DE102016208510A1 - System and method for temporary connection of components in the assembly of aircraft components - Google Patents

Abstract

System and method for temporary connection of components (15, 17, 19) in the assembly of aircraft components (15, 17), the system comprising: a drilling template (19) temporarily attached to two aircraft components (15, 17) to be interconnected is fastened, and at least one thread-forming screw (1, 3), which is adapted to temporarily connect the two aircraft components (15, 17), and / or the drilling template (19) temporarily to the two aircraft components (15, 17) fasten.

Description

The invention relates to a system and a method for the temporary connection of components in the assembly of aircraft components.

FR 2 919 691 A1 discloses a system for connecting components in which the components can be gripped and pressed against one another by means of a pin guided through a coaxial bore in the components from the respective opposite outer sides of the components, ie compressed with high clamping force.

The invention is directed to the task of providing an economical, reliable and efficient temporary connection possibility of components in the assembly of aircraft components.

This object is achieved by a system and a corresponding method having the features of the independent claims.

The system for temporary connection of components in the assembly of aircraft components comprises a drilling template, which is temporarily attachable to two aircraft components to be joined together, and at least one thread-forming screw, which is adapted to temporarily connect the two aircraft components, and / or the drilling template temporarily attached to the two aircraft components. The use of self-tapping screws is economical, since more favorable than the solution of the above prior art allows higher biasing forces and thus a safer attachment of the components to each other, requires only one-sided access to the components and, as described in more detail below, multifunctional ,

In this case, a solid lubricant and / or a washer may be provided on an underside of the screw head. Furthermore, the screw may have a shank.

The drilling template may have at least one through hole into which the screw is insertable to temporarily secure the drilling template to the two aircraft components.

The system may additionally comprise a sleeve which is insertable into a through bore of the drilling template and either as a guide sleeve, as a holding or fastening sleeve, or as a combined guide and holding or fastening sleeve in dependence on the relative to the sleeve position of the associated the sleeve surrounded screw is formed. In this case, the guide and holding or fastening sleeve having a deflecting body, which has a first maximum outer diameter in a first state, and in a second state has a second maximum outer diameter which is greater than the first maximum outer diameter. Preferably, the sleeve reversibly takes the second state due to exclusively elastic deformation of the deflecting, so that can be returned from the second state to the first state. Preferably, the second state can be adopted by pressing the screw head of the screw against the deflecting body to deform it. Preferably, the outer edge of the underside of the screw is capable of deflecting the deflector outwardly into the second state. Alternatively, the underside of the screw is capable of compressing the deflecting body against an aircraft component while causing it to bulge outwardly to assume the second condition.

The sleeve may be provided on an underside of the screw head, wherein the sleeve is preferably attachable as a separate part of the screw or integrally connected thereto.

The sleeve may have a varying diameter along its longitudinal direction, preferably a radially projecting collar, which is designed such that it can be brought into contact with an edge of the through-hole. In this case, the sleeve may have a substantially T-shaped longitudinal cross-section. In this way, outside the through-bore, the sleeve can grip a side of the drilling template opposite the aircraft components.

The sleeve may be in two parts, and / or plastic, metal or both, and / or have a countersink.

The method for temporarily connecting components in the assembly of aircraft components uses one of the systems described above and comprises the preferably successive steps of temporarily connecting two aircraft components, and / or temporarily attaching a drilling template to the two aircraft components by means of at least one thread-forming screw, processing the two aircraft components and removing the at least one thread-forming screw.

The machining of the two aircraft components may comprise the preferably sequential steps of drilling holes in the two aircraft components and joining the aircraft components by means of fastening devices insertable into the holes.

Connecting the aircraft components by means of the fastening devices, which are rivets may include the step of riveting the aircraft components.

After removing the at least one thread-forming screw, the at least one hole which has been freed thereby can be closed by means of at least one fastening device, preferably it can be drilled and riveted.

Preferred embodiments of the invention will now be explained in more detail with reference to the attached schematic drawings. Show

1 two variants of self-tapping screws with and without shank suitable for the system and the method;

2a and 2 B a first state in which two aircraft components and a drilling template thereon are not connected to each other, and a second state in which the aircraft components by means of the self-tapping screw from 1 are temporarily connected;

2c the out 2 B shown second state, wherein on a bottom of the screw head, a washer is arranged as a surface protection element for one of the aircraft components;

3a a temporary connection of the aircraft components by means of the self-tapping screw 1 wherein a sleeve is disposed below the underside of the screw head, which is insertable into a through hole of a drilling template;

3b a modification of in 3a shown sleeve which is now brought into abutment with the wall of the through hole and on the side facing the screw head has a beveled edge;

4a a temporary connection of the two aircraft components with the drilling template by means of the screw 1 wherein the sleeve has a radially projecting collar engageable with an edge of the throughbore;

4b a modification of in 4a shown sleeve, wherein the sleeve is in two parts;

4c a modification of in 4b shown sleeve, wherein the sleeve has a countersink;

5a and 5b a first position of the sleeve relative to the screw in which the sleeve guides the surgical template and a second position of the sleeve relative to the screw in which the sleeve temporarily secures the surgical template to the two aircraft components; and

6 a suspended in a drilling template semi-automatic drill for drilling additional holes in the aircraft components, which are already connected temporarily in the state shown by means of screws and sleeves with the drilling template.

1 shows a first and a second thread-forming screw 1 . 3 , Both screws 1 . 3 have an external thread 5 , a screw head 7 with one to the respective external thread 5 directed bottom 9 and an opposite top to this 11 , The second screw 3 is different from the first screw 1 only in that they additionally have a shaft 13 has, which is between the thread 5 and the bottom 9 of the screw head 7 extends. Of course, self-tapping screws 1 . 3 can be used of any shape and size. This includes any screw head shape, e.g. B. flat head, round head, hexagon head, countersunk head, countersunk head (lens head), cylinder head, etc., and any screw head drive, z. External hexagon, external square, hexagon socket (Allen), hexagon internal (Torx), internal spline (XZN), internal square (Robertson), crosshead (Phillips and Pozidriv), head slot etc., one.

To avoid damage to components caused by such a screw 1 . 3 can be connected, the screw can 1 . 3 coated, for example with a plastic coating or adhesive, preferably on the underside 9 of the screw head 7 ,

2a shows a section of a first and a second plate-shaped aircraft component 15 . 17 , each having a prepared cylindrical bore 15a . 17a to have. The aircraft components 15 . 17 but can also be complex curved components. The first aircraft component 15 is so on the second aircraft component 17 in that their cylindrical bores 15a . 17a are aligned concentrically with each other. Furthermore, a section of a drilling template 19 with a cylindrical through hole 19a and several feet 19b shown which the drilling template 19 at a distance to the first aircraft component 15 hold. The through hole 19a may as well be from one side to the other side of the drilling template 19 tapered through hole 19a be formed and, for example, conical or funnel-shaped. 2a shows a first state in which the aircraft components 15 . 17 and the drilling template 19 still loosely on each other, which can be seen from the fact that the screw 1 . 3 is shown separately.

2 B shows a second state in which the aircraft components 15 . 17 by means of the screw 1 . 3 are connected. The screw runs 1 . 3 through the concentric holes 15a . 17a , engages with its thread 5 self-tapping in at least the second aircraft component 17 and lies with the bottom 9 of the screw head 7 on the first aircraft component 15 so that both aircraft components 15 . 17 detachable, ie temporarily, connected and pressed with high clamping force, thereby characterized in a subsequent drilling operation by the aircraft components 15 . 17 the formation of a gap and Zwischengrats can be avoided. In this case, as will be explained in more detail below, the drilling template 19 as mounting guide for additional such screws to be mounted 1 . 3 serve. Finally, there are at least two such screws 1 . 3 for fastening and aligning the aircraft components 15 . 17 required to each other.

2c shows a modification of the aircraft component connection 2 B , in which at the bottom 9 of the screw head 7 the screw 1 . 3 a washer 21 is appropriate. This may be the adjacent first aircraft component 15 from damage by the screw head 7 protect. For this purpose, in addition to or instead of the washer 21 the above-mentioned coating can be applied.

3a shows the screw 1 . 3 with a cylindrical sleeve 23 that are below the bottom 9 of the screw head 7 is arranged and the screw head 7 at a distance to the first aircraft component 15 holds. The sleeve 23 is longer than the feet 19b the drilling template 19 so the sleeve 23 as a guide for the drilling template 19 can serve. For this purpose, the sleeve 23 on at least the first aircraft component 15 by means of the screw 1 . 3 attached. So the drilling template 19 by means of their through-hole 19a on the sleeve 23 be plugged, which is why such a sleeve 23 can be referred to as a guide sleeve.

3b shows a modification of the sleeve 23 out 3a , in which 3b a sleeve 25 having an outer diameter substantially equal to the inner diameter of the throughbore 19a the drilling template 19 matches, so the sleeve 25 with the wall of the through hole 19a can be brought into contact, and at least on the screw head 7 facing side a beveled edge 25a has to plugging the drilling template 19 to facilitate. Preferably, the first aircraft component is also 15 facing edge of the sleeve 25 chastised to one of the screw 1 . 3 separate insertion of the sleeve 25 into the through hole 19a the drilling template 19 to facilitate. The sleeve shown here 25 is capable of the drilling template 19 against shifting along the aircraft components 15 . 17 to fix. This may vary depending on the mounting arrangement and orientation of the components 15 . 17 . 19 sufficient, for example when the drilling template 19 as shown here with their total weight on the aircraft components 15 . 17 rests. In this case, the attachment may be sufficient because an independent lifting the drilling template 19 even during a drilling process through the drilling template 19 unlikely or at least unproblematic. Nevertheless, in order to exclude this possibility, for example, a separate pressing device may be provided, which is the drilling template 19 in attachment to the aircraft components 15 . 17 holds.

Of course, the mentioned specific diameter and the chamfered edge can be 25a the sleeve 25 individually or individually on the sleeve 23 out 3a apply. Likewise, each of the pods 23 . 25 integral with the screw 1 . 3 be connected. Furthermore, each of the sleeve 23 . 25 be formed so that they are on the screw 1 . 3 attached laterally, in the longitudinal direction of the screw 1 . 3 pushed over or over the thread 5 can be turned on. One on the screw 1 . 3 attachable sleeve 23 . 25 offers the advantage of having the same screws 1 . 3 for connecting the aircraft components 15 . 17 (without sleeve - 2a . 2 B . 2c ) and for subsequently guiding the drilling template 19 (with sleeve - 3a . 3b ) can be used. Advantageously, for connecting the aircraft components 15 . 17 and for guiding the drilling template 19 only screws 1 . 3 with pods 23 . 25 provided so that the entire system and the associated assembly of the aircraft components 15 . 17 can be simplified. Another advantage of using one of the sleeves described above 23 . 25 is that the screw head 7 from the through hole 19a the drilling template 19 can be arranged above, whereby he, for example, to remove the screw 1 . 3 easier to access after assembly.

4a shows another sleeve 27 , which by means of a radially projecting collar 27a with an edge of the through hole 19a the drilling template 19 can be brought into contact. In this way, a positive connection between the sleeve 27 and the drilling template 19 achieved, the one insertion depth of the sleeve 27 into the through hole 19a the drilling template 19 limited. This can be the sleeve 27 have the T-shaped cross-section shown here. Likewise, the sleeve 27 have a trapezoidal or funnel-shaped or a similar tapered cross-section, if, as mentioned above, the through hole 19a the drilling template 19 has a different shape from a cylindrical shape. Such a sleeve 27 can therefore be referred to as a holding or fastening sleeve, since it by means of the screw 1 . 3 is capable of the drilling template 19 temporarily on the aircraft components 15 . 17 to fix.

4b shows a modification of in 4a shown sleeve 27 , which consists in that a two-part sleeve 29 is provided. Here is a first sleeve 31 made of metal from a second sleeve 33 enclosed in plastic. The second sleeve 33 corresponds to the sleeve 27 out 4a , being centered and perpendicular to the collar 33a that's the collar 27a in 4a corresponds, a through hole runs. In this through hole is the first sleeve 31 by means of a collar 31a on the side of the collar 33a the second sleeve 33 an insertion of the first sleeve 31 in the second sleeve 33 limited. Both pods close here 31 . 33 at the collars 31a . 33a flush with opposite sides, but this is not absolutely necessary.

4c shows a modification of in 4b shown sleeve 29 , which consists in that a two-part sleeve 35 shown with lowering. Here is a first sleeve 37 made of metal from a second sleeve 39 enclosed in plastic. The second sleeve 39 corresponds largely to the sleeve 33 out 4b , being centered and perpendicular to the collar 39a that's the collar 33a in 4b corresponds, a two-stage through hole runs. This as a reduction 41 designated first gradation is such that from the collar side of the second sleeve 39 centered and perpendicular to the collar 39a a through hole of decreasing diameter is present, this diameter reduction, as shown here, may be stepwise or stepwise or continuously. The first sleeve 37 has one of the first sleeve 31 out 4b similar shape, so that they due to the tapered diameter of the through hole of the second sleeve 39 also from the side of the collar 39a only up to a certain depth in the second sleeve 39 can be introduced. There is a collar 31a the first sleeve 31 out 4b similar collar 37a the first sleeve shown here 37 unlike in 4b within the through hole of the second sleeve 39 , In this way, the screw head 7 within the sink 41 sunk and protected.

While the aforementioned sleeves 23 . 25 . 27 are made of plastic to protect the components from damage, the sleeves can also be made of metal, ceramic or a composite material with the aforementioned materials. Due to the reduction in hardness from the inside to the outside, in the case of the two-part sleeve 29 . 35 an improved power transmission of the screw 1 . 3 be achieved. Of course, in the 4b and 4c described division into the sleeves 23 . 25 in the 3a and 3b be applied without a collar. In addition, as already in relation to the 3a and 3b mentioned, the outer edge on the respective collar 27a . 33a . 39a opposite side of the respective sleeve 27 . 29 . 35 Be prepared for the sleeve 27 . 29 . 35 easier in the through hole 19a the drilling template 19 to be able to introduce.

5a shows another sleeve 43 that differs from the above sleeves in that they have a cylindrical base body 45 and an adjoining elastic deflecting body 47 having. The latter is in cross section along a longitudinal axis of the sleeve 43 shaped like a hook to the outside, a central one continuously knows from the deflection body end to the main body 45 tapered bore 49 initially having a diameter greater than the diameter of the screw head 7 is and continuously tapers to a diameter smaller than the diameter of the screw head 7 is. The first position of the sleeve shown here 43 to the screw head 7 is such that both do not touch, so are spaced apart. The sleeve 43 serves in this first position preferably exclusively as a guide sleeve for the drilling template 19 , wherein preferably both aircraft components 15 . 17 by means of the screw 1 . 3 are connected.

5b shows the sleeve 43 out 5a in a second position, in which the screw head 7 by means of the in the aircraft components 15 . 17 screwed in 1 . 3 the deflecting body 47 out into a sleeve 43 essentially urges and biases radial direction, so that the drilling template 19 at the two aircraft components 15 . 17 is attached. The sleeve 43 serves in this second position preferably exclusively as a holding or mounting sleeve, preferably both aircraft components 15 . 17 by means of the screw 1 . 3 are connected.

Once the screw head 7 the screw 1 . 3 from the deflector 47 is spaced, takes the deflection 47 his off 5a known starting form and can be reused. For this purpose, the deflecting body 47 be made of an elastic material. Preferably, the deflecting body 47 to the body 45 pieced to give improved deflection in the 5b to reach the second position shown. Of course, here too for easier insertion of the sleeve 43 into the through hole 19a the drilling template 19 the outer edge of the body 45 at its the deflection body 47 to be feasted on the opposite side.

Alternatively to the in the 5a and 5b shown sleeve 43 can the deflecting body 47 be substantially cylindrical rather than hook-shaped and an inner diameter smaller than the outer diameter of the screw head 7 is. Now approaches the screw head 7 the deflection section 47 on, so the deflection section 47 either deflected or compressed to create an outer camber, whereby the drilling template 19 on the aircraft component 15 . 17 is attached. Thus, the bottom is 9 the screw 1 . 3 capable of deflecting 47 against an aircraft component 15 to push and thereby deflect outward or arch to take the second state.

6 serves to illustrate the process. It shows the aircraft components 15 . 17 and the drilling template 19 with several through holes 19a and already mounted screws 1 . 3 with the guide sleeve 23 and with the holding or fastening sleeve 27 , A semi-automatic drilling machine shown here 51 can pierce the aircraft components 15 . 17 and thus creating additional holes through the through-holes 19a the at the aircraft components 15 . 17 attached drilling template 19 be used. For this purpose, the drill 51 into the drilling template 19 be hung and locked with this.

• – Temporäres Verbinden zweier Flugzeugbauteile 15, 17, und/oder temporäres Befestigen einer Bohrschablone 19 an den zwei Flugzeugbauteilen 15, 17 mittels mindestens der gewindefurchenden Schraube 1, 3 und vorzugsweise einer Hülse 23, 25, 27, 29, 35, 43;
• – Bohren von Löchern in die zwei Flugzeugbauteile 15, 17;
• – vorzugsweises Lösen und Entfernen der Bohrschablone 19 von den Flugzeugbauteilen 15, 17;
• – Vernieten der Flugzeugbauteile 15, 17 durch die gebohrten Löcher hindurch;
• – Entfernen der mindestens einen gewindefurchenden Schraube 1, 3 und der vorzugsweise vorhandenen Hülse 23, 25, 27, 29, 35, 43; und
• – Vernieten der Flugzeugbauteile 15, 17 durch das mindestens eine freigewordene Loch.

The method comprises the following steps:

• - Temporarily connecting two aircraft components 15 . 17 , and / or temporarily attaching a drilling template 19 at the two aircraft components 15 . 17 by means of at least the thread-forming screw 1 . 3 and preferably a sleeve 23 . 25 . 27 . 29 . 35 . 43 ;
• - Drilling holes in the two aircraft components 15 . 17 ;
• - Preferably loosening and removing the drilling template 19 from the aircraft components 15 . 17 ;
• - Riveting the aircraft components 15 . 17 through the drilled holes;
• - Remove the at least one thread-forming screw 1 . 3 and the sleeve preferably present 23 . 25 . 27 . 29 . 35 . 43 ; and
• - Riveting the aircraft components 15 . 17 through the at least one vacant hole.

A particular advantage of using the screw 1 . 3 and sleeve 43 from the 5a . 5b and the alternative described above is that a system of screw 1 . 3 and sleeve 43 for connecting the aircraft components 15 . 17 and attaching the drilling template 19 and at the same time for subsequent attachment of the drilling template 19 at the aircraft components 15 . 17 can be used. This is the screw 1 . 3 only different distances in the aircraft components 15 . 17 screwed to between a guide for attaching and removing and an attachment of the drilling template 19 to change for drilling holes and riveting. In this way, the number of screws can be reduced and the assembly of aircraft components 15 . 17 be simplified.

• – Temporäres Verbinden zweier Flugzeugbauteile 15, 17 mittels mindestens zwei gewindefurchender Schrauben 1, 3, wobei sich jeweils eine Hülse 43 unterhalb eines Schraubenkopfs 7 auf der Schraube 1, 3 befindet,
• – Aufstecken einer Bohrschablone 19 mittels dafür vorgesehener Durchgangsbohrungen 19a auf die Hülsen 43,
• – Vollständiges Eindrehen der Schrauben 1, 3 gegen einen Auslenkkörper 47 der Hülsen 45, um die Bohrschablone 19 temporär an den zwei Flugzeugbauteilen 15, 17 zu befestigen;
• – Bohren von Löchern in die zwei Flugzeugbauteile 15, 17 durch weitere vorgegebene Durchgangsbohrungen 19a in der Bohrschablone 19;
• – Teilweises Herausdrehen der Schrauben 1, 3, um die Bohrschablone 19 von den Flugzeugbauteilen 15, 17 zu entfernen, wobei die Schrauben 1, 3 die Flugzeugbauteile 15, 17 weiterhin verbinden;
• – Vernieten der Flugzeugbauteile 15, 17 durch die gebohrten Löcher hindurch;
• – Entfernen der Schrauben 1, 3 und Hülsen 43; und
• – Vernieten der Flugzeugbauteile 15, 17 durch die freigewordenen Löcher hindurch.

Such a method, that of a system with the aforementioned sleeve 43 Use has the following steps:

• - Temporarily connecting two aircraft components 15 . 17 by means of at least two thread-forming screws 1 . 3 , each with a sleeve 43 below a screw head 7 on the screw 1 . 3 is,
• - Attaching a drilling template 19 by means of provided through holes 19a on the sleeves 43 .
• - Completely screwing in the screws 1 . 3 against a deflecting body 47 the sleeves 45 to the drilling template 19 temporarily at the two aircraft components 15 . 17 to fix;
• - Drilling holes in the two aircraft components 15 . 17 through further predetermined through holes 19a in the drilling template 19 ;
• - Partial unscrewing of the screws 1 . 3 to the drilling template 19 from the aircraft components 15 . 17 to remove, taking the screws 1 . 3 the aircraft components 15 . 17 continue to connect;
• - Riveting the aircraft components 15 . 17 through the drilled holes;
• - Remove the screws 1 . 3 and pods 43 ; and
• - Riveting the aircraft components 15 . 17 through the vacated holes.

QUOTES INCLUDE IN THE DESCRIPTION

This list of the documents listed by the applicant has been generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Cited patent literature

• FR 2919691 A1 [0002]

Claims (10)

System for temporary connection of components ( 15 . 17 . 19 ) in the assembly of aircraft components ( 15 . 17 ), comprising: - a drilling template ( 19 ) temporarily on two aircraft components to be interconnected ( 15 . 17 ), and - at least one thread-forming screw ( 1 . 3 ), which is adapted to handle the two aircraft components ( 15 . 17 ) temporarily connect, and / or the drilling template ( 19 ) temporarily on the two aircraft components ( 15 . 17 ) to fix. System according to claim 1, wherein on a lower side ( 9 ) of the screw head ( 7 ) a solid lubricant and / or a washer ( 21 ) is provided, and / or the screw ( 3 ) a shaft ( 13 ) Has. System according to claim 1 or 2, wherein the drilling template ( 19 ) at least one through-hole ( 19a ) into which the screw ( 1 . 3 ) is insertable to the drilling template ( 19 ) temporarily on the two aircraft components ( 15 . 17 ) to fix. System according to claim 3, wherein on a lower side ( 9 ) of the screw head ( 7 ) a sleeve ( 23 . 25 . 27 . 29 . 35 . 43 ) is provided, which is designed in such a way that it into the through hole ( 19a ) is insertable, wherein the sleeve ( 23 . 25 . 27 . 29 . 35 . 43 ) preferably as a separate part on the screw ( 1 . 3 ) attachable or integrally connected thereto. System according to claim 4, wherein the sleeve ( 27 . 29 . 35 ) a radially projecting collar ( 27a . 33a . 39a ), which is designed such that it with an edge of the through hole ( 19a ) can be brought into contact. A system according to claim 4 or 5, wherein the sleeve ( 29 . 35 ) is in two parts, and / or is made of plastic, metal or both, and / or a countersink ( 41 ) Has. Method for temporarily connecting components ( 15 . 17 . 19 ) in the assembly of aircraft components ( 15 . 17 ), wherein a system according to one of the preceding claims is used and the method preferably comprises the following steps: - temporary connection of two aircraft components ( 15 . 17 ), and / or temporarily attaching a drilling template ( 19 ) on the two aircraft components ( 15 . 17 ) by means of at least one thread-forming screw ( 1 . 3 ); - editing the two aircraft components ( 15 . 17 ); and - removing the at least one thread-forming screw ( 1 . 3 ). The method of claim 7, wherein the processing of the two aircraft components ( 15 . 17 ) comprising preferably successive steps: - drilling holes in the two aircraft components ( 15 . 17 ); and - connecting the aircraft components ( 15 . 17 ) by means of attachable into the holes fasteners ( 1 . 3 ). The method of claim 8, wherein connecting the aircraft components ( 15 . 17 ) by means of the fasteners, which are rivets, comprising the step: - riveting the aircraft components ( 15 . 17 ). Method according to one of claims 1 to 9, wherein after removing the at least one thread-forming screw ( 1 . 3 ) the at least one vacant hole is closed by means of a fastening device, preferably by being drilled and riveted.

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