Patent Description:
The material class of Fiber Metal Laminate (FML) has increasingly been applied for the realization of airplane components, in particular of structural airplane components. The reason for this is that with Fiber Metal Laminates extraordinary mechanical properties may be achieved with extremely lightweight design. A Fiber Metal Laminate comprises metal layers and fiber layers stacked onto each other and bound by a normally thermoset resin.

The manufacturing process of Fiber Metal Laminate components of an airplane is complex as the layers to be stacked onto each other are flexible at least as far as the fiber layers are concerned. Due to the flexibility of the layers it is challenging to achieve stable handling processes during stacking up the layers onto each other. Another challenge is to prevent the generation of cavities, when one layer is stacked onto another layer.

For the reasons noted above the manufacturing process is largely performed manually.

However, approaches have been made to introduce an automated manufacturing process for Fiber Metal Laminate components of an airplane.

<CIT> discloses an automated ply layup system using a robot and an end effector for selecting plies from a kit and placing the plies at predetermined locations on a tool.

The known method (<CIT>), which is the starting point of the invention, relies on a manipulator system with one end effector for handling the metal layers and with a second end effector for handling the fiber layers. With this manipulator system the respective layers are being stacked onto each other in a mould in a stacking sequence. Each stacking cycle comprises picking up a layer from a supply stack, transporting the layer to the mould, placement of the layer at a deposition surface in the mould and depositing the so placed layer onto the deposition surface.

In order to prevent a building up of cavities during stacking up the layers, the layers are being fixed to the mould by electrostatic charging.

While the known method generally allows automatic manufacturing of Fiber Metal Laminate components of an airplane, the backdraw of this approach is the high complexity of the resulting manufacturing system and as a result the high costs involved with setting up such a manufacturing system.

It is the objective of the invention to improve the known method as to achieve a stable automated manufacturing process with a manufacturing system of low complexity.

The above noted objective is achieved for a method according to the general part of claim <NUM> by the features of the characterizing part of claim <NUM>.

The idea underlying the invention is to adapt the form of the layer to be stacked to the form of the mould, before the respective layer is being deposited. With this it is possible that a flat contact is achieved between the surface of the layer and the surface of the deposition surface. With such contact the buildup of cavities may be prevented or at least effectively be reduced.

In detail it is proposed that after being picked up from the supply stack and before being deposited onto the position surface the layer to be stacked is being deformed by the end effector as to adapt the form of the layer to the form of the deposition surface. It has been found that the above noted deforming of the layer may be achieved by the end effector itself. This is especially advantageous as no additional tool is necessary for deforming and also as no additional handling step is necessary for adapting the form of the layer to the deposition surface.

The invention provides improved gripping of the layer to be stacked via a gripping arrangement. It is particularly preferred that the gripping arrangement at least partly provided a floating grip of the layer along its surface such that during the proposed deformation of the layer no undesired mechanical tension is building up within the layer.

Especially preferred embodiments are directed to deforming the respective layer with low mechanical complexity.

The idea behind the invention is to pick up and deform the respective layer via one and the same end effector.

It has been found that especially when using suction gripping elements for the gripping arrangement it is well possible to even use one and the same gripping element to grip a metal layer as well as a fiber layer. Opposite to what is taught in the state of the art it is now possible to handle metal layers and fiber layers with one and the same end effector, such that the respective end effector may be applied in a particularly effective way.

A further preferred embodiment allows an air pocked free deposition of the respective layer as a completely flat contact may be established between the surface of the layer and the deposition surface.

However, depending on the design of the mould it may be advantageous that the form of the layer before its deposition at least slightly deviates from the form of the deposition surface. This may prevent the build up of friction between the layer and the deposition surface during placement of the layer into the mould. Such friction may again lead to the build up of the undesired cavities between the layers.

According to claim <NUM>, the manipulator system for performing the proposed method is claimed as such. Reference is made to all explanations even regarding the proposed method, as far as those explanations are suitable to describe the manipulator system.

In the following the invention will be described based on an example with reference to the drawings. In the drawings show.

The manufacturing system <NUM> shown in the drawings serves for producing a Fiber Metal Laminate component of an airplane. Preferably, such component is part of a structural component of an airplane, in particular part of a fuselage or wing of an airplane. Here and preferably the component is part of the outer skin of the fuselage. The component is accordingly of half shell shape.

The manufacturing system <NUM> comprises a manipulator system <NUM> with an end effector <NUM> and a control <NUM> assigned to the manipulator system <NUM>. The control <NUM> is an electronic control which controls not only the movement of the manipulator system <NUM> but also the actions of the end effector <NUM>. The manufacturing system <NUM> here and preferably is structured as a robot cell.

During manufacturing at least one metal layer <NUM> and at least one unhardened fiber layer <NUM> are being stacked onto each other in a mould <NUM> by the manipulator system <NUM> in a stacking sequence. The kind of layers <NUM>, <NUM> and the stacking sequence depends on the kind of Fiber Metal Laminate material, the resulting component shall be made off. The metal layer <NUM> may be any kind of metal sheet, the fiber layer <NUM> may be any kind of fiber sheet, which may be of dry fiber material or preimpregnated fiber material, also known as prepreg.

It is especially preferred that the Fiber Metal Laminate component is a so called GLARE® material (Glass Laminate Aluminium Reinforced Epoxy). Here the metal layer <NUM> is at least partly an aluminium layer. Other metal materials such as titanium may be applied as well. Normally the outer layers of the Fiber Metal Laminate component are metal layers <NUM>. The thickness of the metal layers is below <NUM>,<NUM>, preferably between <NUM>,<NUM> and <NUM>,<NUM>, further preferably between <NUM>,<NUM> and <NUM>,<NUM>. For prevention of corrosion it is anodized. In order to provide good bonding characteristics it is further coated with an appropriate primer.

The fiber layer <NUM> may be of prepreg fiber material or dry fiber material, which during manufacturing is in any case unhardened. It may comprise different kind of fibers such as glass fibers, aramid fibers or the like.

Additionally to the handling of metal layers <NUM> or fiber layers <NUM> also adhesive tape layers can be handled and deposited between two metal layers <NUM> or between two fiber layers <NUM> or a fiber layer <NUM> and a metal layer <NUM>. Preferably, if two metal layers <NUM> are deposited onto each other partly overlapping, an adhesive tape layer is positioned in the overlapping region in between the two metal layers <NUM>. The adhesive tape layer can provide a sealing between the respective two layers.

Each stacking cycle comprises picking up a metal layer <NUM> or a fiber layer <NUM> or an adhesive tape layer from a respective supply stack <NUM> according to the respective stacking sequence. Here and preferably, two supply stacks <NUM>, <NUM> are provided. One supply stack <NUM> for providing the metal layer <NUM> and one supply stack <NUM> providing the fiber layer <NUM>. Both types of layers <NUM>, <NUM> can also be supplied on one supply stack. Whether the metal layer <NUM> is being picked up from the supply stack <NUM> or a fiber layer <NUM> is being picked up from supply stack <NUM> depends on the stacking sequence which largely depends on the layer structure of the Fiber Metal Laminate component to be manufactured. The picking up of the respective layer is shown in <FIG>.

Subsequently within the stacking cycle the picked up a layer <NUM>, <NUM> is being transported to the mould as shown in <FIG>. The transportation of the layer <NUM>, <NUM> is followed the placement of the layer <NUM>, <NUM> at a deposition surface <NUM> in the mould <NUM> according to the stacking sequence which again is followed by depositing the so placed layer <NUM>, <NUM> onto the deposition surface <NUM>, as shown in <FIG>. The deposition surface <NUM> may be the surface of the mould <NUM> or the surface of the respective layer <NUM>, <NUM> that has been stacked in the previous stacking cycle. Accordingly the exact location of the deposition surface <NUM> depends on the stacking sequence. In any case the form of the deposition surface <NUM> is largely defined by the form of the mould <NUM>.

Depending on the fiber metal laminate components to be produced the mould <NUM>, respectively the deposition surface <NUM>, may have a convex and/or a concave form. The mould <NUM>, respectively the deposition surface <NUM>, may have both convex as well as concave sections, for example when fiber metal laminate components for the airplane sections between the fuselage and the wing are to be produced.

It is of particular importance for the invention that after being picked up from the supply stack <NUM>, <NUM> and before being deposited onto the deposition surface <NUM> the layer <NUM>, <NUM> to be stacked is being deformed by the end effector <NUM> as to adapt the form of the layer <NUM>, <NUM> to the form of the deposition surface <NUM>. This is shown in <FIG>. Here the deposition surface is of concave form, to which the layer <NUM>, <NUM> is being adapted by the end effector <NUM>.

It may be pointed out that the step of deforming the respective layer <NUM>, <NUM> may take place at any time between picking up the layer <NUM>, <NUM> and depositing the layer <NUM>, <NUM>. In a preferred embodiment of the proposed method the deforming step is being performed while the manipulator system <NUM> is being moved, in particular during the transporting step. However, it may be advantageous to stop the movement of the manipulator system <NUM> for the deforming step, for example in order to achieve a higher accuracy in deforming. The advantages of providing a deforming step has been explained in the general part of the specification. The possibility of preventing cavities between layers <NUM>, <NUM> becomes especially apparent when looking at <FIG>, d.

It is generally possible for the manipulator system <NUM> to comprise more than one end effector <NUM>, for example if certain process steps are to be performed in parallel. All explanations given for the one shown end effector <NUM> are fully applicable to a manipulator system <NUM> with two or more than two end effectors <NUM>.

The manipulator system <NUM> shown in the drawings comprises a manipulator <NUM>, which is being driven by the control <NUM>. Here and preferably the manipulator <NUM> is a robot with sequential axes. It may also be a robot with any kind of other kinematic, for example the kinematic of a portal robot. The manipulator <NUM> may as well be a construction which is tailored to the manufacturing process explained above.

The end effector <NUM> preferably comprises a gripping arrangement <NUM> for gripping the layer <NUM>, <NUM> during pick up. The gripping arrangement <NUM> includes here and preferably a number of gripping elements <NUM> which each provide a localized gripping interaction with the respective layer <NUM>, <NUM>. The gripping arrangement <NUM> defines a gripping plane <NUM>, along which the gripping interaction with the respective layer <NUM>, <NUM> is possible. The gripping elements <NUM> are distributed across the gripping plane <NUM> of the gripping arrangement <NUM>.

The gripping arrangement <NUM> is being activated by the control <NUM>. The activation of the gripping arrangement <NUM> does not only include turning on and off a gripping interaction but also adjusting operating parameters of the end effector <NUM> as will be noted below.

It is of particular importance that while the gripping elements <NUM> are distributed across the gripping plane <NUM>, the gripping elements <NUM> are being activated separately or in groups by the control <NUM>. With this it is possible to selectively activate the gripping elements <NUM>, for example in order to prevent unused gripping elements <NUM> to undesirably interact with already deposited layers <NUM>, <NUM>. It is possible to handle layers <NUM>, <NUM> smaller than the outline of the gripping arrangement <NUM>.

As may be seen from <FIG> the gripping arrangement <NUM> comprises at least one gripping element 13a, here and preferably a number of gripping elements 13a, of a first type and at least one gripping element 13b, here and preferably a number of gripping elements 13b, of a second type. This generally provides an increase of flexibility of the gripping arrangement <NUM>, as different gripping characteristics may be set by the control <NUM>. In the preferred embodiment shown in <FIG> the gripping element 13a of the first type provided a floating grip of the layer <NUM>, <NUM> along its surface such that the gripping forces only act perpendicular to the surface of the layer <NUM>, <NUM> and are only minimal in the direction along the surface of the layer <NUM>, <NUM>. This allows a compensation movement between the layer <NUM>, <NUM> with respect to the gripping arrangement <NUM> during deformation such that undesired attention within the layer <NUM>, <NUM> is prevented. In order to define the position of the layer <NUM>, <NUM> along its surface the gripping element 13b of the second type provides a stiff grip of the layer <NUM>, <NUM>. For an unambiguous definition of the position of the layer <NUM>, <NUM> at least two gripping elements 13b of the second type are necessary, which are located at a certain distance to each other. With this distance it is possible for the gripping arrangement to provide a support of the layer <NUM>, <NUM> also in view of possible rotation of the layer <NUM>, <NUM>.

There are various possibilities possible for realizing the gripping elements <NUM> of the gripping arrangement <NUM>. Examples are pincer grippers, needle grippers, freezing grippers or the like. Here and preferably however, the gripping elements are suction gripping elements. In particular, the gripping elements 13a of the first type are Bemulli suction gripping elements, while the gripping elements 13b of the second type are Venturi suction gripping elements. The application of suction gripping elements is presently advantageous as damaging of the layers <NUM>, <NUM> may effectively prevented, as is of particular importance for airplane components.

As noted above the deformation of the layer <NUM>, <NUM> is being performed by the end effector <NUM> itself. For this the end effector <NUM> comprises a deformable carrier arrangement <NUM>, which the gripping arrangement <NUM> is located on. Here and preferably the carrier arrangement comprises bendable carrier strips <NUM> which the gripping elements <NUM> are located on.

The end effector <NUM> also comprises an actuator arrangement <NUM> for actuator based deforming of the carrier arrangement <NUM>. For deforming the gripped layer <NUM>, <NUM> the actuator arrangement <NUM> is being driven by the control <NUM>. This becomes a parent from a comparison of <FIG>.

<FIG> also shows that the actuator arrangement <NUM> comprises at least two actuators <NUM>, here and preferably a number of actuators <NUM>, that are driven by the control <NUM>.

The realization of the actuator arrangement <NUM> is possible in various advantageous ways. Here and preferably the actuators <NUM> of the actuator arrangement <NUM> are linear actuators, that are driven by the control <NUM> respectively. Here and preferably the actuators <NUM> are partly of the type of a pneumatic muscle and partly of the type of a pneumatic piston drive. Accordingly the actuator arrangement <NUM> comprises at least two actuators <NUM> of different type. The actuators <NUM> of the type of a pneumatic muscle are denominated with reference number 18a, while the actuators <NUM> of the type of a pneumatic piston drive are denominated with reference number 18b. With the actuators 18a of the first type, exact pulling forces may be introduced into the carrier arrangement <NUM>, at the same time providing a certain elasticity. With the actuators 18b of the second type pulling forces and pushing forces may be introduced into the carrier arrangement <NUM>, such that the actuators 18b of the second kind provide supporting points for the forces generated by the actuators 18a of the first kind. With this combination of actuators 18a, 18b interacting with each other a high flexibility and at the same time accuracy in deformation of the carrier arrangement <NUM> and their risk of the gripped layer <NUM>, <NUM> is possible.

Regarding the detailed construction shown in <FIG> the above noted application of actuators <NUM> of different type is especially advantageous as the actuators <NUM> are each acting on the carrier arrangement <NUM>, here on the carrier strips <NUM>, mainly in a perpendicular direction with respect to the gripping plane <NUM>, which the carrier strips <NUM> are aligned to. The actuators <NUM> are arranged in one or more rows and are attached to an interface arrangement <NUM> at their respective one ends and to the carrier arrangement <NUM>, here the carrier strips <NUM>, on their respective other ends. At least one of the actuators <NUM> is provided with a return spring <NUM> that may be a coil spring aligned to the longitudinal extension of the linear actuator <NUM>.

Further constructional details regarding the gripping arrangement <NUM> may be taken from <CIT>, which goes back on the applicant.

The application of the shown gripping arrangement <NUM> for the proposed manipulator system <NUM> allows an extraordinary amount of flexibility. This is particularly true because depending from driving the above noted actuators <NUM> by the control <NUM> the carrier arrangement <NUM> may be brought into different forms. This includes convex forms, concave forms and combinations of those. Also the degree of deformation of the carrier arrangement <NUM> and therewith of the respective layer <NUM>, <NUM> may be changed on a continuous scale. As the deformation may be achieved actuator based as noted above, it is possible with no effort to change the deformation at any time during production, in particular between two stacking cycles.

As a consequence, it is possible to change the mould <NUM> for the production of one Fiber Metal Laminate component to another mould <NUM> for the production of another Fiber Metal Laminate component with a different geometry of the mould <NUM>. This may be done without having to adapt the manipulator system <NUM> mechanically. In order to produce different Fiber Metal Laminate components changes have only to be made in and/or by the control <NUM>. In particular the control <NUM> changes the drive movement of the manipulator and/or the drive movement of the actuators <NUM> and/or the operating parameters of the gripping arrangement <NUM>.

An advantage of the proposed method and the proposed manipulator system <NUM> is the fact that it is possible to provide the layers <NUM>, <NUM> to be stacked as flat precut layers in the respective supply stack <NUM>, <NUM>. As deforming the layers <NUM>, <NUM> is provided by the end effector <NUM> it is not necessary to have the layers <NUM>, <NUM> provided in the supply stack <NUM>, <NUM> as already preformed layers <NUM>, <NUM>. This makes the logistics of the manufacturing process less complex and as a result cost effective. The outlines of the respective layers <NUM>, <NUM> may vary to each other. In particular, the outlines of the precut metal layers <NUM> and the precut fiber layers <NUM> may vary to each other. Preferably, the end effector <NUM> handles layers <NUM>, <NUM> of different width and/or length during the production of the fiber metal laminate component. The width and/or the length of the metal layers <NUM> in comparison to the width, respectively the length of the fiber layers <NUM>, may vary during the production of one fiber metal laminate component from one stacking cycle to the next stacking cycle. Preferably, the surface area of the fiber layers <NUM> is smaller than the surface area of the metal layers <NUM>. Additionally or alternatively the surface area of different metal layers <NUM> or different fiber layers <NUM> may vary from one stacking cycle to the next stacking cycle.

An increase of effectiveness is also achieved by the fact that at least one metal layer <NUM> and at least one fiber layer <NUM>, here and preferably all metal layers <NUM> and all fiber layers <NUM>, are each being picked up and deformed via one and the same end effector <NUM>. Accordingly it has been found that generally it is not necessary to have different end effectors <NUM> for the different layers of the Fiber Metal Laminate component. This is particular true for those layers of above noted GLARE® materials. During manufacturing it is possible to optimize various operating parameters by the control <NUM>. Here and preferably at least one operating parameter of the end effector <NUM> is being adapted by the control <NUM> depending on the layer <NUM>, <NUM> being a metal layer or a fiber layer. In particular it is preferred that depending on the layer <NUM>, <NUM> to be handled, different gripping forces may be set by the control <NUM>. Another adaption of an operating parameter is that during deforming the layer <NUM>, <NUM> to be stacked, different gripping elements <NUM> are being activated by the control <NUM> depending on the layer <NUM>, <NUM> being a metal layer <NUM> or a fiber layer <NUM>. According to the invention it is well possible to activate the gripping elements <NUM> separately or in groups by the control <NUM>. In particular it is preferred that during transporting and/or deforming of the fiber layers <NUM> a different number of gripping elements are activated then during transporting and/or forming of the metal layers <NUM>, <NUM>. It may also be pointed out that the surfaces of the layers <NUM>, <NUM> to be stacked are normally smaller than the surface of the mould <NUM>. Accordingly stacking of the layers <NUM>, <NUM> means building up a tile structure across the mould surface.

The particular advantage of a Fiber Metal Laminate structure is that specific mechanical properties may be set, which mechanical properties may depend on the direction of force introduced into the structure. This may be achieved simply by placing the fiber layers <NUM> in specific orientations.

Preferably, within the fiber layers <NUM> the fibers are oriented homogeneously. Preferably all fibers are basically aligned to one direction. With this it is easily possible to define the above noted mechanical properties by depositing at least two fiber layers <NUM> onto each other in different fiber orientations.

Depositing at least two fiber layers <NUM>, <NUM> onto each other in different fiber orientations may, however, also be advantageous if the fiber layer <NUM> is of the type of knitted fabrics of interlaced fabrics or the like. It is preferred that at least one fiber layer <NUM> is stacked onto another fiber layer <NUM> such that the fiber orientations of the two layers <NUM> are offset to each other by <NUM>°. In the manufacturing process this means that the first fiber layer <NUM> is deposited at a first angle and that the second fiber layer <NUM> is deposited at a second angle, while the first angle and the second angle are not identical. Preferably, the difference between the two angles is above <NUM>°, preferably above <NUM>°, further preferably <NUM>° and especially preferably <NUM>°. The complete ranges of angles for
depositing the layers <NUM>, <NUM> may be realized by the proposed manipulator system <NUM> simply by turning the end effector <NUM> via the manipulator <NUM> accordingly.

There may be a different freedom in deformation of the layers <NUM>, <NUM> depending on the complexity of the component to be manufactured. Here and preferably the fiber layer <NUM> and the metal layer <NUM> are being deformed in at least two kartesian dimensions. It may even be possible that the fiber layer <NUM> and the metal layer <NUM> are being deformed in three kartesian dimensions. Here and preferably the fiber layer <NUM> and the metal layer <NUM> are being deformed by bending around at least one bending axis, which bending axis is roughly indicated in <FIG>. Further preferably the bending axis <NUM> is arranged basically parallel to the surface of the respective layer <NUM>, <NUM> and there is basically parallel to the gripping plane <NUM>, as may be taken from <FIG> as well.

The placement of the layer <NUM>, <NUM> to be stacked, which precedes depositing the layer <NUM>, <NUM> onto the deposition surface <NUM> may be performed in various advantageous ways. In a first preferred embodiment the placement of the layer <NUM>, <NUM> to be stacked goes along with a layer <NUM>, <NUM> contacting the deposition surface <NUM> along a contact line or a contact point. Preferably the contact line or the contact point is a single contact line or a single contact point. With this, depending on the form of the mould <NUM>, the build up of cavities may be prevented. As an alternative, the placement of the layer <NUM>, <NUM> to be stacked goes along with the layer <NUM>, <NUM> evenly contacting the full deposition surface. This is shown in <FIG>. As the manufacturing system shown in the drawings provides a high accuracy in positioning of the end effector <NUM>, the flat contact between the surface of the layer <NUM>, <NUM> and the deposition surface <NUM> prevents the build up of cavities. As another alternative the placement of the layer <NUM>, <NUM> to be stacked goes along with the layer <NUM>, <NUM> floating directly above the position surface <NUM>. The layer <NUM>, <NUM> is vaguely dropped onto the deposition surface <NUM>. Due to the very short dropping distance and the above noted adaption of the form of the layer <NUM>, <NUM> to the form of the deposition surface <NUM>, also with this alternative the build up of cavities is prevented.

The proposed deforming of the respective layer may be performed in various ways, which may be advantageous depending on the form of the mould <NUM>.

In a first preferred embodiment the deformation of the layer <NUM>, <NUM> to be stacked by the end effector <NUM> before its deposition is performed such that the form of the layer <NUM>, <NUM> is identical to the form of the deposition surface. This is shown in <FIG>.

It may also be advantageous that the deformation of the layer <NUM>, <NUM> to be stacked by the end effector <NUM> before its deposition is performed such that the form of the layer <NUM>, <NUM> at least slightly deviates from the form of the deposition surface <NUM>. This may be advantageous if any friction shall be prevented during the placement of the layer <NUM>, <NUM> at the deposition surface <NUM>. In case of a convex deposition surface <NUM> this is realized that the deformation of the layer <NUM>, <NUM> is performed such that the layer <NUM>, <NUM> is less convex than the deposition surface <NUM>. In case of a concave deposition surface <NUM> (<FIG>) this may be done by deformation of the layer <NUM>, <NUM> such that the surface of the layer <NUM>, <NUM> is more concave than the deposition surface <NUM>. For other designs of the mould <NUM> this principle may be applied accordingly.

After the above noted stacking of the layers <NUM>, <NUM> onto each other the stacked up arrangement is preferably being compressed in order to i. further reduce possible cavities. Preferably together with the mould <NUM> the stacked up arrangement is then preferably transferred into an autoclave, in which it is being heated under pressure, activating the matrix of the fiber layers <NUM> as far as those fiber layers <NUM> are of prepreg material. This heat treatment is being performed for <NUM> to <NUM> hours under a high pressure of about <NUM> bar. Subsequent heat or pressure treatments may follow according to the layer material applied. It may be pointed out that if the fiber layers <NUM> are of dry fiber material they might be impregnated after each placement or the matrix material might be applied to the fiber layers <NUM> before the autoclave.

Claim 1:
Method for producing a Fiber Metal Laminate component of an airplane, using a manipulator system (<NUM>) with an end effector (<NUM>) and a control (<NUM>) assigned to the manipulator system (<NUM>), wherein at least one metal layer (<NUM>) and at least one unhardened fiber layer (<NUM>) are being stacked onto each other in a mould (<NUM>) by the manipulator system (<NUM>) in a stacking sequence, wherein each stacking cycle comprises picking up a metal layer (<NUM>) or a fiber layer (<NUM>) from a respective supply stack (<NUM>, <NUM>) according to the stacking sequence, transporting the layer (<NUM>, <NUM>) to the mould (<NUM>), placement of the layer (<NUM>, <NUM>) at a deposition surface in the mould (<NUM>) according to the stacking sequence and depositing the so placed layer (<NUM>, <NUM>) onto the deposition surface (<NUM>),
characterized in
that after being picked up from the supply stack (<NUM>, <NUM>) and before being deposited onto the deposition surface (<NUM>), the layer (<NUM>, <NUM>) to be stacked is being deformed by the end effector (<NUM>) as to adapt the form of the layer (<NUM>, <NUM>) to the form of the deposition surface (<NUM>) and that at least one metal layer (<NUM>) and at least one fiber layer (<NUM>) are each being picked up and deformed via one and the same end effector (<NUM>) and in that the end effector (<NUM>) comprises a number of gripping elements (<NUM>) for gripping the layer (<NUM>, <NUM>) during pick up, wherein the gripping elements (<NUM>) are being activated separately or in groups by the control (<NUM>).