Airplane interior trim part fixing device

Abstract

The invention relates to an aircraft interior trim part fixing device. The aircraft interior trim part fixing device comprises a first fixing panel, a second fixing panel and a first spring piece. Wherein the first fixing panel and the second fixing panel are connected with each other near one end or the middle position of the aircraft interior trim part fixing device, and a first gap is formed between the first fixing panel and the second fixing panel; wherein the first fixing panel is provided with a groove hole, one end of the first spring piece is fixed to the outer side face of the first fixing panel, the other end of the first spring piece is a free end, the free end of the first spring piece extends into the first gap through the groove hole, and a fixing clamping part is arranged near the tail end of the second fixing panel.

Description

TECHNICAL FIELD

[0001] The present application relates to an aircraft interior part fixing device, and belongs to the field of aircraft equipment installation design. BACKGROUND

[0002] In modern aircraft interior assembly, the fixing type mounting mode is often used to connect the structure of the fuselage through a support. Due to the complexity of the surface of the interior panel and the surrounding structure, the support connected to the structure is complex in design and needs to meet the assembly of different planes and different modules of the interior part. After assembly, it is difficult to ensure the alignment of the joints of each interior module, which affects the overall effect of the passenger cabin interior.

[0003] How to design a simple assembly operation fixing device for complex installation environment, which can not only fix the interior part on different planes, but also meet the simple installation and disassembly process, and can also control the gap after assembly to some extent, has become a technical problem to be solved in the field of aircraft interior assembly design.

[0004] In one prior art scheme, the fixing device cannot adapt to the simultaneous installation of multiple interior parts, and the interior part cannot be adjusted at a certain angle in the gap, which cannot adapt to the complex assembly environment and the assembly angle is single.

[0005] In another prior art scheme, the fixing device realizes the fixation of multiple plane interior parts through an adjustable angle "J" shaped sheet metal support, but the fixation method of each plane is connected by a fastener, which is complicated and does not improve the assembly efficiency.

[0006] In another prior art scheme, the fixing device uses a spring plug-in form, but if the spring loses its elasticity, it can only be replaced in its entirety. SUMMARY

[0007] One object of the present application is to provide an aircraft interior part fixing device which can overcome at least some of the defects of the prior art, can realize the clamping and fixation of the aircraft interior part, and the interior part can rotate at a certain angle, adapt to the complex operating environment on the aircraft, and the operation is simple and reliable, and the installation and disassembly are time-saving and labor-saving.

[0008] The above object of the present application is achieved by an aircraft interior part fixing device, which comprises a first fixed panel, a second fixed panel and a first spring sheet.

[0009] The first fixed panel and the second fixed panel are connected to each other near one end or near the middle position of the aircraft interior part fixing device, and a first gap is formed between the first fixed panel and the second fixed panel.

[0010] The first fixed panel is provided with a slot hole, one end of the first spring sheet is fixed to the outer side of the first fixed panel, the other end is a free end, the free end of the first spring sheet extends into the first gap through the slot hole, and the second fixed panel is provided with a fixed clamping part near the end thereof.

[0011] According to the technical scheme, the aircraft interior part fixing device can realize clamping and fixing of the aircraft interior part, the interior part can rotate by a certain angle, the complex operation environment on the aircraft can be adapted, and the operation is simple and reliable.

[0012] Preferably, the aircraft interior part fixing device further comprises a second spring sheet, one end of the second spring sheet is fixed to the outer side of the second fixed panel, the other end is a free end, the free end of the second spring sheet is arranged on the lateral side of the fixed clamping part and extends towards the first fixed panel.

[0013] Preferably, the first spring sheet is formed with a first corner part, the first corner part is located in the first gap, a second gap is formed between the first corner part and the fixed clamping part, and in a free state, the opening direction of the first corner part faces the first fixed panel.

[0014] Preferably, the second spring sheet is formed with a second corner part, a third gap is formed between the second corner part and the first fixed panel, and in a free state, the opening direction of the second corner part faces away from the first fixed panel.

[0015] Preferably, the section between the fixed end of the first spring sheet and the first corner part is attached to the outer side of the first fixed panel.

[0016] Preferably, the outer side of the second fixed panel is provided with a boss, and the section near the free end of the second spring sheet is attached to the outer side of the boss.

[0017] Preferably, the width of the free end of the first spring sheet is 22-25mm.

[0018] Preferably, the width of the free end of the second spring sheet is 10-13mm.

[0019] Preferably, the interference amount of the first spring sheet and the first interior part is 1.6-1.8mm.

[0020] Preferably, the clamping amount of the second spring sheet and the second interior part is 0.7-0.8mm. DRAWINGS

[0021] Figure 1is a perspective view of an aircraft interior part fixing device according to an embodiment of the present application.

[0022] Figure 2 is another perspective view of an aircraft interior part fixing device according to an embodiment of the present application.

[0023] Figure 3 is a side view of an aircraft interior part fixing device according to an embodiment of the present application.

[0024] Figure 4 is a view of an aircraft interior part fixing device according to an embodiment of the present application when fixing a first interior part.

[0025] Figure 5 is a view of an aircraft interior part fixing device according to an embodiment of the present application when fixing both a first interior part and a second interior part.

[0026] List of reference signs

[0027] 1: first fixing panel

[0028] 2: second fixing panel

[0029] 3: fixing clamping portion

[0030] 4: first spring piece

[0031] 5: second spring piece

[0032] 6: boss

[0033] 7: slot hole

[0034] 8: first corner portion

[0035] 9: second corner portion

[0036] 10: h-shaped fixing support

[0037] 11: first gap

[0038] 12: second gap

[0039] 13: third gap

[0040] 20: first fastener

[0041] 30: second fastener

[0042] P1: first interior part

[0043] P2: second interior part DETAILED DESCRIPTION

[0044] In the following detailed description of embodiments of the application, numerous specific details are set forth in order to provide a thorough understanding of the application. However, well-known methods, procedures, components, and circuits have not been described in detail as such excursions are not necessary to understand the application. It will be apparent, however, to one of ordinary skill in the art in view of the present disclosure, that the application can be practiced without such specific details. In other instances, well-known structures have been completely omitted so as to not obscure the disclosure with material deemed to be of only indirect

[0045] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description of the application herein and the claims that follow is not intended to be limiting of the application. In this specification and in the claims that follow, "first," "second," and like designations referring to objects and to actions of those objects generally are not intended to connote chronological order, although they can. Such designations have been used for convenience and to distinguish one element from another. "A" and "an" and "the" and like phrases indicating a singular noun are not limited to the singular noun, but also include the plural noun or nouns, unless otherwise indicated. "Including" and like phrases as used herein are not intended to be exhaustive, unless otherwise indicated. "Connected" or "coupled" and like phrases as used herein unless otherwise indicated, are intended to encompass a connection that is either direct or indirect, that is mechanical, electrical, magnetic, or a combination thereof.

[0046] In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the application. However, it will be apparent to one skilled in the art that the present application can be practiced in other embodiments that depart from these specific details. In other instances, detailed descriptions of well-known methods, processes, algorithms, devices, and circuits are omitted so as not to obscure the description of the present application with detail that is not

[0047] Figure 1 FIG. 1 is a perspective view of an aircraft interior trim piece fastening device according to an embodiment of the present application. Figure 2 FIG. 2 is another perspective view of an aircraft interior trim piece fastening device according to an embodiment of the present application. Figure 3 FIG. 3 is a side view of an aircraft interior trim piece fastening device according to an embodiment of the present application. Figure 4 FIG. 4 is a view of an aircraft interior trim piece fastening device according to an embodiment of the present application, showing the device in a first position. Figure 5is a schematic view of the aircraft interior part fixing device of an embodiment of the present application when fixing both the first interior part and the second interior part.

[0048] As shown in Figures 1 to 5 , the aircraft interior part fixing device of an embodiment of the present application comprises a first fixing panel 1, a second fixing panel 2, a first spring sheet 4, and a second spring sheet 5.

[0049] The first fixing panel 1 and the second fixing panel 2 are connected to each other near one end or near the middle position of the aircraft interior part fixing device, and a first gap 11 is formed between the first fixing panel 1 and the second fixing panel 2.

[0050] The first fixing panel 1 is provided with a slot hole 7, one end of the first spring sheet 4 is fixed to the outer side of the first fixing panel 1, and the other end is a free end. The free end of the first spring sheet 4 extends into the first gap 11 through the slot hole 7, and the second fixing panel 2 is provided with a fixed clamping part 3 near its end.

[0051] It should be noted that "the first fixing panel and the second fixing panel are connected to each other near one end or near the middle position of the aircraft interior part fixing device" means that the first fixing panel and the second fixing panel are connected to each other within a range of 30% of the length of the aircraft interior part fixing device from one end, or within a range of ±20% of the length of the aircraft interior part fixing device from the middle position.

[0052] The "length" of the aircraft interior part fixing device refers to the size of the aircraft interior part fixing device in the longitudinal direction (i.e., the approximately up-down direction) thereof. The "width" of the aircraft interior part fixing device refers to the size of the aircraft interior part fixing device in the transverse direction (i.e., the approximately left-right direction) thereof, which is perpendicular to the longitudinal direction. Figure 3 Figure 1 The "length" and "width" of the first fixing panel, the second fixing panel, the first spring sheet, and the second spring sheet are defined with reference to the "length" and "width" of the aircraft interior part fixing device.

[0053] "the second fixing panel is provided with a fixed clamping part near its end" means that the second fixing panel is provided with a fixed clamping part within a range of 30% of the length of the second fixing panel from the end.

[0054] According to the above technical solution, the aircraft interior part fixing device of the present application can achieve the following beneficial technical effects: it can achieve clamping and fixing of the aircraft interior part, and the interior part can rotate at a certain angle, adapt to the complex operating environment on the aircraft, and is simple and reliable to operate, and saves time and effort in installation and disassembly.

[0055] Specifically, the aircraft interior part fixing device of the present application has the following innovative points and beneficial technical effects compared with the prior art: ​

[0056] (1) The aircraft interior part fixing device only needs to insert the interior part (for example, the first interior part P1) into the gap of the fixing device, and the clamping and fixing can be realized by the first spring sheet 4 and the fixed clamping part 3. Moreover, the aircraft interior part fixing device support has a large internal space, the interior part can rotate at a certain angle with the fixed clamping part 3 as the fixed shaft, which is suitable for the complex operating environment on the aircraft, and the operation is simple and reliable, the installation and disassembly saves time and labor, and the interior part assembly efficiency is improved.

[0057] (2) The device clamping / coupling force provided by the aircraft interior part fixing device is uniform, and the clamping / coupling holding force is large. The spring sheet and the fixed panel are connected by fasteners, and if the spring sheet fails, it can be replaced independently, thereby reducing the cost of repairing the entire device.

[0058] In some embodiments, as shown in Figures 1 to 5 , the first fixed panel 1 and the second fixed panel 2 form an h-shaped fixed support 10, which can also be referred to as a device support.

[0059] Preferably, as shown in Figures 1 to 5 , the first fixed panel 1 and the second fixed panel 2 are integrally formed.

[0060] Preferably, as shown in Figures 1 to 5 , the second fixed panel 2 is provided with a fixed clamping part 3 at the end thereof within a range of 10% of the length from the end.

[0061] In some embodiments, as shown in Figures 1 to 5 , the aircraft interior part fixing device further comprises a second spring sheet 5, one end of the second spring sheet 5 is fixed to the outer side of the second fixed panel 2, the other end is a free end, the free end of the second spring sheet 5 is arranged on one side of the fixed clamping part 3 in the transverse direction and extends towards the first fixed panel 1.

[0062] Preferably, as shown in Figures 1 to 5 , the free end of the second spring sheet 5 is arranged on both sides of the fixed clamping part 3 in the transverse direction.

[0063] Therefore, by arranging the second spring sheet 5, in addition to clamping and fixing the first interior part P1, the second interior part P2 can be coupled and fixed by the second spring sheet 5, for example, the second interior part P2 is provided with a slot hole corresponding to the free end of the second spring sheet 5, and the free end of the second spring sheet 5 is coupled in the slot hole during assembly. Therefore, the aircraft interior part fixing device can realize the clamping and fixing of multiple interior parts, and the gap between the fixed interior parts is uniform, which improves the overall assembly efficiency on the basis of ensuring the consistency of the interior part gap.

[0064] In some embodiments, as shown in Figures 1 to 5As shown, the first spring sheet 4 is formed with a first corner portion 8, the first corner portion 8 is located in the first gap 11, and a second gap 12 is formed between the first corner portion 8 and the fixed clamping portion 3. In the free state, the opening direction of the first corner portion 8 is towards the first fixed panel 1.

[0065] Therefore, by arranging the first corner portion 8, the first spring sheet 4 can better clamp the first interior trim P1 by means of the first corner portion 8, the operation is simpler and more reliable, and the installation and disassembly are more time-saving and labor-saving.

[0066] In some embodiments, as shown, Figures 1 to 5 As shown, the second spring sheet 5 is formed with a second corner portion 9, and a third gap 13 is formed between the second corner portion 9 and the first fixed panel 1. In the free state, the opening direction of the second corner portion 9 is away from the first fixed panel 1.

[0067] Therefore, by arranging the second corner portion 9, the second spring sheet 5 can better clamp the second interior trim P2 by means of the second corner portion 9, the operation is simpler and more reliable, and the installation and disassembly are more time-saving and labor-saving.

[0068] In some embodiments, as shown, Figures 1 to 5 As shown, the section between the fixed end of the first spring sheet 4 and the first corner portion 8 is in contact with the outer side of the first fixed panel 1.

[0069] Therefore, the first spring sheet 4 can better clamp the first interior trim P1, the operation is simpler and more reliable, and the installation and disassembly are more time-saving and labor-saving.

[0070] In some embodiments, as shown, Figures 1 to 5 As shown, the second fixed panel 2 is provided with a boss 6 on the outer side, and the section near the free end of the second spring sheet 5 is in contact with the outer side of the boss 6.

[0071] Therefore, by arranging the boss 6, the elasticity of the second spring sheet 5 is further improved, the second spring sheet 5 can better clamp the second interior trim P2, the operation is simpler and more reliable, the installation and disassembly are more time-saving and labor-saving, and the overall thickness of the second fixed panel 2 will not be significantly increased.

[0072] In some embodiments, as shown, Figures 1 to 5 As shown, the width of the free end of the first spring sheet 4 is 22-25 mm.

[0073] Preferably, the width of the free end of the first spring sheet 4 remains unchanged from the contact with the edge of the slot hole 7 to the free end, and remains in the range of 22-25 mm.

[0074] Therefore, the first spring sheet 4 can provide uniform and appropriate clamping force, better clamp the first interior trim P1, the operation is simpler and more reliable, and the installation and disassembly are more time-saving and labor-saving.

[0075] In some embodiments, as shown in Figures 1 to 5 The width of the free end of the second spring sheet 5 is 10-13 mm.

[0076] Preferably, the width of the free end of the second spring sheet 5 remains unchanged from the position where it is in contact with the outer side of the boss 6 to the terminal end of the free end, and is kept in the range of 10-13 mm.

[0077] Therefore, the second spring sheet 5 can provide a uniform and appropriate clamping force, better clamping the second interior part P2, and the operation is simpler and more reliable, and the installation and disassembly is more time-saving and labor-saving.

[0078] In some embodiments, as shown in Figures 4 to 5 The interference amount of the first spring sheet 4 with the first interior part P1 is 1.6-1.8 mm.

[0079] That is, the distance that the first spring sheet 4 moves before and after clamping the first interior part P1 is 1.6-1.8 mm.

[0080] Therefore, by setting an appropriate first spring sheet interference amount, the first interior part P1 can be effectively clamped, and the operation is simple and reliable, and the installation and disassembly is time-saving and labor-saving.

[0081] In some embodiments, as shown in Figure 5 The clamping amount of the second spring sheet 5 with the second interior part P2 is 0.7-0.8 mm.

[0082] That is, the distance that the second spring sheet 5 extends into the corresponding groove hole of the second interior part P2 is 0.7-0.8 mm.

[0083] Therefore, by setting an appropriate second spring sheet clamping amount, the second interior part P2 can be effectively clamped, and the operation is simple and reliable, and the installation and disassembly is time-saving and labor-saving.

[0084] In some embodiments, as shown in Figures 1 to 5 The longitudinal length of the first fixed panel 1 from the mutual connection to the terminal end is greater than the longitudinal length of the second fixed panel 2 from the mutual connection to the terminal end. That is, in the longitudinal direction of the aircraft interior part fixing device, the first fixed panel 1 extends longer than the second fixed panel 2.

[0085] Therefore, it is more beneficial for the first interior part P1 to rotate by a certain angle with the fixed clamping portion 3 as the fixed shaft to adapt to the complex operating environment on the aircraft.

[0086] In some embodiments, as shown in Figures 1 to 5As shown, the first fixed panel 1 is made of metal, the second fixed panel 2 is also made of metal, the first spring sheet 4 is made of spring steel, and the second spring sheet 5 is also made of spring steel. The thickness of the first fixed panel 1 can be the same as or different from the thickness of the second fixed panel 2. The thickness of the first spring sheet 4 can be the same as or different from the thickness of the second spring sheet 5, which is selected according to the required clamping force / engaging force.

[0087] In some embodiments, as shown in FIG. 1, the first spring sheet 4 is fixedly connected with the first fixed panel 1 through a first fastener 20, and the second spring sheet 5 is fixedly connected with the second fixed panel 2 through a second fastener 30. Figures 1 to 5

[0088] Therefore, if the first spring sheet 4 or the second spring sheet 5 fails, the first spring sheet 4 or the second spring sheet 5 can be independently replaced, thereby reducing the cost of repairing the entire device.

[0089] In use, the first interior trim part P1 is inserted into the first gap 11 through the second gap 12 in the assembly direction, and the fixation of the first interior trim part P1 is completed. In disassembly, the first interior trim part P1 is pulled out in the reverse direction.

[0090] In use, the second interior trim part P2 is inserted in the assembly direction through the third gap 13, and the fixation of the second interior trim part P2 is completed. In disassembly, the second interior trim part P2 is pulled out in the reverse direction.

[0091] The specific embodiments of the present application are described above, but those skilled in the art will understand that the above specific embodiments do not constitute a limitation on the present application, and those skilled in the art can make various modifications on the basis of the above disclosure without departing from the scope of the present application.​

Claims

1. An aircraft interior trim fixing device, the aircraft interior trim fixing device comprising a first fixing panel, a second fixing panel, and a first spring sheet; in, The first fixing panel and the second fixing panel are connected to each other near one end or near the middle of the aircraft interior part fixing device, and a first gap is formed between the first fixing panel and the second fixing panel; The first fixing panel is provided with a slot, one end of the first spring sheet is fixed to the outer side of the first fixing panel, and the other end is a free end. The free end of the first spring sheet extends into the first gap through the slot, and the second fixing panel is provided with a fixing clamping part near its end.

2. The aircraft interior trim fixing device as described in claim 1, characterized in that, The aircraft interior trim fixing device also includes a second spring plate, one end of which is fixed to the outer side of the second fixing panel, and the other end is a free end. The free end of the second spring plate is located on the lateral side of the fixing clamp and extends toward the first fixing panel.

3. The aircraft interior trim fixing device as described in claim 1, characterized in that, The first spring sheet has a first bend portion, which is located in the first gap. A second gap is formed between the first bend portion and the fixing clamping portion. In the free state, the opening direction of the first bend portion faces the first fixing panel.

4. The aircraft interior trim fixing device as described in claim 2, characterized in that, The second spring sheet has a second bend, and a third gap is formed between the second bend and the first fixed panel. In the free state, the opening direction of the second bend faces away from the first fixed panel.

5. The aircraft interior trim fixing device as described in claim 3, characterized in that, The section between the fixed end of the first spring sheet and the first bend portion is in contact with the outer side of the first fixed panel.

6. The aircraft interior trim fixing device as described in claim 2, characterized in that, A boss is provided on the outer side of the second fixed panel, and the section near the free end of the second spring sheet is in contact with the outer side of the boss.

7. The aircraft interior trim fixing device as described in claim 1, characterized in that, The width of the free end of the first spring sheet is 22~25mm.

8. The aircraft interior trim fixing device as described in claim 2, characterized in that, The width of the free end of the second spring sheet is 10~13mm.

9. The aircraft interior trim fixing device as described in claim 1, characterized in that, The interference between the first spring sheet and the first interior trim piece is 1.6~1.8mm.

10. The aircraft interior trim fixing device as described in claim 2, characterized in that, The engagement amount between the second spring sheet and the second interior trim piece is 0.7~0.8mm.

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