Method for installing a cable in an aircraft spar and aircraft with an aircraft spar

Abstract

Method (1) for installing a conduit (12, 13) in an aircraft spar (10), preferably in a hollow aircraft spar (10), wherein the method (1) comprises the following steps: providing (2) a conduit (12, 13); attaching (3) at least one retaining device (20) to the provided conduit (12, 13); inserting (6) at least section by section the conduit (12, 13) into the cavity of the aircraft spar (10) so that the retaining device (20) is arranged in the cavity of the aircraft spar (10); attaching the retaining device (20) to an inner wall (11.1) of the aircraft spar (10) to fix the conduit (12, 13) in relation to the aircraft spar (10).

Description

Technical field

[0001] The present invention relates to a method for installing a cable in an aircraft spar. Therefore, an aircraft spar produced directly by the method according to the invention, in particular an aircraft spar in which a cable is installed, is also the subject of the present invention.

[0002] The invention further relates to an aircraft with an aircraft spar that was produced directly by the method according to the invention. State of the art

[0003] Aircraft spars are load-bearing structural components of an aircraft. They are used particularly in the wings and / or fuselage, preferably in the airframe. An aircraft spar can, for example, function by absorbing and / or transferring the lateral forces and bending moments resulting from lift, airflow, and inertial forces to other aircraft components.

[0004] Aircraft spars are typically designed as beams or elongated box spars. Despite their hollow shape, which significantly reduces the weight of each individual spar, they still possess sufficient torsional rigidity. In larger aircraft, the cross-sectional area is chosen to be large enough to easily accommodate cables and lines within the cavity formed by the spar. For example, the cross-sectional area of ​​a spar used as a wing box in a wide-body aircraft can be so large that the cavity formed by the spar is even walkable.

[0005] In smaller aircraft, the cross-sectional areas of the spars are significantly smaller. Such a spar can, for example, have a maximum diameter of less than 20 cm, preferably less than 15 cm, and particularly preferably less than 10 cm. However, it is aerodynamically advantageous to also provide lines within the spars with smaller cross-sections. These lines can be, for example, fuel and / or hydraulic lines. Alternatively or additionally, power and / or data cables can also be part of the lines.

[0006] When installing cables in an aircraft spar, a minimum distance must always be maintained between the inner wall of the spar and the cable. This prevents the cables from being damaged by friction against the inner wall, for example, due to vibrations that occur during flight. This aviation regulation also applies, of course, to the installation of cables in aircraft spars with smaller cross-sectional areas. Consequently, there is a need for a method for installing cables in an aircraft spar that allows for the legally compliant installation of cables even in spars with smaller cross-sectional areas. Description of the invention

[0007] It is therefore an object of the present invention to satisfy the aforementioned needs and / or to eliminate the disadvantages associated with the prior art. In particular, it is an object of the present invention to provide a cost-effective and simple method for installing a cable in an aircraft spar.

[0008] This problem is solved by the method according to claim 1. Advantageous further developments of the method according to the invention are the subject of the dependent claims and / or are explained in the following description.

[0009] According to the invention, a method for installing a line in an aircraft spar, in particular in a hollow aircraft spar, is proposed, which essentially comprises the following method steps: a) Providing a line; b) Attaching at least one holding device to the provided line; c) At least partially inserting the cable into the cavity of the aircraft spar, so that the holding device is arranged in the cavity of the aircraft spar; and d) Attaching the holding device to an inner wall of the aircraft spar to fix the line in relation to the aircraft spar.

[0010] The "cavity" of the "hollow aircraft spar" is preferably formed by the free space enclosed by the wall of the aircraft spar. This does not preclude the aircraft spar from having openings at its respective longitudinal ends.

[0011] For the purposes of this invention, the term "conduit" means an elongated, rigid and / or flexible structure designed to carry fluid, electricity, and / or data. A conduit within the meaning of this invention can, for example, be a fuel, hydraulic, and / or compressed air line. Alternatively or additionally, the conduit can be a power and / or data cable. The retaining device can be attached to the conduit by a positive fit, for example, by a clip; by a friction fit, for example, by screwing; and / or by a material bond, for example, by adhesive bonding.

[0012] The aforementioned method is based on the inventive idea of ​​providing the cable with at least one retaining device before it is inserted into the aircraft spar. By means of this retaining device, the cable can be easily and legally secured within the aircraft spar in compliance with aviation regulations.

[0013] In an advantageous further development, the holding device is designed and attached to the cable in such a way that it keeps the cable away from the inner wall of the aircraft spar. The holding device keeps the cable away from the inner wall of the aircraft spar particularly when it is attached to the inner wall of the aircraft spar.

[0014] Preferably, the holding device comprises a cable fastening section and an aircraft spar fastening section. The holding device can be attached to the cable via the cable fastening section. The holding device can be attached to the aircraft spar via the aircraft spar fastening section, in particular to the inner wall of the aircraft spar. Advantageously, the cable fastening section is spaced apart from the aircraft spar fastening section by a spacer section of the holding device.

[0015] The embodiment in which the holding device comprises a cable fastening section, an aircraft spar fastening section, and a spacer section can advantageously ensure that the cable is kept away from the inner wall of the aircraft spar by structural means, namely the spacer section of the holding device. This can have the advantage that the installation procedure is particularly simple and, at the same time, all aviation regulations are complied with.

[0016] In one exemplary embodiment of the method, the holding device is attached to the inner wall of the aircraft spar via the outer wall. For example, a permanent magnet with a corresponding polarity can be provided on the aircraft spar mounting section. A second magnet with a corresponding opposite magnetic polarity can be provided on the outer wall of the aircraft spar. Additionally or alternatively, the aircraft spar mounting section can have an adhesive for bonding to the inner wall of the aircraft spar.

[0017] In another exemplary embodiment, at least one through-hole can be provided in the wall of the aircraft spar. Preferably, the mounting device can be connected to the aircraft spar via the through-hole by frictional and / or positive locking. The mounting device can, for example, be screwed and / or riveted to the aircraft spar via the through-hole. In a further development, several through-holes, in particular several through-holes per mounting device, can be provided in the wall of the aircraft spar.

[0018] A through-hole can advantageously allow the mounting device – and consequently the cable attached to the mounting device – to be attached to the aircraft spar, particularly its inner wall, with particular ease and security. This can have the advantage of ensuring an even simpler and more stable installation of the cable within the aircraft spar.

[0019] Alternatively or additionally, at least one access opening can be provided in the wall of the aircraft spar. The access opening can be designed so that the holding device can be positioned over it before being attached to the aircraft spar. Preferably, the access opening is located in the immediate vicinity of one or more through-holes. For example, an aircraft mechanic can use their fingers to position the holding device over the access opening in relation to the through-hole(s). Advantageously, the access opening can be closed after the holding device has been attached to the aircraft spar, in particular by closing it with a cover.

[0020] An access opening can advantageously make it particularly easy and secure to position the mounting device in the aircraft spar. This can have the advantage of ensuring an even simpler and safer installation of the cable in the aircraft spar.

[0021] In another exemplary embodiment, several retaining devices are attached to the provided cable. Preferably, the multiple retaining devices are attached to the cable at regular intervals along its length. Advantageously, multiple retaining devices can ensure that the cable is installed under a certain tension within the aircraft spar. Additionally or alternatively, multiple retaining devices can ensure that the cable maintains a substantially constant distance from the inner wall of the aircraft spar along its entire length. The multiple retaining devices can have the advantage of ensuring a particularly stable and secure installation of the cable within the aircraft spar.

[0022] In a further advantageous embodiment, multiple cables can also be provided. Preferably, the holding device is attached to the multiple cables in such a way that the holding device keeps the cables spaced apart from one another. This can advantageously ensure that the holding device not only keeps the cables spaced away from the aircraft spar, particularly from the inner wall of the aircraft spar, but also from each other. This can have the advantage that the cables cannot rub against each other in flight and thus cannot be damaged.

[0023] The problem stated at the outset of the invention is also solved with an aircraft spar that has an internal conduit installed in the spar according to one of the aforementioned methods. Accordingly, all of the aforementioned features, combinations of features, and their respective advantages are also transferable to the aircraft spar according to the invention, or at least transferable in an analogous manner. The aircraft spar according to the invention realizes the same inventive idea as the method. Preferably, the aircraft spar is beam-shaped and hollow.

[0024] The problem stated at the outset is also solved with an aircraft according to claim 10. Advantageous further developments of the aircraft according to the invention are the subject of the following description.

[0025] According to the invention, an aircraft is proposed comprising at least one aircraft spar, wherein the aircraft spar has an internal conduit installed in the aircraft spar according to one of the aforementioned methods. Accordingly, all of the aforementioned features, combinations of features, and the respective advantages associated therewith are also transferable to the aircraft according to the invention, or at least transferable in an analogous manner. The aircraft according to the invention realizes the same inventive idea as the method.

[0026] The aircraft according to the invention can in particular be an electrically powered, preferably exclusively electrically powered, aircraft. The aircraft is preferably designed for vertical take-off and landing. The aircraft can be an "electrical Vertical Take-off and Landing" (eVTOL) aircraft.

[0027] The aircraft can have several lift- and / or thrust-generating propulsion devices. Advantageously, at least one of the propulsion devices is arranged on the aircraft spar. The propulsion device can be connected to the control line and supplied with power and / or control data via the line. The propulsion devices can, for example, include propellers / rotors. The propulsion devices are designed to generate lift for the aircraft. When the rotors rotate, they preferably generate a lift force—that is, a vertical thrust force—with which the aircraft can take off vertically, land, and / or hover. Alternatively or additionally, the propulsion devices can be designed to generate thrust. That is, the propulsion devices can generate an acceleration force—that is, a horizontal thrust force—which accelerates the aircraft in a forward direction.Preferably, each of the drive devices is driven by a corresponding electric motor. In particular, the electric motor can be connected to the line in the aircraft spar for power and / or data transmission.

[0028] The invention, as well as advantageous embodiments of the invention, can also be described by the following aspects. The features listed in these aspects can be combined with the aforementioned features as desired, provided this is technically sensible and appropriate.

[0029] Aspect 1: Method for installing a conduit in a hollow aircraft spar, wherein the method comprises the following process steps: a) Providing a line; b) Attaching at least one holding device to the provided line; c) At least section by section, the line is inserted into the cavity of the aircraft spar so that the holding device is arranged in the cavity of the aircraft spar; d) Attaching the holding device to an inner wall of the aircraft spar to fix the line in relation to the aircraft spar.

[0030] Aspect 2: Method according to Aspect 1, wherein the holding device is designed and attached to the line in such a way that the holding device keeps the line away from the inner wall of the aircraft spar.

[0031] Aspect 3: Method according to any of the preceding aspects, wherein the holding device is attached to the line via a line fastening section of the holding device and is attached to the inner wall of the aircraft spar via an aircraft spar fastening section of the holding device, wherein the line fastening section and the aircraft spar fastening section are spaced apart from each other via a spacer section of the holding device.

[0032] Aspect 4: Method according to one of the preceding aspects, wherein the holding device is attached to the inner wall of the aircraft spar via the outer wall during fastening according to method step d).

[0033] Aspect 5: Method according to one of the preceding aspects, wherein at least one through hole is provided in the wall of the aircraft spar and the retaining device for fastening according to method step d) is screwed to the aircraft spar via the through hole.

[0034] Aspect 6: Method according to one of the preceding aspects, wherein at least one access opening is provided in the wall of the aircraft spar and the holding device is positioned over the access opening in relation to the aircraft spar before fastening according to method step d).

[0035] Aspect 7: Procedure according to aspect 6, wherein the access opening is closed after fastening according to procedure step d), in particular by closing it with a cover.

[0036] Aspect 8: Method according to one of the preceding aspects, wherein in process step b) several holding devices are attached to the provided line, preferably along the line at regular intervals to each other.

[0037] Aspect 9: Method according to one of the preceding aspects, wherein in process step a) several lines are provided and in process step b) the holding device is attached to the lines in such a way that the holding device fixes the lines at a distance from each other.

[0038] Aspect 10: Aircraft spar, wherein the aircraft spar has a line installed according to a procedure in accordance with any of Aspects 1 to 10.

[0039] Aspect 11: Aircraft spar according to aspect 10, wherein the aircraft spar is beam-shaped and hollow.

[0040] Aspect 12: Aircraft, preferably an eVTOL aircraft, with an aircraft spar according to one of aspects 10 or 11.

[0041] Aspect 13: Aircraft according to aspect 12, wherein at least one lift- and / or propulsion-generating drive device, preferably a propeller, is arranged on the aircraft spar.

[0042] Aspect 14: Aircraft according to aspect 13, wherein the propulsion device is connected via the aircraft spar to a wing of the aircraft and / or a cell of the aircraft, preferably the aircraft fuselage. Brief description of the drawings

[0043] The various exemplary features described above can be combined with one another to the extent that this is technically sensible and appropriate. In particular, features disclosed in connection with a method can be combined with device features. Features disclosed in connection with a device can be combined with method features. Further combinable features, advantages, and embodiments of the invention will become apparent from the following description of exemplary embodiments and with reference to the figures. The figures show: Fig. 1 a flowchart illustrating a method for installing a cable in an aircraft spar according to a first embodiment, Fig. 2 a perspective view of an embodiment of an aircraft spar, constructed according to the method according to Fig. 1 a line was installed, Fig. 3 another perspective view of the aircraft spar according to Fig. 2, Fig. 4 a schematic sectional view of a holding device from the aircraft spar according to Fig. 2, and Fig. 5 A schematic side view of an exemplary embodiment of an aircraft. Ways to implement the invention

[0044] Fig. Figure 1 shows a flowchart illustrating an embodiment of a method 1 for installing a line 12, 13 in an aircraft spar 10 according to a first embodiment (the line 12, 13 and the aircraft spar 10 are in Fig. 1 not shown).

[0045] Method 1 begins with a process step 2 in which at least one line 12, 13 is provided. In the present embodiment, the line 12, 13 is a power and / or data transmission cable 12, 13. However, it is also conceivable that in alternative embodiments the line 12, 13 is a hydraulic and / or fuel line 12, 13, in particular a flexible hydraulic and / or fuel line 12, 13. Preferably, several lines 12, 13 are provided in process step 2, namely a first line 12 and a second line 13. Subsequent process steps are always described only with respect to one line 12, 13. However, the process steps can also be applied analogously to the multiple lines 12, 13.

[0046] In process step 3 following the aforementioned process step 2, at least one retaining device 20 is attached to the line 12, 13. The retaining device 20 is clipped onto the line 12, 13. According to the present embodiment, several retaining devices 20 are attached to the line 12, 13 at regular intervals.

[0047] According to a first embodiment 8.1 of the exemplary embodiment, the line 12, 13 with the attached retaining devices 20 can then be inserted at least section by section into the aircraft spar 10 (process step 6). In particular, the line 12, 13 is inserted into the aircraft spar 10 such that the retaining devices 20 are arranged inside the aircraft spar 10.

[0048] According to a second embodiment variant 8.2 of the exemplary embodiment, at least one through hole 14 is first made in the wall 11 of the aircraft spar 10 (process step 4, wherein the through hole 14 in the wall 11 in Fig. 2 and Fig. (as shown in Figure 3). In the present embodiment, two through holes 14 are provided in the wall 11 of the aircraft spar 10 in process step 4. The through holes 14 are used in a process step described below for screwing the retaining device 20 inside the aircraft spar 10. If the second embodiment variant 8.2 is used, process step 6 can be carried out after the through holes 14 have been made in the wall 11 of the aircraft spar 10.

[0049] Alternatively, in a third embodiment 8.3, after the through-holes 14 have been made in the wall 11 of the aircraft spar 10, an access opening 15 can be provided in the wall 11 of the aircraft spar 10. The access opening 15 is advantageously located in close proximity to the through-holes 14. In the subsequent process step 6, the access opening 15 can be used to position or align the holding device 20 with respect to the through-holes 14. For example, a user can reach into the aircraft spar 10 through the access opening 15 to position or align the holding device 20 with their fingers with respect to the through-holes 14.

[0050] In a final process step 7, the holding device 20 is attached to the inner wall 11.3 of the aircraft spar 10 via the outer wall 11.2 of the aircraft spar 10 (compare Fig. 2 and Fig. 3) In embodiment 8.1, this can be done, for example, using magnets. In embodiment 8.2, the holding device 20 could be guided to the through-holes 14 by means of magnets and screwed and / or riveted to the aircraft spar 10 via the through-holes 14. Embodiment 8.3 has the advantage that the holding device 20 can be positioned or aligned very easily via the access opening 15 with respect to the through-holes 14. Preferably, the access opening 15 is located in a Fig. 1. Further process step not shown is closed when process step 7 has been completed.

[0051] If several retaining devices 20 have been attached to the line 12, 13, the number of through holes 14 and / or the number of access openings 15 corresponds to the number of retaining devices 20. Procedure step 7 must be repeated accordingly.

[0052] Fig. Figure 2 shows a perspective view of an embodiment of an aircraft spar 10 in which two lines 12, 13, namely a first power and / or data cable 12 and a second power and / or data cable 13, have been installed according to the aforementioned method 1. Since the lines 12, 13 are not normally visible in the chosen representation, they are shown as dashed lines.

[0053] The aircraft spar 10 has a beam-shaped and hollow form. The diameter of the cavity inside the aircraft spar 10 is a few centimeters, preferably less than 20 cm, particularly preferably less than 10 cm. The aircraft spar 10 is essentially formed by a wall 11, which has an inner wall 11.1 or inner surface 11.1 and an outer wall 11.2 or outer surface 11.2.

[0054] The retaining devices 20 attached to the lines 12, 13 are positioned in relation to the through holes 14 such that the retaining devices 20 can be screwed to the aircraft spar 10 from the outer wall 11.2 and via the through holes 14 on the inner wall 11.1 inside the aircraft spar 10 / are screwed to it.

[0055] Each of the in Fig. The two access holes 15 shown are provided so close to corresponding through holes 14 that the retaining devices 20 can be positioned in relation to the through holes 14 when inserting the lines 12, 13.

[0056] Fig. Figure 3 shows another perspective view of the embodiment of the aircraft spar 10 according to Fig. 2. In Fig. 3. The aircraft spar 10 was extended from the point in Fig. The selected representation was rotated. Furthermore, for better visibility, part of the wall 11 was removed, so that the lines 12, 13 and the retaining devices 20 are visible. Regarding the structural design, please refer to the explanations concerning Fig. 2 referred.

[0057] Fig. Figure 4 shows a schematic sectional view of one of the holding devices 20, as shown in Fig. 2 and Fig. 3 will be shown.

[0058] The retaining device 20 is essentially U-shaped. The retaining device 20 is designed to space two cables 12, 13 apart and to attach both cables at a predefined distance to the aircraft spar 10, in particular to the inner wall 11.1 of the aircraft spar 10. For this purpose, the illustrated embodiment of the retaining device 20 comprises two spaced-apart aircraft spar attachment sections 22 and two spaced-apart cable attachment sections 21.

[0059] The aircraft spar mounting sections 22 each have a bore 23, in particular a blind bore 23, with an internal thread. The retaining device 20 can be screwed to the aircraft spar 10, preferably against the inner wall 11.1 of the aircraft spar 10, via the bores 23. Each of the aircraft spar mounting sections 22 is spaced apart from a cable mounting section 21 by a first spacer section 24.

[0060] The cable fastening sections 21 are designed to be connected to a cable 12, 13 each. The cable fastening sections 21 are spaced apart from each other by a second spacer section 25.

[0061] Fig.Figure 5 shows a schematic side view of an embodiment of an aircraft 30, in particular an eVTOL aircraft 30. The aircraft 30 has several propulsion devices 31 which are connected to the fuselage 32 of the aircraft 30 via several aircraft spars 10 according to the aforementioned embodiment. Reference symbol list 1. Method for installing a cable in an aircraft spar 2. Providing a line 3. Attach a holding device to the provided cable 4. Creating a through-hole in the wall of the aircraft spar 5. Creating an access opening in the wall of the aircraft spar 6. Insert the cable with the attached holding device into the aircraft spar. 7. Attaching the holding device to the aircraft spar 8.1 First version 8.2 second version variant 8.3 Third version variant 10 aircraft spar 11 Wall 11.1 Inner wall 11.2 Exterior wall 12 first line 13 second line 14 Through hole 15 Access opening 20 Holding device 21 Cable fastening section 22 Aircraft spar attachment section 23 Hole with internal thread 24 first spacing section 25 second spacing section 30 aircraft 31 Drive device 32 Aircraft fuselage

Claims

[1] Method (1) for installing a line (12, 13) in an aircraft spar (10), preferably in a hollow aircraft spar (10), wherein the method (1) comprises the following process steps: (a) Providing (2) a line (12, 13); (b) Attaching (3) at least one holding device (20) to the provided line (12, 13); (c) Inserting (6) the line (12, 13) at least section by section into the cavity of the aircraft spar (10) so that the retaining device (20) is arranged in the cavity of the aircraft spar (10); (d) Attaching (7) the holding device (20) to an inner wall (11.1) of the aircraft spar (10) to fix the line (12, 13) in relation to the aircraft spar (10). [2] Method (1) according to claim 1, wherein the holding device (20) is designed and attached to the line (12, 13) in such a way that the holding device (20) keeps the line (12, 13) apart from the inner wall (11.1) of the aircraft spar (10). [3] Method (1) according to one of the preceding claims, wherein the holding device (20) is attached to the line (12, 13) via a line fastening section (21) of the holding device (20) and is attached to the inner wall (11.1) of the aircraft spar (10) via an aircraft spar fastening section (22) of the holding device (20), wherein the line fastening section (21) and the aircraft spar fastening section (22) are spaced apart from each other via a spacer section (24) of the holding device (20). [4] Method (1) according to one of the preceding claims, wherein the holding device (20) is attached to the inner wall (11.1) via the outer wall (11.2) of the aircraft spar (10) during the fastening (7) according to method step d). [5] Method (1) according to one of the preceding claims, wherein at least one through hole (14) is provided in the wall (11) of the aircraft spar (10) and the retaining device (20) for fastening (7) according to method step d) is screwed to the aircraft spar (10) via the through hole (14). [6] Method (1) according to one of the preceding claims, wherein at least one access opening (15) is provided in the wall (11) of the aircraft spar (10) and the holding device (20) is positioned over the access opening (15) in relation to the aircraft spar (10) before fastening (7) according to method step d). [7] Method (1) according to claim 6, wherein the access opening (15) is closed after fastening (7) according to method step d), in particular closed with a cover. [8] Method (1) according to one of the preceding claims, wherein in method step b) several holding devices (20) are attached to the provided line (12, 13), preferably along the line (12, 13) at regular intervals from each other. [9] Method (1) according to one of the preceding claims, wherein in method step a) several lines (12, 13) are provided and in method step b) the holding device (20) is attached to the lines (12, 13) such that the holding device (20) fixes the lines (12, 13) apart from each other. [10] Aircraft (30), preferably an eVTOL aircraft (30), with an aircraft spar (10), wherein the aircraft spar (10) has inside a line (12, 13) installed according to a method (1) according to one of claims 1 to 9.

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