Heating element, device and method for resistance welding thermoplastic parts, in particular for aircraft production, and aircraft
阅读说明:本技术 用于电阻焊接热塑性部件,特别是用于飞行器生产,的加热元件、装置和方法,以及飞行器 (Heating element, device and method for resistance welding thermoplastic parts, in particular for aircraft production, and aircraft ) 是由 M·蒂尔亚基 W·艾尔肯 A·巴赫拉尼 于 2019-08-16 设计创作,主要内容包括:用于电阻焊接飞行器的热塑性部件的加热元件(30)包括以线或纤维形式的导电元件(30a),其在向加热元件(30)施加电压时加热,以在由加热元件(30)电加热的区域中将第一部件(11)焊接到第二部件(12)。导电元件(30a)在接触区域(35、36)之间彼此平行地延伸,用于电接触加热元件(30)。在焊接过程之后,加热元件(30)保留在焊接部件(11、12)之间,以增强焊接结合部的强度。一种用于通过电阻焊接结合热塑性部件的装置包括加热元件(30)和滚柱电极形式的单元(31、32),该单元用于沿焊接方向移位部件(11、12)的电加热区域。导电元件(30a)平行于滚柱电极的旋转轴(31a、32a)延伸。(A heating element (30) for resistance welding thermoplastic parts of an aircraft comprises an electrically conductive element (30a) in the form of a wire or fibre which heats up when a voltage is applied to the heating element (30) to weld a first part (11) to a second part (12) in an area which is electrically heated by the heating element (30). The electrically conductive elements (30a) extend parallel to each other between the contact areas (35, 36) for electrically contacting the heating element (30). After the welding process, a heating element (30) remains between the welded components (11, 12) to enhance the strength of the welded joint. An apparatus for joining thermoplastic parts by resistance welding comprises a heating element (30) and a unit (31, 32) in the form of a roller electrode for displacing an electrically heated region of the parts (11, 12) in the welding direction. The conductive element (30a) extends parallel to the rotational axes (31a, 32a) of the roller electrodes.)
1. Heating element for resistance welding thermoplastic parts, in particular for producing aircraft, comprising one or more electrically conductive elements (30a), which electrically conductive elements (30a) are heated when a voltage is applied to the heating element (30) in order to weld a first part (11) to a second part (12) in a region which is electrically heated by the heating element (30), wherein the heating element (30) is designed to remain between the welded parts (11, 12) after the welding process and to form a reinforcement in order to reinforce the strength of the weld joint therein,
and wherein the electrically conductive elements (30a) are designed as wires or fibers, the electrically conductive elements (30a) extending parallel to one another between contact regions (35, 36) for electrically contacting the heating element (30).
2. A heating element according to claim 1, characterized in that the electrically conductive elements (30a) in the heating element (30) are aligned in the direction of the main load, which acts on the parts (11, 12) to be welded to each other.
3. Heating element according to claim 1 or 2, characterized in that the electrically conductive elements (30a) extend electrically insulated from each other between the contact areas (35, 36) of the heating element (30).
4. Heating element according to any one of the preceding claims, characterized in that the orientation of the electrically conductive element (30a) is oriented perpendicularly to the direction X of the weld seam to be produced.
5. Heating element according to any of the preceding claims, characterized in that at least one contact surface (35, 36) is intended to contact an electrode (31, 32) that is movable relative to the heating element (30).
6. Device for joining thermoplastic parts by resistance welding, in particular for producing an aircraft, comprising a heating element (30) according to any one of the preceding claims, and
a unit (31, 32) for displacing an electrically heated region of a component (11, 12) along the component (11, 12) in a welding direction W.
7. The device according to claim 6, characterized in that the unit (31, 32) for displacing the electric heating area comprises one or more contact elements (31, 32), the contact elements (31, 32) being movable relative to the heating element (30) to continuously contact the heating element (30) at different points.
8. Device according to claim 7, characterized in that the contact elements (31, 32) are designed as roller electrodes which roll on the heating element (30) during welding, in order to continuously supply each partial region of the heating element (30) with a continuous current.
9. Device according to claim 8, characterized in that the electrically conductive element (30a) of the heating element (30) extends parallel to the rotational axis (31a, 32a) of the roller electrode (31, 32).
10. Device according to any one of the preceding claims, characterized in that one or more contact pressure elements (41, 42) press the first part (11) and the second part (12) against each other during welding in a contact pressure zone which moves synchronously with the electrically heated zone.
11. Method for joining thermoplastic parts, in particular for producing an aircraft, by resistance welding, in which method,
welding the first component (11) to the second component (12) on an electrically heated region of the components (11, 12), wherein electrically conductive elements (30a) of the heating element (30) are designed as wires or fibers, said electrically conductive elements (30a) extending parallel to one another between contact regions (35, 36) for electrically contacting the heating element (30), and
after the welding process, the heating element (30) remains between the welded components (11, 12) and forms a reinforcement therein to enhance the strength of the welded joint.
12. Method according to claim 11, characterized in that said conductive elements (30a) are aligned in the direction of the main load acting on said parts (11, 12) welded to each other.
13. Method according to claim 11 or 12, characterized in that the electrically heated area of the component (11, 12) is moved in relation to the component (11, 12) in a welding direction W during the welding.
14. Method according to any one of claims 11 to 13, characterized in that one electrode (31, 32) is moved in a welding direction W and continuously supplies an electric current to the respective partial region of the heating element (30), wherein the electrically conductive elements (30a) extend electrically insulated from one another and continuously extend perpendicularly to the welding direction W.
15. An aircraft, comprising a component, the component:
-providing a heating element (30) according to any one of claims 1 to 5; and/or
Welding using the device according to any one of claims 6 to 10; and/or
Produced using a method according to any one of claims 11 to 14.
Technical Field
The invention relates to a heating element for resistance welding thermoplastic components, in particular for producing aircraft. The invention further relates to a device and a method for joining thermoplastic parts by resistance welding, in particular for producing an aircraft, and to an aircraft.
Background
Components made of composite and/or fiber composite materials are increasingly being used for configuring modern aircraft and/or aircraft. The individual components are connected to one another, for example by riveting, adhesive, screws or welding.
The fuselage of an aircraft usually comprises a fixed frame made of stiffening elements, which supports a skin made of composite material. Stringers and frames serve as reinforcing elements, wherein the stringers extend in the longitudinal direction of the fuselage and the frames extend in the circumferential direction of the fuselage. During the production of an aircraft fuselage, the individual fuselage sections are usually produced separately from one another and subsequently joined together to form the entire fuselage.
The overlapping skin portions of the segments are often joined using rivets. However, the rivet connection is point-like and thus may cause a concentration of tension. Rivet connections are complex to produce.
In the case of adhesives, the adhesive surface has to be prepared in a complicated manner and curing of the adhesive used requires a high expenditure of time. In the case of connecting components by means of screws, drilling is required, whereby disadvantages may affect the structure of the respective component.
Document DE 102015110193 a1 describes a method for welding two parts made of thermoplastic composite material having multiple layers.
Document DE 102007003357 a1 describes the bonding of thermoplastic materials to fiber composites by means of movement welding or induction welding. For induction welding, the electrically conductive material is arranged in the joining region between the thermoplastic material and the fibre composite material.
Document EP 3040265 a1 describes a method for connecting two fuselage sections. In this case a connection frame is used.
Fig. 2 shows a known method of joining components by resistance welding. In this case, the
In the case of joining individual fuselage sections of an aircraft, the welded joint must be subjected to very high loads. Particularly in the case of fuselage lengths, for example in the range of 24 meters, a correspondingly long and very strong joint of the fuselage sections must be produced.
Furthermore, when joining the individual fuselage sections by means of resistance welding, there is the further problem that the welded joint must be produced over a long length. In the case of fuselage lengths (which may be in the range of 24 meters, for example), correspondingly long welded joints of overlapping skin sections of fuselage sections joined to one another must be produced. However, current losses may occur during resistance welding over long lengths, which results in an inefficient heating process. Also, the weld joint may be rendered uneven or defective. Furthermore, long distance welding requires high power consumption.
Disclosure of Invention
The object of the invention is to join thermoplastic parts over a length of increased strength by resistance welding, for example as required in aircraft production, in particular in the welding of fuselage sections. In particular, fuselage sections of commercial aircraft can be welded, wherein a high-quality and high-strength joint is ensured.
In order to achieve this object, the invention provides a heating element for resistance welding thermoplastic components, in particular for producing aircraft, comprising one or more electrically conductive elements which are heated when a voltage is applied to the heating element in order to weld a first component to a second component in a region which is electrically heated by the heating element, wherein the heating element is designed to remain between the welded components after the welding process and to form a reinforcement to increase the strength of the welded joint therein, and wherein the electrically conductive elements are designed as wires or fibers which extend parallel to one another between the contact regions for electrically contacting the heating element.
Large components can also be joined with high strength and low time consumption by means of a multifunctional heating element for resistance welding. In particular, in the production of aircraft, large fuselage sections can also be joined to one another to produce a fuselage with increased strength at the connecting seam.
The electrically conductive elements in the heating element are preferably aligned in the direction of the main load, which acts in particular on the components welded to one another in the mounted state of the welded components. In particular, the main load may be a traction force, which pulls apart the welding part in the mounted state.
The electrically conductive elements or fibers are aligned, for example, in the load direction of the solder joint to be produced.
In particular, the heating element and/or its electrically conductive fibers serve as reinforcing elements for components that are welded to one another after the welding process.
The electrically conductive elements advantageously extend electrically insulated from one another between the contact regions of the heating element.
The orientation of the conductive element is advantageously oriented perpendicular to the direction X of the weld seam to be produced.
For example, the heating element comprises at least one contact surface for contacting an electrode that is movable relative to the heating element.
The partial region defined in the heating element is preferably heatable by means of an electric current, the position of which in the heating element is variable during the welding process.
In particular, the heating element is located in a region outside the defined partial region, and is not heated thereby due to the current in the electrically conductive element arranged there.
The heating element is used in particular for welding a first component comprising thermoplastic material to a second component comprising thermoplastic material in a region which is electrically heated by the heating element.
The conductive elements are advantageously formed as carbon fibers.
The electrically conductive element advantageously extends beyond the heating element and forms a contact element there for the power supply.
In particular, these components are elements of an aircraft fuselage which are to be joined along a weld seam, wherein the main load is oriented, for example, perpendicular to the direction X of the weld seam. This may be the case, for example, in an aircraft fuselage longitudinal seam.
The present invention provides a multifunctional heating element which on the one hand serves to heat the weld zone during resistance welding and on the other hand forms a structural-mechanical reinforcement of the parts welded to each other. In particular, the orientation of the fibers of the heating element in the direction of the main stress or main load enables an increased load transfer capacity.
According to one aspect of the invention, a system or a device for joining thermoplastic parts by resistance welding is provided, which is particularly suitable for producing aircraft, wherein the device comprises a heating element according to the invention and particularly also a unit for displacing an electrically heated region of the part in the welding direction W along the part.
The weld joint of the thermoplastic component is thus realized in particular over a high-quality length, as is required, for example, in aircraft production, wherein the power consumption is additionally reduced and the time consumption is reduced. For example, the entire fuselage section can be joined in the longitudinal direction by welding, wherein a high quality and strength of the joint is ensured, the power consumption is reduced, and the time consumption is reduced.
Advantageously, the electrically heated region of the component is heated by a partial region of the heating element, wherein the position of the partial region in the heating element is changed during the welding process. In particular, in this case, the position is constantly changing. In particular, the unit for displacing the electric heating area during welding continuously supplies a continuous current to different partial areas of the heating element to enable the heating area to be performed or to be performed continuously.
The unit for displacing the electric heating field preferably comprises one or more contact elements which are movable relative to the heating element for continuously electrically contacting the heating element at different points.
The heating element may thus be in continuous contact and/or provide a continuous current at different areas or points during the welding process.
In particular, the contact element is in contact with the heating element during its movement and serves as a power source for the heating element. They are designed, for example, as electrodes.
The contact element is advantageously designed as a roller or roller electrode which rolls on the heating element during the welding process in order to continuously supply the respective partial region of the heating element with a continuous current.
The electrically conductive elements of the heating element advantageously extend parallel to the axis of rotation of the roller electrode. During the welding process, therefore, only locally defined, welded points are heated in the entire joint region, at which the components lie against one another or overlap one another.
For example, the device comprises one or more contact pressure elements to press the first and second parts against each other in a contact pressure area during welding, wherein the contact pressure area is movable in synchronization with the electrically heated area. The components can thus be pressed together in a targeted manner in the respective heating region in order to weld them to one another in this way.
In particular, the first and/or the second contact-pressure element is designed as a movable contact-pressure roller, or it may comprise one or more contact-pressure rollers.
In particular, devices and/or systems for resistance welding thermoplastic parts have a contact pressure unit to press the thermoplastic parts against each other during welding.
The device and/or system advantageously comprises at least one movable electrode which is moved over the contact surface of the heating element during welding to continuously provide a continuous current to the respective partial region of the heating element. In particular, the movable electrode is in this case designed as a roller, which rolls on the contact surface of the heating element during welding.
In particular, a device and/or a system for joining thermoplastic parts by resistance welding is provided, which is suitable for producing aircraft and comprises a heating element according to the invention.
According to another aspect of the invention, a device for joining thermoplastic parts by resistance welding is proposed, which is particularly suitable for producing aircraft, comprising: welding a first part comprising thermoplastic material to an electrically conductive heating element of a second part comprising thermoplastic material in an electrically heated region of the parts, and a unit for continuously displacing the electrically heated region of the parts in a welding direction W along the parts.
According to another aspect of the invention, a method of joining thermoplastic parts by resistance welding is provided, which is particularly suitable for producing aircraft, wherein a first part is welded to a second part in an electrically heated region of the parts. Wherein the electrically conductive elements of the heating element are present as wires or fibers extending parallel to each other between the contact areas for electrically contacting the heating element, and the heating element remains between the welded parts after the welding process and forms a reinforcement therein to enhance the strength of the welded joint.
The conductive elements are advantageously aligned in the direction of the main load acting on the components welded to each other.
Preferably, the electrically heated area of the component is moved relative to the component in the welding direction W during welding.
Different partial regions of the heating element advantageously provide a continuous current during the welding process to effect movement of the electrically heated region (also referred to as the weld region) relative to the component.
The electrode is advantageously moved in the welding direction W and continuously supplies a continuous current to the respective partial regions of the heating element, wherein the electrically conductive elements extend, for example, electrically insulated from one another and perpendicularly to the welding direction W.
For example, during welding, one or more contact elements or electrodes for the current supply of the heating element are moved relative to the heating element to continuously contact the heating element at different points.
The contact element is preferably in continuous electrical contact with the heating element during its movement.
During the welding process, the first part and the second part are advantageously pressed against each other in a contact pressure region, wherein in particular the contact pressure region moves relative to the part synchronously with the electric heating region.
One or more contact pressure rollers are preferably moved over the parts to be welded in order to press the parts against each other in the welding area during welding.
Furthermore, the device described herein is used for joining components, in particular fuselage sections of aircraft.
In particular, the method is carried out using a heating element according to the invention and/or using a device according to the invention.
According to a further aspect of the invention, a method for joining thermoplastic parts by resistance welding is proposed, which method is particularly suitable for producing aircraft, wherein a first part comprising thermoplastic material is welded to a second part comprising thermoplastic material in an electrically heated region of the parts, wherein the electrically heated region of the parts is moved relative to the parts in a welding direction W during the welding process.
According to a further aspect of the invention, a method for joining thermoplastic parts by resistance welding is proposed, in particular for producing aircraft, wherein a first part comprising thermoplastic material is welded to a second part comprising thermoplastic material in an electrically heated region of the parts, wherein a heating element remains between the welded parts after the welding process and forms a reinforcement or stiffening element there in order to reinforce the strength of the weld joint of the parts welded to one another.
According to a further aspect, the invention provides an aircraft having a component provided as a heating element according to the invention and/or being welded or produced using a device according to the invention or a method according to the invention.
Furthermore, an aircraft is provided, which is produced using the above-described device and/or using the above-described method.
In particular, the fuselage of an aircraft is produced in this way.
In particular, by means of the invention, during the production of an aircraft, fuselage sections can be quickly and reliably joined to one another in order to produce a fuselage. Furthermore, power consumption and current consumption during resistance welding are reduced. The power loss is minimized, since the heating takes place continuously, in particular in the respective locally defined weld zone. Furthermore, improved tolerance management can be achieved, in particular for very long solder joints. In particular, the welding process can be better controlled during continuous resistance welding. Furthermore, production time is saved by the various advantages of the present invention.
The advantages and details described in connection with the heating element according to the invention also apply to the device according to the invention and to the method according to the invention, and the advantages and details described in connection with the device according to the invention or the method according to the invention also apply to the heating element according to the invention.
Drawings
Exemplary embodiments of the present invention will be explained in more detail below based on the drawings. In the drawings:
fig. 1 schematically shows a sectional view of a preferred embodiment of a system according to the invention with a heating element according to the invention during the production of an overlap joint in the region of an aircraft fuselage;
FIG. 2 shows a schematic view of a known apparatus for resistance welding;
figures 3a and 3b schematically show a top view of the preferred embodiment of the invention shown in figure 1 during production of a weld joint of two overlapping parts;
figure 4 shows a cross-section of a multifunctional heating element according to the invention;
FIG. 5 shows a flow chart showing the steps of a method according to the invention;
FIG. 6 shows a side view of an aft fuselage section of a commercial aircraft having longitudinal seams welded in accordance with the present invention;
FIG. 7 shows a cross-sectional view of the fuselage section shown in FIG. 6 with longitudinal seams welded in accordance with the present invention;
fig. 8 shows a cross-sectional view of a longitudinal seam of a commercial aircraft welded according to the invention.
Detailed Description
Fig. 1 shows a cross-sectional view of a system or device for joining thermoplastic parts of an aircraft by means of resistance welding according to a preferred embodiment of the invention. The apparatus or resistance welding system includes an electrically
The
The
The
The electrically conductive fibers or
The
The
Two contact elements in the form of
In each case, the
The two contact elements formed as
The region or partial region heated by the current in the electrically
The
On the first side of the
On the second side of the
The contact points in the
Since the roller-shaped
The two
In the contact pressure region during the welding process, the two skin portions or
In operation, the two contact pressure elements or
Fig. 3a and 3b show a resistance welding system or an arrangement with a
The
The first or
The bottom or
The two
The two
The width of the
In order to locally join the heated soldering zones in the longitudinal direction L or X-direction (i.e. in the direction of the soldering movement W), the electrically
The
The overlapping fuselage shown in fig. 3a and 3b, which joins the two
The direction of the
Fig. 4 shows a cross-sectional view of a
The electrically conductive elements or
The joint of the two
The
In order to form a weld zone which is locally defined in the welding direction, the
During welding, the
The
After being welded together, the
When performing the method, the various parameters required for the welding process are taken into account. For example, the welding speed is preferably 100 to 350 millimeters (mm)/minute. Ceramic insulators are preferably used as the
In fig. 6 a side view of an aft fuselage section 80 of a commercial aircraft with a
In fig. 7 a cross section of the fuselage portion 80 shown in fig. 6 is shown with the location of the
Fig. 8 shows a cross-sectional view of a
After being welded together, the
The heating elements, devices and methods described above represent particularly preferred embodiments of the invention. In certain applications, it is also possible, for example, to design only one contact-pressure element as movable or as a roller, while the other, opposite contact-pressure element is stationary and forms a fixed contact-pressure surface, for example, below the overlap region of the two
Furthermore, in certain cases, it is possible, for example, to design only one electrode as movable or as a roller, while the other electrode is stationary and contacts the region of the
By thermoplastic welding, the present invention results in a weld joint area with increased strength relative to conventional joints, where only a thermoplastic matrix is used to join the components. In particular, in this way very long components (in particular fuselage sections of aircraft or commercial aircraft) can be joined to one another by means of resistance welding.
With the invention, instead of heating the entire length of the welded joint to be produced immediately, continuous heating is carried out during resistance welding by means of one or more movable elements. Thus reducing power consumption and current consumption during resistance welding.
Since the heating which takes place continuously only locally at the location of the currently heated weld zone, the power loss is minimized. In particular, very long parts (in particular fuselage sections) can be joined to one another by means of resistance welding. The tolerances of the long parts to be welded can be better handled. Due to the continuous resistance welding, the welding process can be better controlled.
Furthermore, by the method according to the invention, in particular using a multifunctional heating element, the time consumption during production of the aircraft fuselage is reduced.
List of reference numerals
11 first component/first skin component
12 second part/second skin part
30 heating element
30a conductive elements or fibres
31. 32 contact element/electrode
31a, 32a rotary shaft
34 insulator
35. 36 contact area
37. 38 terminal element
41. 42 contact pressure element or contact pressure roller
41a, 42a rotation axis
50 voltage source
80 fuselage section
81 longitudinal seam
L longitudinal direction
M main load or main load direction
W welding direction
In the X longitudinal direction
Y transverse or peripheral direction
110. 120 parts
130 heating element
131. 132 connecting clamp
133 voltage source
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