• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    TITLE: Fastening system for attaching a component to a fuselage structure A fastening system (6) for attaching components (4) to a fuselage structure (1) in an interior space of an aircraft comprises a frame of retainer (20) comprising a first edge (26) and a second edge (28) spaced therefrom, at least one first retainer (16) which can be coupled to the fuselage structure (1) and is constructed for being articulately connected to the retaining frame (20) in a first region (24), close to the first edge (26), of the retaining frame (20), at least one second retaining element (18) which can be coupled to the fuselage structure (1) and at least one retaining bar (22) which can be hingedly connected at one end to the second retaining element (18) and which can be articulately connected by a second end, to the retaining frame (20) in a two th region (30) facing the second edge (28) and opposite the first edge (26). The retaining frame (20), the retaining bar (22) and the first retaining element (16) and the second retaining element (18) are designed to form, together with the first and second retaining elements (16, 18) arranged spaced from one another along a peripheral direction of the fuselage structure (1), a triangular structure, the retaining bar (22) and the retaining frame (20) forming a first side and a second side of the triangular structure, and at least one of the retaining frame (20), the retaining bar (22), the first retaining element (16) and the second retaining element (18). ) being adapted to variably adjust a length of the first side and / or the second side to adjust the position of the retaining frame (20). Figure 1
    公开号:FR3076541A1
    申请号:FR1873493
    申请日:2018-12-20
    公开日:2019-07-12
    发明作者:Hermann Dipl. -Ing.BENTHIEN
    申请人:Airbus Operations GmbH；
    IPC主号:
    专利说明:

    Description
    Title of the invention:: Fastening system for fixing a component to a fuselage structure
    Technical Field [0001] The invention relates to a fixing system making it possible to fix a component to a fuselage structure in an interior space of an aircraft, as well as an aircraft comprising a fuselage provided with a fuselage structure and at least one component which is attached to the fuselage structure using such a fastening system.
    Background of the invention [0003] In an aircraft which comprises a fuselage, a passenger cabin provided with a plurality of items of equipment is generally present. The fuselage constructed using a fuselage structure is provided for this purpose, on its inner side, with a plurality of retaining elements which are individually adapted to the items of equipment to be received and achieve their safe mounting in a predefined location. In aircraft and in particular in large airliners with a fuselage length of well over 10 m, there are always some manufacturing tolerances that must be taken into account when fitting restraints. While equipment objects must have a clearly predefined geometry in the fuselage, it is therefore necessary to adapt the individual retaining elements to compensate for the manufacturing tolerances of the fuselage structure. For example, a corrugation of a line or surface formed from several upper storage compartments is much more limited than, for example, dimensional tolerances of the fuselage structure.
    Compensation of tolerances to adapt the visible contour inside an aircraft cabin is difficult. The adjustment can in particular go hand in hand with the opening and closing of screw connections which consist, for example, of nuts and lock nuts on threaded bodies. In addition, due to the necessary retaining elements on the fuselage structure, individualization or retrofitting of equipment items is difficult since additional retaining elements have to be mounted on structural elements or existing retaining elements have to be be removed and reassembled in other locations. The items of equipment are fixed in the fuselage against collision accelerations for the emergency case. If the position of the equipment objects changes, a new fuselage-side link must also be made and the old link must be removed. The invention also aims to prevent this complexity. Summary of the invention
    权利要求:
    Claims (3)
    [1" id="c-fr-0001]
    It could be very advantageous to have available a fixing system which allows a flexible connection, which can be individualized or allowing the retrofitting of equipment objects.  This should as far as possible be achieved without complex modification or high manufacturing complexity.  [0006] Consequently, the invention aims to provide a fixing system making it possible to fix components to a fuselage structure in an aircraft, which fixing system can be used as flexibly as possible for receiving items of equipment. and is able to apply loads evenly distributed in connection points of the structure, the adjustment having to be as simple as possible in particular for compensation of tolerances.  The object of the invention is also to prevent the complexity associated with the abovementioned withdrawal of old routes and the creation of new routes.  This objective is achieved thanks to a fixing system having the characteristics of independent claim 1.  Advantageous improvements and embodiments arise from the dependent claims and the description below.  The invention relates to a fixing system for fixing components to a fuselage structure in an interior space of an aircraft.  The fastening system comprises a retaining frame comprising a first edge and a second edge spaced therefrom, at least a first retaining element which can be coupled to the fuselage structure and is designed to be hingedly connected to the frame retaining device in a first region, close to the first edge, of the retaining frame, at least one second retaining element which can be coupled to the fuselage structure and at least one retaining bar which can be hingedly connected by a first end, to the second retaining element and which can be hingedly connected, by a second end, to the retaining frame in a second region facing the second edge and opposite the first edge.  The retaining frame, the retaining bar, and the first retaining member and the second retaining member are adapted to form, with the first and second retaining members spaced apart from one another along a peripheral direction of the fuselage structure, a triangular structure, the retaining bar and the retaining frame forming a first side and a second side of the triangular structure.  At least one of the retaining frame, the retaining bar, the first retaining member and the second retaining member is adapted to variably adjust a length of the first side and / or the second side to adjust the position of the retaining frame.  The fixing system thus comprises a row of main components, which jointly produce devices, very advantageous and easy to handle, used to fix a component.  A support frame as mentioned above is used to receive a component or to connect it to the fuselage structure.  The retaining frame can in this case form a part of the component, support a component or retain a plurality of independent or interdependent components.  Regardless of the external shape, for the system according to the invention, it suffices that the retaining frame comprises two regions which are respectively located near a limit edge of the retaining frame and can be connected to a first retaining element or to a retaining bar.  A retaining frame may in particular have a flat, planar shape.  This form does not have to be completely filled with material.  The planar form can also be only an extent plane in which a frame or framework structure is arranged which allows the connection to a first retaining element or to a retaining bar.  Depending on the embodiment of the aircraft or cabin, the retaining frame may have a length such that it is fixed to the fuselage structure using several first retaining elements, several retaining bars and therefore several second retaining elements.  A first retaining element is intended to connect a fuselage element and the retaining frame.  The first retaining element can be connected directly to an element of the fuselage structure.  Alternatively, the first retaining element may also be connected indirectly, that is to say by means of at least one intermediate component, to the fuselage structure.  For example, the first retaining element may be coupled to a fuselage couple, to a flange, to a point of intersection between a fuselage couple and a longitudinal (smooth) stiffening element or to another element.  In a simple case, the first retaining element can be a kind of clamping element, which engages around a fuselage structure element in the manner of clamps and is fixed by complementarity of form or by bonding of material. in a desired position.  The second retaining element can be produced similarly to the first retaining element and serves to retain the first end of the retaining bar.  It may be advantageous to have the first retaining elements and the second retaining elements in pairs on the same fuselage structure element or at least in the same longitudinal position inside the fuselage.  The first and second retaining elements, which can be mounted on the fuselage structure, can be fixed to fuselage structure elements at regular intervals.  It is conceivable that the retaining elements are arranged, already during the manufacture of the fuselage or of the fuselage structure, on the latter.  This may be the case regardless of the subsequent configuration of the interior space of the aircraft.  In a particularly preferred manner, the first and second retaining elements can be made as a complement to angles, flanges or the like already existing which must in any case be used for the manufacture of the fuselage structure.  Thanks to an appropriate modification of the external shape of elements of this type, it is possible to obtain a corresponding adequacy as first or second retaining elements.  The retaining bar can be considered as an elongated component or a component which is characterized at least by a direction of significant extent.  The retaining bar retains the retaining frame, by its second region, on the second retaining member, the first region of the retaining frame being disposed above a first retaining member on the first base body.  The retaining bar therefore extends from the fuselage structure into the interior of the cabin, in order to retain there a second region, opposite to the fuselage structure, of the retaining frame, which also extends in the cabin.  The retaining bar and the retaining frame thus form two sides of the triangular structure which extend inside the cabin.  In order to adjust a spatial orientation of the retaining frame, which subsequently defines the spatial orientation of the component to be retained, at least one of the retaining frame, the retaining bar, the first retaining element and the second retainer can be designed to adjust a length of the first side and / or the second side.  The orientation of the retaining frame on the first retaining element can for example be modified by an adjustable distance between the first retaining element and the retaining frame.  For a row of retaining frames arranged one behind the other in a cabin, a lateral position of all the restraining frames concerned can thus for example be adjusted so that these lead together to a harmonious arrangement in the case where the first retaining element is used for the lateral support.  To further adjust the orientation of the retaining frame, the distance between the second region of the retaining frame and the second retaining element can be changed.  In the case where this distance must remain identical, the position of a connection between the retaining frame and the second end of the retaining bar in the second region can however also be modified.  These two adjustment variants can also be combined with one another.  Overall, a very flexible possibility of adjustment is thus offered.  Another advantage of this configuration results from a very advantageous assembly.  For example, a component to be connected to the retaining elements can first of all be connected to corresponding second retaining elements by means of the retaining bar or of several such retaining bars.  If a whole row of components of the same configuration are connected to the fuselage structure, all of these components can already be connected via a plurality of retaining bars, so that they are thus suspended from the second retaining element .  In this position, a piece of equipment, a mechanical or electrical connection or the like can be produced before all the components can then be fixed to the first retaining elements by approximation by pivoting.  Of course, this can also be done in reverse, by the fact that all the components are hooked first of all to the first retaining element or to the first retaining elements to then be connected to the corresponding second base bodies by pivoting towards the top and connection of the retaining bars.  The assembly and in particular the combination of the individual components is thus considerably facilitated.  This advantage may, in a particular example, arise from the fact that electrical or pneumatic systems which are associated with a service channel or with a plurality of service blocks above passenger seats can be arranged behind an upper storage compartment of shortened profile.  An advantageous embodiment further comprises at least one elongated base body, said at least one elongated base body which can be fixed to several first and / or second retaining elements and is designed to apply a force acting along an axis of extent of the basic body in several first or second retaining elements.  An elongated base body is an elongated bar-shaped body which body can be attached to the fuselage structure using a number of retaining elements.  The base body is in particular intended to absorb forces which act along the axis of extension of the base body and are transmitted, by means of the base body, along its direction of extension.  The forces may in this case be applied by first retaining elements or second retaining elements in such a basic body or be absorbed by the basic body by means of first or second retaining elements.  It is possible, by means of such an assembly, to relieve one or more force retaining elements which are oriented along the direction of extension of the base body.  In addition, a basic body is able to retain component supports which can for their part be used to retain a component.  Embodiments are described below.  The basic bodies can, when arranged on the fuselage structure, form a kind of interface with the help of which forces can be transmitted from equipment items or components to the fuselage structure.  These are in particular forces proportional to mass and inertial forces.  A basic body can extend over a large part of the fuselage, in particular along a longitudinal axis of the fuselage.  A basic body may in particular have a uniform and constant cross section, so that at any location inside the fuselage, the same conditions for a support of a component can be achieved.  The type of cross-section of the base body is immaterial.  It may be appropriate, as described below, to provide a circular cross section.  In an advantageous embodiment, the first base body and the second base body are produced respectively in the form of a tube.  The use of a tube has particular advantages in terms of attachment to the fuselage structure.  In addition, a tube as such can be made particularly easily by established methods and can also be made in relatively large lengths.  In airliners with fuselages of aircraft whose length greatly exceeds 10 m, it is possible here to work with long tubes made continuously.  The cross section of such a tube is characterized by a peripheral wall and a hollow space.  The thickness of the wall and the outside diameter of the tube depend on the expected stress and the material used.  Metals in particular may be suitable as a material, in particular aluminum-based alloys.  These exhibit a behavior at expansion similar to that of a metallic fuselage structure.  The first or second retaining elements are, in an advantageous embodiment, designed to rigidly retain the respective base body.  It is conceivable that a plurality of first or second retaining elements extend along the fuselage structure, to retain one or more basic bodies.  The material structure of the base body could, in such an embodiment, be provided such that a base body can flex to a certain degree to compensate for adaptation to positional deviations within the range of manufacturing tolerances of the first or second individual retaining elements.  A base which is particularly easy to manufacture and which is used to arrange any components and to transmit forces in an aircraft fuselage is thus made possible.  Thanks to the fixing system's compensation possibilities, sufficient accuracy in the orientation of the components can also be obtained in the case of a base of this type.  It should be noted here that the first retaining element can constitute a retaining element both for the retaining frame and for a basic body.  The first retaining element can be designed to adjust an adjustable distance between the first region of the retaining frame and the first retaining element.  Thus, the side length represented by the support frame can be enlarged or reduced depending on local conditions.  The adjustable distance can be achieved by different means.  In addition to a usual combination of a threaded body and a nut or lock nut, a safety pin and other fixing measures, other toothed elements could also be used, which can be inserted and fixed, in variable positions, in a homologous toothed part.  The first retaining element may comprise a first connector provided with an opening comprising, in certain areas, a first toothing and a second connector provided with an elongated body comprising, in certain areas, a second toothing, the elongated body can, in a first orientation relative to the opening of the first connector, be plugged therein and providing, by rotation in a second orientation, a connection by complementarity of shape of the first toothing and the second toothing.  One of the first connector and the second connector can be permanently coupled to the fuselage structure, while the other one of the first connector and the second connector can come into connection with this connector then secured to the structure.  The insertion depth of the second connector can therefore be selected by joining the first connector and the second connector and then be locked by rotation.  With this measurement, the insertion depth of the second connector can easily be selected so that the first region of the retaining frame is at a desired distance from the fuselage structure.  The gradation of the distance is in this case directly dependent on the teeth of the first connector and of the second connector.  In this case, it does not matter which side of the first connector the opening or the elongated body is connected to.  It must however be ensured that, during assembly of the component, good access to the elongated body or to the body comprising the opening is obtained, so as to be able to rotate during assembly.  This type of adjustment is very judicious because the elongated body can for example be inserted into the opening only to a certain degree, through a mounting frame which defines a final position of the retaining frame, to then be turned and thus fix the position reached.  Screwing, mounting a safety pin and the like could be eliminated in this case.  These features can of course also be achieved in the second aforementioned second retaining element.  To obtain these characteristics, the first retaining element or the second retaining element can be provided with a fixing cylinder which can be positioned in the first or the second retaining element.  If an elongated base body in the form of a tube is located in the relevant retaining element, the fixing cylinder can be inserted into this base body, so that it is located directly at the interior of the affected retainer.  Through the slot or cavity in the base body, which corresponds to a slot or cavity in the relevant retaining element, the fixing cylinder can be accessed from the outside.  For example, the fixing cylinder may have a longitudinal axis and a transverse axis extending perpendicularly to the latter.  An opening in which a toothing is arranged extends along the transverse axis.  The opening with the teeth thus forms the first connector.  An elongated body with a second set of teeth can be inserted, into a desired insertion depth, into the fixing cylinder from the outside through the relevant retaining element and the opening or the cavity in the tube, to to produce by a subsequent rotation a bond by complementarity of form.  The retaining bar can be provided with a similar configuration.  The retaining bar or the second retaining element may comprise a first connector provided with an opening comprising, in certain areas, a first toothing and a second connector provided with an elongated body comprising, in certain areas, a second toothing, the elongate body which, in a first orientation relative to the opening of the first connector, can be inserted in the latter and making, by rotation in a second orientation, a connection by complementary shape of the first toothing and the second toothing.  Thus, one end, opposite the retaining frame, of the retaining bar and / or one side, opposite the retaining frame, of the retaining bar can be provided with an adjustment possibility similar to that of the first retaining element. .  In view of the acoustic decoupling of the fixing cylinder and the first or second base body, it is conceivable to use a decoupling element made of a synthetic material.  This can surround the fixing cylinder in an annular manner and can be introduced with the fixing cylinder into the base body concerned.  In order to obtain a transverse bore in which the toothing of the fixing cylinder is located, the decoupling element can be provided with a cutout, in particular with an oblong hole.  Preferably, the decoupling element comprises a synthetic material.  In a particularly preferred manner, the synthetic material is a thermoplastic synthetic material.  The fixing system may further comprise at least one tolerance compensation device arranged in the second region of the retaining frame, the tolerance compensation device being able to be connected to the retaining bar and being designed to move and for locking a position for connecting the retaining bar to the retaining frame between the second edge and the first edge.  In case of otherwise unchanged length of the retaining bar, a very precise adjustment in particular of the position angle of the retaining frame can be carried out according to the geometry of the triangular structure.  This tolerance compensation device may include a slide pivotally connected to the retaining bar and an elongated recess disposed on the retaining frame and provided with a sliding guide, extending along the extent of the recess, serving to guide the slide by sliding, the recess and the slide being respectively equipped, in certain zones, with a first toothing, and an elongated locking element provided with a second toothing in certain zones being positioned in the recess and being designed to make, in a first orientation, a connection by complementary shape between the first toothing and the second toothing, so that the position of the slide on the sliding guide is locked, and that the connection by complementarity of form is released in a second orientation.  Consequently, the retaining bar can be moved by means of the slide along the recess when the elongated locking element is oriented in such a way that no teeth form a connection by shape complementarity with the locking element. elongate.  It is therefore very easy to adjust the position angle of the retaining frame, for example in the case of a released locking element and of the retaining frame placed on a support.  If a desired end position is reached, the locking element can perform locking.  In a particularly advantageous embodiment, the retaining frame can be an element of the component to be fixed.  The component can for example be a module which allows different communication devices between a passenger and another electronic device.  In addition, an oxygen supply device and a corresponding electronic unit can be arranged thereon.  All of these elements can be arranged on a common or similar module support, which forms the retaining frame.  Of course, other examples and embodiments are conceivable, which can be positioned at any location inside an interior space of an aircraft.  The invention further relates to an aircraft comprising a fuselage with a fuselage structure and at least one component which is fixed to the fuselage structure using a fixing system mentioned above.  The aircraft may in particular be an airliner.  In an advantageous embodiment, the component can be a passenger service unit or an upper storage compartment.  These two components form a large part of an aircraft passenger cabin because the upper storage compartments as well as the service blocks extend above the passenger seats practically throughout the cabin.  Thanks to the fixing system according to the invention, a very uniform orientation of the individual components is allowed, so that the visual appearance of the cabin meets all requirements.  The fuselage may have a longitudinal axis, a right side and a left side and, along a large part of the fuselage, at least one elongated base body on the right side and on the left side.  One could also provide, on each side of the fuselage, basic bodies spaced from each other in the peripheral direction.  One could also consider other basic bodies which can be arranged in the cabin in order to retain different components.  In addition, the aircraft comprises at least one piece of equipment and at least one piece of equipment support, the equipment being erected on a floor arranged in the fuselage and being connected to a basic body by means of the at least an equipment support, by a part, spaced from the floor, of the equipment.  For example, a bottom side of the equipment can be fixed near the floor, for example on a floor or seat slide.  At an end opposite to it or at a region at least opposite to it, secure attachment may be allowed to a base body by means of the equipment support.  This equipment support is intended in particular to absorb forces which act along the longitudinal axis of the fuselage.  The equipment support can be produced in the form of an elongated bar which is connected, by one end, to a part, spaced from the equipment along the longitudinal axis, of the basic body concerned and is connected, by another end, to the equipment.  The equipment support consequently extends along the longitudinal axis away from the equipment, so that, thanks to this connection, in particular only compression and traction forces act on the body. corresponding base.  The equipment support can be made similar to the aforementioned retaining bar.  In particular, the equipment support can also be provided with a device for compensating tolerances, which device makes it possible to adjust a position along the basic body.  BRIEF DESCRIPTION OF THE FIGURES Other characteristics, advantages and possibilities of application of the present invention follow from the description below of the exemplary embodiments and the figures.  In this case, all the features described and / or illustrated form in themselves and in any combinations the subject of the invention also independently of their composition in the individual claims or their dependencies.  In the figures, identical reference signs designate identical or similar objects.  [Figure 1] illustrates a component fixed, by means of the fixing system, to a fuselage structure of an aircraft.  [Figures 2a to 2c] illustrate the arrangement of a second retaining element 18 on the fuselage structure.  [Figure 3 illustrates an arrangement consisting of an upper storage compartment and a component on the fuselage structure.  [Figure 4] illustrates a detailed representation of a first retaining element.  [Figures 5a to 5d] illustrate different equipment of a basic body.  [Figures 6a to 6c] illustrate a possibility of compensation for tolerances for the attachment of a retaining bar.  [Figures 7a and 7b] illustrate a fixing, in certain areas, of equipment.  [Figure 8] illustrates a detailed view of a second retaining element.  [Figures 9a and 9b] illustrate an acoustic decoupling of a fixing cylinder.  [Figure 10] illustrates an aircraft in which components are arranged.  Detailed representation of examples of embodiments [Figure 1] illustrates a fuselage structure 1 provided with a component 4, which is connected to the fuselage structure 1 by means of a system of fixing 6.  The fuselage structure 1 is shown by way of example in the form of a pair 2, which generally surrounds a substantially fuselage of an aircraft on its interior side.  Several pairs 2 are spaced apart from each other along the longitudinal axis x.  Of course, longitudinal stiffening elements 8 can also be provided, which are in direct connection with an outer skin 10 as well as with the pairs 2 and extend along the longitudinal axis x of the fuselage spaced apart others in the peripheral direction.  Component 4 may, for example, be part of a passenger service unit (Passenger Service Unit, PSU), which service blocks are arranged above passenger seats and make various devices available to passengers.  In particular, there are devices which are supplied with electricity, data and air.  Component 4 in Figure 1 is greatly simplified and can be fitted with various supply lines or lines.  The fastening system 6 comprises, in this example, a first elongated base body 12, a second elongated base body 14, several first retaining elements 16 and several second retaining elements 18 using which, between others, the basic bodies 12 and 14 are retained on the fuselage structure 2.  The fastening system 6 also comprises a retaining frame 20 as well as retaining bars 22.  The two base bodies 12 and 14 can be made in the form of tubes which extend substantially over the entire length, to be fitted with components 4, of the fuselage.  The base bodies 12 and 14 have a first outside diameter Da as well as an inside diameter D; the dimensions of which can be adapted to the material properties of the base bodies 12 and 14.  It is conceivable that the base bodies 12 and 14 are fixed to each pair 2 inside the vehicle fuselage, cross them or pass in front of them.  In other words, this means that the base body 12 or 14 is rigidly connected to a plurality of points of the fuselage structure 2 by means of first retaining elements 16 or second retaining elements 18.  For each base body 12, 14, there is therefore provided a chain of first retaining elements 16 or second retaining elements 18 which are connected to the fuselage structure 1.  These retaining elements 16 and 18 then serve to absorb all the loads which are absorbed by the base bodies 12 and 14.  The first base body 12 is connected to a first region 24 of the retaining frame by means of the first retaining element 16.  The first region 24 means a position which is located near a first edge 26 of the retaining frame 20 and is equipped with a corresponding device for connection to the first retaining element 16.  This is explained below.  The retaining frame 20 further comprises a second edge 28 which is opposite the first edge 26.  Here, a second region 30 is indicated, which is equipped with a corresponding housing for the connection to the retaining bar 22.  This is explained in more detail in the figures below.  The retaining bar 22 is however connected not only to the retaining frame 20 in the second region 30 but also to the second retaining element 18.  The result is a fixing triangle in which one side is formed by the retaining frame 20 and another side is formed by the retaining bar 22.  An imaginary connecting line between the first base body 12 and the second base body 14 can be interpreted as the third side.  Thanks to such an arrangement, the mounting of a component 4 can be considerably facilitated compared to known methods, and the orientation of the retaining frame 20 in space, that is to say in the cabin of the aircraft, is greatly improved thanks to the triangular structure.  An adjustment of a distance from the first edge 26 to the first base body 12 or to the first retaining element 16 as well as an adjustment of the length of the retaining bar 22 or of its connection to the second base body 14 or the second retaining element 18 and / or the retaining frame 20 allow two-dimensional orientation over large angular and linear zones.  The possible embodiments of adjustable retaining elements, that is to say first retaining elements 16 and second adjustable retaining elements 18 and the connection of the retaining bar 22 are indicated below.  [In FIGS. 2A to 2C] is shown a fuselage structure 1 on which are arranged several flanges 32 which can be connected both to a couple 2 and to the fuselage skin 10.  The flanges 32 have a shape curved several times and allow support for the couple 2 on the fuselage skin 10 or on the heddles 8.  The fastening system 6 can be connected to flanges 32 of this type.  For this purpose, a surface part 34 extending along the longitudinal axis x must for example be enlarged at least in certain areas so as to produce an extension, which is designated by 34 ’.  This very slight modification of the flange 32 leads to the capacity of the fuselage structure 1 to absorb even greater loads.  A modification of the flanges 32 may preferably extend over the entire fuselage structure 1, the flanges 32 having to be integrated themselves directly during the manufacture of the fuselage structure 1 or of the aircraft.  On one side, opposite the flange 32, of the couple 2 is shown a receiving device 36 which is connected to the flange 32.  The receiving device 36 comprises, by way of example, a U-shaped profile and is used to receive, in the case presented, the second retaining element 18 or is part of it.  It may be appropriate to integrate the reception devices 36 already also during the manufacture of the fuselage structure 1 or of the aircraft, in order to be able to mount second retaining elements 18 if necessary.  This is however not absolutely necessary, the receiving devices 36 can also be fitted later.  The equipment of the fuselage structure 1 with flanges 32 of this type, enlarged slightly by way of example, allows very flexible equipment, if necessary, of the fuselage with first retaining elements 16, second retaining elements 18, base bodies 12 and 14, on which some components 4 can be retained.  The mounting of a second retaining element 18 on the fuselage structure 2 is shown in Figure 2B.  At this location, we see a receiving surface 19 opposite the couple 2, which is indicated again in Figure 3 and is used to receive an upper storage compartment.  If a receiving device 36 is connected to the fuselage structure 2, a base body 14 which is for example already equipped with second retaining elements 18 can be brought closer to the receiving device 36, to then be fixed there, for example, using a safety pin 38 or another device.  It may be appropriate to provide a retaining frame inside the cabin when mounting a whole row of components 4, retaining frame on which base bodies 14 already prepared, to which components 4 are connected, are brought together of all receiving devices 36.  Then, a fixing can be carried out little by little along the whole extent of the cabin.  Of course, the fixing can also be carried out inversely in this sense that the prepared base bodies 12, on which are arranged the first retaining elements 16, are brought together, in the cabin, of the couples 2 on which devices are arranged reception (not shown), to then carry out the fixing.  As explained with reference to Figure 1, the fastening system according to the invention can perform particularly simple tolerance compensation.  This is intended to be able to orient relative to each other components 4 juxtaposed in particular along the longitudinal axis of the aircraft so that they form a very uniform continuous surface, the latter preferably being able to be substantially free from undulations, steps or other irregularities, independently of the undulation of the fuselage structure 1.  [Figure 3] illustrates a slightly reduced view of the fuselage structure with the components 4 according to Figure 1 as well as an additional upper storage compartment 40.  This is modified compared to the known upper storage compartments in the sense that it has a reduced depth compared to the known storage compartments.  While a traditional upper storage compartment often extends further towards the underlying couple 2, the upper storage compartment 40 illustrated here comprises a rectilinear rear edge 42 which extends approximately parallel to the retaining bar 22 and is slightly spaced from it.  An upper region of the rear edge 42 or of the rear limit surface 42 rests on the bearing surfaces 19 of several second retaining elements 18 and is in particular screwed onto them.  A front region 44 of the storage compartment 40 is provided with a retaining bar 46, which extends from the storage compartment 40 upwards in the direction of the pair 2.  The retaining bar 46 is connected thereto to a third retaining element 48.  The retaining bar 46 as well as the third retaining element 46 can be produced in a similar manner to the retaining bar 22 and to the first retaining elements 16.  The third retaining element 48 can in particular be provided with the same adjustment possibilities as the second retaining element 18.  The only thing missing is the support surface 19, which is intended exclusively for receiving the storage compartment 40 on the second retaining element 18.  Thanks to the independent fixing of the storage compartment 40 on the fuselage structure 1 or on the pairs 2, the advantageous configuration of the component 4 can be obtained.  While, in the usual storage compartments, an arrangement of electronic modules, air nozzles and the like must be mounted on a rear side of a storage compartment, it is possible, thanks to the configuration according to FIG. 3, separate manufacture and advantageous separate support.  For example, the storage compartment 40 can firstly be mounted on third retaining elements 48 by means of retaining bars 46.  After the mounting of the retaining bars 22 of the component 4 on second retaining elements 18, an upward pivoting of the storage compartments 40 can be carried out for fixing to the second retaining elements 18.  Then, the retaining frames 20 can be connected to the first retaining elements 16.  [Figure 4] illustrates, by way of example, a first retaining element 16 and FIG. 8 illustrates, by way of example, a second retaining element 18 which is fixed to the torque
    [2" id="c-fr-0002]
    2. For this purpose, the retaining pin 38 or the bolt 38 is shown as an example. The first retaining element 16 is characterized by an opening 50 which comprises a first toothing 52, which corresponds to a second toothing 54 of a bolt or of a socket 56. The socket 56 is securely connected to the first base body 12, for example by means of another threadable sleeve 55 which is fixed with the aid of a bolt 38 (see FIG. 8). As can be seen in Figure 4, the toothing 52 or 54 is only provided in certain areas, so that only 90 ° segments, which are facing each other, are toothed. The segments can also extend slightly less than 90 °. This allows the passage of the first base body 12 in which are disposed nozzles 56, after which, by rotation of the first toothing and the second toothing 52 and 54 relative to each other, a commitment by complementarity of form can be achieved. This is illustrated in FIG. 4. Thanks to this configuration, the assembly can be considerably facilitated, since all the first retaining elements 16 can be plugged into the first base body 12, to then be moved to a desired position. Only the subsequent 90 ° rotation of the sleeve or of a part supporting the toothing 52 allows the first retaining element 16 to mesh with the first base body 12. Thanks to this engagement by complementarity of form, the base body 12 is able to transmit forces along its direction of extension and to distribute them consequently on all the retaining elements 16. The same variant is selected for the second retaining elements 18 as well as for the third retaining elements 48 [Figure 5a] illustrates a first variant of a fastening means which can be mounted on a tube in the form of the first base body 12. It must first be noted that the first body base 12 comprises, at a desired location, an opening 58 arranged on the peripheral side. Thus, the interior space of the first base body 12 can be reached. At the indicated location is further arranged a fixing cylinder 60 acting as the first connector, which is provided with an opening 62. The fixing cylinder 60 is pushed from an opening in the base body 12 to the desired location. The opening 62 of the fixing cylinder 60 includes a first toothing 64 which is, as in the case of the first retaining element 16, arranged only in two segments opposite one another, the segments s '' extending up to 90 °. An elongated body 66 acting as a second connector is provided with a second toothing 68 which is also produced in the form of two segments facing each other. Consequently, the elongated body 66 can be, in one orientation, inserted without other resistance into the opening 58 of the first base body 12 and the opening 62 of the fixing cylinder 60. An engagement of the teeth 64 and 68 has not place only by rotation of the elongated body 66. As mentioned in the introduction, the distance of the retaining frame 20 to the torque can be influenced by the first retaining elements 16. In the case of the arrangement of the elongated body 66 on the retaining frame 20, it can therefore be variably positioned by modifying the insertion depth of the elongated body 66 in the fixing cylinder 60. Thus, very small tolerances can be compensated for. As also mentioned previously, a frame or a retaining element can for example be retracted directly into the cabin, frame or retaining element on which all the components 4 to be installed are arranged. Thanks to the upward pivoting and fixing of the retaining frame 20 on the first retaining elements 16, one of the positions of the first retaining elements 16 can be positioned independently of the retaining frame 20 in the cabin. The necessary insertion depths of the elongated bodies 66 are thus automatically obtained in the fixing cylinders 60. By subsequent tightening of the elongated bodies 66 as well as by their fixing, it is therefore possible very quickly to compensate for tolerances. The same attachment can be made to fix an upper end of the retaining bar 22. As illustrated in FIG. 8, the second retaining element 18 comprises an opening 57 through which the retaining bar 22 can extend in the interior of the second retaining element 18, to engage with a fixing cylinder 60 which is arranged there. [In Figure 5b] is illustrated a variant of a rotational mounting of an element not shown in more detail. Here, only one kind of pin is inserted through the first base body 12, a fixing of the component concerned can be carried out at an end 72 which projects from the base body 12. [0077] [FIG. 5c] illustrates a simple cable support which can be connected to the base body 12 by means of pins 76. Conduits 80 can be laid or glued thereon. [Figure 5d] illustrates a modification in the form of pipe supports 78, which are made in one piece and respectively surround the pipe 80 concerned. A tolerance compensation device 82 is represented in FIGS. 6a, 6b and 6c, which has been mentioned briefly with reference to FIG. 1. Here, a type of slide 84 is illustrated, which is pivotally connected to the retaining bar 22. The slide 84 extends in a sliding guide 86 and projects outwards from an elongated cavity 88. An elongated locking element 90 has a configuration such that it can be inserted in a recess 92 of the slide 84. This recess 92 comprises a first toothing 94, also a region of the slide 84. The elongated locking element 90 is also equipped with a second toothing 96 which, in FIG. 6B, forms an engagement with the toothing 94 and the toothing 96 and is arranged on two segments arranged opposite one another of the profile of the elongated locking element 90. When this locking element illage 90 is rotated 90 ° around its longitudinal axis, the teeth no longer mesh with each other, so that the slide 84 is freely movable in the sliding guide 86. Thus, the connecting region between the retaining bar 22 and the retaining frame 20 can be moved into the second region 30. Due to the rotation, which results therefrom, of the retaining bar 22 around the second retaining element 18, the distance between this connecting point and the second retainer 18 is changed in the vertical direction. Consequently, by using the lever ratios, it is possible to obtain, for a relatively coarse movement of the slide 84 in the sliding guide 86, a very precise orientation of the retaining frame 20 in the horizontal direction. In addition to the general ability to adjust the second retaining element 18, it is therefore possible to obtain precise adjustment. [In the figures Lig. 7a and 7b] is illustrated another example of attachment of a component. This is the attachment of cabin equipment at least by an upper end or a region opposite a floor. As an example, the first basic body 12 is here again illustrated. This is equipped with a socket 98, which is connected to the base body 12. For example, the socket 98 can be fixed to the base body 12 by means of a safety pin 100. The socket 98 comprises an external thread 102 which corresponds to an internal thread 104 of another socket 106. This second socket 106 has, by comparison with the first socket 98, a shorter length. By screwing, the position of the second socket 106 on the first socket 98 can be adjusted. The second socket 106 can be left in a desired position, and then be connected, by means of pins, screws 108 or the like, to an equipment support acting as a connecting member 110 in the form of an elongated bar . A flange 112 of the equipment can for example be mounted thereon. The equipment can for example be fixed to a floor of the cabin and be connected to the base body 12 via the connecting members 110, by a region opposite the floor. The loads, occurring during the operation of the aircraft, in the direction x are therefore applied in the basic body 12. An item of equipment can be connected by means of several connecting members 110 of this type and, if necessary, of several first sockets 98 and second sockets 106. Another aspect of the invention is shown in Figures 9a and 9b. Here, the representation of FIG. 5a or of FIG. 8 is given by way of example. The fixing cylinder 60 in the first base body 12 or the second base body 14 which, in the latter case, is connected to the retaining bar 22, is somewhat modified in the variant according to FIGS. 9a and 9b. The fixing cylinder 60 is here dimensioned so as to have a diameter somewhat less than the diameter in the previous representations. In addition, a decoupling element 61 is provided which surrounds at least a large part of the fixing cylinder 60. At the same time, it is dimensioned so that it can be introduced into the base body 12 or 14 when it surrounds the fixing cylinder 60. The decoupling element 61 consequently forms a ring around the fixing cylinder 60. The decoupling element 61 can be made from a material other than that of the fixing cylinder 60. In particular, the material can be more flexible. Thus, the mechanical contact between the fixing cylinder 60 and the second base body 14 is absorbed. In particular, the rattling, due to vibrations, of the fixing cylinder 60 in the base body 12 or 14 is thus prevented. It is conceivable that the fixing cylinder 60 is made of a metallic material, just like the base body 12 or
    [3" id="c-fr-0003]
    14. In this case, there could be a rattling noise in case of load variations due to the dimensional tolerances between these two elements. This can be prevented by means of the decoupling element 61. This can for example be made from an elastic synthetic material, for example from a thermoplastic material. Alternatively, a rubber would be possible. The contact noise between the damping element 61 and the base body 12 or 14 concerned is thus much lower than in the case of metallic elements. By arrangement of the decoupling element 61 between the fixing cylinder 60 and the second base body 14, there can therefore occur a very significant decoupling of the noise. In order to introduce the opening 62 of the fixing cylinder 60 through the opening 58 of the base body 12 or 14, the decoupling element 61 comprises a cutout 63 which is brought into alignment with the openings 58 and 62. If the decoupling element 61 is mounted on the second base element 14, as shown explicitly in FIG. 9b, the cutout 58 is preferably produced in the form of an oblong hole. Finally, Figure 10 illustrates an airliner 114 with an interior space formed as a cabin 116 in a fuselage 118 and several components 4 arranged therein. In addition, it should be noted that "comprising" does not exclude any other element or any other step and "one" or "one" does not exclude any plurality. In addition, it should be noted that characteristics which have been described with reference to one of the examples of embodiments mentioned above can also be used in combination with other characteristics of other examples of embodiments described above. The reference signs in the claims should not be considered as limiting. Claims [Claim 1] A fastening system (6) for fixing components (4) to a fuselage structure (1) in an interior space (116) of an aircraft (114), comprising: a retaining frame (20 ) comprising a first edge (26) and a second edge (28) spaced therefrom, at least a first retaining element (16) which can be coupled to the fuselage structure (1) and is designed to be connected articulated to the retaining frame (20) in a first region (24), near the first edge (26), of the retaining frame (20), at least one second retaining element (18) which can be coupled to the structure fuselage (1), and at least one retaining bar (22) which can be hingedly connected by a first end to the second retaining element (18) and which can be hingedly connected by a second end , to the retaining frame (20) in a second region (30) facing the second e edge (28) and opposite the first edge (26), the retaining frame (20), the retaining bar (22) as well as the first retaining element (16) and the second retaining element (18) being designed to form, with the first and second retaining elements (16, 18) spaced apart from each other along a peripheral direction of the fuselage structure (1), a triangular structure, the bar retainer (22) and the retainer frame (20) forming a first side and a second side of the triangular structure, and at least one of the retainer frame (20), the retainer bar (22), the first a retainer (16) and the second retainer (18) being adapted to variably adjust a length of the first side and / or the second side to adjust the position of the retainer frame (20). [Claim 2] A fastening system (6) according to claim 1, further comprising at least one elongated base body (12, 14), the at least one elongated base body (12, 14) being attachable to more than one first and / or second retaining elements (16, 18) and being adapted to apply a force acting along an axis of extent of the base body (12, 14) in several first or second retaining elements (16, 18). [Claim 3] Fastening system (6) according to claim 1, the first base body (12) and the second base body (14) being produced respectively in the form of a tube. [Claim 4] Fixing system (6) according to claim 2 or 3, the first retaining element (16) and the second retaining element (18) being designed to rigidly retain the respective base body (1, 14). [Claim 5] Fixing system (6) according to any one of the preceding claims, the first retaining element (16) being designed to adjust an adjustable distance between the first region (24) of the retaining frame (20) and the first retaining element (16). [Claim 6] Fastening system (6) according to claim 5, the first retaining element (16) comprising a first connector (60) provided with an opening (62) comprising, in certain areas, a first toothing (64) and a second connector (66) provided with an elongated body (66) comprising, in certain areas, a second toothing (68), the elongated body (66) being able, in a first orientation relative to the opening (62) of the first connector (60), be plugged into it and making, by rotation in a second orientation, a connection by complementary shape of the first toothing (64) and the second toothing (68). [Claim 7] Fixing system (6) according to any one of the preceding claims, the retaining bar (22) or the second retaining element (18) comprising a first connector (60) provided with an opening (62) comprising, in certain areas, a first toothing (64) and a second connector (66) provided with an elongated body (66) comprising, in certain areas, a second toothing (68), the elongated body (66) being able, in a first orientation relative to the opening (62) of the first connector (60), to be inserted in the latter and making, by rotation in a second orientation, a connection by complementarity of form of the first toothing (64) and of the second toothing (68). [Claim 8] A fastening system (6) according to claim 6 or 7, further comprising a decoupling element (61) made of a synthetic material, which surrounds the first connector (60) at least partially annularly. [Claim 9] Fastening system (6) according to any one of the preceding claims, further comprising at least one tolerance compensation device (82) disposed in the second region of the retaining frame (20), the compensation device of tolerances (82) connectable to the retaining bar (22) and being adapted to move and lock a position for connecting the retaining bar (22) to the retaining frame (20) between the second edge (28) and the first edge (26). [Claim 10] Fastening system (6) according to claim 9, the tolerance compensation device (82) comprising a slide (84) pivotally connected to the retaining bar (22) and an elongated recess (92) arranged on the retaining frame (20) and provided with a sliding guide (86), extending along the extent of the recess (92), serving to guide the sliding slide (84), the recess (92) and the slide (84) being respectively equipped, in certain areas, with a first toothing (94), and an elongated locking element (90) provided with a second toothing (96) in certain areas being positioned in the recess (92) and being designed to achieve, in a first orientation, a connection by complementary shape between the first toothing (94) and the second toothing (96), so that the position of the slide (84) on the sliding guide (86) is locked, and to release the bond by complementarity of form in a second orientation. [Claim 11] An aircraft (114) comprising a fuselage (118) having a fuselage structure (1) and at least one component which is attached to the fuselage structure (1) using a fastening system (6) according to any one of claims 1 to 10. [Claim 12] Aircraft (114) according to claim 11, the component being a passenger service unit or an upper storage compartment. [Claim 13] Aircraft (114) according to claim 10 or 11, the fuselage (118) having a longitudinal axis, a right side and a left side and comprising, along a large part of the fuselage (118), at least an elongated base body (12, 14) on each side of the fuselage (Π8). [Claim 14] Aircraft (114) according to claim 13, further comprising at least one equipment and at least one equipment support (110), the equipment being erected on a floor disposed in the fuselage (118) and being connected to one of the base bodies (12, 14) by means of the at least one equipment support (110), by a part, spaced from the floor, of the equipment. [Claim 15] Aircraft (114) according to claim 13, the equipment support (110) being in the form of an elongated bar (110) which is connected, by one end, to a part, spaced from the equipment along of the longitudinal axis, of the retaining element (16, 18) concerned and is connected, by another end, to the equipment.
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    同族专利:
    公开号 | 公开日
    CN110015397A|2019-07-16|
    DE102017131130A1|2019-06-27|
    US11136124B2|2021-10-05|
    US20190193871A1|2019-06-27|
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    法律状态:
    2019-12-19| PLFP| Fee payment|Year of fee payment: 2 |
    2020-12-23| PLFP| Fee payment|Year of fee payment: 3 |
    2021-12-24| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017131130.0|2017-12-22|
    DE102017131130.0A|DE102017131130A1|2017-12-22|2017-12-22|Attachment system for attaching a component to a fuselage structure|
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