Patent Description:
The importance of automation is ever increasing, specifically in the field of aircraft manufacturing. Many tasks are still performed manually. While some manufacturing steps, such as the manufacturing of wings, fuselage parts, and the like already enjoy a certain degree of automation. However, the assembly of the cabin interior still requires many man-hours till completion.

<CIT> discloses a rotary joint that comprises a socket rod with a basically spheroid concave bearing surface. A housing nut encircles the socket rod and has a threaded wrenching head. A ball rod has a basically spheroid convex bearing surface and threaded side walls around the bearing surface. The socket rod is swivably supported relative to the ball rod.

<CIT> discloses an interior component for an aircraft. The interior component comprises a wall being connected to an interior component carrier system. The wall has an indentation directed towards a cabin of the aircraft, and the indentation has a shape corresponding to at least part of the interior component carrier system.

<CIT> discloses a fixation assembly for affixing a first object to and variably spaced from a second object. A male fastener comprises a bolt-shaped part having a circumferential outer surface, wherein the circumferential outer surface includes alternately at least one ridged section and at least one plain section. A female fastener comprises a circumferential inner surface including alternately at least one ridged section and at least one plain section. The male fastener is inserted into the female fastener. When the ridged section coincides with the plain section of the female fastener, the respective ridges of the ridged sections of the male fastener and the female fastener engage each other after a relative rotation of male and female fastener.

<CIT> discloses a coupling device to be connected to a corner fitting of a container.

<CIT> discloses a tolerance compensation subassembly in the form of a tolerance compensation element. The tolerance compensation subassembly contains an actuator which is formed from an electro-active polymer. The tolerance compensation subassembly is electrically switchable between a fixed state and a non-fixed state.

<CIT> discloses a positioning bushing. The bushing is used to set a distance and an orientation between two aircraft components. The positioning bushing comprises an outer bushing which is inserted into a first aircraft component and an inner bushing which is inserted into the outer bushing. The inner bushing accommodates a second aircraft component or conventional fastener. The outer bushing and the inner bushing are designed such that when the inner bushing is inserted into the outer bushing, rotation of the inner bushing relative to the outer bushing is blocked. The positioning bushing is used in aircraft mounting arrangements. In particular, the positioning bushing is used when connecting parts of the aircraft structure, such as the primary structure or the secondary structure.

It is the object of the invention to provide measures which improve automation in the mounting of interior components to the aircraft primary structure.

The object is achieved by the subject-matter of the independent claims. Preferred embodiments are subject-matter of the dependent claims.

The invention provides a coupling kit-of-parts for a mounting arrangement that is configured for mounting an interior substructure to a primary structure of an aircraft, the kit-of-parts comprising:.

Preferably, the kit-of-parts further comprises an elastic member that is arranged to urge the first and second member parts radially inward along the radial direction such that, when the locking member is removed from the locking channel, the first and second member parts are pushed radially inward by the elastic member, preferably along opposing radial directions.

Preferably, the support member includes a guiding recess that is configured to guide the first and second member parts along the radial direction.

Preferably, the first member part and/or the second member part include a head portion that engages the support member, preferably the guiding recess, in a sliding manner.

Preferably, the head portion includes a head support portion that engages the support member, preferably the guiding recess, in a sliding manner. Preferably, the head portion includes a head recessed portion that is configured such that the head recessed portion engages the support member at an inner circumferential surface, when the locking member is inserted in the locking channel. Preferably, the head portion includes a head recessed portion that is configured such that the head recessed portion is disengaged from the support member, when the locking member is removed from the locking channel.

Preferably, the support member includes a support opening, and the first and second member parts are partially inserted in the support opening. Preferably, the head portion is arranged within the support opening. Preferably, the guiding recess is formed in an inner circumferential surface of the support opening.

Preferably, the first member part and/or the second member part include an engagement surface that is configured to engage a structure interface bushing in a form-fitting manner. Preferably, the engagement surface is formed on a radially outward facing surface. Preferably, the engagement surface comprises a plurality of engagement ridges.

Preferably, the first member part and/or the second member part include a shank portion and the engagement surface is formed on the shank portion. Preferably, the shank portion is formed adjacent to the head portion. Preferably, the shank portion is arranged outside the support member, preferably outside the support opening.

Preferably, the locking channel comprises a tapered channel entrance portion and a channel portion that matches the locking member. Preferably, when the locking member is inserted past the channel entrance portion, the first and second member parts are radially moved apart, and the channel portion is supported on the locking member.

Preferably, the first member part and/or the second member part include a mounting member end portion that comprises an outward facing tapered surface.

Preferably, the kit-of-parts further comprises a retaining bushing that is inserted in the support member and retains the locking member in a manner that requires overcoming a mechanical resistance, when removing the locking member from the support member, preferably from the locking channel. Preferably, the retaining bushing includes a detent member that engages the locking member, when inserted in the support member.

Preferably, the locking member extends in a longitudinal direction. Preferably, the locking member comprises a locking member head portion and a locking member end portion. Preferably, the head portion includes a head tapered portion that is configured to interact with the support member and/or the retaining bushing, preferably the detent member, such that the locking member is removable from the locking channel against a resistance due to that interaction.

Preferably, the locking member end portion includes a retaining portion and a tapered end portion, wherein the retaining portion is configured to interact with the support member and/or the retaining bushing, preferably the detent member, such that, when the locking member is removed from the locking channel but still inside the support member, the tapered portion is arranged adjacent to or in contact with the mounting member.

Preferably, the retaining portion is arranged closer to the locking member head portion than the tapered end portion.

Preferably, the kit-of-parts further comprises a structure interface bushing that is configured to get engaged by the radially pushed first and second member parts, when the locking member is inserted in the locking channel, such that the mounting member is affixed to the structure interface bushing.

The invention provides a mounting arrangement for mounting an interior substructure to a primary structure of an aircraft, the arrangement comprising:.

wherein the structure interface bushing is affixed to the primary structure portion, wherein the mounting member is inserted in the mounting opening such that the support member is arranged in a manner that prevents the interior substructure from being removed from the mounting member.

Preferably, the elastic member is arranged between the structure interface bushing and the support member. Preferably, the elastic member is arranged closer to the support member or in contact with the support member.

Preferably, the first member part and/or the second member part include an engagement surface that engages the structure interface bushing in a form-fitting manner, when the locking member is inserted in the locking channel.

Preferably, the first member part and/or the second member part include a shank portion that is at least partially inserted in the structure interface bushing.

The invention provides an aircraft cabin or a cargo hold comprising an interior component, an interior substructure, and a preferred mounting arrangement as previously described, wherein the interior substructure member is part of the interior substructure, wherein the cabin component is mounted to the interior substructure and the interior substructure is mounted to the primary structure portion by the mounting arrangement.

The invention provides an aircraft comprising a preferred aircraft cabin.

Typically, individual customer requirements regarding the cabin interior are considered by having some kind of substructure that can be mounted to the standardized primary structure. The individual customer equipment is mounted to the substructure. The substructure therefore should perform several functions simultaneously. The substructure should fulfil structural requirements, such as stiffness, toughness, etc. Furthermore, the substructure should be able to compensate for manufacturing tolerances in both the primary structure and the interior cabin component.

An example for a cabin component is the cabin crown module that is attached at the top of the aircraft cabin. In a typical manner the cabin crown module may include hat-racks, overhead compartments, lighting devices, etc. Further examples may include interior cabin panels, floor boards, or cargo bins.

With the disclosed coupling kit-of-parts it is possible to mount a substructure to a primary structure of an aircraft without additional tools. Manufacturing tolerances of the substructure can be compensated. Furthermore, an automated locking of the substructure to the primary structure is possible. The kit-of-parts can be installed/deinstalled in a blind spot with high reliability. In addition, the installation is rotation safe, i.e. even if the fastener rotates, e. due to vibration and the like, the installation is prevented from coming loose.

Embodiments of the invention are described in more detail with reference to the accompanying schematic drawings that are listed below.

Referring to <FIG> an aircraft <NUM> comprises a primary structure <NUM>, e.g. a fuselage <NUM>. The aircraft <NUM> further comprises a pair of wings <NUM> that are attached to the fuselage and that include an engine <NUM>.

The aircraft <NUM> comprises an aircraft cabin <NUM> that is arranged inside the fuselage <NUM>.

Referring to <FIG>, the fuselage <NUM> houses an interior substructure <NUM>. The interior substructure <NUM> is mounted to the primary structure <NUM>. The interior substructure <NUM> is configured as an interface between the primary structure <NUM> and an interior component <NUM>.

The aircraft cabin <NUM> may include the interior component <NUM>, preferably in the form of a cabin component, such as a cabin crown module <NUM>, interior cabin panels <NUM>, or the like.

The aircraft <NUM> may include a cargo hold <NUM> that is typically arranged in a bottom portion of the primary structure <NUM>. The cargo hold <NUM> may include the interior component <NUM>, preferably in the form of a cargo hold component.

Referring to <FIG> and <FIG>, a mounting arrangement <NUM> is illustrated in an unmounted state (<FIG>) and an engaged, but not yet fixed state (<FIG>). The mounting arrangement <NUM> includes a primary structure portion <NUM>. The primary structure portion <NUM> is part of the primary structure <NUM> and configured as a frame <NUM>, for example. The frame <NUM> extends along a circumferential direction of the primary structure <NUM> and preferably supports an aerodynamic skin of the fuselage <NUM>.

The mounting arrangement <NUM> includes the interior substructure <NUM>. The interior substructure <NUM> may include a plurality of interior substructure members <NUM>, e.g. struts. Each substructure member <NUM> has a substructure mounting opening <NUM>. The substructure member <NUM> is preferably configured such that two or more substructure members <NUM> may form a spherical joint <NUM>.

The mounting arrangement <NUM> includes a coupling kit-of-parts <NUM> that is configured for mounting the substructure members <NUM> to the primary structure portion <NUM>.

Referring to <FIG>, the coupling kit-of-parts <NUM> is described in more detail.

The coupling kit-of-parts <NUM> comprises a locking member <NUM>. The locking member <NUM> extends in a longitudinal direction. The locking member <NUM> is preferably formed as a pin member.

The locking member <NUM> has a locking member head portion <NUM> that is formed on one end. The locking member head portion <NUM> preferably includes a plate-like pushing member <NUM> that can be pushed by a tool or manually by a worker.

The locking member head portion <NUM> may include a head tapered portion <NUM>. The head tapered portion <NUM> is preferably arranged adjacent to the pushing member <NUM>. The head tapered portion <NUM> is formed with the smaller diameter towards the locking member head portion <NUM>.

The locking member <NUM> may include a locking member end portion <NUM>. The locking member end portion <NUM> is preferably formed on the opposite end as the locking member head portion <NUM>.

The locking member end portion <NUM> may include a retaining portion <NUM>. The retaining portion <NUM> may be formed as a recess in a circumferential surface of the locking member <NUM>.

The locking member end portion <NUM> may include a tapered end portion <NUM>. The tapered end portion <NUM> is arranged further away from the locking member head portion <NUM> than the retaining portion <NUM>.

The coupling kit-of-parts <NUM> further comprises a mounting member <NUM>. The mounting member <NUM> is formed from a first member part <NUM> and a second member part <NUM>.

The first and second member parts <NUM>, <NUM> are arranged so as to form a locking channel <NUM> between them. The locking channel <NUM> is configured to receive the locking member <NUM>.

The first and second member parts <NUM>, <NUM> are substantially identical to each other. Thus, only the first member part <NUM> will be described in more detail for sake of brevity.

The first member part <NUM> extends in a longitudinal direction. The first member part <NUM> preferably has the shape of one half of a pin-like member that was split along the longitudinal direction.

The first member part <NUM> preferably includes an engagement surface <NUM> that is formed on a circumferential surface of the first member part <NUM> that faces radially outward. The engagement surface <NUM> may include a plurality of engagement ribs <NUM>.

The first member part <NUM> can comprise a head portion <NUM>. The locking channel <NUM> is partially arranged in the head portion <NUM>. The locking channel <NUM> preferably includes a tapered channel entrance portion <NUM> that is formed in the head portion <NUM>.

The first member part <NUM> may have a mounting member end portion <NUM> that may have a tapered surface.

The coupling kit-of-parts <NUM> further includes a support member <NUM>. The support member <NUM> may include a support opening <NUM>. The support member <NUM> supports the mounting member <NUM> in a manner that allows the first and second member parts <NUM>, <NUM> to move in a radial direction. The mounting member <NUM> is preferably partially inserted in the support opening <NUM>. The support member <NUM> may include a guiding recess <NUM> in which the mounting member <NUM> is supported in a sliding manner, preferably on the head portion <NUM>.

The support member <NUM> may include a joint portion <NUM>. The joint portion <NUM> is shaped such that it matches the substructure mounting opening <NUM> and can form the spherical joint <NUM>.

The coupling kit-of-parts <NUM> may further comprise an elastic member <NUM>. The elastic member <NUM> is preferably annularly shaped and may be supported on the mounting member <NUM> on a circumferential surface thereof. The elastic member <NUM> is arranged such that the first and second member parts <NUM>, <NUM> are urged towards each other.

In addition, the elastic member <NUM> may cooperate with the mounting member <NUM> such that the mounting member <NUM> is supported against the support member <NUM> via the elastic member <NUM>.

The coupling kit-of-parts <NUM> may include a structure interface bushing <NUM>. The structure interface bushing <NUM> is affixed to the primary structure portion <NUM>. The structure interface bushing <NUM> includes a bushing opening <NUM> that is sized and shaped such that the mounting member <NUM> can be inserted thereinto. The bushing opening <NUM> is further sized and shaped to engage the mounting member <NUM> in a form-fitting manner, specifically via the engagement surface <NUM>.

The coupling kit-of-parts <NUM> may include a retaining bushing <NUM>. The retaining bushing <NUM> is inserted into the support member <NUM>, preferably into the support opening <NUM>. The retaining bushing <NUM> my include a detent member <NUM> that protrudes from an inner circumferential surface.

Subsequently, a mounting process using the coupling kit-of-parts <NUM> is described in more detail with reference to <FIG>.

As depicted in <FIG>, the mounting member <NUM> is inserted into the mounting opening <NUM>. The support member <NUM> is positioned in contact with the interior substructure member <NUM>. With reference to <FIG>, the mounting arrangement <NUM> is moved in a manner such that the mounting member <NUM> is inserted into the bushing opening <NUM>. The locking member <NUM> is partially inserted in the support member <NUM>. Specifically, the retaining portion <NUM> can engage the detent member <NUM> such that the locking member <NUM> can only be removed by overcoming the force exerted by the detent member <NUM> upon pulling the locking member <NUM>.

Subsequently, the locking member <NUM> is pushed into the locking channel <NUM>. The locking member <NUM> engages the channel entrance portion <NUM> with the tapered end portion <NUM>. Due to the taper the locking channel <NUM> the first and second member parts <NUM>, <NUM> are pushed in a radial direction. The head portion <NUM> slides in the guiding recess <NUM> radially outward. The engagement surface <NUM> engages the inner circumferential surface of the bushing opening <NUM> in a form-fitting manner. The first and second member parts <NUM>, <NUM> are supported by the locking member <NUM> such that a movement of the first and second member parts <NUM>, <NUM> radially inward is blocked. The locking member head portion <NUM> engages the detent member <NUM> such that the detent member <NUM> engages the head tapered portion <NUM>. The substructure <NUM> is now affixed to the primary structure portion <NUM>. Subsequently, the locking member <NUM> can be pulled from this position by overcoming the force exerted by the detent member <NUM> onto the locking member <NUM>.

When the locking member <NUM> is removed from the locking channel <NUM>, the elastic member <NUM> urges the first and second member parts <NUM>, <NUM> in a radial direction inward such that the mounting member <NUM> is disengaged from the structure interface bushing <NUM>. Thus, the mounting member <NUM> can be removed from the bushing opening <NUM> and the substructure <NUM> is loosened from the primary structure portion <NUM>.

Referring to <FIG> another embodiment of the mounting member <NUM> and the support member <NUM> are described in more detail, but only insofar as they differ from the previously described embodiment.

Here, the head portion <NUM> is formed such that it is supported along the longitudinal direction of the mounting member <NUM> on an outer surface of the support member <NUM>. In this configuration no retaining bushing <NUM> is required.

The elastic member <NUM> is arranged on the opposite side of the support member <NUM> in order to prevent the mounting member <NUM> from being removed from the support member without resistance.

Claim 1:
A coupling kit-of-parts (<NUM>) for a mounting arrangement (<NUM>) that is configured for mounting an interior substructure (<NUM>) to a primary structure of an aircraft, the kit-of-parts (<NUM>) comprising:
- a locking member (<NUM>); and
- a mounting member (<NUM>) including a first member part (<NUM>) and a second member part (<NUM>) that are movably supported by a common support member (<NUM>),
wherein the first and second member parts (<NUM>, <NUM>) form a locking channel (<NUM>) therebetween that is configured to receive the locking member (<NUM>),
wherein the mounting member (<NUM>) is configured such that, when the locking member (<NUM>) is inserted into the locking channel (<NUM>), the first and second member parts (<NUM>, <NUM>) are pushed radially outward by the locking member (<NUM>).