon, glass, fiber glass, graphite, boron, aromatic polyamide, silicon carbide, or other suitable reinforcement or high strength material. The resin matrix material 97 (see figure 5) may comprise polymeric, ceramic, metallic, or other matrix materials, such as epoxy, polyester, vinyl ester resins, polyetheretherketone polymer (PEEK), polyetheretherketone polymer (PEKK) ), polyimides, bismaleimide, aluminum, titanium, alumina, or other suitable matrix material. When used here, “cured” means undergoing a process of total or partial hardening, with or without heat, for example, the resin matrix material hardening to form a strong, rigid fiber-reinforced laminate composite.
[0036] The plurality of sheets 94 (see figure 5) of composite laminate 28 (see figures 1.5) may comprise a unidirectional "prepreg" tape, a unidirectional fiber tape, a tape reinforced with fiber reinforced plastic carbon (CFRP), or other suitable tape; a carbon fiber reinforced plastic (CFRP) fabric, a "prepreg" fabric, a woven fabric including a carbon fiber woven cloth, or other suitable fabric; a combination of a ribbon or cloth made from it; or other suitable composite material.
[0037] The composite laminate 28 (see figure 5) can be formed of a composite material by any suitable means including, but not limited to, manual laying, automatic laying, or other suitable forming process. Each canvas 94 (see figure 5) preferably has a canvas orientation 98 (see figure 5). The canvas orientation 98 (see figure 5) can be configured for any desired canvas direction. For example, the canvas orientation 98 (see figure 5) may include, without limitation, such canvas orientations as: 0o (zero degree) canvas orientation, where a canvas orientation angle 190 (see figure 5) the fiber is 0o (zero degrees) or parallel to a cross-sectional surface 114 (see figures 5, 6A) of the prepared edge 92a (see figures 5, 6A); 90 ° canvas orientation (ninety degrees), where the canvas orientation angle 190 (see figure 5) of the fiber is 90 ° (ninety degrees) or perpendicular or normal to the cross-sectional surface 114 (see figures 5 , 6A) of the prepared edge 92a (see figures 5, 6A); + 45 ° (plus forty-five degrees) / -45 ° (minus forty-five degrees) canvas orientation, where the canvas orientation angle 190 (see figure 5) of the fiber is + 45 ° (plus forty-five degrees) five degrees) / -45 ° (minus forty-five degrees) to the cross-sectional surface 114 (see figures 5, 6A) of the prepared edge 92a (see figure 5), or other suitable canvas orientation.
[0038] When used here, "canvas orientation angle" means the angle that the fibers of a canvas make with a cross-sectional surface of a prepared edge of a composite laminate, or alternatively, the angle that the fibers of a canvas they make a surface of an scanning device on which a sample of the composite laminate is positioned for image scanning. Also, as an example, when used here, "+ 45 ° (plus forty-five degrees)" means that a canvas is generated by 45 ° (forty-five degrees) clockwise in relation to the orientation of a adjacent canvas layer and "-45 ° (minus 45 degrees)" means that a canvas is rotated by 45 ° (forty-five degrees) counterclockwise relative to the orientation of an adjacent canvas layer .
[0039] As shown in figure 4A, method 66 additionally comprises step 70 of performing a first scan 104 (see figures 5, 6A) of the prepared edge 92a (see figure 5) of composite laminate 28 (see figure 5) . The first scan 104 (see figure 5) is preferably carried out using a light source inclined off-axis 106 (i.e., the light source that is not perpendicular to the prepared edge 92a, as shown in figure 5). The tilted off-axis light source 106 (see figure 5) preferably directs light 108 (see figure 5) at a first acute angle 110 with respect to the prepared edge 92a (i.e., an angle that is not perpendicular to the surface prepared, as shown in figure 5), to direct light 108 to a first area 112 (see figure 5) on the prepared edge 92a (see figure 5) to produce a first scanned image 116 (see figure 5). The inclined off-axis light source 106 (see figure 5) illuminates the first area 112 (see figure 5) on the prepared edge 92a (see figure 5).
[0040] As shown in figure 4A, method 66 further comprises step 72 of rotating an orientation 117 (see figure 5) of the tilted light source off-axis 106 (see figure 5) at a rotation 125 (see figure 5) in relation to the prepared edge 92a (see figure 5) of composite laminate 28 (see figure 5). Step 72 of rotating the orientation 117 (see figure 5) of the tilted off-axis light source 106 (see figure 5) preferably comprises rotating the 117 orientation (see figure 5) of the tilted off-axis light source geometric 106 in a 180 degree rotation 125a (see figure 5) in relation to the prepared edge 92a (see figure 5) of composite laminate 28 (see figure 5).
[0041] As shown in figure 4A, method 66 further comprises step 74 of performing a second scan 126 (see figure 5) of the prepared edge 92a (see figure 5) of composite laminate 28 (see figure 5). The second scan 126 (see figure 5) is preferably carried out with the orientation of the tilted light source off-axis 106 (see figure 5) general 180 degrees from that of the first scan. With the orientation of the tilted light source off-axis generated by 180 degrees relative to that of the first scan, the tilted light source off-axis 106 (see figure 5) preferably directs light 108 (see figure 5) in a second acute angle 130 with respect to the prepared edge 92a which is symmetrically opposite the first acute angle 110 (see figure 5), to direct light at a second angle symmetrically opposite 110 to the first area 112 (see figure 5) on the edge prepared 92a to produce a second scanned image 128 (see figure 5).
[0042] Step 70 (see figure 4A) of performing the first scan 104 (see figure 5) of the prepared edge 92a (see figure 5) and step 74 (see figure 4A) of carrying out the second scan 126 (see figure 5) of the prepared edge 92a (see figure 5) preferably comprise using an scanning device 102 (see figure 5) having a light source 106a (see figure 5) oriented at an angle of 45 ° ( forty-five degrees) in relation to the prepared surface, so that light directed at the first acute angle 110 is about 45 ° (forty-five degrees) in relation to the prepared surface and light directed at the second acute angle 130 is about 45 ° (forty-five degrees) in relation to the prepared surface and symmetrically opposite the first acute angle 110.
[0043] Scanning device 102 (see figure 5) is preferably a flat color image scanning device or other suitable scanning device. The scanning device 102 (see figure 5) preferably has one or more light sources tilted off the axis 106 (see figure 5), housed within a housing 164 (see figure 6A) of the scanning device 102 ( see figure 6A). The tilted off-axis light source 106 (see figure 5) can comprise a fluorescent light source, such as a fluorescent lamp or a cold cathode fluorescent lamp; a xenon light source, such as a xenon lamp; LED (light emitting diode) lights, or other suitable light source. The tilted off-axis light source 106 (see figure 5) can be connected to a voltage regulator (not shown) to ensure consistency of light over the scanning pass.
[0044] The scanning device 102 (see figure 5) may preferably have an inclined light source off-axis 106 (see figure 5). Alternatively, the scanning device 102 (see figure 5) can have more than one light source tilted off the axis 106 (see figure 5), as can two light sources tilted off the axis 106 (see figure 5). For example, for scanning composite laminate 28 (see figure 5) with scanning device 102 (see figure 5) having two inclined light sources off the axis 106 (see figure 5), the light sources tilted off-axis 106 (see figure 5) can be controlled so that a first off-axis tilted light source is switched on and a second off-axis tilted light source is switched off during the first scan 104 (see figure 5). Then, with the second scan 126 (see figure 5), the first light source tilted off the axis is turned off and the second light source tilted off the axis is turned on.
[0045] In one embodiment, during the first scan 104, the light source tilted off the geometric axis 106 can direct light 108, for example, at an angle of +45 (plus forty-five degrees) to the first area 112 ( see figure 5) on the prepared edge 92a (see figure 5). The orientation 117 (see figure 5) of the tilted off-axis light source 106 (see figure 5) can then be rotated by preferably in a 180 degree rotation 125a (see figure 5) with respect to the prepared edge 92a (see figure 5) of composite laminate 28 (see figure 5). Then, during the second scan 126 (see figure 5), the tilted light source off-axis 106 (see figure 5) can direct light 108 (see figure 5), for example, at an angle of -45 ° (minus forty-five degrees) for the first area 112 (see figure 5) on the prepared edge 92a (see figure 5).
[0046] Alternatively, during the first exploration 104, the light source tilted off the geometric axis 106 can direct light 108, for example, at an angle of +45 (plus forty-five degrees) to the first area 112 (see the figure 5) on the prepared edge 92a (see figure 5). Then, the composite laminate 28 (see figure 5) can be physically rotated 180 degrees and scanned, so that during the second scan 126 (see figure 5), the inclined light source off-axis 106 (see figure 5) directs light 108 (see figure 5), for example, at an angle of -45 ° (minus forty-five degrees) to the first area 112 (see figure 5) on the prepared edge 92a (see figure 5). By rotating the composite laminate 28 (see figure 5) by 180 degrees and then scanning, the orientation 117 (see figure 5) of the inclined light source off-axis 106 (see figure 5) is effectively also rotated by 180 degrees in relation to the prepared edge 92a (see figure 5) of composite laminate 28 (see figure 5).
[0047] Step 70 (see figure 4A) of performing the first scan 104 (see figure 5) of the prepared edge 92a (see figure 5) and step 74 (see figure 4A) of carrying out the second scan 126 (see figure 5) of the prepared edge 92a (see figure 5) preferably comprise using the scanning device 102 (see figure 5) having an optical resolution 122 (see figure 5) of 1,200 dpi (dots per inch), or superior. The scanning device 102 (see figure 5) preferably has a hardware resolution of 1,200 x 1,200 dpi, or higher; a maximum resolution of 9,600 x 9,600 dpi, or higher; a scanning speed of 1.6 msec./line (milliseconds per line), or higher, for black and white scanning at 1,200 dpi; and a scanning speed of 4.9 msec./line (milliseconds per line), or higher, for color scanning at 1,200 dpi. However, the scanning device 102 (see figure 5) may have other suitable resolutions and speeds.
[0048] An example of an exploration device that can be used with method 66 (see figure 4A), method 80 (see figure 4B), and system 90 (see figure 5), described here, includes , but is not limited to, an EPSON flat scanning device from Epson America, Inc. of Long Beach, California. (EPSON is a registered trademark of Seiko Epson Kabushiki Kaisha DBA - Seiko Epson Corporation of Tokyo, Japan.) However, other suitable scanning devices may also be used.
[0049] As shown in figure 4A, method 66 further comprises step 76 of comparing the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) to determine the canvas orientation 98 (see figure 5) of each canvas 94 (see figure 5) of composite laminate 28 (see figure 5). The orientation of the canvas 98 (see figure 5) is preferably determined based on reflections from the light source 124 (see figure 5) of the inclined light source off-axis 106 (see figure 5).
[0050] In one embodiment, step 76 (see figure 4A) of comparing the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) to determine the canvas orientation 98 (see figure 5) comprises a manual visual comparison 146a (see figure 5) of the reflections of light source 124 (see figure 5) of the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5). Preferably, manual visual comparison 146a is performed by one or more operators of method 66 (see figure 4A).
[0051] In another embodiment, step 76 (see figure 4A) of comparing the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) to determine the canvas orientation 98 (see figure 5) comprises using an automatic comparison 146b (see figure 5) with process software 154 (see figure 5) to compare the light source reflections 124 (see figure 5) of the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5). In yet another embodiment, step 76 (see figure 4A) of comparing the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) to determine the canvas orientation 98 (see figure 5) can be understood using a combination of manual visual comparison 146a (see figure 5) and automatic comparison 146b (see figure 5) with process software 154 (see figure 5).
[0052] Step 76 (see figure 4A) of comparing the first scanned image (see figure 5) and the second scanned image 128 (see figure 5) to determine the canvas orientation 98 (see figure 5) preferably it comprises determining the canvas orientation 98 (see figure 5) based on reflections from the light source 124 (see figure 5). Preferably, the light source reflections 124 (see figure 5) comprise light / dark transition reflections 144a, 144b (see figure 5) on the canvas 142 (see figure 5) outside the geometric axis with respect to the section surface cross-section 114 (see figure 5) from the prepared edge 92a (see figure 5), such as +/- 45 ° (plus / minus forty-five degrees) plies 142a, 142b (see figure 5) to the cross-sectional surface 114 (see figure 5) of the prepared edge 92a (see figure 5). Preferably, the light source reflections 124 (see figure 5) further comprise dark reflections 136 (see figure 5) for canvases 134 (see figure 5) normal or perpendicular to the cross-sectional surface 114 (see figure 5) the prepared edge 92a (see figure 5), such as the 90 ° (ninety degrees) tarpaulins. Preferably, the light source reflections 124 (see figure 5) further comprise light reflections 140 (see figure 5) for canvas 138 (see figure 5) parallel to the cross-sectional surface 114 (see figure 5) of the edge prepared 92a (see figure 5), such as tarpaulins at 0o (zero degree).
[0053] As shown in figure 4A, method 66 further comprises step 78 of checking the canvas orientation 98 (see figure 5) of composite laminate 28 (see figure 5) against one or more reference canvas directions 99 ( see figure 5) of a composite reference laminate 29 (see figure 5), and preferably against reference canvas guidelines 99 (see figure 5) of a plurality of reference plies 95 (see figure 5) of the laminate reference composite 29 (see figure 5). Step 78 (see figure 4A) of verifying the canvas orientation 98 (see figure 5) of composite laminate 28 (see figure 5) comprises verifying that the plurality of plies 94 (see figure 5) of composite laminate 28 (see figure 5) is correctly seated as intended by the project, such as a defined sequence of tarps, specified by design and / or quality requirements for composite laminate 28 (see figure 5), for example, to optimize performance , such as load-bearing capacity.
[0054] Method 66 (see figure 4A) can optionally further comprise, before the verification step 78 (see figure 4A), the step of preparing the reference matrix 148 (see figure 5) comprising the orientation of reference sheet 99 (see figure 5) of the plurality of reference sheets 95 (see figure 5) of the composite reference laminate 29 (see figure 5). The reference matrix 148, an example of which is shown in figure 8, can be prepared using a known composite laminate or known composite laminates with known canvas orientations.
[0055] Figure 4B shows method 80 to determine and verify the canvas orientation 98 (see figure 5) of composite laminate 28 (see figures 1, 5) of a composite aircraft structure 12 (see figure 1) . As shown in figure 4B, method 80 comprises step 82 of preparing edge 92 (see figure 5) of composite laminate 28 (see figure 5) to obtain prepared edge 92a (see figure 5). One or more edges 92 (see figure 5) of composite laminate 28 (see figures 1, 5) may require one or more preparation treatments 93 (see figure 5) in order to obtain the prepared edge 92a which is smooth or polished before being subjected to method 80 (see figure 4B). As discussed above, preparation treatments 93 (see figure 5) preferably comprise one or more procedures, such as smoothing, polishing, abrasion, finishing, cleaning, or other preparation treatment suitable for edge 92a (see figure 5 ) of composite laminate 28 (see figure 5). Preparation treatments 93 (see figure 5) can be carried out manually or through automation, as discussed above. Preferably, the one or more preparation treatments 93 (see figure 5) from edge 92 (see figure 5) facilitate the visibility of the plurality of plies 94 (see figure 5) on prepared edge 92a (see figure 5) in images of prepared edge 92a, after prepared edge 92a has been explored.
[0056] As discussed above, composite laminate 28 (see figures 1, 5) is preferably in the form of a fiber reinforced composite laminate 28a (see figures 1, 5) composed of a plurality of canvas 94 (see figure 5). The plurality of plies 94 (see figure 5) preferably comprise continuous fibers 96 (see figure 5) in a resin matrix material 97 (see figure 5).
[0057] As shown in figure 4B, method 80 further comprises step 83 of carrying out with scanning device 102 (see figure 5) having at least one light source inclined off-axis 106 (see figure 5), a first scan 104 (see figure 5) of the prepared edge 92a (see figure 5) of composite laminate 28 (see figure 5). The first scan 104 (see figures 5, 6A) preferably uses at least one light source tilted off-axis 106 (see figure 5) to direct light 108 (see figure 5) at the first acute angle 110 with respect to to prepared edge 92a (see figure 5), to direct light 108 to the first area 112 (see figure 5) over prepared edge 92a (see figure 5) to produce the first scanned image 116 (see figure 5) .
[0058] As shown in figure 4B, method 80 further comprises step 84 of rotating an orientation 117 (see figure 5) 180 degrees from at least one light source tilted off-axis 106 (see figure 5) in one rotation 125 (see figure 5) in relation to the prepared edge 92a (see figure 5) of composite laminate 28 (see figure 5). As shown in figure 4B, method 80 further comprises step 85 of carrying out with the scanning device 102 (see figure 5) a second scan 126 (see figure 5) of the prepared edge 92a (see figure 5) of the composite laminate 28 (see figure 5). With the orientation of the tilted off-axis light source rotated 180 degrees from that of the first scan, the second scan 126 (see figure 5) uses at least one off-axis tilted light source 106 (see the figure 5) to direct light 108 (see figure 5) at the second acute angle 130 in relation to the prepared edge 92a which is symmetrically opposite the first acute angle 110 (see figure 5), to direct light at a second acute angle 130, symmetrically opposite, for the first area 112 (see figure 5) on the prepared edge 92a (see figure 5) to produce the second scanned image 128 (see figure 5).
[0059] As discussed above, in one embodiment, during the first scan 104, the light source tilted off the geometric axis 106 (see figure 5) can direct light 108 (see figure 5), for example, at an angle +45 (plus forty-five degrees) for the first area 112 (see figure 5) on the prepared edge 92a (see figure 5). The orientation 117 (see figure 5) of the tilted off-axis light source 106 (see figure 5) can then be rotated by preferably in a 180 degree rotation 125a (see figure 5) with respect to the prepared edge 92a (see figure 5) of composite laminate 28 (see figure 5). Then, during the second scan 126 (see figure 5), the tilted light source off-axis 106 (see figure 5), rotated 180 degrees, can direct light 108 (see figure 5), for example, at an angle of -45 ° (minus forty-five degrees) for the first area 112 (see figure 5) on the prepared edge 92a (see figure 5), which is symmetrically opposite to that used in the first exploration 104.
[0060] Alternatively, as discussed above, during the first exploration 104 (see figure 5), the light source tilted off the geometric axis 106 (see figure 5) can direct light 108 (see figure 5), for example , at an angle of +45 (plus forty-five degrees) for the first area 112 (see figure 5) on the prepared edge 92a (see figure 5). Then, the composite laminate 28 (see figure 5) is physically rotated by preferably 180 degrees over the scanning device 102 (see figure 5) and explored, so that during the second scan 126 (see figure 5), the tilted light source off-axis 106 (see figure 5) directs light 108 (see figure 5), for example, at an angle of -45 ° (minus forty-five degrees) to the first area 112 (see figure 5) on the prepared edge 92a (see figure 5).
[0061] Step 83 (see figure 4B) of carrying out the first scan 104 (see figure 5) of the prepared edge 92a (see figure 5) and step 85 of carrying out the second scan 126 (see figure 5) of the prepared edge 92a (see figure 5) preferably comprise using the scanning device 102 (see figure 5) having a light source at 45 ° (forty-five degrees) 106a (see figure 5) and having an optical resolution 122 (see figure 5) of 1,200 dpi (dots per inch), or higher. The specifics of scanning device 102 (see figure 5) used in method 66 (see figure 4A), as discussed above, also apply to scanning device 102 (see figure 5) used in method 80 (see figure 4B).
[0062] As shown in figure 4B, method 80 further comprises step 86 of transferring the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) from the scanning device 102 (see figure 5) for a processing device 150 (see figure 5) for processing. The first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) can be converted to digital pixel information, which can be transferred via one or more connection elements 152 (see figure 5 ) for the processing device 150 (see figure 5), such as in the form of a computer 150a (see figure 5), and saved as a digital file in the processing device 150 (see figure 5). The one or more connection elements 152 (see figure 5) can comprise wired cable connections or wireless connections. After the transfer, the digital file or digital files of the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) can, for example, be opened, saved, edited, deleted or printed.
[0063] As shown in figure 4B, method 80 further comprises step 87 of comparing the first scanned image (see figure 5) and the second scanned image 128 (see figure 5) to determine the canvas orientation 98 (see the figure 5) of each canvas 94 (see figure 5) of composite laminate 28 (see figure 5). The orientation of the canvas 98 (see figure 5) is preferably determined based on the reflections of light source 124 (see figure 5) of at least one light source inclined off-axis 106 (see figure 5).
[0064] Step 87 (see figure 4B) of comparing the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) to determine the canvas orientation 98 (see figure 5) comprises using at least one of a manual visual comparison 146a (see figure 5) and / or an automatic comparison 146b (see figure 5) with process software 154 (see figure 5) to compare reflections from light 124 (see figure 5) of the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5). Preferably, manual visual comparison 146a is performed by one or more operators of method 80 (see figure 4B).
[0065] Step 87 (see figure 4B) of comparing the first scanned image (see figure 5) and the second scanned image 128 (see figure 5) to determine the canvas orientation 98 (see figure 5) preferably it comprises determining the canvas orientation 98 (see figure 5) based on reflections from the light source 124 (see figure 5). Preferably, the light source reflections 124 (see figure 5) comprise light / dark transition reflections 144a, 144b (see figure 5) on the canvas 142 (see figure 5) outside the geometric axis with respect to the section surface cross-section 114 (see figure 5) from the prepared edge 92a (see figure 5), such as +/- 45 ° (plus / minus forty-five degrees) plies 142a, 142b (see figure 5) to the cross-sectional surface 114 (see figure 5) of the prepared edge 92a (see figure 5). Preferably, the light source reflections 124 (see figure 5) further comprise dark reflections 136 (see figure 5) for canvases 134 (see figure 5) normal or perpendicular to the cross-sectional surface 114 (see figure 5) the prepared edge 92a (see figure 5), such as the 90 ° (ninety degrees) tarpaulins. Preferably, the light source reflections 124 (see figure 5) comprise light reflections 140 (see figure 5) for canvas 138 (see figure 5) parallel to the cross-sectional surface 114 (see figure 5) of the prepared edge 92a (see figure 5), such as tarpaulins at 0o (zero degree).
[0066] As shown in figure 4B, method 80 further comprises step 88 of preparing the reference matrix 148 (see figure 5) comprising one or more orientations of reference canvas 99 (see figure 5) of the composite laminate reference 29 (see figure 5) of the composite structure of the aircraft 12 (see figures 1, 5), and preferably, comprising the reference canvas guidelines 99 (see figure 5) of a plurality of reference plies 95 (see figure 5) of the composite reference laminate 29 (see figure 5) of the composite structure of the aircraft 12 (see figures 1.5).
[0067] As shown in figure 4B, method 80 additionally comprises step 89 of verifying the canvas 98 (see figure 5) orientations of composite laminate 28 (see figure 5) against the reference canvas 99 orientation (See the figure 5) of the reference matrix 148 (see figure 5), and in particular, against the reference canvas guidelines 99 (see figure 5) of the plurality of reference tarps 95 (see figure 5) of the composite laminate reference 29 (see figure 5). The step 89 (see figure 4B) of verifying the canvas guidelines 98 (see figure 5) of the composite laminate 28 (see figure 5) comprises verifying that the plurality of canvas 94 (see figure 5) of the composite laminate 28 (see figure 5) is correctly seated as intended by the project, such as a defined sequence of tarps specified by design and / or quality requirements for composite laminate 28 (see figure 5), for example, to optimize performance, as as load-bearing capacity.
[0068] Figure 5 shows system 90 for determining and verifying the canvas orientation 98 of composite laminate 28. System 90 (see figure 5) comprises composite laminate 28 (see figure 5) which is cured. As shown in figure 5, composite laminate 28 comprises at least one prepared edge 92a and the plurality of tarps 94. Each tarpaulin 94 (see figure 5) has a tarpaulin orientation 98 (see figure 5). Composite laminate 28 (see figure 5) is preferably a fiber-reinforced composite laminate 28a (see figure 5), composed of continuous fibers 96 (see figure 5) in a resin matrix material 97 (see figure 5 ).
[0069] As discussed above, composite laminate 28 (see figure 5) may have one or more edges 92 (see figure 5) that may require one or more preparation treatments 93 (see figure 5) in order to obtain a prepared edge 92a (see figure 5) that is smooth or polished before being explored and analyzed. Preferably, preparation treatments 93 (see figure 5) comprise one or more procedures, such as smoothing, polishing, abrasion, finishing, cleaning or other preparation treatment suitable for edge 92a (see figure 5) of composite laminate 28 (see figure 5). Preparation treatments 93 (see figure 5) can be carried out manually or through automation, as discussed above. Preferably, the prepared edge 92a (see figure 5) facilitates visibility of the plurality of plies 94 (see figure 5) on the prepared edge 92a (see figure 5) after the prepared edge 92a is scanned.
[0070] As shown in figure 5, system 90 additionally comprises an scanning set 100. Scanning set 100 (see figure 5) comprises scanning device 102 (see figure 5) having at least one light source inclined off geometry axis 106 (see figure 5). Preferably, the at least one light source inclined off-axis 106 (see figure 5) comprises at least one light source at 45 ° (forty-five degrees) 106a (see figure 5). Scanning device 102 (see figure 5) is preferably a flat color scanning device, as discussed above, and preferably has an optical resolution 122 (see figure 5) of 1,200 dpi (dots per inch), or higher.
[0071] The at least one light source inclined off-axis 106 (see figure 5) is preferably configured to direct light 108 (see figure 5) at the first angle 110 (see figure 5) to the first area 112 (see figure 5) on the prepared edge 92 a (see figure 5) of composite laminate 28 (see figure 5) to illuminate and capture the first scanned image 116 (see figure 5). As shown in figure 5, the first scan 104 produces the first scanned image 116, such as in the form of a first scanned cross-section image 116a.
[0072] The light source tilted off the geometric axis 106 (see figure 5) of the scanning device 102 (see figure 5) is further configured to direct light 108 (see figure 5) at the second angle 130 (see the figure 5) for the first area 112 (see figure 5) on the prepared edge 92a (see figure 5) to illuminate and capture the second scanned image 128 (see figure 5). As shown in figure 5, the second scan 126 produces the second scanned image 128, such as in the form of a second scanned cross-sectional image 128a.
[0073] The scanning device 102 (see figure 5) performs the first scan 104 and the second scan 126 in an scanning direction 120 (see figure 5). During the first scan 104 (see figure 5), the tilted light source off-axis 106 (see figure 5) moves along a light source displacement path 118 (see figure 5) to illuminate and capture the first scanned image 116 (see figure 5). During the second scan 126 (see figure 5), the tilted light source off-axis 106 (see figure 5) moves along a light source displacement path 118 (see figure 5) to illuminate and capture the second scanned image 128 (see figure 5). As shown in figure 5, between the first scan 104 and the second scan 126, the orientation 117 of the at least one light source tilted off the axis 106 is rotated by a rotation 125, preferably a 180 degree rotation 125a, with respect to to the prepared edge 92a of the composite laminate 28.
[0074] As shown in figure 5, scanning set 100 further comprises processing device 150 coupled to scanning device 102. Processing device 150 (see figure 5) is preferably configured to receive and process the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) via one or more connecting elements 152 (see figure 5) from the scanning device 102 (see figure 5). As shown in figure 5, the processing device 150 is preferably in the form of a computer 150a. As further shown in Figure 5, processing software 154, storage media 156, and a printing mechanism 158 can also be used with processing device 150 to process, store, and print the first scanned image 116 and the second image explored 128.
[0075] The processing device 150 (see figure 5) can comprise any of an extensive variety of computers 150a (see figure 5) now known in the art or that can be developed in the future. For example only, computer 150a may consist of a personal computer, including a desktop computer, a laptop computer, a notebook computer, or other suitable computer.
[0076] The processing device 150 (see figure 5) can preferably additionally include several other components and features known in the art, such as a central processing unit (CPU), system memory, an operating system, a plurality of applications, one or more input / output interface (s) that interface with corresponding input / output devices (s), one or more communication interface (s) that can interface with other system (s) computer or computer networks, or other suitable components.
[0077] The storage media 156 (see figure 5) can comprise storage media, readable by computer, for storing such items, such as process data, an algorithm, a computer-readable software program (code), or others suitable items. The storage media 156 may comprise any suitable computer-readable storage media, such as read-only memory (ROM), random access memory (RAM), video memory (VRAM), hard disk, floppy disk, compact disk (CD), magnetic tape, a combination thereof, or another suitable computer-readable storage device.
[0078] The printing mechanism 158 (see figure 5) preferably comprises a printer or other suitable output device for displaying or providing the first scanned image 116 and the second scanned image 128, either textually or graphically. In other embodiments, any number of suitable peripheral devices (for example, monitor, printer, keyboard, "mouse", or other devices) can be connected to processing device 150, either directly or indirectly.
[0079] Process software 154 (see figure 5) can implement an algorithm designed to be used in conjunction with processing device 150 (see figure 5), such as computer 150a (hardware). The process software algorithm 154 (see figure 5) can facilitate the processing of the first scanned image 116 and the second scanned image 128. When used here, "algorithm" means a set of instructions or list of steps to perform a task or solve a problem.
[0080] Figure 5 further shows the scanning set 100 comprising one or more controllers 160 to control scanning device 102 and / or processing device 150. Controllers 160 may comprise motor controllers, electrical controllers, control systems software, or other suitable controlling devices or mechanisms. Figure 5 further shows the scanning assembly 100 comprising one or more power supplies 162 to supply power to the scanning device 102 and / or the processing device 150. The power supplies 162 may comprise motors, batteries, power systems electrical power, or other suitable power sources.
[0081] Figure 5 also shows the exploration set 100 comprising the reference matrix 148 (see also figure 8) comprising the orientation (s) of reference canvas 99 of the plurality of reference sheets 95 of the composite laminate. reference 29. The processing device 150 (see figure 5) preferably processes the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) to allow comparison of the first scanned image 116 ( see figure 5) and the second scanned image 128 (see figure 5) with respect to each other and against the reference matrix 148 (see figure 5).
[0082] As shown in figure 5, system 90 provides a determination of canvas orientation 146 of each canvas 94 of composite laminate 28 based on reflections from light source 124 of at least one off-axis tilted light source 106 and a comparison of the first scanned image 116 and the second scanned image 126. A canvas orientation determination 146 (see figure 5) can be determined using a manual visual comparison 146a (see figure 5) and / or an automatic comparison 146b (see figure 5) with process software 154 (see figure 5), to compare the light source reflections 124 (see figure 5) of the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5). Preferably, manual visual comparison 146a is performed by one or more operators of system 90 (see figure 5).
[0083] A determination of canvas orientation 146 (see figure 5) is preferably based on reflections from light source 124 (see figure 5). Preferably, the reflections of the light source 124 (see figure 5) comprise light / dark transition reflections 144a, 144b (see figure 5) on the canvas 142 (see figure 5) outside the geometric axis with respect to the section surface transversal 114 (see figure 5) of the prepared edge 92a (see figure 5), such as +/- 45 ° (plus / minus forty-five degrees) plies 142a, 142b. Preferably, the light source reflections 124 (see figure 5) further comprise dark reflections 136 (see figure 5) for canvases 134 (see figure 5) normal or perpendicular to the cross-sectional surface 114 (see figure 5) the prepared edge 92a (see figure 5), such as the 90 ° (ninety degrees) tarpaulins. Preferably, the light source reflections 124 (see figure 5) further comprise light reflections 140 (see figure 5) for canvas 138 (see figure 5) parallel to the cross-sectional surface 114 (see figure 5) of the edge prepared 92a (see figure 5), such as tarpaulins at 0o (zero degree).
[0084] The orientation of canvas 98 (see figure 5) can cause a differential scanning clarity 132 (see figure 5) of the plurality of canvas 94 (see figure 5) on the prepared edge 92a (see figure 5) when the prepared edge 92a (see figure 5) of the composite laminate 28 (see figure 5) is explored. The clearness of differential scanning 132 (see figure 5) of the plurality of tarps 94 may result in the scanned images showing dark tarpaulins, light tarpaulins, lighter tarpaulins, or another variation of light or dark tarpaulins. Differential scanning clarity 132 (see figure 5) can be used to check the orientation of canvas 98 (see figure 5). As shown in figure 5, system 90 further provides a canvas orientation check 147 of composite laminate 28 using reference matrix 148.
[0085] Figure 6A is a schematic illustration of a side view of a system modality 90 for determining and verifying the canvas orientation 98 (see figure 5) of composite laminate 28, where composite laminate 28 is being subjected to a first scan 104. As shown in figure 6A, system 90 comprises composite laminate 28 having a prepared edge 92a which is to be scanned and analyzed with scanning set 100. Composite laminate 28 (see figure 6A) is preferably in the form sample portion or coupon. As shown in figure 6A, the composite laminate 28 is positioned on the scanning device 102 of the scanning set 100. Scanning device 102 (see figure 6A) is preferably a flat color scanning device or other suitable scanning device , as discussed above. The processing device 150 (see figure 6A) is connected to the scanning device 102 (see figure 6A) via connection element 152 (see figure 6A).
[0086] As further shown in figure 6A, the scanning device 102 includes a housing 164 that houses the controller 160, the power supply 162, such as in the form of a motor, and a mobile support 176. The inclined light source off-axis 106 (see figure 6A), as in the form of a light source at 45 ° (forty-five degrees) 106a (see figure 6A), it is shown mounted on the mobile support 176, together with a image capture assembly 172. Mobile support 176 (see figure 6A) preferably moves up and down the length of scanning device 102 at a constant rate and is preferably driven by the engine.
[0087] The image capture set 172 (see figure 6A) can include one or more image sensors 174 (see figure 6A) and / or other various components (not shown), such as an optical set of reflective mirrors and a lens unit, as known in the art. The one or more image sensors 174 (see figure 6A) may comprise a charge-coupled device (CCD) arrangement, a complementary metal oxide semiconductor (CMOS) type image sensor, a contact image sensor (CIS), or other suitable image sensor. The one or more image sensors 174 (see figure 6A) preferably contain light-sensitive diodes that convert analog light waves to digital signals and that allow the conversion of reflections from light source 124 (see figure 6A) for information of digital pixel, which is transferred as the first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) to the processing device 150 (see figures 6A, 6B).
[0088] The scanning device 102 (see figure 6A) additionally comprises a glass plate 166 (see figure 6A). As shown in figure 6A, the prepared edge 92a of composite laminate 28, in the form of a sample to be analyzed and explored, is placed on an upper surface 168 of the glass plate 166. A lid (not shown) of the scanning device 102 (see figure 6A) can be closed on composite laminate 28 or can be left open while scanning composite laminate 28. Figure 6A shows composite laminate 28 with sides 178 and positioned in a forward orientation 202 in the scanning direction 120. The sides 178 (see figure 6A) of the fibers in the plurality of tarpaulins 94 (see figure 5) reflect more light than the light ends.
[0089] As shown in figure 6A, during the first scan 104, the tilted light source off-axis 106 directs light 108 at a first angle 110, such as in the form of a 45 ° angle (forty-five degrees) , for the first area 112 on the prepared edge 92a. Light 108 (see figure 6A) illuminating the first area 112 (see figure 6A) reflects back as a reflection of light source 124 (see figure 6A). Image sensors 174 (see figure 6A) detect the reflection of light source 124 (see figure 6A) and convert the reflection of light source 124 (see figure 6A) to digital pixel information, which is transferred as the first scanned image 116 (see figure 5) to the processing device 150 (see figure 6A), such as in computer form 150a (see figure 6A). The first scanned image 116 (see figure 5) is preferably processed with process software 154 (see figure 6A) and can be stored on storage media 156 (see figure 6A) and / or printed with a printing mechanism 158 (see figure 6A).
[0090] As shown in figure 6A, composite laminate 28 includes plies 134, such as plies at 90 ° (ninety degrees), normal or perpendicular to the cross-sectional surface 114 of the prepared edge 92a, and also normal or perpendicular to the surface 168 of the glass plate 166. As shown in figure 6A, the canvas 134, such as the 90 ° (ninety degree) canvas, exhibited dark reflections 136 when explored in the first exploration 104.
[0091] As shown in figure 6A, composite laminate 28 further includes plies 138, such as 0o (zero degree) plies, parallel to the cross-sectional surface 114 of the prepared edge 92a, and also parallel to the surface 168 of the glass plate 166. As shown in figure 6A, tarpaulins 138, such as tarpaulins at 0o (zero degree), exhibited clear reflections 140 when explored in the first exploration 104.
[0092] As shown in figure 6A, composite laminate 28 further includes tarpaulins 142, such as tarpaulins at -45 ° (minus forty-five degrees) 142b and tarpaulins at 45 ° (forty-five degrees) 142a, off-axis geometric with respect to the cross-sectional surface 114 of the prepared edge 92a, and also outside the geometric axis to the surface 168 of the glass plate 166. As shown in figure 6A, the canvas 142b, such as the canvas at -45 ° (minus forty-five degrees), exhibited dark transition reflections 144b, when explored in the first exploration 104. As shown in figure 6A, canvas 142a, such as 45 ° canvas (forty-five degrees), exhibited transition reflections at clearer 144a, when explored in the first exploration 104.
[0093] Figure 6B is a schematic illustration of a side view of system 90 to determine and verify the canvas orientation 98 (see figure 5) of composite laminate 28 in figure 6A, where composite laminate 28 is being subjected to a second scan 126. As shown in figure 6B, the system 90 includes the composite laminate 28 positioned on the scanning device 102 of the scanning set 100 of figure 6A, and the processing device 150 connected to the scanning device 102 via a scanning element. connection 152. System components 90 in figure 6B are identical to figure 6A, except that the orientation 117 (see figure 5) of the tilted light source off-axis 106 (see figure 6B) is now rotated by a rotation 180 degrees 125a (see figure 5) in relation to the prepared edge 92a (see figure 6B) of composite laminate 28 (see figure 6B). Before the second scan 126 is carried out, the orientation 117 (see figure 5) of the tilted light source off-axis 106 (see figure 5) is rotated by a rotation 125 (see figure 5), just like a rotation 180 degrees 125a (see figure 5), in relation to the prepared edge 92a (see figure 6B) of composite laminate 28 (see figure 6B).
[0094] As shown in figure 6B, during the second scan 126, the tilted light source off-axis 106, like the 45 ° (forty-five degree) light source 106a, directs light 108 at a second angle 130, such as at a -45 ° (minus forty-five degrees) angle, for the first area 112 on the prepared edge 92a. Light 108 (see figure 6B) illuminating the first area 112 (see figure 6B) reflects back as a reflection of light source 124 (see figure 6B). The image sensors 174 (see figure 6B) detect the reflection of light source 124 (see figure 6B) and convert the reflection of light source 124 (see figure 6B) to digital pixel information, which is transferred as the second scanned image 128 (see figure 5) for the processing device 150 (see figure 6B), as in the form of computer 150a (see figure 6B). The second scanned image 128 (see figure 5) is preferably processed with process software 154 (see figure 6B) and can be stored on storage media 156 (see figure 6B) and / or printed with the printing mechanism 158 (see figure 6B).
[0095] As shown in figure 6B, composite laminate 28 includes plies 134, such as plies at 90 ° (ninety degrees), normal or perpendicular to the cross-sectional surface 114 of the prepared edge 92a, and normal or perpendicular to the surface 168 of the glass plate 166. As shown in figure 6B, the canvas 134, such as the 90 ° (ninety degree) canvas, exhibited dark reflections 136 when explored with the second exploration 126.
[0096] As shown in figure 6B, composite laminate 28 further includes plies 138, such as 0o (zero degree) plies, parallel to the cross-sectional surface 114 of the prepared edge 92a, and parallel to the surface 168 of the glass plate 166. As shown in figure 6B, the canvas 138, such as the 0 ° (zero degree) canvas, showed clear reflections 140, when explored with the second exploration 126.
[0097] As shown in figure 6B, composite laminate 28 further includes tarpaulins 142, such as tarpaulins at -45 ° (minus forty-five degrees) 142b and tarpaulins at 45 ° (forty-five degrees) 142a, off-axis geometric with respect to the cross-sectional surface 114 of the prepared edge 92a, and outside the geometric axis with respect to the surface 168 of the glass plate 166. As shown in figure 6B, the canvas 142b, such as the canvas at -45 ° ( minus forty-five degrees), exhibited the lightest transition reflections 144a, when explored with the second exploration 126. As shown in figure 6B, the canvas 142a, such as the 45 ° canvas (forty-five degree), exhibited dark transition reflections 144b, when explored with the second exploration 126.
[0098] In an analysis of the first scanned images 116 (see figure 5) from the first scan 104, as shown in figure 6A, and in an analysis of the second scanned images 128 (see figure 5) from the second scan 126, as shown in figure 6B, it was found, both in the first exploration 104 and in the second exploration 126, that both 0 ° (zero degree) and 90 ° (ninety degree) canvas perpendicular to surface 168 (see figure 6A ) of the glass plate 166 (see figure 6A) always appeared dark and exhibited dark reflections 136 when explored. It was also found that, both in the first exploration 104 and in the second exploration 126, both the 0 ° (zero degree) and the 90 ° (ninety degree) sheets parallel to the surface 168 (see figure 6A) of the glass plate 166 (see figure 6A) always appeared clear with streaks and exhibited clear reflections 140 when explored.
[0099] It was also verified, both in the first exploration 104 and in the second exploration 126, that the clarity of the tarpaulins at +/- 45 ° (plus / minus forty-five degrees) depended on whether the tarpaulin was oriented parallel or perpendicular to the light 108 (see figures 6A-6B) from the tilted light source off-axis 106 (see figures 6A-6B). Which tarpaulins exhibited light or dark reflections depended on whether the composite laminate sample 28 was cut in a cross section 196 (see figure 8) or a longitudinal section 200 (see figure 8), depended on which side of the aircraft 10 ( see figure 1) the composite laminate sample 28 was obtained, such as the left side 192 (see figure 8) or the right side 194 (see figure 8), and depended on the orientation of the composite laminate sample 28, as such as orientation in a crown direction 198 (see figure 8) or orientation in a forward direction 202 (see figures 6A-6B, 8).
[00100] Figure 7 is a schematic illustration of images scanned side by side 180 of first scanned images 116, such as in the form of first scanned images of cross section 116a, taken by first scanned 104, and second scanned images 128, such as in the form of second scanned cross-sectional images 128a, taken by second scan 126. Both the first scan 104 and the second scan 126 were taken from the prepared edge 92a (see figures 6A-6B) of composite laminate 28 (see figures 6A -6B), obtained using one of the modalities of method 66 (see figure 4A), method 80 (see figure 4B), and system 90 (see figure 5), to determine and verify the orientation of canvas 98 ( see figure 5) of composite laminate 28 (see figure 5). As shown in figure 7, the images scanned side by side 180 comprise a first half 182 consisting of the first scanned images 116, and a second half 184 consisting of the second scanned images 128. As shown further in figure 7, the first scanned images 116 and the second scanned images 128 are divided by a dotted line 186.
[00101] In obtaining the first scanned images 116 and the second scanned images 128 shown in figure 7, sample coupons from composite laminate 28 (see figure 5) were cut with a band saw in a longitudinal cut 200 (see figure 8) at a canvas orientation angle of 0o (zero degree) 190 (see figure 5). An edge 92 (see figure 5) of the cut laminate composite 28 (see figure 5) was prepared by a preparation treatment 93 (see figure 5) consisting of polishing edge 92 for about 10 (ten) minutes. A first scan 104 and a second scan 126 for each canvas orientation shown in figure 7, that is, 0o, 90 °, 45 °, -45 ° and PW, were made with scanning device 102 (see figures 6A -6B), and each exploration was carried out in about 5 (five) minutes. The first explorations 104 and the second explorations 126 were made with cross-sectional surfaces 114 (see figure 5) of the composite laminate samples 28, parallel to the scanning direction 120 (see figures 5, 6A).
[00102] As shown in figure 7, the first scanned images 116 and the second scanned images 128 included scanned images of canvas 138, such as 0o (zero degree) canvas, parallel to the cross-sectional surface 114 (see figures 6A -6B) of the prepared edge 92a (see figure 5). As shown in Figure 7, both the first exploration 104 of the 0 ° (zero degree) tarpaulins and the second exploration 126 of the 0 ° (zero degree) tarpaulins exhibited clear reflections 140.
[00103] As shown in figure 7, the first scanned images 116 and the second scanned images 128 included scanned images of canvas 134, such as the 90 ° (ninety degree) canvas, at the cross-sectional surface 114 (see figures 6A-6B) of the prepared edge 92a (see figure 5). As shown in figure 7, both the first exploration 104 of the 90 ° (ninety degrees) tarpaulins and the second exploration 126 of the 90 ° (ninety degrees) tarpaulins exhibited dark reflections 140.
[00104] As shown in figure 7, the first scanned images 116 and the second scanned images 128 included scanned images of 45 ° (forty-five degrees) canvas 142a off the geometry axis with respect to the cross-sectional surface 114 (see figures 6A-6B) of the prepared edge 92a (see figure 5). As shown in Figure 7, the first scan 104 of the canvases at 45 ° (forty-five degrees) 142a exhibited the lightest reflections 144a, and the second scan 126 of the canvases at 45 ° (forty-five degrees) exhibited dark reflections 144b .
[00105] As shown in figure 7, the first scanned images 116 and the second scanned images 128 included scanned images of tarpaulins at -45 ° (minus 45 degrees) 142b outside the geometric axis with respect to the cross-sectional surface 114 (see figures 6A-6B) of the prepared edge 92a (see figure 5). As shown in Figure 7, the first scan 104 of the tarpaulins at -45 ° (minus 45 degrees) 142b exhibited dark reflections 144b, and the second scan 126 of the tarps at -45 ° (minus 45 degrees) exhibited reflections the clearest 144a.
[00106] Figure 7 shows the first scanned images 116 and the second scanned images 128 included PW 187 tarpaulins. PW 187 tarpaulins comprise a type of woven cloth consisting of a mixture of tarpaulins 134, such as 90 ° tarpaulins. (ninety degrees), normal to the cross-sectional surface 114 (see figures 6A-6B) of the prepared edge 92a (see figure 5), and canvas 138, such as the 0o (zero degree) canvas, parallel to the surface of cross section 114 (see figures 6A-6B) of the prepared edge 92a (see figure 5). As shown in figure 7, both the first scan 104 of the PW 187 tarps and the second scan 126 of the PW 187 tarps exhibited speckled dark / light mixed reflections 188.
[00107] Figure 8 is an illustration of a modality of the reference matrix 148 that was used as the canvas orientation check 147 (see figure 5) for the canvas guidelines 98 (see figure 5) of the plurality of canvas 94 (see figure 5) shown in figure 7. Reference matrix 148, as shown in figure 8, was created using a known composite laminate or known composite laminates, such as composite films, with known canvas orientations , to verify the canvas orientation 98 (see figure 5), determined from the first explorations 104 and the second explorations 126, shown in figure 7. The reference matrix 148 shown in figure 8 is merely an example of a matrix of reference 148 that can be used with one of the modalities of method 66 (see figure 4A), method 80 (see figure 4B), and system 90 (see figure 5), to determine and check the canvas orientation 98 (see figure 5) of composite laminate 28 (see figure 5). The reference matrix 148 (see figure 8) can be modified depending on the orientation of the reference canvas 99 (see figure 8) and the orientation angle of canvas 190 (see figure 8) of the plurality of reference canvas 95 ( see figure 5), which constitute the reference composite laminate 29 (see figure 8) used as a reference to verify a composite laminate 28 (see figure 5).
[00108] As shown in figure 8, the reference matrix 148 shows the reference canvas orientation 99 having the canvas orientation angles 190 of 45 ° (forty-five degrees) and -45 ° (minus forty-five degrees) . As further shown in figure 8, the reference matrix 148 shows that samples of the reference composite laminate 29 (see figure 5) were obtained from the left side 192 and the right side 194 of the aircraft 10 (see figure 1). As shown in figure 8, the reference matrix 148 shows that the composite reference laminate samples 29 were cut in a cross section 196 and a longitudinal cut 200 and were oriented in a crown direction 198, or from top 204 down 206, and were oriented in a forward direction 202, or from top 204 to bottom 206.
[00109] As shown in figure 8, the light source reflections 124 (see figure 5) of the tarpaulins at 45 ° (forty-five degrees) exhibited both dark transition reflections 144b and light transition reflections 144a on the left side 192 and on the right side 194. As shown in figure 8, the light source reflections 124 (see figure 5) of the tarpaulins at -45 ° (minus 45 degrees) exhibited both clear transition reflections 144a and transition reflections dark 144b on the left side 192 and on the right side 194. The reference matrix 148 shows the differential scanning clarity 132 (see figure 5) of each tarpaulin at +/- 45 ° (plus / minus forty-five degrees) with light / dark transition reflections 144a, 144b. Differential scanning clarity 132 can also be used to check the orientation of canvas 98 (see figure 5)
[00110] The described modalities of method 66 (see figure 4A), method 80 (see figure 4B), and system 90 (see figure 5) provide numerous advantages over known methods and systems, including the provision of a quick process to determine and verify the orientation of canvas 98 (see figure 5) of composite laminates 28 (see figure 5) that are cured to maintain uniformity and consistency of composite laminates 28 (see figure 5) and to meet the design and / or quality requirements for composite laminates 28 (see figure 5). In addition, the described modalities of method 66 (see figure 4A), method 80 (see figure 4B), and system 90 (see figure 5) provide a process and system that can substantially reduce time, labor, equipment, and costs for determining and verifying the canvas orientation of composite laminates 28 (see figure 5), compared to known methods and systems for determining and verifying the canvas orientation. Known methods and systems can be very time-consuming and can take several days to complete, can be labor-intensive and tedious, and can require a large number of equipment, all of which, in turn, can result in high uptime. manufacturing and high expense.
[00111] In addition, the modalities described in method 66 (see figure 4A), method 80 (see figure 4B), and system 90 (see figure 5) involve carrying out a first exploration 104 and a second scanning 126 of only the prepared edge 92a of composite material 28 (see figure 5) to determine the orientation of canvas 98 (see figure 5) of the plurality of plies 94 (see figure 5) that make up composite laminate 28 (see figure 5). The prepared edge 92a (see figure 5) is preferably scanned from two different angles, including a first angle 110 (see figures 5, 6A) and a second angle 130 (see figures 5, 6B). Unlike the known methods and systems for determining and verifying the canvas orientation, the modalities described in method 66 (see figure 4A), method 80 (see figure 4B), and system 90 (see figure 5) do not require extensive polishing of edge 92 (see figure 5) of composite laminate 28 (see figure 5) prior to exploration, do not require the assembly of composite laminate 28 (see figure 5) to be polished, do not require a plurality of images microscopes are taken and edited together to allow sufficient visibility under a microscope, and do not require intensive analysis in terms of the work of each canvas to discern the difference between canvas at 0 ° (zero degree) and canvas at +/- 45 ° (plus / minus) forty-five degrees). In addition, unlike the known methods and systems for determining and verifying the orientation of the canvas, the described modalities of method 66 (see figure 4A), method 80 (see figure 4B), and system 90 (see figure 5) do not require a second cut to be made on the composite laminate sample coupon 28 (see figure 5), and do not require a repeated process and analysis of the second cut to sufficiently distinguish between +/- 45 ° plies (plus / minus forty and five degrees) to meet the qualification requirements.
[00112] In addition, the methods described in method 66 (see figure 4A), method 80 (see figure 4B), and system 90 (see figure 5) use a 45 ° light source (forty five degrees) 106a (see figure 5) from an scanning device 102 (see figure 5) and form images of composite laminate 28 (see figure 5) oriented transversely to a displacement path of the light source 118 ( see figure 5), twice, with a 180 degree rotation 125a (see figure 5) between scanning the first scanned image 116 and scanning the second scanned image 128. The first scanned image 116 (see figure 5) and the second scanned image 128 (see figure 5) preferably provides opposite light / dark transition reflections 144a, 144b (see figure 5) on the canvas +/- 45 ° (plus / minus forty-five degrees) from the surface cross-section 114 (see figure 5) of the prepared edge 92a (see figure 5), while maintaining dark reflections 136 for the canvas 134 (see figure 5) normal to the cross-sectional surface 114 (see figure 5) of the prepared edge 92a (see figure 5), and clear reflections 140 (see figure 5) for canvas 138 (see figure 5 ) parallel to the cross-sectional surface 114 (see figure 5) of the prepared edge 92a (see figure 5). Using process software 154 (see figure 5), a complete canvas orientation 98 (see figure 5) of composite laminate 28 (see figure 5) can be determined.
[00113] Also, the described methods of method 66 (see figure 4A), method 80 (see figure 4B) and system 90 (see figure 5) provide an efficient process, in which the number of polishing steps and preparation to prepare an edge 92 (see figure 5) before scanning can be reduced, and a lower polishing finish can be obtained from a typical 240 grit sandpaper with a 0.05 pm (micron) finish ) to a 600 grit sandpaper with a 0.06 pm (micron) finish, as the shape of the fiber in the cross section is no longer being questioned. Instead, light source reflections 124 (see figure 5) from two light source explorations or passes, tilted off-axis, angled in opposition, can be used. An scanning device 102 (see figure 5) with a light source at 45 ° (forty-five degrees) 106a (see figure 5) can be used to image the entire thickness of composite laminate 28 (see figure 5 ). Alternatively, if the scanning device 102 (see figure 5) has two light sources tilted off the axis 106 (see figure 5), a layer of tape can be placed over a light source tilted off the axis 106 (see figure 5), and scanning device 102 (see figure 5) can be used to image the entire thickness of composite laminate 28 (see figure 5). Images can be formed of multiple composite laminates 28 (see figure 5) simultaneously, and can be constrained only by the size of the scanning device 102 (see figure 5).
[00114] Thus, the described methods of method 66 (see figure 4A), method 80 (see figure 4B) and system 90 (see figure 5) can be polished much more quickly than in the polishing procedures required with the known methods and systems, may require only a single cut of the composite laminate sample 28, instead of two, may not require assembly to be polished, may not require composite formation of images, and may significantly reduce the difficulty of visual methods for determining the canvas orientation.
[00115] Many modifications and other modalities of the description will come to mind for a person specialized in the technique to which this description belongs, having the benefit of the teachings presented in the preceding descriptions and in the associated drawings. The modalities described here are intended to be illustrative and not intended to be limiting or exhaustive. Although specific terms are used here, they are used only in a generic and descriptive sense and not for purposes of limitation.

权利要求:
Claims (10)
[0001]
1. Method (66) to determine and verify the canvas orientation (98) of a composite laminate (28), method (66) characterized by the fact that it comprises the steps of: performing a first scan (104) of an edge prepared (92a) of the composite laminate (28) using an inclined off-axis light source (106) directing light (108) at a first acute angle (110) to a first area (112) on the prepared edge (92a) to produce a first scanned image (116); rotate an orientation (117) of the tilted light source off-axis 106 with respect to the prepared edge (92a), so that the tilted light source off-axis (106) directs light at a second acute angle (130) symmetrically opposite the first acute angle (110); perform a second scan (126) of the prepared edge (92a) using the inclined light source outside the geometric axis (106) directing light (108) at the second acute angle (130), symmetrically opposite, to the first area (112) on the prepared edge (92a) to produce a second scanned image (128); compare the first scanned image (116) and the second scanned image (128) to determine a canvas orientation (98) of each canvas (94) of the composite laminate (28), where the canvas orientation (98) is determined with based on reflections from the light source (124) of the tilted light source off-axis (106); and, checking the canvas orientation (98) of the composite laminate (28) against a reference canvas orientation (99) of a reference composite laminate (29).
[0002]
Method (66) according to claim 1, characterized by the fact that it further comprises, before the step of carrying out the first exploration (104) of the prepared edge (92a), the step of preparing an edge (92) of the laminate composite (28) to obtain the prepared edge (92a), wherein preparing the edge (92) comprises one or more of the smoothing, polishing, abrasion, finishing, and edge cleaning of the composite laminate (28).
[0003]
3. Method (66) according to claims 1 to 2, characterized by the fact that the steps of performing the first scan (104) of the prepared edge (92a) and performing the second scan (126) of the prepared edge (92a) comprise use an scanning device (102) having a light source (106a) 45 ° (forty-five degrees).
[0004]
4. Method (66) according to claims 1 to 3, characterized in that the step of rotating the orientation (117) of the light source inclined off the geometric axis (106) in relation to the prepared edge (92a) comprises rotating the orientation (117) of the light source tilted off-axis (106) by 180 degrees with respect to the prepared edge (92a).
[0005]
5. Method (66) according to claim 1, characterized in that the step of comparing the first scanned image (116) and the second scanned image (128) to determine the canvas orientation (98) comprises using a comparison (146b) with process software (154) to compare the reflections of the light source (124) of the first scanned image (116) and the second scanned image (128).
[0006]
6. Method (66) according to claim 1, characterized in that the step of comparing the first scanned image (116) and the second scanned image (128) to determine the canvas orientation (98) comprises determining the orientation canvas (98) based on light source reflections (124) comprising light / dark transition reflections (144a, 144b) at +/- 45 ° (plus / minus forty-five) degrees to a cross-sectional surface ( 134) of the prepared edge (92a), dark reflections (136) for canvas normal to the surface of cross section (134) of the prepared edge (92a), and light reflections (140) for canvas parallel to the surface of cross section (138) of prepared edge (92a).
[0007]
Method (66) according to claims 1 to 6, characterized by the fact that it further comprises, before the verification step, the step of preparing a reference matrix (148) comprising the orientation of reference canvas (99) of a plurality of reference plies (95) of the composite reference laminate (29).
[0008]
8. System (90) for determining and verifying the canvas orientation (98) of a composite laminate (28), the system (90) characterized by the fact that it comprises: a composite laminate (28) that is cured and comprises at least one prepared edge (92a) and a plurality of tarpaulins (94), each tarpaulin (94) having a tarpaulin orientation (98); and an scanning set (100) comprising: an scanning device (102) having at least one off-axis tilted light source (106) configured to direct light (108) at a first acute angle 110) to a first area (112) on the prepared edge (92a) of the composite laminate (28) to illuminate and capture a first scanned image (116), and further configured to reorient the direction of the off-axis light source (106) to a second angle acute (130) symmetrically opposite the first acute angle (110), to direct light (108) at a second acute angle (130), symmetrically opposite, to the first area (112) on the prepared edge (92a) to illuminate and capture a second scanned image (128); a processing device (150) coupled to the scanning device (102), the processing device (150) configured to receive and process the first scanned image (116) and the second scanned image (128) from the scanning device ( 102); and a reference matrix (148) comprising a reference canvas orientation (99) of a composite reference laminate (29), wherein the system (90) provides a determination of canvas orientation (146) of each canvas (94) ) of the composite laminate (28) based on reflections from the light source (124) of at least one light source tilted out of the geometric axis (106) and a comparison of the first scanned image (116) and the second scanned image (128 ), and yet the system (90) provides a canvas orientation check (146) of the composite laminate (28) using the reference matrix (148).
[0009]
System (90) according to claim 8, characterized in that the at least one light source inclined off the geometric axis (106) comprises a light source (106a) oriented at 45 ° (forty-five degrees) ) in relation to the prepared edge (92a).
[0010]
10. System (90) according to claim 9, characterized by the fact that the light source reflections (124) comprise light / dark transition reflections (144a, 144b) on +/- canvases (142a, 142b) 45 ° (plus / minus forty-five degrees) (142a, 142b) to a cross-sectional surface (114) from the prepared edge (92a), dark reflections (136) to canvas noials to the cross-sectional surface (134) of the prepared edge (92a), and clear reflections (140) for canvas parallel to the cross-sectional surface (138) of the prepared edge (92a).

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同族专利:

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公开号 | 公开日

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EP2896496A1|2015-07-22|

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CA2872026A1|2015-07-17|

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US20160102973A1|2016-04-14|

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CN104960317A|2015-10-07|

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EP2896496B1|2020-10-21|

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CN104960317B|2018-12-18|

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US9897440B2|2018-02-20|

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BR102015000999A2|2015-09-22|

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CA2872026C|2017-09-05|

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法律状态:
2015-09-22| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|

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2018-10-30| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|

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2020-07-07| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|

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2020-09-15| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 15/01/2015, OBSERVADAS AS CONDICOES LEGAIS. |

优先权:

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申请号 | 申请日 | 专利标题

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US14/158762|2014-01-17|

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US14/158,762|US9897440B2|2014-01-17|2014-01-17|Method and system for determining and verifying ply orientation of a composite laminate|

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