DE102008020614A1 - Method of inserting a socket into a component and socket - Google Patents

Abstract

The invention relates to a method for inserting a socket (4) in a component (1) and a corresponding socket. In order to simplify the insertion of the bushing into the component and to reduce the costs for tools and the expenditure of time, in particular with CFRP components, it is proposed according to the invention that the method comprises the steps of producing a through-bore (3) in the component for the bushing (4) having a predetermined diameter larger than the outer diameter of the bushing (4) so that a clearance (10) remains between the member (1) and the bushing (4), inserting the bushing (4) into the throughbore (3) and filling the gap (10) with a filling material. The corresponding bushing has at least one channel (11) in the flange (7) and / or the sealing element (5) for injecting filler material into an intermediate space (10) between the bushing (4) and the component (1).

Description

The Invention relates to the form-fitting Put together of components and in particular, but not exclusively Method for inserting a bush into a component according to the preamble of claim 1, and a bushing with sealing element for insertion in a component according to the preamble of claim 7.

At the Put together components of, for example, an aircraft, it is for certain components such as B. the vertical tail is common, in both components bushings bring. The connection of the components is then done by pins, bolts, screws, etc., which are through extend the jacks of two components joined together. The Inserting bushes, in particular in carbon fiber reinforced (CFRP) components takes place today in a very elaborate and lengthy process with the operations Drilling, spindling, rubbing and pressing the bush into the component. Not less than seven different tools like drills and cutters and an extremely massive drill rig with high forces are used for putting the current hull connection sockets needed in a rudder. in the For example, in the process, the following operations are performed: 1. In a milling machine Core drillings are made in the component with a first tool. 2. In a drilling rig, the holes are drilled with a second tool spindled twice, rubbed once with a third tool and with a fourth and fifth Tool lowered. 3. The sockets will then be in the same drilling position pressed in the component. 4. Thereafter, in the drilling stand the Bushings with a sixth tool spindled and with a seventh tool planned. The requirements for the accuracy of the bore and the Pressing the bushes are very high, and the wear of the tools is significant due to the properties of CFRP material. Accordingly high are the costs incurred by the consumption of tools.

task The invention is the process for joining components, in particular CFRP components using socket connections to make it easier and the cost for tools as well as reduce the time required.

These The object is achieved by the method for inserting a socket into a component according to claim 1 or through the bushing with a sealing element according to claim 7. Preferred embodiments The invention are the subject of the respective subclaims.

The Invention is not to bring the bore in the component to nominal size and then squeeze the bushes, but the hole with the core drill a bit bigger (approx. 1.5 mm), so that the socket has a remaining one after insertion has little play. An injection is thus eliminated, the socket can easily set by hand or automatically without much effort become. Then the set socket is received in a device and fixed so that they are the best position for later fuselage connection has. Before the bush with the union nut from the opposite side is screwed, the remaining gap between socket and Component with a filling compound (Shim mass, quick shim) filled, which is then cured. The padding with filling material can be done in several ways, eg. B. via injection on the component or over channels in the socket. After curing The shim is used for spindling and planning the bushing.

The inventive method to insert a socket into a component, the steps include: Generating a through hole in the component for the socket with a predetermined diameter that is larger than the outer diameter the socket, leaving a gap between the component and the Socket remains, insert the bush in the through hole and filling the gap with a filling material.

• – der vorgegebene Durchmesser der Durchgangsbohrung zwischen 1 mm und 2 mm und insbesondere 1,5 mm größer als der Außendurchmesser der Buchse ist;
• – das Einfügen der Buchse umfasst: Ausrichten der Buchse in der Durchgangsbohrung in eine gewünschte Richtung, Fixieren der Buchse in einer Haltevorrichtung und Verschrauben der Buchse mit einer Überwurfmutter;
• – das Auffüllen des Zwischenraums mit Füllmaterial ein Einspritzen über Kanäle im Bauteil umfasst;
• – das Auffüllen des Zwischenraums mit Füllmaterial ein Einspritzen über Kanäle in der Buchse und/oder der Überwurfmutter umfasst;
• – das Bauteil besteht aus einem kohlefaserverstärkten Kunststoff.

In a preferred embodiment, this is realized as a further feature or - as far as is technically possible and meaningful - as further features that:

• - The predetermined diameter of the through hole between 1 mm and 2 mm and in particular 1.5 mm is greater than the outer diameter of the bushing;
• - The insertion of the socket comprises: aligning the socket in the through hole in a desired direction, fixing the socket in a holding device and screwing the socket with a union nut;
• - the filling of the intermediate space with filling material comprises an injection via channels in the component;
• - the filling of the intermediate space with filling material comprises an injection via channels in the bushing and / or the union nut;
• - The component consists of a carbon fiber reinforced plastic.

The corresponding socket according to the invention with sealing element for insertion into a component, wherein the socket at one end comprises a flange and at an opposite end a sealing element is characterized by at least a channel in the flange and / or the sealing element for injection of filler material in a gap between the socket and the component.

Preferably has the at least one channel for injecting filler in the flange and / or the sealing element a distance from one Pipe section of the bushing, which is between 1 mm and 2 mm.

In a further preferred embodiment the bushing comprises an outer thread at an end opposite the flange, on that as a sealing element a union nut is screwed on.

advantages the invention are u. a. that fewer tools are needed. Further, re-alignment of the socket is due to its play in the bore even after insertion into the component possible. This vice versa means that the initial drilling is no longer so demanding in Terms of a precise Meet alignment must, but that the alignment if necessary, corrected later can be.

Further Features and advantages of the invention will become apparent from the following DESCRIPTION OF PREFERRED EMBODIMENTS Referring to FIG is attached to the Drawing.

1 shows a center box of a vertical stabilizer with longitudinal force fittings, to which the invention is applicable, in perspective view.

2 shows part of the center box 1 in magnification, in perspective view.

3 shows a socket according to the prior art in cross section.

4 shows an embodiment of the socket according to the invention in cross section.

5 shows the embodiment of the socket according to the invention in the installed state in a perspective view.

The Drawing is not to scale. Same or like elements are given the same reference numerals, unless stated otherwise.

In 1 is a center box 1 a rudder of an aircraft shown. Around this center box 1 To firmly connect with the fuselage (not shown) of the aircraft are on one side of the center box 1 Lugs attached, which absorb the force acting on the compound longitudinal force. The tabs 2 are therefore referred to as longitudinal power fittings.

They are preferably at the center box 1 welded or are a part of the same.

In the longitudinal power fittings 2 are through holes 3 provided, the (not shown) receive connecting pin accurately, which ultimately connect to (complementary longitudinal force fittings on) to the fuselage.

The center box 1 is produced on modern aircraft made of carbon fiber reinforced plastics (CFRP). The connecting bolts are usually made of titanium. The bolt must be in the through hole 3 be recorded accurately. If this is not the case, then it (small) movements of the bolt in the hole 3 so that it is knocked out after some time and so the accuracy of fit decreases increasingly with time. Therefore, the hole 3 in the center box 1 lined with a metal bush whose inner diameter substantially coincides with the outer diameter of the bolt. Inserting the metal bush in the through hole 3 The prior art will be briefly explained below.

• – Aufbohren der Längskraftbeschlagsbohrung 3,
• – Senken der Bohrung 3,
• – Einpressen, Verschrauben und Spindeln der Längskraftbeschlagsbuchsen 4,
• – Entfernen von (nicht dargestellten) Aufnahme- und Führungslöchern (AFL).

With the longitudinal force fittings 2 The vertical stabilizer is bolted to the fuselage section of the aircraft. For this are longitudinal force fitting bushes 4 introduced into the component. The essential steps are automated. The production plant is a drilling rig. With him are the holes 3 machined for the longitudinal force fitting bushes and the sockets 4 pressed. The boring stands for the assembly of central boxes 1 The vertical stabilizers are identical in design for single aisle (SA) aircraft and twin aisle (TA) aircraft, but it is possible for them to be used in a 90 ° rotated position. They each have two workplaces where the longitudinal force fittings 2 can be edited. In the drilling stand, after testing and measuring, the following operations are performed on the structure:

• - Drilling the longitudinal force fitting hole 3 .
• - Lowering the bore 3 .
• - Pressing, screwing and spindling of the longitudinal force fitting bushes 4 .
• - Remove (not shown) receiving and guiding holes (AFL).

For "twin aisle" aircraft deleted the last step, since the receiving and guide holes for the referencing in another Processing steps still needed become.

Checking and measuring the positions for the longitudinal force fitting bushes 4 runs as follows: The longitudinal force fittings 2 are pre-drilled in the shell production, so that the components with pre-drilled holes (VBL) 3 come to the assembly station equipped. Before the longitudinal force fitting holes 3 can be introduced or the Vorbohrlöcher be drilled, the exact hole positions must be determined. This is done by means of (not shown) buttons. Such a probe is used for this purpose in the drilling. The drill bit uses the probe to check the position of the pilot holes and determine the exact position of the longitudinal fitting holes 3 , Since the rudder is connected to the fuselage via the longitudinal force fitting bushes, very high demands are placed on the quality of the bore.

The boring of the longitudinal fitting hole is as follows: With the drill stand, the holes for the longitudinal force fitting bushes 4 reworked. For this purpose, several tools are used successively in the drill stand, with which the respective processing is performed. These tools include tool carriers equipped with multiple indexable inserts. To the holes 3 To approximate the final gauge, they are drilled with a boring head. Subsequently, the holes are machined with a so-called. Reibwerkzeug. The hole is finished with the reaming tool. The reaming tool is similar to a drill bit, but with the reaming tool the cutters are also on the circumference and not just on the tip as in the drill. Reaming tools may have different cutting shapes, either spiral shaped (as in a drill) or grooved. When working with the reaming tool, only a few tenths of a millimeter of material is removed in the hole, the hole is then a perfect fit and has a high surface quality. In addition, higher accuracies are achieved with respect to the shape tolerances. Overall, a grated hole has a more accurate roundness and has a higher cylindricity than a drilled hole.

The lowering of the hole joins it as another step. In this step, the bore is lowered from both sides. The counterbores are introduced to facilitate the insertion of the longitudinal force fitting bushes. The self-injection, the screwing and the spindle of the longitudinal force fitting bushings take place in the following manner: The longitudinal force fitting bushes 4 are made of titanium. They consist of two parts, a socket 4 and a sealing element, in particular a nut 5 , They are pressed into the holes and bolted together with a prescribed torque. Any existing material overhang 8th at the edge of the bushes 4 is milled away. Last, the jacks 4 spindled to final dimensions. The bushings 4 have a flange 7 , It serves as a guard ring, as at this point later fuselage and rudder lie together. The flange 7 It can absorb the high frictional forces between both sections, thus protecting the surface of the longitudinal force fitting 2 before wear.

• – Erzeugen einer Durchgangsbohrung 3 in jedem Bauteil für eine Buchse 4 zum Aufnehmen des Verbindungsbolzens,
• – Oberflächenbearbeiten der Innenfläche der Durchgangsbohrung 3 für die Aufnahme der Buchse 4, so dass die Durchgangsbohrung 3 einen kreisförmigen Querschnitt aufweist, und
• – Einfügen der Buchse 4 in der Durchgangsbohrung 3.

In other words, the method according to the prior art for producing a positive connection of at least two CFRP components 1 essentially has the steps:

• - Create a through hole 3 in each component for a socket 4 for receiving the connecting bolt,
• - Surface treatment of the inner surface of the through hole 3 for receiving the socket 4 so that the through hole 3 has a circular cross-section, and
• - Insert the socket 4 in the through hole 3 ,

The result of the above operations is in 3 shown. The socket 4 is in the fastening tab 2 pressed. Apart from friction and sticking in the tab 2 she is in the tab 2 through a flange 7 on both sides of the hole 3 held. The flange 7 is stuck on one side with a pipe section 6 the socket 4 connected, on the other side of the pipe section 6 becomes the flange 7 on the jack protrusion 8th , about the hole 3 protrudes, placed separately or is screwed in particular as a union nut.

After inserting the socket 4 with the pipe section 6 into the hole 3 and attaching the flanges 7 become in a final step, the usually still existing jack projections 8th milled off so that the surface of the longitudinal force fitting 2 plan is. Thus, in a process according to this state of the art relatively diverse and laborious steps are necessary.

According to the invention, this complex process can surprisingly be simplified by the fact that the through hole 3 is provided with a predetermined diameter which is larger than the outer diameter of the bushing 4 , This will be in 4 clear. Due to the different diameter of bushing 4 and bore 3 stays next to the jack 4 in the material of the center box 1 a gap 10 between the component 1 and the socket 4 free. In this way, the insertion of the socket can be 4 into the hole 3 simplify, and by the resulting play of the socket in the bore can be the socket 4 still later in the hole 3 align. On the other hand, however, a sufficient strength and thus resilience of the socket 4 in the hole 3 to ensure the gap becomes 10 filled with a (not shown) filling material. This filling material can, for example, via a channel 11 in the flange 7 the socket 4 in the gap 10 be injected. Analog can be in the union nut 5 that the flange 7 opposite to an external thread de 9 of the pipe section 6 the socket 4 is screwed on, a channel 12 be provided by the additional or alternative filler in the space 10 can be injected. The filling material is in particular a so-called shim material, wherein the shim material is preferably fast-curing. In this way it is ensured that the socket can be aligned, then shim material into the gap 10 can be injected, which hardens quickly, and then the socket is fully loadable.

When curing the shim material is the socket 4 preferably fixed in a (not shown) holding device, and then the socket 4 with the union nut 5 screwed. Should the jack 4 After alignment slightly inclined to the surface, in a further processing step, the surface of the longitudinal force fitting 2 then still be milled plan.

In 5 is a perspective view of the socket 4 shown after being in the longitudinal power fitting 2 used, aligned and fixed with filler. Visible is the borehole 3 in the fitting 2 and the flange 7 the socket 4 , In the flange 7 there are injection openings 13 for the filling material. After a final surface finish, the socket closes 4 plan with the surface of the tab 2 from.

The distance of the injection holes 13 from the hole 3 is preferably between 1 mm and 2 mm and in particular less than 1.5 mm, so that the predetermined diameter of the through hole 3 essentially 1.5 mm larger than the outer diameter of the bushing 4 without flange 7 is, ie as the outer diameter of the pipe section 6 ,

However, the invention is not limited to that of the filling material via the channels 11 and 12 in the flange 7 or the union nut 5 the socket 4 be injected. Instead, filling up the gap 10 with filling material also via channels (not shown) in the component 1 yourself.

A socket according to the invention with a union nut for receiving a connecting bolt is with channels 11 respectively. 12 Mistake. Consequently, the socket comprises 4 at one end of the pipe section 6 a flange 7 and at an opposite end of the pipe section 6 an external thread 9 for the union nut 5 , In the flange 7 or in the union nut 5 is at least one channel 11 . 12 for injecting filler into a space 10 next to the socket 4 , In the embodiment according to 5 Four channels are symmetrical around the pipe section 6 arranged around.

Of the inventive process is opposite The process of the prior art significantly shortened. 1. In the milling machine The core holes are made in the component with a first tool and lowered the hole with a second tool. 2. The socket is used (if necessary without tools) and fixed in the device (best fit). 3. For gap compensation, a filling compound (Shim) is filled and hardened. In a drilling stand, the bush is spindled with a third tool and subsequently planned with a fourth tool.

It is understood that the invention described herein is not limited to aircraft and not to the connection of a rudder with a fuselage. Instead, the invention may also find application in the absorption of shear forces and in all component connections where a highly accurate fit of connecting bolts is necessary. In addition, the invention is particularly advantageous applicable to components made of CFRP material, but it can just as well be used for components made of aluminum. Furthermore, the invention is not limited to bushings with union nut, instead, a smooth-walled socket can be used, in which the gap 10 between the socket and the component is closed by a pressed-on lid or other sealing device.

1

center box a rudder, in particular CFRP, CFRP component

2

Longitudinal force fitting, mounting tab

3

Through Hole in longitudinal power fitting, fastening strap

4

Rifle for receiving a connecting bolt

5

sealing, in particular union nut

6

pipe section from socket

7

flange from socket

8th

Liner protrusion

9

external thread from socket

10

gap between socket and component

11

Injection channel in flange

12

channel in union nut

13

Opening of Injection channel

Claims (9)

Method for inserting a socket ( 4 ) into a component ( 1 ) comprising the steps of: creating a through-bore ( 3 ) in the component for the bushing ( 4 ) having a predetermined diameter which is larger than the outer diameter of the bushing ( 4 ), leaving a gap ( 10 ) between the component ( 1 ) and the socket ( 4 ver remains, insert the socket ( 4 ) in the through hole ( 3 ) and filling the gap ( 10 ) with a filler. The method of claim 1, wherein the predetermined diameter of the through-hole ( 3 ) between 1 mm and 2 mm and in particular 1.5 mm larger than the outer diameter of the bushing ( 4 ). The method of claim 1 or 2, wherein inserting the socket comprises: aligning the socket in the throughbore ( 3 ) in a desired direction, fixing the bushing ( 4 ) in a holding device and screwing the bushing ( 4 ) with a union nut ( 5 ). Method according to one of the preceding claims, in which the filling of the intermediate space ( 10 ) with filling material an injection via channels in the component ( 1 ). Method according to one of claims 1 to 3, wherein the filling of the gap ( 10 ) with filling material an injection over channels ( 11 ) in the socket and / or the union nut ( 5 ). Method according to one of the preceding claims, in which the component ( 4 ) consists of a carbon fiber reinforced plastic. Socket with sealing element for insertion into a component ( 1 ), the bushing ( 4 ) at one end a flange ( 7 ) and at one opposite end a sealing element ( 5 ), characterized by at least one channel ( 11 ) in the flange ( 7 ) and / or the sealing element ( 5 ) for injecting filler into a space ( 10 ) between the bush ( 4 ) and the component ( 1 ). A bushing with a sealing member according to claim 7, wherein the at least one channel ( 11 . 12 ) for injecting filler material into the flange ( 7 ) and / or the sealing element ( 5 ) a distance from a pipe section ( 6 ) of the socket ( 4 ), which is between 1 mm and 2 mm. Socket with a sealing element according to claim 7 or 8, wherein the bushing ( 4 ) on a flange ( 7 ) opposite end an external thread ( 9 ), as a sealing element ( 5 ) a union nut is screwed on.