阅读说明：本技术 内饰板装配结构及其装配方法和采用该装配结构的飞机 (Interior trim panel assembly structure, assembly method thereof and airplane adopting assembly structure ) 是由 吴洋 穆腾飞 严玲 张振伟 徐晶 俞金海 于 2020-05-29 设计创作，主要内容包括：本发明提出了一种内饰板装配装置,用于将内饰板装配于机身框架,包括机身连接单元、机身连接定位件、内饰板连接单元和内饰板连接定位件,机身连接单元和内饰板连接单元采用具有一定轴向自由度的连接单元,机身连接定位件和内饰板连接定位件具有锁紧机构,在非锁紧状态下可允许连接单元调整定位位置,锁紧状态下固定连接单元,使得内饰板装配结构能够实现内饰板的快速定位和装配,解决了内饰板安装过程繁琐、难以进行定位调整且后期维护不便的问题。(The invention provides an interior trimming panel assembling device, which is used for assembling an interior trimming panel on a frame of a machine body and comprises a machine body connecting unit, a machine body connecting positioning piece, an interior trimming panel connecting unit and an interior trimming panel connecting positioning piece, wherein the machine body connecting unit and the interior trimming panel connecting unit adopt connecting units with certain axial freedom, the machine body connecting positioning piece and the interior trimming panel connecting positioning piece are provided with locking mechanisms, the connecting units can be allowed to adjust the positioning positions in a non-locking state, and the connecting units are fixed in a locking state, so that the interior trimming panel assembling structure can realize the quick positioning and assembling of the interior trimming panel, and the problems of complex installation process, difficulty in positioning and adjustment and inconvenience in later maintenance of the interior trimming panel are solved.)

1. An interior trim panel assembly apparatus for assembling an interior trim panel to a fuselage frame in an aircraft longitudinal direction, comprising:

a plurality of fuselage connection units arranged coaxially and/or in parallel and parallel to the longitudinal direction of the aircraft for connection to the fuselage frames;

the machine body connecting positioning pieces are arranged at two ends of each machine body connecting unit, abut against the machine body frame and are used for fixing the machine body connecting units on the machine body frame;

the interior trim panel connecting units are positioned on one side of the interior trim panel, which faces the machine body frame, and are used for being connected with the machine body connecting units; and

an interior trim panel connection location piece mounted on at least one of the fuselage connection units and abutting against the interior trim panel connection unit on the at least one fuselage connection unit adjacently for fixing the interior trim panel connection unit to the at least one fuselage connection unit,

wherein the machine body connecting positioning piece and the interior trim panel connecting positioning piece are respectively provided with a locking mechanism which is in a locking state and a non-locking state,

allowing the fuselage connection unit to move on the fuselage frame in the longitudinal direction of the aircraft in the non-locking state of the locking mechanism of the fuselage connection positioning element, fixing the fuselage connection unit on the fuselage frame in the locking state of the locking mechanism,

the interior trim panel connection positioning element of the locking mechanism is allowed to move along the fuselage connection unit in the longitudinal direction of the aircraft under the non-locking state of the locking mechanism, and the interior trim panel connection positioning element of the locking mechanism is fixed on the fuselage connection unit under the locking state of the interior trim panel connection positioning element.

2. The interior panel assembly apparatus of claim 1, wherein the interior panel attachment unit is integrally formed with the interior panel.

3. The interior panel assembly apparatus of claim 1, wherein the interior panel attachment unit is removably secured to the interior panel.

4. The interior panel assembly apparatus of claim 3, further comprising an adjustment block, wherein the interior panel attachment unit is removably secured to the adjustment block, and wherein the adjustment block is removably secured to the interior panel.

5. The interior trim panel assembly device of claim 1, wherein the body connection unit is a tubular structure and is inserted into the opening of the body frame, and the interior trim panel connection unit is a hook structure, and the hook can be hooked on the body connection unit.

6. The interior panel assembly apparatus of claim 5, wherein the interior panel attachment unit is a C-hook configuration or a U-hook configuration.

7. The interior panel assembly apparatus of claim 5, wherein the opening is a lightening hole of the fuselage frame.

8. The interior panel assembly apparatus of claim 5, wherein the body connection positioning element and the interior panel connection positioning element are discrete loop structures that can be sleeved on the body connection unit, and the locking mechanism is configured by providing a fastener at a discrete location to adjust an inner diameter of the loop structures.

9. A method of assembly for the interior trim panel assembly apparatus of any of claims 1-8, comprising the steps of:

the corresponding position of the machine body connecting unit and the inner decoration plate connecting unit is provided with the inner decoration plate connecting positioning piece;

mounting the plurality of fuselage connection units to the fuselage frame coaxially and/or in parallel and parallel to the longitudinal direction of the aircraft;

the machine body connecting positioning piece is arranged at two ends of the machine body connecting unit and is abutted against the machine body frame;

locking the locking mechanism of the body connection positioning piece so as to fix the body connection unit to the body frame;

connecting an interior trim panel connection unit on the interior trim panel to the fuselage connection unit in a manner that the interior trim panel connection unit is movable in an aircraft longitudinal direction along the fuselage connection unit;

moving the interior trim panel along the fuselage connection unit in an aircraft longitudinal direction to a locating position;

abutting the interior trim panel connecting positioning piece and the interior trim panel connecting unit adjacently;

and locking the locking mechanism of the interior trim panel connecting positioning piece, so that the interior trim panel connecting unit is fixed on the machine body connecting unit.

10. An aircraft comprising the interior trim panel assembly apparatus of any of claims 1-8.

Technical Field

The invention relates to an aircraft cabin assembly technology, in particular to an interior trim panel assembly structure and an interior trim panel assembly method for an aircraft cabin.

Background

When being assembled, the interior trim panel of the airplane passenger cabin needs to be installed on an inner frame of the airplane fuselage through a specific assembling device. Present interior plaque assembly quality adopts fixed assembly quality usually, adopts this kind of structure, though can guarantee the reliability of being connected of interior plaque and fuselage frame to a certain extent, but the installation procedure is comparatively complicated, can't carry out rapid Assembly, and be not convenient for carry out quick location and positioning adjustment to interior plaque in the installation, also be difficult to dismantle after accomplishing the installation, lead to also having great difficulty in the aspect of later maintenance, consequently need improve in order to improve above-mentioned problem to interior plaque assembly quality in aircraft cabin.

Disclosure of Invention

The invention aims to solve the technical problems that aiming at the defects of the prior art, the invention provides the interior trim panel assembling structure and the interior trim panel assembling method, which can quickly position and assemble the interior trim panel and solve the problems that the interior trim panel is complicated in installation process, difficult to position and adjust and inconvenient in later maintenance.

In order to solve the above problem, according to a first aspect of the present invention, there is provided an interior panel attachment device for attaching an interior panel to a fuselage frame in an aircraft longitudinal direction, comprising:

a plurality of fuselage connection units arranged coaxially and/or in parallel and parallel to the longitudinal direction of the aircraft for connection to the fuselage frames;

the machine body connecting positioning pieces are arranged at two ends of each machine body connecting unit, abut against the machine body frame and are used for fixing the machine body connecting units on the machine body frame;

the interior trim panel connecting units are positioned on one side of the interior trim panel, which faces the machine body frame, and are used for being connected with the machine body connecting units; and

an interior trim panel connection location piece mounted on at least one of the fuselage connection units and abutting against the interior trim panel connection unit on the at least one fuselage connection unit adjacently for fixing the interior trim panel connection unit to the at least one fuselage connection unit,

wherein the machine body connecting positioning piece and the interior trim panel connecting positioning piece are respectively provided with a locking mechanism which is in a locking state and a non-locking state,

allowing the fuselage connection unit to move on the fuselage frame in the longitudinal direction of the aircraft in the non-locking state of the locking mechanism of the fuselage connection positioning element, fixing the fuselage connection unit on the fuselage frame in the locking state of the locking mechanism,

the interior trim panel connection positioning element of the locking mechanism is allowed to move along the fuselage connection unit in the longitudinal direction of the aircraft under the non-locking state of the locking mechanism, and the interior trim panel connection positioning element of the locking mechanism is fixed on the fuselage connection unit under the locking state of the interior trim panel connection positioning element.

Preferably, the interior trim panel connection unit and the interior trim panel are integrally formed.

Preferably, the interior trim panel connection unit is detachably fixed to the interior trim panel.

Preferably, the interior trim panel assembly device further comprises an adjusting block, the interior trim panel connection unit is detachably fixed to the adjusting block, and the adjusting block is detachably fixed to the interior trim panel.

Preferably, the body connecting unit is of a tubular structure and is arranged in the hole of the body frame in a penetrating mode, the interior trim panel connecting unit is of a hook structure, and the hook can be hung on the body connecting unit.

Preferably, the interior trim panel connecting unit is of a C-shaped hook structure or a U-shaped hook structure.

Preferably, the opening is a lightening hole of the fuselage frame.

Preferably, the fuselage connection positioning element and the interior trim panel connection positioning element are discontinuous annular structures which can be sleeved on the fuselage connection unit, and the locking mechanism is formed by arranging a fastener at the discontinuous part to adjust the inner diameter of the annular structures.

According to a second aspect of the present invention, there is provided an assembling method for the interior panel assembling apparatus, comprising the steps of:

the corresponding position of the machine body connecting unit and the inner decoration plate connecting unit is provided with the inner decoration plate connecting positioning piece;

mounting the plurality of fuselage connection units to the fuselage frame coaxially and/or in parallel and parallel to the longitudinal direction of the aircraft;

the machine body connecting positioning piece is arranged at two ends of the machine body connecting unit and is abutted against the machine body frame;

locking the locking mechanism of the body connection positioning piece so as to fix the body connection unit to the body frame;

connecting an interior trim panel connection unit on the interior trim panel to the fuselage connection unit in a manner that the interior trim panel connection unit is movable in an aircraft longitudinal direction along the fuselage connection unit;

moving the interior trim panel along the fuselage connection unit in an aircraft longitudinal direction to a locating position;

abutting the interior trim panel connecting positioning piece and the interior trim panel connecting unit adjacently;

and locking the locking mechanism of the interior trim panel connecting positioning piece, so that the interior trim panel connecting unit is fixed on the machine body connecting unit.

According to a third aspect of the invention, an aircraft is provided, comprising the aforementioned interior trim panel assembly device.

Compared with the prior art, the invention utilizes the connecting unit and the positioning piece with certain axial freedom degree to allow the positioning of the interior trim panel to be conveniently adjusted and locked on the frame of the airplane body, realizes the quick assembly of the interior trim panel on the basis of ensuring the assembly reliability of the interior trim panel, improves the convenience of later maintenance, and simultaneously can provide preassembly positioning for other assembly modes of the interior trim panel and the frame structure of the airplane.

Drawings

The foregoing summary, as well as the following detailed description of the invention, will be better understood when read in conjunction with the appended drawings. It is to be noted that the appended drawings are intended as examples of the claimed invention. In the drawings, like reference characters designate the same or similar elements.

Fig. 1 is a schematic structural view of a body attachment unit according to an embodiment of the present invention;

FIG. 2 is a schematic view of a construction of an interior trim panel according to an embodiment of the invention;

FIG. 3 is a schematic view of a C-hook construction trim panel attachment unit according to one embodiment of the present invention;

FIG. 4 is a schematic view of a panel attachment unit in a U-hook configuration according to one embodiment of the present invention; and

fig. 5 is a schematic structural view of a fuselage frame according to an embodiment of the invention.

1: an interior trim panel; 2: a fuselage frame; 3: a body connection unit; 4: the machine body is connected with a positioning piece; 5: an interior trim panel connection unit; 6: the interior trim panel is connected with the positioning piece; 7: the fuselage is connected with a unit net; 8: an adjusting block; 9: opening holes

Detailed Description

The detailed features and advantages of the present invention are described in detail in the detailed description which follows, and will be sufficient for anyone skilled in the art to understand the technical content of the present invention and to implement the present invention, and the related objects and advantages of the present invention will be easily understood by those skilled in the art from the description, claims and drawings disclosed in the present specification.

The invention provides an interior trim panel assembling device which is used for assembling an interior trim panel 1 on a frame 2 of an airplane body and comprises a body connecting unit 3, a body connecting positioning piece 4, an interior trim panel connecting unit 5 and an interior trim panel connecting positioning piece 6.

The fuselage connection unit 3 is mounted on the fuselage frames 2 substantially parallel to the longitudinal direction of the aircraft (of course, it may also deviate from the longitudinal direction of the aircraft due to changes in the configuration of the aircraft itself), a number of fuselage connection units 3 are arranged coaxially and/or in parallel, forming a network of fuselage connection units 7, a fuselage connection location 4 is mounted at each end of each fuselage connection unit 3 adjacent to the fuselage frame 2 for releasably securing the fuselage connection unit 3 to the fuselage frames 2, the fuselage connection location 4 is a detachable construction with a locking mechanism which can be changed by manual operation between a locked state and an unlocked state in which the fuselage connection location 4 is in a non-fixed connection with the fuselage connection unit 3 and which can be moved along the fuselage connection unit 3 in the longitudinal direction of the aircraft, so that the fuselage connection unit 3 can be moved on the fuselage frame 2 in the longitudinal direction of the aircraft to adjust the positioning position, the fuselage connection location 4 fixing the fuselage connection unit 3 to the fuselage frame 2 in the locked state of the locking mechanism.

As shown in fig. 2, the interior trim panel side plate and the interior trim panel top plate, the interior trim panel connection unit 5 is located on one side of the interior trim panel facing the body frame 2, and is disposed at a position corresponding to the body connection unit 3, so as to connect the interior trim panel 1 to the body connection unit 3, preferably, the arrangement number of the interior trim panel connection unit 5 should be the minimum number on the premise that the interior trim panel can be stably fixed under various flight conditions, and the vertical arrangement height of the interior trim panel connection unit 5 should be matched with the vertical height of the corresponding body connection unit 3.

The interior trim panel connecting units 5 close to the two ends of the interior trim panel 1 are adjacently propped against and provided with interior trim panel connecting positioning pieces 6, used for fixing the interior trim panel connecting unit 5 on the machine body connecting unit 3, the interior trim panel connecting positioning piece 6 is a detachable structure with a locking mechanism, the locking mechanism can be changed between a locking state and a non-locking state through manual operation, and in the non-locking state of the locking mechanism, the interior trim panel connecting and positioning piece 6 is in non-fixed connection with the machine body connecting unit 3, which is movable in the longitudinal direction of the aircraft along the fuselage connection unit 3, so that the trim panel connection unit 5 can also be moved in the longitudinal direction of the aircraft along the fuselage connection unit 3 for adjusting the positioning position, in the locked state of the locking mechanism, the interior panel connection spacer 6 fixes the interior panel connection unit 5 to the body connection unit 3, thereby fixedly attaching the interior panel 1 to the body frame 2.

The invention also provides an assembling method for the interior trimming panel assembling device. When assembling, the interior trim panel connection positioning element 6 and the fuselage connection positioning element 4 may be installed on the fuselage connection unit 3 first, and of course, as long as the structures of the interior trim panel connection positioning element 6 and the fuselage connection positioning element 4 allow, the interior trim panel connection positioning element may be installed again when locking and fastening are required, which will be understood by those skilled in the art. Then, the fuselage connection units 3 are installed, at this time, fine adjustment can be performed on each fuselage connection unit 3 to keep the axes of the fuselage connection units 3 on the same axis and/or parallel to each other, the fuselage connection positioning piece 4 is installed and locked, the fuselage connection units 3 are fixed on the fuselage frame 2, the interior trim panel is installed on the fuselage connection unit 3 through the interior trim panel connection unit 5, the interior trim panel connection unit 5 can move in the longitudinal direction of the airplane along the fuselage connection unit 3 and can move to different positioning positions according to the design requirements of the airplane, the interior trim panel connection positioning piece 6 is installed and locked, the interior trim panel connection unit 5 is fixed on the fuselage connection unit 3, and therefore the interior trim panel 1 is assembled to the fuselage frame 2.

After assembly is completed, if the positioning position of the interior trimming panel 1 needs to be adjusted again, the locking mechanism of the interior trimming panel connecting positioning piece 6 is only required to be loosened, the interior trimming panel connecting unit 5 is moved to a new positioning position, and the interior trimming panel connecting positioning piece 4 is tightly locked next to the interior trimming panel connecting unit 5, so that positioning adjustment and assembly can be completed quickly.

Further, the interior trim panel connection unit 5 may be a structure integrally formed with the interior trim panel 1, or may be a split mounting structure, for example, the interior trim panel connection unit 5 may be detachably fixed to the interior trim panel 1 by means of pasting, and when the arrangement position of the interior trim panel connection unit 5 on the interior trim panel 1 is determined, the positions of two interior trim panel connection units 5 located at two ends of the interior trim panel 1 in the longitudinal direction of the aircraft should be determined first, and then the interior trim panel connection unit 5 is added according to the force analysis as needed. Preferably, as shown in fig. 3, an adjusting block 8 serving as a transition structure between the interior panel 1 and the interior panel connection unit 5 may be designed according to the shape, size and assembly requirement of the interior panel 1, so as to finely adjust the position of the interior panel connection unit, thereby improving the assembly precision of the interior panel, where the adjusting block 8 may be detachably fixed to the interior panel 1 by means of pasting or the like, and the interior panel connection unit 5 may also be detachably fixed to the adjusting block 8 by means of pasting or the like.

The size of the body connection unit 3 needs to be designed according to the interval of the adjacent body frames 2, the position and size of lightening holes and the stress analysis result, in a preferred embodiment, the body connection unit 3 is of a tubular structure and is arranged in an opening 9 of the body frames 2 matched with the external size of the body connection unit 3 in a penetrating way, as shown in fig. 5, the opening 9 can be an opening specially used for installing the body connection unit 3 or an original lightening hole on the body frame 2, the interior trim panel connection unit 5 is of a hook structure matched with the external size of the body connection unit 3, as shown in fig. 3, a C-shaped hook or a U-shaped hook as shown in fig. 4 can be hung on the body connection unit 3. In a preferred embodiment, the fuselage connection spacer 4 and the trim panel connection spacer 6 are discrete ring structures that fit over the fuselage connection unit 3 to match the external dimensions of the fuselage connection unit 3, and their locking mechanisms can be configured by providing fasteners at the discontinuities to adjust the inner diameter of the ring structures, as shown in fig. 1 and 2.

The invention further provides an aircraft comprising the interior trim panel assembling device.

The terms and expressions which have been employed herein are used as terms of description and not of limitation. The use of such terms and expressions is not intended to exclude any equivalents of the features shown and described (or portions thereof), and it is recognized that various modifications may be made within the scope of the claims. Other modifications, variations, and alternatives, such as the replacement of components of different specifications, may also exist. Accordingly, the claims should be looked to in order to cover all such equivalents.

Also, it should be noted that although the present invention has been described with reference to the current specific embodiments, it should be understood by those skilled in the art that the above embodiments are merely illustrative of the present invention, and various equivalent changes or substitutions may be made without departing from the spirit of the present invention, and therefore, it is intended that all changes and modifications to the above embodiments be included within the scope of the claims of the present application.