Process for producing a fiber-plastic composite comparison body and test method

专利摘要:
The invention relates to a method for producing a fiber-plastic composite (FKV) comparative body (26) for simulating a delamination (24) for the non-destructive testing of FKV components, in particular aircraft components, with the steps: i. Manufacture of a first insert part (3) by a. Arranging a first FKV layer (1); b. Forming a recess (4) in the first FKV layer (1); c. Pre-hardening the first FKV layer (1) in order to obtain the first insert part (3); ii. Manufacture of a second insert part (9) by a. Arranging a second FKV layer (25); b. Pre-hardening the second FKV layer (25) in order to obtain the second insert part (9); iii. Providing at least a first (10) and at least a second FKV layer (12) with a first (11) and a second recess (13); iv. Inserting the first (3) or second insert (9) into the respective recess (11, 13) of the corresponding FKV layer (10, 12); v. Hardening of the arrangement, a delamination being simulated on the recess (4) of the first insert part (10).
公开号:AT521355A4
申请号:T50764/2018
申请日:2018-09-10
公开日:2020-01-15
发明作者:
申请人:Facc Ag；
IPC主号:

专利说明:

The invention relates to a method for producing a fiber-plastic composite (FKV) comparative body for simulating delamination for the non-destructive testing of FKV components, in particular aircraft components.
The invention further relates to a method for the non-destructive testing of a FKV component, in particular an aircraft component.
In the manufacture of safety-critical fiber-plastic composite (FKV) components, such as aircraft components, the subsequent inspection and detection of component errors is of particular importance. For this purpose, non-destructive testing (NDT) is usually used in order to be able to immediately recognize defective components on the one hand and fault-free ones on the other
Do not damage components yourself through the test procedure. In order to be able to draw conclusions about potential sources of error in production in the test methods, detected component errors are assigned to a type of error or an error class. For comparison and calibration purposes, comparative bodies with deliberately introduced artificial component defects are produced and measured using an NDT method.
In order to ensure the exact assignment of a component defect to a defect class, the artificial component defects in the reference blocks that serve as a reference must reproduce the production defects of the test specimens as precisely as possible.
Most of the component defects are difficult or impossible to reproduce without the help of foreign bodies and, up to now, artificial component defects, depending on the type of defect, differ more or less in terms of their nature from the defects of the test objects. In particular a so-called delamination,
i.e. a local, two-dimensional separation of two FKV locations in one
Part of a FKV component with air trapped, so far has not been able to be reproduced satisfactorily without introducing foreign bodies. In addition to delamination, there are other component defects, in particular the layer porosity and the
Count volume porosity. Concerning the layer porosity, there is a concentrated concentration of microscopic and macroscopic
Gas or air inclusions take place in the matrix or the connecting means of the FKV material between two FKV layers of a component. Accordingly, there is a 2D component defect. In the case of volume porosity, gas or air inclusions accumulate in the matrix or the connecting means of the FKV material in several FKV layers of a component, in particular essentially over the entire cross section of the FKV laminate. So it is a 3D component defect. Since delamination, i.e. the two-dimensional separation of FKV locations, can have serious consequences for aircraft components, the detection of delamination and thus the generation of reference blocks with a realistic simulation of the delamination is of great importance.
Different methods for emulating component defects are known from the prior art. EP 3 193 164 A1, for example, describes a method in which component defects can be introduced into FRP parts with the aid of an expansion body. To do this, the expansion body is between several
Layers of FKV material, resin added and then heated. Due to the high expansion coefficient of the expansion body, it shrinks more during cooling than the FKV material surrounding it, thereby creating a large permanent cavity. The expansion body then remains in the component as a foreign body.
With the CN104407060, porosity of the material is simulated with the help of glass beads that are introduced into the material during the production process. However, these also remain in the material.
In addition, a method for producing porosity in composite materials is known from US 2014/0346405 A1. For this purpose, the composite materials are exposed to different curing processes in order to produce different degrees of porosity due to escaping gases.
A disadvantage of the prior art is that delamination, that is to say a flat separation of individual FKV layers within a / 25
FKV component, not satisfactory or can not be reproduced without foreign bodies. Among other things, the foreign bodies falsify the measurement result.
The invention is therefore based on the object of alleviating or eliminating at least individual disadvantages of the prior art. The invention therefore has the particular aim of creating a method which enables realistic simulation of a delamination at defined points in a FKV comparison body.
The task is solved by a method with at least the following steps:
i. Manufacture of a first insert for the FKV comparison body
a. Arranging a first FKV location;
b. Forming a recess in the first FKV location;
c. Pre-harden the first FKV layer to the first
Obtain insert for the FKV reference block;
ii. Manufacture of a second insert for the FKV comparison body
a. Arranging a second FKV location;
b. Pre-harden the second FKV layer to obtain the second insert for the FKV reference block;
iii. Providing at least one first FKV layer with a first recess and at least one second FKV layer with a second recess;
iv. Insert the first insert into the first
Recess of the first FKV layer and insertion of the second insert part into the second recess of the second FKV layer;
v. Hardening of the arrangement of the first FKV layer with the first insert part and the second FKV layer with the second insert part, delamination being simulated on the recess in the first FKV layer of the first insert part.
Advantageously, the method according to the invention enables the targeted introduction of an (artificial) delamination into a comparison body made of FKV material. Since the delamination without the introduction of a foreign body, i.e. a non-FKV material that does not exist on the component to be compared
Substance that can be generated, the FKV comparison body is particularly suitable for realistically simulating delamination of the FKV components to be tested, especially for the aviation industry. The simulated delamination can be used, among other things, for calibration purposes by subjecting the FKV comparison body to an NDT measurement method, for example a thermography method. Due to the realistic nature of the simulated delamination, the measurement results obtained from the reference body are particularly suitable as comparison or reference values for the NDT test of FKV components. Since the creation of the FKV comparative body relies on the introduction of foreign bodies, i.e.
parts that do not consist of the FKV material and that do not exist on the component to be compared can be omitted, measurement curves of the FKV comparison body can be recorded, which correspond with great accuracy to those of components that have a natural, i.e. have delamination that has arisen during series production. As mentioned at the beginning, delamination is a local, two-dimensional separation of two FKV layers in one
Part of a FKV component with air trapped. In contrast, in the case of layer porosity, there is only a partial separation of the FKV layers. In the case of volume porosity, the separation takes place over several FKV layers with air enclosed.
For the purposes of the disclosure, an FKV layer also represents a FKV layer. The individual FKV layers are preferably in the FKV comparison body - as with the FKV components to be tested - by loose or woven fabrics and with resin or another connecting means soaked fibers formed. The connecting means can be used to connect the fibers within an FKV layer, to connect the FKV layers to one another and to connect the FKV layers to the pre-hardened insert parts. CFRP (carbon fiber reinforced plastic), GRP (glass fiber reinforced plastic) or aramid fiber5 / 25 can be used as the FKV material for all FKV layers
Composite material, in particular CFRP, GFRP or aramid fiber composite material processed into prepreg, can be provided.
In the method according to the invention, the delamination is generated by inserting the (pre-hardened) insert parts into the corresponding recess in the FKV layers and curing the adjacent arrangement of the first and second FKV layers, preferably under pressure. The first and the second recess are expediently cut into the first or second FKV layer with a knife or another cutting tool and preferably have essentially the shape or
Contour of the outer edge of the first or second insert part. The connecting means for connecting the insert parts, such as resin or another connecting means, is preferably already contained in the FKV layers. By the
Connecting the first and second FKV layers and pressing the two FKV layers together with the insert parts, in particular during curing, the connection means is sucked up to the recess by the capillary effect into a narrow joint gap lying between the first and second insert part and thereby connects the two insert parts in an edge area outside the recess with each other and with the FKV layers. Accordingly, the connecting means for connecting the insert parts arrives from the FKV layer between the pre-hardened insert parts.
At the border to the depression or the enclosed cavity, the suction effect of the capillary effect finally comes about due to the greater distance between the two insert parts
Failure and the connecting means is essentially not drawn into the recess. The depression is therefore essentially free of connecting means and the first and second FKV layers do not adhere to one another in the area of the depression, so that the delamination which is simulated can occur as a result of curing. In the areas outside the recess, the sucked-in connecting means creates a positive and non-positive connection between the insert parts or the first or second
FRP layer. In terms of material properties, an FKV layer essentially corresponds to an FKV layer.
/ 25
After inserting the insert parts into the respective recesses and connecting the FKV layers, the opening of the recess of the first insert part faces the second insert part. In addition, it is advantageous if the FKV layers are connected in such a way that the cutouts in the FKV layers are essentially congruent with one another. For this purpose, the cutouts and the insert parts are preferably in the
Essentially the same size. In addition, it is important that the first insert part is inserted into the first recess in such a way that a cavity, the so-called air pocket, defined by the recess of the first insert part and the second insert part is formed.
In the method according to the invention, the first and second insert parts are inserted into the respective recesses in a pre-hardened state. In this context, pre-hardened means that the two parts are hardened to such an extent that they form their shape in the further process steps
Maintained by itself. For pre-hardening, the first hardening steps of a hardening process suitable for the FKV material used can be used, i.e. the curing process can be ended as soon as the parts have hardened to such an extent that they essentially retain their shape automatically for the further process steps. After the first
If the FKV layer is connected to the second FKV layer and the insert parts have been inserted into the corresponding recesses, the arrangement of the first and second FKV layer is completely hardened, which creates the simulated delamination. In this context, hardening means that the first and second FKV layer together with insert parts and connecting means are completely hardened. The first and the second cutout preferably have essentially the shape or contour of the outer edge of the first and of the second insert part. The insert parts thus have essentially the same dimensions as the respective cutouts.
In order to produce a particularly realistic FKV comparison body of any thickness, at least one FKV basis on one side of the arrangement from the first and second FKV layer and / or at least one FKV final layer on the other side / 25 of the arrangement from the first and second FKV layer can be provided. By adding any number of FKV basics and / or the FKV end layers, a FKV comparison body of any thickness can be created. The number of FKV final layers and FKV basics can differ from each other. With the method according to the invention, the
The cavity or the artificial delamination can therefore be arranged at any desired depth within the FKV comparison body. Depending on the application, several delaminations (air pockets) can also be provided. The other air pockets can be described in the same way as above, i.e. by means of first and second insert parts.
In order to favor the capillary effect and to produce a particularly realistic delamination, it is advantageous if the first insert part has a circumferential and preferably essentially flat edge surface around the depression. In this context, encircling means that the depression is surrounded on all sides by the edge surface. This allows connecting means to be drawn evenly from all sides into the joint gap between the two insert parts. The edge surface can expediently be formed symmetrically around the depression. In order to adapt the edge surface to a specific shape or to remove subareas of the edge surface that are not required, it can be provided that the edge surface has a corresponding
Cutting tool is at least partially cut.
In the course of the invention it has been found that there are particularly favorable dimensions for the insert parts, with which the capillary effect can be regulated to such an extent that, on the one hand, sufficient connecting means for an adequate connection of the insert parts are sucked into the joining gap and, on the other hand, one
Entry of the lanyard into the cavity can be prevented. For this purpose, it is advantageous if the edge surface is formed symmetrically around the depression and the ratio of the constant width of the peripheral edge surface to the width of the opening cross-sectional area of the depression delimited by the peripheral edge surface is essentially between 0.1 and 10, in particular essentially between 2 and 8. The width of the peripheral edge surface is therefore preferably wider than the / 25
Opening cross-sectional area. These dimensions result from the knowledge that if the edge surface is too wide, too little connecting means is drawn into the gap between the insert parts, while if the edge surface is too narrow, connecting means disadvantageously get into the cavity. It has also been found in tests that the ratio must be chosen to be greater the deeper the recess in the arrangement of the first and second FKV layer is located,
i.e. the more FKV basics / final locations above or below the
Depression are arranged. The width of the opening cross-sectional area refers to the maximum distance between two edge points of the opening cross-sectional area. In the case of a circular opening cross-sectional area, the width corresponds to the diameter of the opening cross-sectional area. The width of the peripheral edge surface refers to the maximum distance between the inner one and the one adjacent to the opening cross-sectional area
Edge of the edge surface, and the outer edge of the edge surface coinciding with the outer edge of the insert part. In this embodiment, the depression is located essentially in the center of the first insert part, so that the edge surface is formed symmetrically around the depression.
In a preferred embodiment it is provided that the maximum height of the depression is less than the thickness of the first FKV layer, in particular less than the thicknesses (i.e. height extensions) of all FKV layers and FKV layers. As a result, bulging of overlying FKV layers or FKV layers can be reduced. In a particularly preferred embodiment, all the FKV layers and FKV layers used in the FKV comparison body have essentially the same layer thickness. In this embodiment it is preferably provided that the height of the depression is less than the layer thickness used.
In a preferred embodiment variant, it is provided that the depression passes through before the first FKV layer has pre-hardened
Laying the first FKV layer is formed on a mold. For this, the first FKV layer is in an uncured, i.e. malleable condition, placed on the mold. By
The pre-hardening then remains in the first / 25
FKV location and thus in the first part.
In order to form the depression in a particularly simple manner, a plate part, in particular a metal plate, is provided as a molding tool in a first embodiment. This metal plate is removed again after the FKV layer has pre-hardened and can advantageously be used again.
In an alternative embodiment variant, a projection is provided on a mold carrier as a molding tool. For this purpose, the first FKV layer is placed in the uncured state on the mold carrier and the projection, and the recess is thereby formed. After pre-hardening, the FKV layer is removed from the mold carrier.
In order to facilitate the loosening of the pre-hardened FKV layers, it is advantageous if the molding tool is provided with a release agent, in particular a liquid release agent or a release film, before being inserted into the recess. As a result, the molding tool can be removed without damaging the first or second FKV layer. Of course, other parts, such as mold carriers, can also be provided with such a release agent in order to be able to easily remove all of the FRP components.
In a preferred embodiment it is provided that a further depression is formed in the second FKV layer.
Advantageously, the cavity and thus the air entrapment of the delamination can be enlarged. Assigns the second
Insert part a further recess, the second insert part is preferably inserted into the second recess such that the opening of the further recess of the second insert part faces the first insert part. The FKV layers or insert parts are advantageously aligned such that the openings of the depressions are essentially opposite and enclose an air volume with one another in a cavity formed by the depressions. In a particularly preferred form, the first and second insert parts are in the
Essentially identical. All statements and manufacturing steps in this disclosure, which relate to the deepening of the first insert part, can be applied to the further recess / 25 in the second insert part.
The FKV comparison block described above can be used for NDT testing of FKV components.
The method for the non-destructive testing of a FKV component, in particular an aircraft component, comprises at least the following steps:
- Production of a fiber-plastic composite (FKV) comparison body as described above;
- Checking the FKV component using a non-destructive test method, for example a thermography method; and
- Comparison of measurement results from the non-destructive test procedure for the FKV component with comparison values from the FKV comparison body.
The invention is further explained below on the basis of preferred embodiments.
Fig. 1 shows the placement of a first FKV location on a
Mold carrier for the production of the first insert.
Fig. 2 shows a first and second insert part.
3a-3b shows the insertion of the insert parts in the respective FKV layers.
4a-4b each show two insert parts in cross section.
5a-5c shows the formation of a delamination.
FIG. 6 shows a flow diagram of the method according to the invention for producing a FKV comparison body in a preferred embodiment variant.
FIG. 7 shows a flow diagram of an NDT test method with a FKV comparison body produced by the method according to the invention according to claims 1 to.
The figures show individual method steps for producing / 25 an FKV comparison body 26, which can be used in the NDT test of FKV components, such as aircraft wings or aircraft flaps.
1 shows a (uncured) first FRP layer 1, which is placed on a mold carrier 2 in the direction of the arrow in order to produce a first insert 3 with a recess 4 (cf. FIG. 2). The first FKV layer 1 preferably consists, as is usual, in particular in the case of aircraft components, of CFRP, GFRP or aramid fibers, in particular of CFRP, GFRP or aramid materials processed into Prepreq. To generate the recess 4 is on the
Mold carrier 2 preferably has a molding tool 5 in the form of a projection 6 provided on the mold carrier. By placing the uncured first FKV layer 1 on the mold carrier 2, it essentially adapts to the shape of the mold carrier 2, in particular the projection 6, and forms the recess 4. Instead of the projection 6, for example, a
Metal plates can be provided as a mold 5. The mold carrier 2 specifies the later shape of the (pre) hardened FKV layers, preferably an essentially flat surface 7 as in FIG
Fig. 1.
After the first FKV layer 1 has been placed on the mold carrier 2 and the recess 4 has been formed, the first FKV layer is pre-hardened by appropriate methods known to the person skilled in the art, while the molding tool 5 remains in the recess 4 formed. Such a pre-curing process can be carried out, for example, by the first steps of a curing process in an autoclave (not shown). By the
Pre-hardening, the first insert part 3 essentially retains its shape automatically for the further process steps.
FIG. 2 shows a pre-hardened first insert part 3 with the recess 4 and a peripheral edge surface 8 which is symmetrical about the recess 4. The recess 4 is in
Arranged essentially centrally in the first insert part 3 and has (on the underside of the first insert part 3, which is more clearly visible in FIGS. 4a and 4b) an opening 22 and an opening cross-sectional area 23, which corresponds to the area of the opening 22 in the plane of the edge surface 8, on. The opening cross-sectional area / 25 is limited by the edge area 8. The arrows indicate that the peripheral edge surface 8 is partially cut and removed, for example by a suitable cutting tool (not shown), in order to adapt the insert part 3. Depending on the starting material, the cutting of the edge surface 8 is not absolutely necessary.
In order to produce a second insert part 9 from a second FKV layer 25 (cf. FIGS. 4a and 4b), the same method steps as for the first insert part 3 can be carried out. In this way, a second insert 9 can be produced, which in
Is essentially identical to the first insert 3. However, it can also be provided that the second insert part 9 does not
Has depression, i.e. is essentially flat.
For this purpose, the second FKV layer 25 without a molding tool 5 on one
Mold carrier 2 placed and pre-hardened. The second insert part 9 produced in this way has an essentially flat surface and is free from bulges.
3a shows a first FKV layer 10 with a first recess 11 and a second FKV layer 12 with a second recess 13. The recesses 11, 13 are expediently cut into the first with a knife or another cutting tool (not shown) or second FKV layer 10, 12 cut.
The arrow again indicates the removal of excess sections. The recesses 11, 13 point for the later insertion of the
Insert parts preferably have the shape or contour of the outer edge 14 of the first 3 or the second insert part 9. Furthermore, it is provided that the first FKV layer 10 is connected to the second FKV layer 12 in such a way that the recess 11, 13 and thus later the insert parts 3, 9 lie essentially congruently one above the other. The recesses 11, 13 and the insert parts 3, 9 are preferably of the same size, so that the
Insert parts 3, 9 can be inserted flush into the respective recesses 11, 13.
In order to improve the fixation of the insert parts 3, 9 and to produce a particularly realistic FKV comparison body 26, in which the delamination is arranged at any depth within the FKV comparison body 26, there is at least one FKV13 / 25
Basis 15 (in Fig. 3a is a FKV basis 15 and in Fig.
3b, two FKV basics 15 are shown) on one side of the arrangement of first 10 and second FKV layer 12. 3b, on the other side of the arrangement of first 10 and second FKV layer 12, at least one FKV final layer 16 is provided. The entire arrangement is also placed on a mold carrier 2 for later curing. The arrows again indicate the joining of the later one
FKV comparison body.
3b shows the insertion of the first insert part 10 into the first recesses 11 of the first FKV layer 10 and the insertion of the second insert part 9 into the second recess 13 of the second FKV layer 12. It is important that the first 3 and the second insert 9 in the respective recesses
11, 13 are used in such a way that a cavity 17, the so-called air pocket, defined by the recess 4 of the first insert part 3 and the second insert part 3 is formed, as can be seen in FIGS. 4a and 4b. The opening 22 of the
Well 4 of the first insert 3 is the second
Insert part 9 facing. If the second insert part 9 has a further recess 18, the second insert part 9 is likewise inserted into the second recess 13 such that the opening of the further recess 18 of the second insert part faces the first insert part 3. It is also essential that the first 3 and the second insert part 9 or the cutouts 11, 13 are essentially congruent with one another.
4a shows the first insert part 3 and an essentially identical second insert part 9 with a further recess 18. The two insert parts 3, 9 are arranged such that one through the recesses of the first and the second insert part
3, 9 limited cavity 17 is formed. The opening 22 of the
Well 4 of the first insert 10 is the second
Insert part 9 faces, while the opening of the further recess 18 of the second insert part 12 faces the first insert part 10. As shown in FIG. 4a, the peripheral edge surface 8 of the insert parts 3, 9 has a width 19 between the inner edge adjoining the opening cross-sectional surface 23 of the recess 4 and the outer edge 14 of the edge surface 8 or
/ 25 of the insert part. The opening cross-sectional area 23 of the recess 4 is indicated by the broken line 23. The opening cross-sectional area 23 of the recess 4 delimited by the peripheral edge surface 8 also has a width 20, which relates to the maximum width in the case of non-circular opening cross-sectional areas 23. The ratio of the width 19 of the edge surface 8 to the width 20 of the opening cross-sectional area 23 is preferably essentially between 0.1 and 10, in particular essentially between 2 and 8.
4b shows an embodiment in which the second insert part 9 has no further recess. The second insert part is essentially flat, i.e. free from bulges.
5a shows the arrangement of the first FKV layer 10 with the first insert part 3 and the second FKV layer 12 with the second insert part 9. The application of contact pressure, in particular during a curing process suitable for the FKV material, means that the capillary effect connecting means, which is contained in the used FKV material, in the arrow direction in a narrow, between the first and second insert parts 3, 9 lying gap 21 to the recess and thereby connects the two insert parts 3, 9 in the
Edge surface 8 outside of the recess 4 with one another and with the first 10 and second FKV layers 12
Connection means for connecting the insert parts 3, 9 of the
FKV layers provided. At the border to the recess 4 or the enclosed cavity 17, as shown in FIG.
5c, the suction effect of the capillary effect finally comes to a standstill due to the greater distance between the two insert parts 3, 9 and the connecting means is not drawn into the recess 4 or the cavity 17. Thus, the recess 4 is essentially free of connecting means and the first and second insert parts 3, 9 do not adhere to one another in the region of the recess 4. As a result, the simulated delamination 24 is formed in the recess 4 or in the cavity 17 after curing.
6 shows a preferred method sequence for producing / 25 an FKV comparison body 26 with an artificially generated one
Delamination 24. In a step 101, a
Inserted a first FKV layer 1 in the uncured state on a mold carrier 2. To form a recess 4, a mold 5 in the form of a projection 6 can be provided on the mold carrier 2 or in the form of a metal plate. In a step 102, the first FKV layer 1 is pre-hardened in order to produce the first insert part 3. In one
Step 103, which is, however, not absolutely necessary, the first insert part 3 can be cut to a certain size. Steps 101-103 accordingly produce the first insert part 3. By using steps 101 103 again (as indicated by the arrow), further insert parts, in particular the second insert part 9, can be generated. In a step 201, the first 10 and the second FKV layer 12 are placed on a mold carrier 2 in an uncured state. In a step 202, the first 11 and the second
Cut recess 13 from the first 10 or second FKV layer 12. In a step 203, the first 3 and the second insert part 9 are inserted into the first 11 and second recess 13, respectively. In step 204, if necessary, at least one FKV base 15 on one side of the arrangement of the first 10 and second FKV layer 12 and / or at least one
FKV final layer 16 on the other side of the arrangement of first 10 and second FKV layer 12 are added. In one
Step 205 becomes the entire arrangement of first 10 and second
FKV layer 12, the first 3 and second insert 9 and any FKV fundamentals 15 and / or FKV end layers 16 completely hardened by a curing process suitable for the FKV material used.
FIG. 7 shows a preferred method sequence of an NDT test method with an FKV comparison body 26. In a step 701, an FKV comparison body 26 is produced by the method sequence according to FIG. 6. In a step 702, the comparison body is tested using a non-destructive test method, for example a thermography method or an ultrasound method, in order to detect and measure the artificially generated delamination in the FKV comparison body 26.
This allows comparison values to be set. In a / 25
In step 703, an FKV component made of FKV material, in particular an aircraft component, is tested using the same non-destructive test method in order to obtain test results. In one step
704, the test results from step 703 are compared with the comparison values from step 702 in order to be able to carry out an assessment of the FKV component with regard to any component defects, in particular delamination. For this purpose, signal amplitudes or other signal types generated by the non-destructive tester method are preferably compared with one another. If a specified limit value, which can be derived from the comparison values, is exceeded, a faulty FKV component can be identified.

权利要求:
Claims (11)
[1]
claims:
1. A method for producing a fiber-plastic composite (FKV) comparison body (26) for simulating a delamination (24) for the non-destructive testing of FKV components, in particular aircraft components, with the steps:
1. Manufacture of a first insert part (3) for the FKV comparison body (26) by
a. Arranging a first FKV layer (1);
b. Forming a recess (4) in the first FKV layer (1);
c. Pre-hardening the first FKV layer (1) in order to obtain the first insert part (3) for the FKV comparison body;
ii. Manufacture of a second insert part (9) for the FKV comparison body
a. Arranging a second FKV layer (25);
b. Pre-hardening the second FKV layer (25) in order to obtain the second insert part (9) for the FKV comparison body;
iii. Providing at least one first FKV layer (10) with a first recess (11) and at least one second FKV layer (12) with a second recess (13);
iv. Insert the first insert (3) into the first
Recess (11) of the first FKV layer (10) and insertion of the second insert part (9) into the second recess (13) of the second FKV layer (12);
v. Hardening of the arrangement of the first FKV layer (10) with the first insert part (3) and the second FKV layer (12) with the second insert part (9), whereby on the recess (4) in the first FKV layer ( 1) the first insert (10) is simulated delamination.
[2]
2. The method according to claim 1, characterized in that at least one FKV basis (15) on one side of the arrangement of the first (10) and second FKV layer (12) and / or at least one FKV final layer (16) the other side of the arrangement of the first (10) and second FKV layer (12) is provided.
18/25
[3]
3. The method according to any one of claims 1 or 2, characterized in that the first insert part (3) has a circumferential and preferably substantially flat edge surface (8) around the recess (4).
[4]
4. The method according to claim 3, characterized in that the edge surface (8) is symmetrical about the recess (4) and the ratio of the width (19) of the peripheral edge surface (8) to the width (20) of the peripheral edge surface ( 8) limited opening cross-sectional area (23) of the depression (4) is essentially between 0.1 and 10, in particular essentially between 2 and 8.
[5]
5. The method according to any one of claims 1 to 4, characterized in that the maximum height of the recess (4) less than the thickness of the first FKV layer (10), in particular less than the thickness of all FKV layers and FKV- Layers, is.
[6]
6. The method according to any one of claims 1 to 5, characterized in that the recess (4) prior to pre-curing the first FKV layer (1) by placing the first FKV layer (1) on a mold (5) becomes.
[7]
7. The method according to claim 6, characterized in that a plate part, in particular a metal plate, is provided as the molding tool (5).
[8]
8. The method according to claim 6, characterized in that a projection (6) on a mold carrier (2) is provided as the molding tool (5).
[9]
9. The method according to any one of claims 6 to 8, characterized in that the molding tool (5) before placing the first FKV-
Layer (1) is provided with a release agent, in particular a liquid release agent or a release film.
[10]
10. The method according to any one of claims 1 to 9, characterized in that a further recess (18) is formed in the second FKV layer (25).
19/25
[11]
11. A method for the non-destructive testing of a FKV component, in particular an aircraft component, with the steps:
- Production of a fiber-plastic composite (FKV) comparison body (26) in a method according to one of claims 1 to 10;
- Checking the FKV component using a non-destructive test method, for example a thermography method; and
- Comparison of measurement results from the non-destructive test procedure for the FKV component with comparison values from the FKV comparison body (26).

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同族专利:

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公开号 | 公开日

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AT521355B1|2020-01-15|

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EP3850353A1|2021-07-21|

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BR112021001797A2|2021-04-27|

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RU2756488C1|2021-09-30|

---

EP3850353B1|2022-01-26|

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WO2020051608A1|2020-03-19|

---

CN112673253A|2021-04-16|

---

US20210190710A1|2021-06-24|

---

CA3108393A1|2020-03-19|

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法律状态:

优先权:

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申请号 | 申请日 | 专利标题

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ATA50764/2018A|AT521355B1|2018-09-10|2018-09-10|Process for producing a fiber-plastic composite comparison body and test method|ATA50764/2018A| AT521355B1|2018-09-10|2018-09-10|Process for producing a fiber-plastic composite comparison body and test method|

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BR112021001797-6A| BR112021001797A2|2018-09-10|2019-09-10|process for manufacturing a composite synthetic material and fiber comparison body and process for testing|

---

EP19772970.0A| EP3850353B1|2018-09-10|2019-09-10|Method for producing a fibre-plastic-composite reference body and test method|

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PCT/AT2019/060291| WO2020051608A1|2018-09-10|2019-09-10|Method for producing a fibre-plastic-composite reference body and test method|

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CA3108393A| CA3108393A1|2018-09-10|2019-09-10|Method for producing a fiber-plastic composite reference body and test method|

---

RU2021106075A| RU2756488C1|2018-09-10|2019-09-10|Method for producing reference sample from fiber-plastic composite and method for testing|

---

US17/267,773| US20210190710A1|2018-09-10|2019-09-10|Method for producing a fiber-plastic composite reference body and test method|

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CN201980058979.9A| CN112673253A|2018-09-10|2019-09-10|Manufacturing and detecting method of fiber plastic composite material reference body|