Device for fixing an interior part of an aircraft

Abstract

The present application relates to the interior trim fixing device of aircraft. The interior trim fixing device of aircraft includes first fixed panel, second fixed panel, first spring piece;Among them, first fixed panel and second fixed panel are connected to each other near one end of the interior trim fixing device of aircraft or near the middle position, and the first gap is formed between first fixed panel and second fixed panel.;Among them, first fixed panel is provided with slot hole, one end of first spring piece is fixed to the outer side of first fixed panel, the other end is free end, the free end of first spring piece is extended into the first gap through the slot hole, and the second fixed panel is provided with fixed clamping part near the end.

Description

Technical Field

[0001] This invention relates to aircraft interior component fixing devices, and belongs to the field of aircraft equipment installation design. Background Technology

[0002] In modern aircraft interior assembly, interior panels are often fixed to the fuselage structure using brackets. Due to the complexity of the interior panel shapes and surrounding structures, the brackets connecting them to the structure are complex to design, needing to accommodate interior components from different planes and modules. After assembly, it is difficult to ensure alignment at the seams of the various interior modules, affecting the overall aesthetics of the cabin interior.

[0003] How to design a simple mounting device for complex installation environments, which can not only fix interior parts on different planes, but also simplify the installation and disassembly process, and control the gap after assembly to a certain extent, has become an urgent technical problem to be solved in the field of aircraft interior assembly design.

[0004] In one existing technical solution, the fixing device cannot be adapted to the simultaneous installation of multiple interior parts, and the interior parts cannot be adjusted at a certain angle in the gaps, making it unable to adapt to complex and ever-changing assembly environments, and the assembly angle is limited.

[0005] In another existing technical solution, the fixing device uses an adjustable angle "U"-shaped sheet metal bracket to fix the interior parts on multiple planes. However, each plane is fixed by fasteners, which is cumbersome and does not improve assembly efficiency.

[0006] In another existing technical solution, the fixing device uses a spring-plug connection, but if the springs lose their elasticity, they must all be replaced. Summary of the Invention

[0007] One objective of this invention is to provide an aircraft interior component fixing device that overcomes at least some of the defects of the prior art, enables the clamping and fixing of aircraft interior components, allows the interior components to rotate at a certain angle to adapt to the complex operating environment on board, and is simple and reliable to operate, saving time and effort in installation and disassembly.

[0008] The above-mentioned objective of the present invention is achieved by an aircraft interior trim fixing device, which includes a first fixing panel, a second fixing panel, and a first spring sheet;

[0009] Wherein, 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;

[0010] 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.

[0011] According to the above technical solution, the aircraft interior parts fixing device of the present invention can achieve the following beneficial technical effects: it can clamp and fix the aircraft interior parts, and the interior parts can rotate at a certain angle to adapt to the complex operating environment on the aircraft. It is also simple and reliable to operate, and saves time and effort in installation and disassembly.

[0012] Preferably, the aircraft interior trim fixing device further 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 disposed on the lateral side of the fixing clamp and extends toward the first fixing panel.

[0013] Preferably, the first spring sheet has a first bend portion located in the first gap, and 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.

[0014] Preferably, 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.

[0015] Preferably, 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.

[0016] Preferably, 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.

[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 between the first spring sheet and the first interior trim piece is 1.6~1.8mm.

[0020] Preferably, the engagement amount between the second spring sheet and the second interior trim piece is 0.7~0.8mm. Attached Figure Description

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

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

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

[0024] Figure 4 This is a schematic diagram of an aircraft interior trim fixing device according to an embodiment of the present invention when fixing a first interior trim part.

[0025] Figure 5 This is a schematic diagram of an aircraft interior trim fixing device according to an embodiment of the present invention, when fixing both the first interior trim and the second interior trim.

[0026] List of reference numerals

[0027] 1: First fixed panel;

[0028] 2: Second fixed panel;

[0029] 3: Fixed clamping part;

[0030] 4: First spring sheet;

[0031] 5: Second spring sheet;

[0032] 6: Boss;

[0033] 7: Slots;

[0034] 8: First fold corner;

[0035] 9: Second fold corner;

[0036] 10: H-shaped fixing bracket;

[0037] 11: First gap;

[0038] 12: Second gap;

[0039] 13: Third gap;

[0040] 20: First fastener;

[0041] 30: Second fastener;

[0042] P1: First interior trim component;

[0043] P2: Second interior trim. Detailed Implementation

[0044] The following describes specific embodiments of the present invention. It should be noted that, in order to provide a concise description, this specification cannot exhaustively describe all features of the actual embodiments. It should be understood that, in the actual implementation of any embodiment, just as in any engineering or design project, various specific decisions are often made to achieve the developer's specific goals and to meet system-related or business-related constraints, and this can change from one embodiment to another. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this invention, some design, manufacturing, or production modifications based on the technical content disclosed herein are merely conventional technical means and should not be construed as insufficient content of this disclosure.

[0045] Unless otherwise defined, the technical or scientific terms used in the claims and description shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in the patent application description and claims of this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. The terms "an" or "a" and similar terms do not indicate a quantity limitation, but rather indicate the presence of at least one. The terms "comprising" or "including" and similar terms mean that the element or object preceding "comprising" or "including" encompasses the element or object listed following "comprising" or "including" and its equivalents, and do not exclude other elements or objects. The terms "connected" or "linked" and similar terms are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0046] In the following description, in order to clearly demonstrate the structure and working method of the present invention, a number of directional terms will be used. However, terms such as "front", "back", "left", "right", "outside", "inside", "outward", "inward", "up", and "down" should be understood as convenient terms and not as limiting terms.

[0047] Figure 1 This is a perspective view of an aircraft interior trim fixing device according to an embodiment of the present invention. Figure 2 This is another perspective view of an aircraft interior trim fixing device according to an embodiment of the present invention. Figure 3 This is a side view of an aircraft interior trim fixing device according to an embodiment of the present invention. Figure 4 This is a schematic diagram of an aircraft interior trim fixing device according to an embodiment of the present invention when fixing a first interior trim part. Figure 5This is a schematic diagram of an aircraft interior trim fixing device according to an embodiment of the present invention, when fixing both the first interior trim and the second interior trim.

[0048] like Figures 1 to 5 As shown, an embodiment of the aircraft interior trim fixing device of the present invention includes a first fixing panel 1, a second fixing panel 2, and a first spring sheet 4;

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

[0050] The first fixed panel 1 is provided with a slot 7. One end of the first spring plate 4 is fixed to the outer side of the first fixed panel 1, and the other end is a free end. The free end of the first spring plate 4 extends into the first gap 11 through the slot 7. The second fixed panel 2 is provided with a fixing 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 in the middle of the aircraft interior trim fixing device" means that the first fixing panel and the second fixing panel are connected to each other within a range from one end of the aircraft interior trim fixing device to 30% of the device length from that end, or within a range of ±20% of the device length in the middle of the aircraft interior trim fixing device.

[0052] The "length" of an aircraft interior trim fastener refers to the length of the aircraft interior trim fastener in its longitudinal direction (i.e., Figure 3 The "width" of an aircraft interior trim fastener refers to its lateral dimension (roughly vertically). The "width" of an aircraft interior trim fastener refers to its lateral dimension (perpendicular to the longitudinal dimension, i.e., the width of the fastener in the horizontal direction). Figure 1 The dimensions (approximately left-right in the center). The "length" and "width" of the first fixed panel, the second fixed panel, the first spring plate, and the second spring plate are defined with reference to the "length" and "width" of the aircraft interior trim fastening device.

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

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

[0055] Specifically, the aircraft interior component fixing device of the present invention has the following innovations and beneficial technical effects compared with the prior art:

[0056] (1) When using this aircraft interior part fixing device, simply insert the interior part (e.g., the first interior part P1) into the gap of the fixing device, and it can be clamped and fixed by the first spring plate 4 and the fixing clamp 3. Moreover, the aircraft interior part fixing device has a large internal space, and the interior part can rotate at a certain angle with the fixing clamp 3 as the fixed axis, which can adapt to the complex operating environment on the aircraft. It is simple and reliable to operate, and the installation and disassembly are time-saving and labor-saving, thus improving the assembly efficiency of the interior parts.

[0057] (2) The clamping / locking force provided by the aircraft interior parts fixing device is uniform and has a large clamping / locking holding force. The spring sheet is connected to the fixing panel by fasteners. If the spring sheet fails, it can be replaced independently, reducing the cost of overall device maintenance.

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

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

[0060] Preferably, such as Figures 1 to 5 As shown, the second fixed panel 2 is provided with a fixing clamping part 3 from its end to a distance of 10% of the length from the end.

[0061] In some embodiments, such as Figures 1 to 5 As shown, the aircraft interior trim fixing device also includes a second spring plate 5. One end of the second spring plate 5 is fixed to the outer side of the second fixing panel 2, and the other end is a free end. The free end of the second spring plate 5 is located on the lateral side of the fixing clamping part 3 and extends toward the first fixing panel 1.

[0062] Preferably, such as Figures 1 to 5 As shown, the free ends of the second spring sheet 5 are disposed on both sides of the fixed clamping part 3.

[0063] Therefore, by providing the second spring plate 5, in addition to clamping and fixing the first interior trim piece P1, the second interior trim piece P2 can also be fixed by the second spring plate 5. For example, the second interior trim piece P2 has a slot corresponding to the free end of the second spring plate 5, and during assembly, the free end of the second spring plate 5 is engaged in this slot. Thus, this aircraft interior trim piece fixing device can clamp and fix multiple interior trim pieces, and the gaps between the fixed interior trim pieces are uniform, improving overall assembly efficiency while ensuring the consistency of the gaps between the interior trim pieces.

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

[0065] Therefore, by setting the first bend 8, the first spring sheet 4 can better clamp the first interior trim piece P1 with the help of the first bend 8, making the operation simpler and more reliable, and the installation and disassembly more time-saving and labor-saving.

[0066] In some embodiments, such as Figures 1 to 5 As shown, the second spring sheet 5 has a second bend 9, and a third gap 13 is formed between the second bend 9 and the first fixed panel 1. In the free state, the opening direction of the second bend 9 is opposite to that of the first fixed panel 1.

[0067] Therefore, by setting the second bend 9, the second spring sheet 5 can better engage the second interior trim piece P2 with the help of the second bend 9, making the operation simpler and more reliable, and saving time and effort in installation and disassembly.

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

[0069] Therefore, it can ensure that the first spring plate 4 can better clamp the first interior part P1, making the operation simpler and more reliable, and the installation and disassembly more time-saving and labor-saving.

[0070] In some embodiments, such as Figures 1 to 5 As shown, a boss 6 is provided on the outer side of the second fixed panel 2, 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 setting the boss 6, the elasticity of the second spring plate 5 is further improved. The second spring plate 5 can better engage the second interior trim piece P2, making the operation simpler and more reliable, and the installation and disassembly more time-saving and labor-saving, without significantly increasing the overall thickness of the second fixed panel 2.

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

[0073] Preferably, the width of the free end of the first spring plate 4 remains constant from the edge of the slot 7 toward the end of the free end, and is kept in the range of 22~25mm.

[0074] Therefore, the first spring plate 4 can provide a uniform and suitable clamping force, better clamping the first interior part P1, making the operation simpler and more reliable, and saving time and effort in installation and disassembly.

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

[0076] Preferably, the width of the free end of the second spring sheet 5 remains constant from the point where it fits against the outer side of the boss 6 toward the end of the free end, and is kept within the range of 10 to 13 mm.

[0077] Therefore, the second spring plate 5 can provide a uniform and suitable clamping force, better engage the second interior trim piece P2, make the operation simpler and more reliable, and save time and effort in installation and disassembly.

[0078] In some embodiments, such as Figures 4 to 5 As shown, the interference between the first spring sheet 4 and the first interior trim piece P1 is 1.6~1.8mm.

[0079] In other words, the distance that the first spring plate 4 moves before and after clamping the first interior trim piece P1 is 1.6~1.8mm.

[0080] Therefore, by setting an appropriate amount of interference from the first spring plate, it is possible to effectively clamp the first interior trim piece P1, while also making the operation simple and reliable, and saving time and effort in installation and disassembly.

[0081] In some embodiments, such as Figure 5 As shown, the engagement amount between the second spring sheet 5 and the second interior trim piece P2 is 0.7~0.8mm.

[0082] In other words, the distance from which the second spring sheet 5 extends into the corresponding slot of the second interior trim piece P2 is 0.7~0.8mm.

[0083] Therefore, by setting an appropriate second spring clip engagement amount, it is possible to ensure effective engagement of the second interior trim piece P2, while also making the operation simple and reliable, and saving time and effort in installation and disassembly.

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

[0085] Therefore, it is more advantageous for the first interior trim part P1 to rotate at a certain angle with the fixed clamping part 3 as the fixed axis, so as to adapt to the complex operating environment on the machine.

[0086] In some embodiments, such as Figures 1 to 5As shown, the first fixing panel 1 is made of metal, the second fixing panel 2 is also made of metal, the first spring plate 4 is made of spring steel, and the second spring plate 5 is also made of spring steel. The thickness of the first fixing panel 1 and the second fixing panel 2 can be the same or different. The thickness of the first spring plate 4 and the second spring plate 5 can be the same or different, depending on the required clamping force / locking force.

[0087] In some embodiments, such as Figures 1 to 5 As shown, the first spring plate 4 is fixedly connected to the first fixed panel 1 by the first fastener 20; the second spring plate 5 is fixedly connected to the second fixed panel 2 by the second fastener 30.

[0088] Therefore, if the first spring plate 4 or the second spring plate 5 fails, the first spring plate 4 or the second spring plate 5 can be replaced independently, reducing the cost of overall device maintenance.

[0089] In use, insert the first interior trim piece P1 into the first gap 11 through the second gap 12 along the assembly direction to fix one side of the first interior trim piece P1. To disassemble, simply pull it out in the opposite direction.

[0090] When in use, insert the second interior trim piece P2 along the assembly direction through the third gap 13 until it reaches the fixed position, thus securing one side of the second interior trim piece P2. For disassembly, simply pull it out in the opposite direction.

[0091] The specific embodiments of the present invention have been described above. However, those skilled in the art will understand that the above specific embodiments do not constitute a limitation on the present invention. Those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.

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; wherein 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 trim fixing device, and a first gap is formed between the first fixing panel and the second fixing panel. The first fixed panel is provided with a slot, one end of the first spring sheet is fixed to the outer side of the first fixed 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 fixed panel is provided with a fixing clamping part near its end. The first spring sheet has a first bend, which is located in the first gap. A second gap is formed between the first bend and the fixing clamp. In the free state, the opening of the first bend faces the first fixing panel, and the interior trim can rotate at a certain angle with the fixing clamp as the fixing axis.

2. The aircraft interior trim piece securement device of claim 1, wherein, 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 piece securement device of claim 2, wherein, 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.

4. The aircraft interior trim piece securement device of claim 1, wherein, 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.

5. The aircraft interior trim piece securement device of claim 2, wherein, 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.

6. The aircraft interior trim piece securement device of claim 1, wherein, The width of the free end of the first spring sheet is 22~25mm.

7. The aircraft interior trim piece securement device of claim 2, wherein, The width of the free end of the second spring sheet is 10~13mm.

8. The aircraft interior trim piece securement device of claim 1, wherein, The interference between the first spring sheet and the first interior trim piece is 1.6~1.8mm.

9. The aircraft interior trim piece securement device of claim 2, wherein, The engagement amount between the second spring sheet and the second interior trim piece is 0.7~0.8mm.

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