Aircraft seat device

An aircraft seat, including at least one electronics unit and at least one seat frame unit. The electronics unit is at least partially arranged in a hollow space spanned by the seat frame.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is a U.S. national stage application of PCT/EP2011/000743 filed on Feb. 16, 2011, and claims priority to, and incorporates by reference, German patent application No. 10 2010 008 460.3 filed on Feb. 18, 2010.

BACKGROUND

Aircraft seat devices having an electronics unit and a seat frame unit are already known, the electronics unit being secured on an underside of a seat base, which is supported on an aircraft floor via the seat frame unit.

SUMMARY

An aircraft seat device having at least one electronics unit and at least one seat frame unit, wherein the electronics unit is arranged at least partially in a hollow space defined by the seat frame unit, is proposed. Furthermore, an aircraft seat device having at least one electronics unit which has at least one supply unit for at least two components, and having at least one seat component, wherein the electronics unit is arranged at least partially in a hollow space defined by the seat component, is proposed. It is thereby possible to provide a solution with a design which saves a particularly large amount of space overall through advantageous use of a previously unused hollow space.

In this context, “seat frame unit” should be understood, in particular, to mean a unit provided for transmitting a weight force of at least one seat base and/or at least one backrest and, in particular, a weight force acting on the seat base and/or the backrest, to an aircraft floor. “Provided” should in all cases be understood to mean specifically equipped, designed and/or programmed. In particular, the seat frame unit has at least one seat leg, a seat divider which an armrest and/or a backrest is secured to, and/or at least one seat support beam, which is, in particular, aligned transversely to a sitting direction and which, in particular, is provided for the purpose of transmitting weight forces of the seat base and/or the backrest to the seat legs. “Hollow space” should be understood, in particular, to mean a space bounded on at least three sides by the component part forming the hollow space. For this purpose, the component part forming the hollow space can have a concave region, e.g. a U-shaped and/or V-shaped region, and/or preferably has, in at least one plane, a closed profile, within which the hollow space is arranged or by which the hollow space is surrounded in at least one plane. For this purpose, the component part forming the hollow space can, in particular, have the concave region on an outer side of an outer wall of the component part. The hollow space is preferably arranged within a component part of the seat frame unit, particularly preferably in a seat leg, in a seat divider and/or particularly advantageously in a seat support beam. If the hollow space is bounded at least partially by a seat support beam, it is possible, in a design which saves a particularly large amount of space overall, to use an advantageous hollow space, especially if the seat support beam is formed by a single seat support beam. “Single seat support beam” should be understood, in particular, to mean a seat support beam which is provided for the purpose of accepting torsional moments, in particular for use as an only crossbeam in a row of seats, via which weight forces of several seat bases and/or backrests are transmitted to seat legs.

“Seat components” should be understood to mean all the components of an aircraft seat, such as the seat base, the backrest, a seat casing, components of a seat frame unit etc. “Electronics unit” should be understood, in particular, to mean a unit which goes beyond a mere line and a mere plug, comprising at least one passive and/or, in particular, at least one active electronic component which is provided, in particular, at least in part for supplying power and/or, in particular, for processing data, for storing data, for open-loop and/or closed-loop control. “Supply unit for at least two components” should be understood, in particular, to mean a unit which is provided for the purpose of storing, making available and/or processing power and/or, in particular, data for at least two separate components, e.g. monitors, PC supply units, seat actuators, especially for separate seats. In particular, the electronics unit can be provided as an auxiliary unit for another data box to enable the other data box to be made as small and light-weight as possible. Through an appropriate configuration, existing, previously unused spaces can be used in an advantageous manner, and additional component parts, such as in particular additional housing elements, installation space and weight can be saved.

It is furthermore proposed that the seat frame unit have an access unit, which is provided for the purpose of allowing access to the hollow space in a direction oriented perpendicularly to a main extension direction of the seat frame unit in a floor-mounted state of the seat frame unit. In this context, “main extension direction” should be understood, in particular, to mean a direction which is parallel to an outer contour of the seat frame unit, and in which the seat frame unit has a maximum dimension. It is thereby possible to provide a solution that can be maintained and repaired in a simple manner, despite using the previously unused installation space.

If the access unit comprises a covering unit for covering the access to the hollow space, an electronics unit arranged behind the covering unit can be protected, in a particularly effective manner, from environmental influences and from unwanted interference by unauthorized persons.

It is furthermore proposed that the covering unit have a fixing means for fixing an installation position of the electronics unit. The fixing unit is preferably connected securely but detachably to the electronics unit. In this context, “connected securely but detachably” should be understood, in particular, to mean that a spatial separation of the fixing unit and the electronics unit is provided without any damage thereto, the separation requiring the use of tools. As an alternative, the fixing unit can be provided so as to form a positive-locking connection to the electronics unit in order to fix the installation position of the latter. In another embodiment, it is furthermore possible for the fixing unit to be configured to be connected integrally and, in particular, by a material bond to at least part of a housing unit of the electronics unit. It is thereby possible to combine covering of the access to the hollow space with reliably fastening the electronics unit to give a particularly compact solution.

It is furthermore proposed that the fixing means be at least partially matched to an outer contour of the seat frame unit in an installed state of the covering unit.

In this context, this should be taken to mean, in particular, that at least part of an outer edge region of the fixing means runs substantially parallel to a contact surface of the fixing means with the access unit. It is thereby possible to enable particularly good thermal coupling of the fixing means to the access unit of the seat frame unit, and to achieve good dissipation of waste heat from the electronics unit.

If the electronics unit is designed at least partially without a housing, it is, in particular, possible to save additional weight. “Without a housing” should be understood, in particular, to mean that the electronics unit has at least two passive and/or, in particular, active electronic components, which are preferably provided at least in part for processing data, storing data and/or supplying power, and are arranged adjacent to one another without a housing jointly enclosing said two electronics units.

In another embodiment of the invention, it is proposed that the aircraft seat device have at least one slide-in fastening element, onto which the electronics unit is slid in the mounted state. The slide-in fastening element is preferably formed by a rail which, when viewed in the mounted state, is advantageously aligned in a longitudinal direction of the hollow space and, in particular, in the longitudinal direction of the seat support beam. Through corresponding embodiment, easy assembly can be achieved, in particular by providing the slide-in fastening element for preassembly in the hollow space before the electronics unit is slid onto the slide-in fastening element. The slide-in fastening element preferably has a guide channel and/or a raised guide portion in order to guide the electronics unit when it is slid on and/or, in particular, to hold it in a positive-locking manner, in particular transversely to the longitudinal direction and parallel to a supporting surface of the slide-in fastening element and/or transversely to the longitudinal direction and in a direction away from the supporting surface.

If the electronics unit has at least one plug plate oriented in a longitudinal direction of the electronics unit, simple coupling respectively cable connection of the electronics unit to input-side and/or output-side units can be ensured. Herein, “plug plate” should be understood, in particular, to mean a unit having at least two, preferably at least three, plug connections, at least some of which are preferably arranged in one plane. Herein, “plug connection” should be understood, in particular, to mean a male and/or female plug-in means, such as a pin and/or a receptacle.

If the electronics unit has a fastening plate spaced apart, in the longitudinal direction, from the plug plate on a side facing the plug plate, advantageous fastening of the electronics unit can be ensured and an advantageous free space for a simple cable connection of the electronics unit can be achieved. In this context, “spaced apart” should be understood, in particular, to mean that the fastening plate and the plug plate are spaced apart in the longitudinal direction by at least 1 cm, preferably by several centimeters, thus providing, in particular, an interspace with a length in the longitudinal direction of at least 1 cm and preferably of several centimeters.

DETAILED DESCRIPTION

FIG. 1shows individual parts of an aircraft seat having an aircraft seat device according to the invention obliquely from above. The aircraft seat device comprises an electronics unit10and a seat component formed by a seat frame unit12, wherein the electronics unit10is arranged in a hollow space14defined by the seat frame unit12. The electronics unit10has a supply unit16for a plurality of components, in particular for a plurality of monitor units (not specifically shown) and for a plurality of seat control units (not specifically shown) for a plurality of aircraft seats in a row of seats, floor-mounted in a known manner on an aircraft floor52. For this purpose, the electronics unit10is connected to the plurality of monitor units and to the plurality of seat control units directly and/or indirectly, e.g. via a hub, which is provided, in particular, to connect network nodes in a star shape.

The hollow space14is bounded by a seat support beam18, more specifically by a single seat support beam, and is surrounded in a plane transverse to the longitudinal direction of the single seat support beam by a closed profile of the single seat support beam (FIGS. 1 to 4). The single seat support beam has an upper shell28and a lower shell30(FIGS. 2 and 4), which form the closed profile, the upper shell28being omitted inFIGS. 1 and 3to better illustrate the electronics unit10. The seat support beam18is made of aluminum, thereby making it possible to ensure advantageous heat dissipation from the electronics unit10. The seat support beam18is connected to seat legs46,48and to seat dividers50and is arranged transversely to a sitting direction122. A plurality of seat bases (not specifically shown) and backrests of aircraft seats of the row of seats are attached to the seat support beam18. The seat support beam18is used, in particular, to transmit to the seat legs46,48forces acting on the seat bases and on the backrests of the row of seats.

The electronics unit10has a support plate32and a plug plate22, which is arranged on the support plate32, is oriented in the longitudinal direction20thereof and closes off a housing unit34of the electronics unit10a(FIGS. 5 to 7). The electronic components of the electronics unit10are arranged on the support plate32. The support plate32is made of a metallic material, namely aluminum, thereby ensuring particularly advantageous heat dissipation. The plug plate22comprises plugs (not specifically shown) for cable connection of the electronics unit10. The outer contour of the housing unit34is matched to an inner contour of the seat support beam18. Here, “matched” should be understood, in particular, to mean that, in at least one plane transverse to the longitudinal extent of the seat support beam18, there is, in the region of the housing unit34, an interface between the outer contour of the housing unit34and the inner contour of the seat support beam18, which is less than 30%, preferably less than 20%, and particularly preferably less than 10% of a total area defined by the inner contour of the seat support beam18in said plane.

Instead of an electronics unit10with a housing unit34, it would also be possible to provide an electronics unit10adesigned at least partially without a housing, as illustrated schematically inFIG. 9. The electronics unit10ahas a plurality of electronic components, which are provided for processing data and/or storing data and are arranged adjacent to one another without a common housing surrounding them.

On a side facing the plug plate22, the electronics unit10has a fastening plate24spaced apart from the plug plate22in a longitudinal direction20. The fastening plate24is used for fastening to an outer rib of the seat support beam18and, for this purpose, has two fastening apertures36,38. The fastening plate24furthermore has an aperture40arranged in a central region thereof, said aperture40allowing advantageous cable routing from the plug plate22out of the hollow space14. Cables coupled to the plug plate22are passed out of the hollow space14through the aperture40at a front end of the seat support beam18. Outside the hollow space14respectively outside the seat support beam18, the cables are advantageously guided onwards in cable ducts (not specifically shown) which are fastened to an underside of the seat support beam18. Advantageous contacting of the electronics unit10is ensured by means of an interspace which is formed between the plug plate22and the fastening plate24.

For simple mounting of the electronics unit10, the aircraft seat device has a slide-in fastening element26, onto which the electronics unit10is slid in the mounted state (FIGS. 4 and 8). The slide-in fastening element26is slid into the seat support beam18in the longitudinal direction of the latter in advance, without the electronics unit10, and fastened therein, more specifically the slide-in fastening element26is screwed to the lower shell30of the seat support beam18. On its top side, the slide-in fastening element26has a guide channel, which is formed by a longitudinal groove42of T-shaped cross section. On its underside, the electronics unit10has a T-shaped foot44, by means of which the electronics unit10is slid into the T-shaped longitudinal groove42of the slide-in fastening element26and is fixed in a positive-locking manner, in particular transversely to the longitudinal extent of the seat support beam18, in the mounted state.

FIG. 10shows a detail of the aircraft seat device shown inFIG. 1with another embodiment of a single seat support beam58and an electronics unit54in an installed state. The electronics unit54is arranged in a hollow space56defined by the seat frame unit12. In contrast to the embodiment inFIG. 1, the single seat support beam58of the seat frame unit12has an access unit60on an underside facing the aircraft floor52, said access unit60comprising an edge region62of a rectangular opening in the single seat support beam58and a plurality of fastening means designed as threaded holes64. The access unit60is provided for the purpose of allowing access to the hollow space56in a direction oriented perpendicularly to a main extension direction66of the seat frame unit12in a floor-mounted state of the seat frame unit12. By virtue of the access, the electronics unit54can be removed easily from the hollow space56for installation and for maintenance or repair work.

For the purpose of covering the access to the hollow space56, the access unit60furthermore has a covering unit68, which comprises a rectangular plate70the dimensions of which are larger than those of the rectangular opening and which is provided with circular apertures72, the positions of the circular apertures72corresponding to positions of the threaded holes64in the edge region62of the opening of the single seat support beam58, and further comprises fastening means in the form of screws74. The electronics unit54arranged, in an installed state, behind the covering unit68in the hollow space56defined by the seat frame unit12is thus protected from environmental influences and from unwanted interference by unauthorized persons.

FIG. 11shows a detail of the aircraft seat device shown inFIG. 1with another embodiment of a single seat support beam78and an electronics unit76. In contrast to the embodiments inFIGS. 1 and 10, the single seat support beam78of the seat frame unit12has an access unit80on an upper side facing away from the aircraft floor52, said access unit80comprising an edge region82of a rectangular opening in the single seat support beam78and a plurality of fastening means which are formed by threaded holes84. The access unit80allows access to a hollow space86defined by the seat frame unit12(left-hand part ofFIG. 11).

For the purpose of covering the access to the hollow space86defined by the seat frame unit12and to the electronics unit76arranged in the hollow space86, the access unit80furthermore has a covering unit88. The covering unit88is equipped with a fixing means90for fixing an installation position of the electronics unit76. The fixing means90, which is designed as a flange element, is securely connected to a housing unit92of the electronics unit76by means of a material bond effected by welding. Dimensions of the rectangular opening of the single seat support beam78and of the housing unit92of the electronics unit76are designed in such a way that the electronics unit76can be inserted through the rectangular opening into the hollow space86defined by the seat frame unit12.

The flange element, the dimensions of which are larger than those of the rectangular opening and which is provided with circular apertures, the positions of said apertures corresponding to positions of the threaded holes84in the edge region82of the opening in the single seat support beam78, can be fastened to the single seat support beam78by means of further fastening means in the form of screws94, thereby fixing the installation position of the electronics unit76. The right-hand part ofFIG. 11shows the electronics unit76in the installation state.

The flange element has an external shape which is matched to outer contours of the single seat support beam78of the seat frame unit12, said contours being formed, on the one hand, by a cut with a cutting plane which is oriented in the sitting direction122and perpendicularly to the aircraft floor52and, on the other hand, by a cut with a cutting plane which is oriented perpendicularly to the sitting direction122. As a result, the flange element is, over its full circumferential length, in contact with the single seat support beam78of the seat frame unit12in the installed state of the electronics unit76, thus ensuring good dissipation of waste heat produced by operation of the electronics unit76to the seat frame unit12.

A detail of the aircraft seat device shown inFIG. 1with another embodiment of a single seat support beam and an electronics unit96is illustrated schematically inFIG. 12. In contrast to the embodiments inFIGS. 1,10and11, the single seat support beam98of the seat frame unit12has a concave region on an outer side100of an outer wall102, namely an upper side facing away from the aircraft floor52, by means of which region the single seat support beam98of the seat frame unit12forms a hollow space104, which is bounded by the outer side100of the outer wall102on three sides. In a section plane aligned parallel to the aircraft floor52, at a level indicated by the line V-V′, the hollow space104designed as a concave region has a closed profile in the form of a circle.

The single seat support beam98of the seat frame unit12has an access unit106which comprises an annular edge region108of the concave region of the single seat support beam98and a plurality of fastening means, which are formed by threaded holes110. The access unit106is provided for the purpose of allowing, in a floor-mounted state of the seat frame unit12, access to the hollow space104formed by the concave region in a direction oriented perpendicularly to a main extension direction112of the seat frame unit12. By virtue of the access, the electronics unit96can be removed easily from the hollow space104for installation and for maintenance or repair work.

For the purpose of covering the access to the hollow space104, the access unit106furthermore has a covering unit114, which comprises a circular plate116the diameter of which is larger than that of the concave region and which is provided with circular apertures, the positions of said circular apertures corresponding to positions of the threaded holes110in the annular edge region108of the concave region of the single seat support beam98, and which has further fastening means in the form of screws118. The circular plate116of the covering unit114is connected securely but detachably to a housing unit120of the electronics unit96and can be separated from the latter nondestructively by means of tools. The plate116of the covering unit114thus simultaneously forms a fixing means for fixing an installation position of the electronics unit96. The outside dimensions of the electronics unit96are matched to the concave region of the single seat support beam98. The circular plate116of the covering unit114is matched, in its edge region and in a central region, to a contour of the single seat support beam98. As a result, the covering unit114is, in the installed state of the electronics unit96, in contact with the single seat support beam of the seat frame unit12over the full circumferential length of the covering unit114, thus ensuring good dissipation of waste heat produced by operation of the electronics unit96to the seat frame unit12. In an installed state of the electronics unit96, the covering unit114furthermore forms a substantially smooth contour with the single seat support beam98of the seat frame unit12, and therefore the covering unit114can be regarded as an extension of the outer side100of the outer wall102of the single seat support beam98, outside the concave region. Behind the covering unit114, the electronics unit96arranged in the hollow space104defined by the seat frame unit12is protected from environmental influences and from unwanted interference by unauthorized persons.