WO2015038042A1 - Aircraft section shafts forming a common shaft and method for assembly - Google Patents

Aircraft section shafts forming a common shaft and method for assembly Download PDF

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Publication number
WO2015038042A1
WO2015038042A1 PCT/SE2013/051060 SE2013051060W WO2015038042A1 WO 2015038042 A1 WO2015038042 A1 WO 2015038042A1 SE 2013051060 W SE2013051060 W SE 2013051060W WO 2015038042 A1 WO2015038042 A1 WO 2015038042A1
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WO
WIPO (PCT)
Prior art keywords
section
shaft
aeronautical
sections
join
Prior art date
Application number
PCT/SE2013/051060
Other languages
French (fr)
Inventor
Mats ENMAR
Original Assignee
Saab Ab
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Saab Ab filed Critical Saab Ab
Priority to PCT/SE2013/051060 priority Critical patent/WO2015038042A1/en
Publication of WO2015038042A1 publication Critical patent/WO2015038042A1/en

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64FGROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces and the like
    • B64C1/06Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068Fuselage sections
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces and the like
    • B64C1/06Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068Fuselage sections
    • B64C1/069Joining arrangements therefor
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings

Abstract

The present invention regards an aeronautical structural section (3) provided for assembly with a mating section (3", 4), the section (3) comprises end portions (17a, 17b) adapted for join-up with said mating section (3", 4). The (3) comprises an elongated shaft-like element (7) exhibiting a first shaft entry (19a) and a second shaft entry (19b), each of which are provided in the respective end portion (17a, 17b). It also regards an aeronautical structure join-up comprising a plurality of sections (3) having shafts, wherein the sections (3) are arranged to each other for forming a common shaft. The present invention also regards a method for join-up of sections (3, 4) having channels together forming a common shaft (10) of the assembled join-up. It has steps of providing the sections (3, 4) comprising the elongated shaft-like elements (7); positioning the sections (3, 4) for join-up; and joining the sections (3, 4) to each other in such way that an entry (19a) of an element (7) of a first section (3) faces an entry (19b) of an element (7) of a joined second section (4) so that the elements (7) form a common shaft-like element (10).

Description

Aircraft section shafts forming a common shaft and method for assembly TECHNICAL FIELD

The present invention relates to an aeronautical structural section provided for assembly with a mating section according to the pre-characterizing part of claim 1. The present invention also relates to an aeronautical structure join-up comprising a plurality of aeronautical structural sections. It also relates to a method for assembly of an aeronautical structure according to claim 12.

The invention relates to the aeronautical industry and to aircraft industry especially. However, the invention is not limited thereto. Preferably, the invention relates to automatized production of aeronautical structures.

BACKGROUND ART

Current technology is commonly based on fitting aircraft with electric wires in an outfitting procedure after that the sections have been assembled. There is shown in US 6 237 210 a fuselage, wherein the wires are installed separately after assembly.

Prior art mounting of aircraft also implies that the aircraft structure (frames, stringers, spares, etc.) during production often forms a framework prior the mounting of cabling. The mounting of cabling is thus dependent upon how the framework of the aircraft structure is designed. Cabling is often drawn crisscrossing through the structure, passing a frame and around a spare, under a bracket etc., dependent upon mounting personell efforts. An object is to provide an aeronautical structural section that implies cost-effective production of aerial vehicles.

An object is to provide a structural section provided for assembly with a mating section, wherein the cabling (and/or other elongated communication objects) can be mounted in a time saving and controlled manner.

An object is to provide easy access to the interior of the structure during the assembly. The foregoing and other objects and advantages of the present invention will be apparent to those skilled in the art, in view of the following detailed description, taken in conjunction with the appended claims and the accompanying drawings.

SUMMARY OF THE INVENTION

This has been solved by the fixture device mentioned in the introduction, which fixture device being defined by the features claimed in the characterizing part of claim 1.

In such way is provided manufacture of a structure (i.e. an aircraft fuselage), which manufacture is cost-effective and time saving. Thus is also provided that an aeronautical structure can be manufactured separately, wherein cabling and pipes being installed in the elongated shaft-like elements of the separately manufactured aeronautical structure. The aeronautic structure is thus ready to be mounted to a mating structure comprising means for cabling etc.

Preferably, the finished aeronautical structural section being sealed and thereafter transported to another assembly station (of another manufacturer), wherein the finished aeronautical structural section will be assembled with the mating section. The cabling and pipes of each elongated shaft-like element may exhibit standardized couplings, which are connectable to mating cabling and pipes of the mating elongated shaft-like element of the mating section. The inventive solution provides that no mess up of cables and pipes being present in the structure with cables run crisscrossing through the structure. On the contrary, by the invention there is provided an aeronautical structure having cabling and pipes at predetermined locations in the aeronautical structure. In such way the aeronautical structure is cost-effective to manufacture. It is also efficient to provide maintenance and servicing for repair and exchange of cabling. Service personnel can, for example, open a service door being provided in the structure outer skin (as a wall portion of the shaft-like element).

Preferably, the elongated shaft-like element is formed as a channel or an elongated basketlike tunnel, wherein the tunnel walls and/or channel walls serve as strengthening portions of the aeronautical structural section. Suitably, the elongated shaft-like element serves as a guide element arranged for guidance of the cabling and/or pipes during mounting.

Preferably, the elongated shaft-like element being an integrated portion of the structural aeronautical section.

In such way is achieved that weight is saved at the same time as cabling and pipes will have a pre-determined position (already at the drawing table the designer takes into account the cabling and pipes position) and no additional cut out has to be made to the structure. Preferably, strengthening stringers may extend along the elongated shaft-like element and bond to the wall of the latter.

Suitably, at least one of the shaft entries being adapted to be sealed with a cover. Thereby is achieved that the interior of the elongated shaft-like element is protected from dust and other unwanted objects. The cabling and/or pipes are thus, after removing the cover, ready to be mounted in a clean environment of the structural aeronautical section.

Preferably, the elongated shaft-like element embodies cabling and/or pipe arrangement extending between the first shaft entry and the second shaft entry.

In such way is achieved that a structural aeronautical section including also the cabling and/or pipes can be manufactured at one assembly station. This is cost-effective and time- saving.

Suitably, the first shaft entry of the structural aeronautical section is arranged to be joined to a corresponding shaft entry of the mating section.

In such way is provided that a common shaft can be formed by the assembly, whereby the first shaft entry faces the corresponding shaft entry of the mating section. When the assembly is assembled, there is thus at the same time automatically provided one or several common shafts through the structure. The aeronautical structure is formed by the structural aeronautical sections having a plurality of structural aeronautical sections having said elongated shaft-like elements.

This is also solved by an aeronautical structure join-up comprising a plurality of aeronautical structural sections, wherein the sections are arranged to each other in such way that at least one entry of an elongated shaft-like element faces an entry of an elongated shaft-like element of another section. In such way is achieved an aeronautical structure (preferably an aircraft fuselage), which can be made in one production pulse, wherein the sections to be assembled already are finished in view of cabling and tubing (pipes) (or in view of prepared channel to be filled with cabling and/or tubes/pipes after assembly of the sections).

Suitably, corresponding elongated shaft-like elements of the sections together form a common shaft.

In such way is achieved that cables and/or pipes will have a predetermined position in the aircraft. The mounting personnel can thus cost-effective mount the cables and tubes/pipes in the aircraft. The designers can thus already on the "drawing table" take into account the positions of the cabling and/or pipes within the aircraft and thereby adapt the strength estimation of the structure as early as possible in view of said positions. Preferably, the join-up is an aircraft fuselage join-up.

In such way an aircraft section producer can manufacture and finish a section (or series fabrication of sections) on order and transport the section to the customer separately. The customer has adapted the design and the positions of the elongated shaft-like elements in the same way as the present aircraft section producer. The mating structural aeronautical sections being produced by the customer will thus have the same positions of the shaft entries of the elongated shaft-like elements of the end portion, as that of the above- mentioned section produced by the aircraft section producer. In such way is achieved that in case of an unlikely emergency landinge procedure, such as belly landing, where chaos of entangled cables and pipes otherwise may hinder passenger to evacuate, the cabling and pipes are protected and held away by means of the elongated shaft-like elements.

Suitably, each section comprises at least two shaft-like elements. In such way is achieved that an aircraft fuselage will be formed with at least two channels running along the fuselage prolongation and also in the periphery of the fuselage, i.e. inside and adjacent the fuselage skin. Preferably, service doors are provided at suitable places along the channels primary extension. The service doors alternatively serve as parts of the channel walls.

Preferably, the elongated shaft-like element extends along the extension of and in the periphery of the join-up.

Thereby is achieved that mounting of cabling and/or pipes (also connection) can be made efficiently.

Suitably, the interior of the elongated shaft-like element fully or partially is covered by a door member being an integrated portion of a structural skin of the join-up.

In such way is provided user friendly service and maintenance and also easy manufacture of aeronautical structures. In such way is cost-effective manufacture of aeronautical structures is achieved.

This has also been solved by a method according to claim 12, wherein the method comprises the steps claimed in claim 12. Thereby is provided a method for manufacture of structural aeronautical sections and also join-ups of such sections, e.g. aircraft fuselages, which method promotes a cost-effective manufacture and assembly of aircraft or other aerial vehicles. By means of (already at the drawing table) in space determined elongated shafts of the fuselage, preferably defining a relatively straight or slightly curved shaft-like element running along the fuselage or wing structure, no extra bent of cables and pipes has to be made through the structure, which extra bents otherwise would imply increased weight and costs. Suitably, the method comprises the further steps of; sealing the entries of the elongated shaft like elements after the step of providing the sections, but before (prior) the step of positioning the sections for join-up.

In such way is achieved an efficient way to produce a structural aeronautical section comprising a sealed accommodation for cabling and/or pipes, wherein in such case the elongated shaft-like elements comprise wall means that also is tight (e.g. closed tunnel walls). One option is to mount the cabling and/or pipes as a part of a full length cabling and/or pipes in one single section before said sealing. The cabling and/or pipes will in such case comprise connection members for easy connection to an adjacent line of cabling and/or pipes of a mating section thereby forming the full length. One option is to mount the full length cabling and/or pipes through the common shaft-like element after that the sections are assembled. Still, the sections will have guaranteed clean shafts without any dust or other dam, which is important within the aeronautical industry. Preferably, the method comprises the step of mounting a line of cabling and/or pipes into respective elongated shaft-like element after the step of providing the sections, but before (prior) the step of positioning the sections for join-up.

Thereby is provided that a section can be transported to a join-up station as a ready to assembly article.

Suitably, the method comprises the further step of mounting cabling and/or pipes through the formed common shaft-like element. In such way is provided a method that is cost-effective.

The inventive solutions achieved by the invention can be taken into account for all claim categories herein disclosed.

BRIEF DESCRIPTION OF THE DRAWINGS

The present invention will now be described by way of examples with references to the accompanying schematic drawings, of which:

Fig. 1 illustrates a portion of an aircraft fuselage in a side view according to one aspect of the invention;

Fig. 2a illustrates a commercial aircraft in a view from above according to one aspect of the invention;

Fig. 2b illustrates a cross section of an aerial vehicle other than aircraft, according to one aspect of the invention;

Fig. 3a illustrates a perspective view of a wing box section according to one aspect of the invention;

Fig. 3b illustrates a cross section of a structural aeronautical article according to one aspect of the invention;

Fig. 4 illustrates a structural aeronautical section from inside and in perspective according to one aspect of the invention;

Figs. 5a to 5c illustrate steps of providing structural aeronautical sections for join-up;

Figs. 6a and 6b illustrate in cross-section portions of sections according to different aspects; Figs. 7a to 7c illustrate method steps of feeding electrical wires and tubes through peripheral electric wiring channels and cable ducts of an aeronautical structure according to one aspect of the invention; Figs. 8a and 8b illustrate a join-up according to one aspect of the invention; and

Figs. 9a and 9b illustrate flow charts of different methods according to different aspects of the invention. DETAILED DESCRIPTION

Hereinafter, aspects or embodiments of the present invention will be described in detail with reference to the accompanying drawings, wherein for the sake of clarity and understanding of the invention some details of no importance are deleted from the drawings. Where indicative of continuity between different figures, the same references can be used for same or similar details of the figures.

Fig. 1 illustrates a portion of an aircraft fuselage 1 in a side view according to one aspect of the invention. The Fig. 1 illustrates three aircraft fuselage structural sections 3, which have been assembled and bond to each other and covered with a skin 5. Each section 3 has been formed with two interior electric wiring channels 7', which are placed adjacent the skin 5 and in the periphery of the sections 3. When the assembly of the sections 3 is finished there is provided a production pulse for mounting of cabling equipment 9. Electric wires 1 1 are drawn through the channels 7' by means of a separate tool wire 13 having a loop 15, which has been coupled to one end of the electric wires 11. The aircraft fuselage sections 3 are provided for assembly with each other. That is, one section 3 is provided for assembly with a mating section 3, wherein the mid section 3 comprises end portions 17a, 17b being adapted for join-up with the respective mating section 3. Furthermore, the electric wiring channels 7' of each section 3 comprise a first shaft entry 19a and a second shaft entry 19b, each of which are provided in the respective end portion 17a, 17b.

Fig. 2a illustrates a commercial aircraft 21 in a view from above according to one aspect of the invention. The fuselage 1 is provided with elongated electric wiring channels 10 and ducts 10' for pipes and tubes. Each section 3 of the fuselage 1 comprises channel sections 7", 7"', 7"'. For example one common channel 10 (formed by joined and in each section 3 mating channel sections 7", 7"' ...7") extends between cockpit 23 and the aircraft tail 25. Fig. 2b illustrates a cross section of a missile 21 ' according to one aspect of the invention. The missile 21 ' is provided with two structural sections 3 (only one is shown). Each section 3 comprises four shaft basket-like elements 7. These elements 7 are provided to be joined with corresponding four elements of the mating section. Thus, four common cable basketlike channels 10 are provided inside the skin 5 of the missile 21 ' after assembly. The channels 10 encompass signal wires 1 1 '. The channels 10 also serve as stringers of the skin 5 and the four channels 10 thus being used as integrated portions of the structural sections 3 of the missile 21 ', in view of each separate structural section 3 but also in view of the join-up.

Fig. 3a illustrates a perspective view of a wing box section 3' according to one aspect of the invention. The wing box section 3' is provided with a hollow structural bracket 7a. Electric cables (not shown) are to be drawn through the bracket 7a interior when the wing box section 3' has been assembled with an adjacent section (not shown), for example a wing tip or winglet. Fig. 3b illustrates a cross section of a section 3' of a structural aeronautical article 1 ' according to one aspect of the invention, where different positioning of channels 7b is shown. A channel 7b does not have to run parallel with the structure prolongation, but can extend diagonally and/or in the center portion of the section 3'. The achieved common channel may also extend diagonally and/or in the center portion of the wing structure.

Fig. 4 illustrates a structural aeronautical section 3" from inside and in perspective view according to one aspect of the invention. This section 3" forms a corner-shaped structural article to be assembled with the aircraft structure (not shown) and to be joined to a mating corner-shaped article (not shown). The section 3" comprises a channel wall 27 forming a space 29 between the wall 27 and the section 3" skin 5. Within the space 29 being positioned two cable pipes 31 adapted for encompassing electrical wires (not shown). By means of said channel wall 27 is thus achieved protection of the electrical wires at the same time as the electrical wires will be protected against strain. Also, the use of additional cable pipes 31 implies that bunching and taping of the electric wires can be avoided. Also, the use of a single separate channel (elongated shaft-like elements being joined) for encompassing the wires would imply that bunching and taping of wires could be avoided. The two shaft entries 19a, 19b are sealed with a cover 32. The sealed space 29 provides protection against dust and unwanted penetration of liquids into the channel prior join-up.

Figs. 5a to 5c illustrate steps of providing structural aircraft fuselage sections 3 for join-up. Fig. 5a illustrates a first structural aircraft fuselage section 3 comprising two cable tunnels 7. The section 3 shown in Fig. 5a is manufactured by an aircraft manufacturer. The section 3 comprises frames 33 that are fixed to each other via stringers 35. A cover skin 5 is bond to the frames 33 and the stringers 35. The cable tunnels 7 are in this embodiment part of the structural section 3 and provide strength to the section 3. In Fig. 5b is shown in flight direction a second section 4 having a conical shape (e.g. fuselage tail section). Two cable tunnels 7 are mounted to the second section 4 also being covered by a cover skin 5 in a similar way as the first section 3 in Fig. 5a. Fig. 5c illustrates the sections 3, 4 being lined up for assembly. The respective corresponding cable tunnels 7 of the sections will together form a common shaft (such as reference 10 in Fig. 2a). In such way is achieved that cables and/or pipes will have a predetermined position in the aircraft fuselage. Mounting personnel can thus cost-effective mount the cables and tubes/pipes in the aircraft. A first shaft entry 19a of the first section 3 is adapted (arranged) in position relative the first section 3, so that the first shaft entry 19a can be joined to a corresponding second shaft entry 19b (also adapted, or arranged, in position but relative the second section 4). That is, the first 3 and second 4 sections comprise identical positions of the first 19a and second 19b entries (within their join- up area) relative the geometrical shape of the end portions of the sections 3, 4 to be joined. In such way is provided that a common shaft is formed by the assembly, whereby the first shaft entry 19a faces the corresponding second shaft entry 19b of the mating section. Fig. 6a illustrates in cross-section a portion of a structural section 3 according to one aspect. Two tubes 40 are mounted in an elongated shaft 7 of the section 3. Support 42 is provided for supporting the tubes 40 in the shaft 7. Fig. 6b illustrates in cross-section a channel 10 of an aircraft fuselage 1 more in detail. A door 44 of the aircraft fuselage 1 skin 5 is arranged to partially cover the channel 10, so that the interior of the channel 10 can be reached for service. The channel 10 shown in Fig. 6b embodies both electrical wires 1 1 and pneumatic tubes 14. The channel 10 is inserted into recesses R of the structural sections 3 frames 33. Figs. 7a to 7c illustrate method steps of feeding electrical wires 1 1 and tubes through peripheral electric wiring channels 10 and cable ducts of an aeronautical structure (aircraft) according to one aspect of the invention. Fig. 7a illustrates the providing of a first structural section 3 comprising a shaft 7 for cabling. Fig. 7b illustrates the positioning of a second 3" structural section to the first structural section 3. The first 3 and second 3" structural sections are joined to each other in such way that an entry 19 of the shaft of the first structural section faces an entry of a shaft of the joined second structural section so that the first and second structural sections form a common shaft 10. Fig. 7c illustrates the positioning of a third 3"' structural section mounted to the second 3" structural section. The third 3"' and second 3" structural sections are joined to each other in such way that an entry 19 of the shaft 7 of the third structural section 3"' faces an entry 19 of a shaft 7 of the joined second structural section 3" so that the third 3"' and second 3" structural sections together with the first structural section 3 form a common shaft 10. In Fig. 7c also being illustrated installation of a cabling into the formed common shaft 10. The cabling is pushed from a cable pulley 50 into the common shaft 10 of the aircraft (part of it is shown). Thereby is provided a method for manufacture of structural aeronautical sections 3 and also join-ups of such sections 3, e.g. aircraft fuselages 1 , which method promotes a cost-effective manufacture and assembly of aircraft or other aerial vehicles. Figs. 8a and 8b illustrate a join-up according to one aspect of the invention. Fig. 8a illustrates a section 3 in position for join-up with another section. A channel 7 of the respective section 3 embodies pre-installed cabling 1 1 and/or pipe arrangement extending between a first shaft entry 19' and a second 19" shaft entry of the respective section 3. Fig. 8b illustrates a third section 3"' (with dotted lines) to be further assembled. Also the third section 3"' comprises a pre-installed cabling 11 and/or pipe arrangement. Electrical coupling means 60 and/or pipe coupling means are provided at each end 19', 19" of the pre-installed cabling and/or pipe arrangement. In this aspect the coupling means 60 are connected to each other at the pulse production step of joining the sections 3 in said join-up. This is cost-effective and time-saving and each section 3 is thus produced as a completed and finished product/article/structure comprising ready-in-position and in the structure positioned cables (cabling) and pipes (tubes) or wires.

Fig. 9a illustrates a flowchart of a method according to one aspect for join-up of structural aeronautical sections 3, wherein at least two of which each comprises an elongated shaft-like element 7, the elongated shaft-like elements together form a common shaft 10 along and in the periphery of the assembled join-up. The method starts in Step 101. In Step 102 is provided a method for assembly of the structural aeronautical sections 3. In Step 103 the method is stopped wherein the assembly is finished. The step 102 comprises the steps of: providing structural aeronautical sections 3 comprising the elongated shaft-like elements 7; positioning the sections 3 for join-up; and joining the sections 3 to each other in such way that an entry 19 of an elongated shaft-like element 7 of a first section 3 faces an entry of an elongated shaft-like element 7 of a joined second section 3 so that they form a common shaft-like element 10.

Fig. 9b illustrates a flowchart of a method according to one aspect of the invention. The method starts in Step 201 with manufacture of aircraft fuselage sections 3 comprising cabling shafts 7 arranged in the periphery of the sections 3. In step 202 is provided mounting of a line of cabling into respective cabling shaft 7. In step 203 is provided sealing of the entries of the elongated shaft like elements. In step 204 is provided a transport of a finished section to an assembly plant. In step 205 is provided a positioning of the sections 3 for join-up. In step 206, the sealings 31 are removed. In step 207 is provided a joining of the sections 3 to each other in such way that an entry 19 of a cabling shaft faces an entry of a cabling shaft of an adjacent section so that the cable shafts form a common cabling shaft. At the same time in step 207 is provided connection of said lines of cabling of respective cabling shaft so that they constitute unbroken cabling through the cabling shaft. In step 208 the method is stopped and the aircraft structure comprising the cabling being ready to receive further production pulses.

Alternatively, there is a separate or additional step comprising mounting cabling and/or pipes through the formed common cabling shaft, either with or without the step 202.

Thereby is provided a method for manufacture of structural aeronautical sections and also join-ups of such sections, e.g. aircraft fuselages, which method promotes a cost-effective manufacture and assembly of aircraft or other aerial vehicles. In such way is also achieved a efficient way to produce a structural aeronautical section comprising a sealed

accommodation for cabling and/or pipes, wherein in such case the elongated shaft-like elements comprise wall means that also is tight (closed tunnel walls).

The present invention is of course not in any way restricted to the preferred embodiments described above, but many possibilities to modifications, or combinations of the described embodiments, thereof should be apparent to a person with ordinary skill in the art without departing from the basic idea of the invention as defined in the appended claims. For example, the cabling and pipe arrangement can be of any suitable type, such as electronic, signal transmitting, fluid transport, hydraulic pipes etc. The invention can be put in use for military and commercial aircraft, helicopters and other aerial vehicles.

Claims

1. An aeronautical structural section (3) provided for assembly with a mating section (3", 4), the structural aeronautical section (3) comprises end portions (17a, 17b) adapted for join-up with said mating section (3", 4), characterized by that the structural aeronautical section (3) comprises an elongated shaft-like element (7) exhibiting a first shaft entry (19a) and a second shaft entry (19b), each of which being provided in the respective end portion (17a, 17b).
2. The structural aeronautical section according to claim 1 , wherein the elongated shaftlike element (7) being an integrated portion of the structural aeronautical section (3).
3. The structural aeronautical section according to claim 1 or 2, wherein at least one of the shaft entries (19a, 19b) being adapted to be sealed with a cover (32).
4. The structural aeronautical section according to any of claim 1 to 3, wherein the
elongated shaft-like element (7) embodies cabling and/or pipe arrangement (1 1 , 11 ') extending between the first shaft entry (19a) and the second shaft entry (19b).
5. The structural aeronautical section according to any of the preceding claims, wherein the first shaft entry 19a of the structural aeronautical section (3) is arranged to be joined to a corresponding shaft entry (19b) of the mating section (4).
6. An aeronautical structure join-up comprising a plurality of aeronautical structural sections (3) according to any of the preceding claims, wherein the sections (3) are arranged to each other in such way that at least one entry (19a) of an elongated shaft-like element (7) faces an entry (19b) of an elongated shaft-like element of another section.
7. The aeronautical structure join-up according to claim 6, wherein corresponding
elongated shaft-like elements (7) of the sections (3) together form a common shaft (10, 10').
8. The aeronautical structure join-up according to claim 6 or 7, wherein the join-up is an aircraft fuselage (1) join-up.
9. The aeronautical structure join-up according to any of claim 6 to 8, wherein each section (3) comprises at least two elongated shaft-like elements (7", T").
10. The aeronautical structure join-up according to any of the preceding claims, wherein the elongated shaft-like element (7) extends along the extension of and in the periphery of the join-up.
1 1. The aeronautical structure join-up according to any of the preceding claims, wherein the interior of the elongated shaft-like element (7) fully or partially is covered by a door member (44) being an integrated portion of a structural skin (5) of the join-up.
12. A method for join-up of structural aeronautical sections (3, 4), at least two of which each comprises an elongated shaft-like element (7), the elongated shaft-like elements (7) together form a common shaft (10) positioned along and in the periphery of the assembled join-up, the method comprises the steps of:
-providing structural aeronautical sections (3, 4) comprising the elongated shaft-like elements (7);
-positioning the sections (3, 4) for join-up; and -joining the sections (3, 4) to each other in such way that an entry (19a) of an elongated shaft-like element (7) of a first section (3) faces an entry (19b) of an elongated shaft-like element (7) of a joined second section (4) so that the elements (7) form a common shaft-like element (10).
13. The method according to claim 12, comprising the further steps of:
-sealing the entries of the elongated shaft like elements (7) after the step of providing the sections (3, 4).
14. The method according to claim 12 or 13, comprising the step of mounting a line of cabling (1 1) and/or pipes into respective elongated shaft-like element (7) after the step of providing the sections (3, 4).
15. The method according to any of claims 12 to 14, comprising the further step of
-mounting cabling (1 1) and/or pipes through the formed common shaft-like element (10).
PCT/SE2013/051060 2013-09-11 2013-09-11 Aircraft section shafts forming a common shaft and method for assembly WO2015038042A1 (en)

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