Patent ID: 12194904

DETAILED DESCRIPTION

FIG.1shows an aircraft seat44a. The aircraft seat44ais part of a row of seats54awithin an aircraft passenger cabin. The aircraft seat44ahas an aircraft seat backrest56a. The aircraft seat44ahas an aircraft seat bottom58a. The aircraft seat44acomprises an aircraft seat device46a. The aircraft seat44ais illustrated inFIG.1in a ready to use state relative to an mounting direction70aof the aircraft seat44a.

FIGS.2to5show different views of the aircraft seat device46a. The aircraft seat device46ahas a backrest frame unit10a. The backrest frame unit10ais formed from many parts. The backrest frame unit10acomprises a first side frame element12a. The backrest frame unit10acomprises a second side frame element14a. The side frame elements12a,14aare at least substantially identical to each other. The side frame elements12a,14aare formed in mirror-image fashion relative to each other. Alternatively, the side frame elements12a,14a, apart from production tolerances, could be identical to each other or different from each other. The second side frame element14ais separate from the first side frame element12a. The second side frame element14ais separate from the first side frame element12a. The first side frame element12aand the second side frame element14aare arranged on opposite sides of the backrest frame unit10a. The side frame elements12a,14aare formed as in particular bent and/or curved, aluminum or magnesium extruded profiles. Alternatively, the side frame elements12a,14acould also be formed from a plastic or another metal.

The backrest frame unit10ahas a cover36a(cf.FIG.5). The cover36ais formed as a textile or else as a fiber mat. The side frame elements12a,14aare configured for mounting the cover36aof the backrest frame unit10a. The side frame elements12a,14aeach have a piping guide element60a. The piping guide element60ais configured to hold the cover36aunder tension.

The backrest frame unit10ahas a transverse frame element16a. The transverse frame element16ais separate from the side frame elements12a,14a. The transverse frame element16ais configured to connect the side frame elements12a,14a. The transverse frame element16ais formed in one piece. The transverse frame element16ais monolithic. The transverse frame element16aillustrated by way of example is to a large extent produced by means of primary forming. The transverse frame element16aillustrated by way of example is produced as an injection molded part. The transverse frame element16aillustrated by way of example is produced as a casting made of fiber reinforced plastic. The transverse frame element16aforms an upper termination38aof the backrest frame unit10a. The backrest frame unit10ahas a further transverse frame element42a. The further transverse frame element42ais connected to the side frame elements12a,14ain a central area of the side frame elements12a,14a. The further transverse frame element42ais used to further increase the stiffness and the stability of the aircraft seat device46a.

The transverse frame element16ais realized at least substantially plate-shaped. The transverse frame element16ahas a maximum height76a(cf.FIG.4). The maximum height76ais an extent of the transverse frame element16aparallel to the mounting direction70a. The maximum height76aof the transverse frame element16aillustrated by way of example is 22 cm. The transverse frame element16ahas a maximum width74a(cf.FIG.4). The maximum width74ais an extent of the transverse frame element16aperpendicular to the mounting direction70aand parallel to a main extension plane of the transverse frame element16a. The maximum width74aof the transverse frame element16aillustrated by way of example is 38 cm. The transverse frame element16ahas a maximum depth72a(cf.FIG.3). The maximum depth72ais an extent of the transverse frame element16aperpendicular to the mounting direction70aand perpendicular to the main extension plane of the transverse frame element16a. The maximum depth72aof the transverse frame element16aillustrated by way of example is 27 mm. The maximum height76aof the transverse frame element16ais more than 8 times greater than the maximum depth72aof the transverse frame element16a. The maximum width74aof the transverse frame element16ais more than 14 times greater than the maximum depth72aof the transverse frame element16a. The transverse frame element16ais at least substantially cubic. The transverse frame element16ahas, at least substantially, the shape of a rectangle.

The transverse frame element16ahas a skeleton-like structure18a. The transverse frame element16ahas a plurality of passages62a,64a,66a. The transverse frame element16ahas a plurality of recesses68a. The skeleton-like structure18ais formed at least by the plurality of recesses68aand passages62a,64a,66a. The transverse frame element16ais formed mirror-symmetrically relative to a mirror plane78a. The mirror plane78aruns perpendicular to the main extension plane, centrally through the transverse frame element16a. The transverse frame element16ahas an edging80a. The edging80aruns partially around the transverse frame element16a. The edging80aimparts to the transverse frame element16aapproximately a shape of a flat box. The edging80aprojects perpendicularly from a plate plane of the transverse frame element16a. The edging80aprojects perpendicularly from the main extension plane of the transverse frame element16a. The side frame elements12a,14aare continued circumferentially around the transverse frame element16aby the edging80a. The edging80aforms the maximum depth72aof the transverse frame element16a. The edging80aprojects by at least 10 mm, preferably at least 15 mm and preferably at least 20 mm above an in particular central surface84aof the transverse frame element16ain an inner area82a(cf.FIG.5) of the transverse frame element16a. The edging80aprojects in the direction of a front side86aof the transverse frame element16a. Alternatively, the edging80acould also project in the direction of a rear side88aof the transverse frame element16a.

The transverse frame element16ahas a first connection element20a. The first connection element20ais configured for fastening at least one of the side frame elements12a,14a. The first connection element20ais formed integrally with the transverse frame element16a. The first connection element20ais formed in one piece with the transverse frame element16a. The transverse frame element16ahas a second connection element90a. The second connection element90ais configured for fastening at least a further one of the side frame elements12a,14a. The second connection element90ais at least substantially identical to the first connection element20a. The second connection element90ais formed integrally with the transverse frame element16a. The second connection element90ais formed in one piece with the transverse frame element16a. The connection elements20a,90aare each formed as a cavity22ain the transverse frame element16athat is matched to an external shape of the side frame element12a,14a(cf. alsoFIG.6). During the mounting of the side frame elements12a,14aon the transverse frame element16a, the side frame elements12a,14aare inserted into the cavities22aof the connection elements20a,90aand fixed therein. It is conceivable that the transverse frame element16ahas further connection elements, which can be used optionally for mounting the side frame elements12a,14a, depending on the desired implementation of the backrest frame unit10a, in particular depending on the desired width of the aircraft seat device46a.

The transverse frame element16ahas a fastening unit24a. The fastening unit24ais configured for mounting at least one functional unit26a. The functional unit26acan be realized as a headrest134a(cf.FIG.10), as a headrest mount102a(cf.FIG.6), as an aircraft meal table locking132a(cf.FIG.10), as a tall literature pocket128a(cf.FIG.10), as a monitor, as a monitor mount, as an upholstery attachment, as a cup holder, as a tablet holder, as a USB connector or as a further electronic component. The fastening unit24acomprises a fastening matrix. The fastening unit24acomprises a hole matrix92a. The fastening unit24acomprises fastening elements28a,30a,98a,100a. The fastening elements28a,30a,98a,100aare at least partly formed as holes of the hole matrix92a. The fastening unit24acomprises preformed receiving regions94a,96afor the at least substantially form-fitting holding of functional units26a. The fastening elements28a,30a,98a,100aare at least partly formed as receiving regions94a,96a. The shape and arrangement of the fastening elements28a,30a,98a,100aare specifically matched to the respective functional units26ato be mounted. The fastening unit24ahas the plurality of fastening elements28a,30a,98a,100a. Each of the different fastening elements28a,30a,98a,100ais respectively configured for fastening a different implementation of one of the functional units26aor different functional units26a.

The transverse frame element16ahas a functional unit26a, which is formed as an energy absorption element130a. The energy absorption element130ais used to absorb impact energy in the event of an impact of a part of a body in the transverse frame element16a. The energy absorption element130ais formed as an intended fracture point. During the impact of the part of the body, the transverse frame element16abreaks along the intended fracture point and thus releases additional travel for a movement of the part of the transverse frame element16athat has broken out. As a result, personal safety, in particular in the event of a catastrophe, can advantageously be improved. Alternatively or additionally, the energy absorption element130acan also be formed as at least one component made of an absorber material, such as, for example, a particulate foam, in particular EPP (expanded polypropylene), which is fastened to the transverse frame element16a.

FIG.6shows a partial view of the aircraft seat device46awith an alternative transverse frame element16′a. The alternative transverse frame element16′adiffers from the transverse frame element16aofFIGS.2to5mainly in a different arrangement of the fastening elements28a,30a,98a,100aand in a different implementation of the cavity22aof the connection elements20a,90a. In addition, the headrest mount102ais fastened to the fastening unit24aof the alternative transverse frame element16′a. The headrest mount102ahas a rail104a. The headrest mount102ais configured for mounting a headrest134a. The headrest134amounted on the headrest mount102ais movable along the rail104a. A vertical adjustment of the headrest134amounted on the headrest mount102acan be performed by means of the movement along the rail104a.

The fastening unit24aof the alternative transverse frame element16′ahas a first fastening element98aon a first side32aof the transverse frame element16′a. The first side32aof the transverse frame element16′aforms the rear side88aof the transverse frame element16′a. The fastening unit24aof the alternative transverse frame element16′ahas a second fastening element28aon a second side34aof the transverse frame element16′a. The second side34aforms the front side86aof the transverse frame element16′a. The second side34ais arranged opposite from the first side32a. The first fastening element98ais formed as a receiving region94a. The first fastening element98ais formed as a hole to hold one of the functional units26a. The first fastening element98ais configured for mounting an aircraft meal table locking132a. The second fastening element28ais formed as a hole of the hole matrix92a. The second fastening element28ais formed for firmly screwing or riveting one of the functional units26a. The second fastening element28ais configured for mounting the headrest mount102a. The headrest mount102aand the aircraft meal table locking132aare fastened to the transverse frame element16′aon different sides32a,34aof the transverse frame element16′ain an operation-ready state of the aircraft seat device46a. The fastening unit24aoffers the possibility of fastening a multiplicity of further or alternative functional units26ato both sides32a,34aof the transverse frame element16′a.

FIG.7shows a flowchart of a method for producing the aircraft seat device46a. The method steps106a,108a,110a,112a,114a,116a,118a,120a,122acan be carried out in different orders. In particular, it is possible to depart substantially from the order described below. In at least one method step106a, the transverse frame element16ais produced by means of a primary forming method, for example injection molding, diecasting and/or 3D printing. In particular, it is conceivable that smaller reprocessing by means of primary forming processes are then carried out. The transverse frame element16ais produced in one piece in the method step106a. In at least one further method step108a, the side frame elements12a,14aare produced by means of extrusion and possible subsequent bending. In at least one further method step110a, the side frame elements12a,14aare introduced into the cavities22aof the connection elements20a,90aand are fastened to the transverse frame element16a. In at least one further method step112a, the further transverse frame element42ais fastened in the central area of the side frame elements12a,14a. In at least one further method step114a, the cover36ais fixed to the side frame elements12a,14a. In at least one further method step116a, a functional unit26ais fastened to the front side86aof the transverse frame element16a. In at least one further method step118a, a further functional unit26ais fastened to the rear side88aof the transverse frame element16a. In at least one method step120a, a cover (not shown) is slipped over the transverse frame element16a. In at least one further method step122a, the aircraft seat device46ais integrated into the aircraft seat44a.

FIG.8shows a modular system48afor assembling the aircraft seat device46a. The modular system48ahas a set50aof differently realized pairs of side frame elements12a,12′a,12″a. The various side frame elements12a,12′a,12″aof the set50aof side frame elements12a,12′a,12″aare configured for the assembly of different aircraft seat devices46a. At least some of the side frame elements12a,12′a,12″aof the set50aof side frame elements12a,12′a,12″ahave different lengths124a. At least some of the side frame elements12a,12′a,12″aof the set50aof side frame elements12a,12′a,12″ahave different materials and/or material thicknesses. At least some of the side frame elements12a,12′a,12″aof the set50aof side frame elements12a,12′a,12″ahave different outer shapes, for example different curvatures.

The modular system48ahas a set52aof differently realized transverse frame elements16a,16′a,16″a. The various transverse frame elements16a,16′a,16″aof the set52aof transverse frame elements16a,16′a,16″aare configured for the assembly of different aircraft seat devices46a, in particular aircraft seat devices46aof different widths, preferably aircraft seats44aof different widths. At least some of the various transverse frame elements16a,16′a,16″aof the set52aof transverse frame elements16a,16′a,16″aare configured to hold different functional units26a. At least some of the transverse frame elements16a,16′a,16″aof the set52aof transverse frame elements16a,16′a,16″ahave different widths74a. At least some of the transverse frame elements16a,16′a,16″aof the set52aof transverse frame elements16a,16′a,16″acan have different heights76a. At least some of the transverse frame elements16a,16′a,16″aof the set52aof transverse frame elements16a,16′a,16″acan have different depths72a. At least some of the transverse frame elements16a,16′a,16″aof the set52aof transverse frame elements16a,16′a,16″ahave different shapes and/or different structuring, for example different fastening units24a. The transverse frame elements16a,16′a,16″aof the set52aof differently realized transverse frame elements16a,16′a,16″aeach have connection elements20a,90a. The connection elements20a,90aof the transverse frame elements16a,16′a,16″aof the set52aof differently realized transverse frame elements16a,16′a,16″aeach permit mounting of all the pairs of side frame elements12a,12′a,12″aof the set50aof side frame elements12a,12′a,12″a. The side frame elements12a,12′a,12″aof the set50aof side frame elements12a,12′a,12″acan be combined as desired with the transverse frame elements16a,16′a,16″aof the set52aof transverse frame elements16a,16′a,16″a. As a result of the combinations of the side frame elements12a,12′a,12″aof the set50aof side frame elements12a,12′a,12″aand the transverse frame elements16a,16′a,16″aof the set52aof transverse frame elements16a,16′a,16″a, a multiplicity of differently formed backrest frame units10acan be constructed. The set52aof transverse frame elements16a,16′a,16″aand/or the set50aof side frame elements12a,12′a,12″acan in particular each have more or fewer different transverse frame elements16a,16′a,16″aand/or more or fewer different side frame elements12a,12′a,12″athan illustrated inFIG.8.

A further exemplary embodiment of the invention is shown inFIGS.9and10. The following descriptions and the drawings are restricted substantially to the differences between the exemplary embodiments, wherein, with respect to identically designated components, in particular in relation to components with the same designations, in principle reference can also be made to the drawings and/or the description of the other exemplary embodiments, in particularFIGS.1to8. In order to distinguish the exemplary embodiments, the letter a is appended to the designations of the exemplary embodiment inFIGS.1to8. In the exemplary embodiment ofFIGS.9and10, the letter a is replaced by the letter b.

FIG.9shows an alternative aircraft seat device46b. The aircraft seat device46bhas an alternative backrest frame unit10b. The backrest frame unit10bcomprises a first side frame element12b, a second side frame element14band a transverse frame element16b. The first side frame element12bis shaped differently from the second side frame element14b, in particular curved differently. The transverse frame element16bconnects the two side frame elements12b,14b. The transverse frame element16bis formed as a visible part of an aircraft seat backrest56b. The transverse frame element16bhas a fastening unit24b. The fastening unit24bis configured for mounting at least one functional unit26b. The transverse frame element16billustrated by way of example inFIG.9is produced as a diecast part. The transverse frame element16ais produced as a magnesium and/or aluminum diecast part.

FIG.10shows the alternative aircraft seat device46bwith four functional units26band with a backrest covering40b. The aircraft seat device46bhas the backrest covering40b. The backrest covering40bis configured to cover an interspace between the side frame elements12b,14b. The backrest covering40bis arranged on a rear side126bof the aircraft seat device46b. The backrest covering40bis fastened to the side frame elements12b,14b. The backrest covering40bends flush with the transverse frame element16b. The backrest covering40bis formed from a deep-drawn film. The first functional unit26billustrated by way of example inFIG.10is formed as a tall literature pocket128b. The tall literature pocket128bis fastened to a rear side88bof the transverse frame element16bby means of the fastening unit24b. The second functional unit26billustrated by way of example inFIG.10is realized as a headrest134b. The headrest134bis fastened to a front side86bof the transverse frame element16bby means of the fastening unit24b. In the case illustrated by way of example, the headrest134bis formed as a foam part, which is connected to a further backrest foam part142b, in particular formed in one piece. In such a case, direct fastening of the headrest134bto the transverse frame element16bis optional. In particular, such a headrest134bcan also only be leant on the transverse frame element16b. The third functional unit26billustrated by way of example inFIG.10is formed as an aircraft meal table locking132b. The aircraft meal table locking132bis fastened to a rear side88bof the transverse frame element16bby means of the fastening unit24b. The fourth functional unit26billustrated by way of example inFIG.10is formed as an upholstery attachment138b, in particular as part of an upholstery attachment138b, for example as a fastening of a hook tape or a fleece tape. In the case illustrated, the upholstery attachment138bis formed in one piece with the transverse frame element16b. The upholstery attachment138bis arranged in a marginal area140bof the transverse frame element16b. The upholstery attachment138bruns partly around the transverse frame element16bon an outer side of the transverse frame element16b. Alternatively, the upholstery attachment138bcan be fastened to the transverse frame element16bby means of the fastening unit24b. The transverse frame element16billustrated by way of example inFIG.10has a stiffening element136b. The stiffening element136bis formed as a depression running in the form of a curve in the transverse frame element16b. The stiffening element136bconnects the two side frame elements12b,14b. The stiffening element136breplicates a course of a circumferential frame.

FIG.11shows a further alternative aircraft seat device46c. The aircraft seat device46chas a further alternative backrest frame unit10c. The backrest frame unit10ccomprises a first side frame element12c, a second side frame element14cand a transverse frame element16c. The transverse frame element16cconnects the two side frame elements12c,14c. The transverse frame element16cis formed as a bent sheet metal part. The transverse frame element16chas a fastening unit24c. The fastening unit24cis configured for mounting at least one functional unit26c. The transverse frame element16chas a stiffening element136c. The stiffening element136cis formed as a depression running in a curve in the transverse frame element16c. The stiffening element136cconnects the two side frame elements12c,14c. The stiffening element136creplicates a course of a circumferential frame. The stiffening element136cis configured to prevent torsion of the transverse frame element16c. The stiffening element136cis arranged, at least to a large extent, preferably completely, in a lower sub-region of the transverse frame element16c, preferably a lower half of the transverse frame element16c. Preferably, the stiffening element136cis arranged at least underneath fastening elements28c,30cof the fastening unit24c, such as, for example, a hole matrix92cfor fastening a headrest134c.