Fixing device for heat insulation and sound insulation layer of airplane

Abstract

The utility model belongs to the technical field of airplane heat insulation and sound insulation layer installation, and discloses an airplane heat insulation and sound insulation layer fixing device which comprises a clamping assembly and two connecting pieces. The clamping assembly comprises a first clamping piece, a second clamping piece and a wrapping piece. The first clamping piece and the second clamping piece can be far away from each other under the action of external force; when the external force is relieved, the first clamping piece and the second clamping piece can get close to each other under the action of resilience force so as to clamp the outer sides of the two ends of the frame-wrapped heat insulation and sound insulation layer assembly, and the other part of the frame-wrapped heat insulation and sound insulation layer assembly is wrapped with the wrapping piece. The two connecting pieces are located on the outer side face of the first clamping piece and the outer side face of the second clamping piece correspondingly and are connected with and fix bent skirt edges at the ends of the frame wrapping heat insulation and sound insulation layer assembly. The aircraft heat and sound insulation layer fixing device is good in heat and sound insulation performance, good in fixing effect, easy to connect and convenient to disassemble and assemble.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft thermal insulation and sound insulation layer installation, in particular to an aircraft thermal insulation and sound insulation layer fixing device. Background Art

[0002] The main body of the aircraft is usually equipped with a heat-insulating and sound-insulating layer made of materials with good corrosion resistance and flame propagation resistance. On the one hand, it maintains the stability of the temperature and humidity in the cabin, and on the other hand, it isolates the noise generated by the external engine, fuselage, etc. during the flight from the aircraft inside the cabin.

[0003] Usually, the thermal insulation and sound insulation layer of an aircraft is installed on the aircraft body, for example, fixed on the structural frame edge of the aircraft, connected to the aircraft skin, etc. The existing thermal insulation and sound insulation layer installation methods usually adopt spring clip fixing, nylon buckle or tape fixing and the like. Among them, the spring clip is usually a clamp made of elastic metal material, which clamps the thermal insulation and sound insulation layer with the edges of the components on both sides thereof, thereby fixing the thermal insulation and sound insulation layer on the standard structural frame edge. However, the elastic clamping force of the spring clip is sometimes insufficient to ensure that the thermal insulation and sound insulation layer is firmly fixed; during the flight of the aircraft, the spring clip will loosen due to the long-term vibration of the aircraft, or even fall off; and the spring clip itself is also relatively heavy, further increasing the risk of its falling off. The nylon buckle fixing method is to respectively set a nylon velvet belt and a nylon hook belt on the skin or irregular frame edge and the thermal insulation and sound insulation layer, and fix the thermal insulation and sound insulation layer to the fuselage through the connection between the two. The tape fixes different parts of the thermal insulation and sound insulation layer, which can be used to fix the thermal insulation and sound insulation layer to the wall panel of the aircraft. However, the fixing methods of Velcro and adhesive tape also have the problem of insufficient fixing firmness and easy loosening. Therefore, it is urgent to propose a fixing device for the thermal insulation and sound insulation layer of an aircraft to solve the above problems. Utility Model Content

[0004] The utility model provides a device for fixing a heat-insulating and sound-insulating layer of an aircraft, which has good heat-insulating and sound-insulating performance, good fixing effect, simple connection and convenient assembly and disassembly.

[0005] To achieve this purpose, the utility model adopts the following technical solutions:

[0006] The aircraft thermal insulation and sound insulation layer fixing device is used to fix the frame thermal insulation and sound insulation layer assembly wrapped on the aircraft structure frame edge, including:

[0007] A clamping assembly, comprising a first clamping member and a second clamping member arranged at a relative interval and a covering member connecting the first clamping member and the second clamping member, wherein the first clamping member and the second clamping member can move away from each other under the action of an external force, and when the external force is released, the first clamping member and the second clamping member can approach each other under the action of a rebound force to clamp the outer sides of the two ends of the frame heat insulation and sound insulation layer assembly, and the covering member covers the rest of the frame heat insulation and sound insulation layer assembly;

[0008] The two connecting pieces are respectively located on the outer side surfaces of the first clamping piece and the second clamping piece, and are connected and fixed to the bent skirt at the end of the heat-insulating and sound-insulating layer assembly of the frame.

[0009] As an optional technical solution for the aircraft thermal insulation and sound insulation layer fixing device, the connecting member is also connected to the skirt of the corresponding inter-frame thermal insulation and sound insulation layer assembly, and the inter-frame thermal insulation and sound insulation layer assembly is adjacent to the frame-enclosing thermal insulation and sound insulation layer assembly.

[0010] As an optional technical solution for the aircraft thermal insulation and sound insulation layer fixing device, the connecting piece is arranged to penetrate and connect the group edge of the folded and opposite frame thermal insulation and sound insulation layer assembly and the skirt edge of the inter-frame thermal insulation and sound insulation layer assembly.

[0011] As an optional technical solution for fixing the thermal insulation and sound insulation layer of an aircraft, each of the connecting parts includes a nail cap and a nail rod connected to each other, the two nail caps are respectively attached to the outer side of the first clamping part and the outer side of the second clamping part, and the two nail rods are penetrated in directions away from each other to connect the group edge of the frame thermal insulation and sound insulation layer assembly and the skirt edge of the inter-frame thermal insulation and sound insulation layer assembly.

[0012] As an optional technical solution for the aircraft thermal insulation and sound insulation layer fixing device, at least two annular bosses are provided along the axial direction of the nail rod, and the group edge of the frame thermal insulation and sound insulation layer assembly and the skirt edge of the inter-frame thermal insulation and sound insulation layer assembly are clamped between two adjacent annular bosses.

[0013] As an optional technical solution for the device for fixing the thermal and sound insulation layer of an aircraft, the radial dimension of the annular boss decreases along the axis of the nail rod in a direction away from the nail cap.

[0014] As an optional technical solution for the aircraft thermal insulation and sound insulation layer fixing device, the aircraft thermal insulation and sound insulation layer fixing device also includes a gasket, which is sleeved on the nail rod and cooperates with the nail rod to connect the group edge of the frame thermal insulation and sound insulation layer assembly and the skirt edge of the inter-frame thermal insulation and sound insulation layer assembly.

[0015] As an optional technical solution of the device for fixing the thermal and sound insulation layer of an aircraft, each of the connecting members further comprises a protective sleeve, and the protective sleeve is sleeved on the free end of the nail rod.

[0016] As an optional technical solution for the aircraft thermal insulation and sound insulation layer fixing device, the first clamping member and the second clamping member are both plates, and the free ends of the first clamping member and the second clamping member are both curved in a direction away from the structural frame edge.

[0017] As an optional technical solution for the device for fixing the thermal insulation and sound insulation layer of an aircraft, the covering member is in a continuous arc shape along the outer surface of the thermal insulation and sound insulation layer assembly of the frame.

[0018] Beneficial effects of the utility model: The aircraft thermal insulation and sound insulation layer fixing device provided by the utility model is used to fix the frame thermal insulation and sound insulation layer assembly wrapped on the edge of the aircraft structure frame, including a clamping assembly and two connecting pieces. The clamping assembly includes a first clamping piece, a second clamping piece and a covering piece. The first clamping piece and the second clamping piece can move away from each other under the action of an external force; when the external force is released, the first clamping piece and the second clamping piece can move closer to each other under the action of a rebound force to clamp the outer sides of the two ends of the frame thermal insulation and sound insulation layer assembly, and the covering piece covers the rest of the frame thermal insulation and sound insulation layer assembly. The two connecting pieces are respectively located on the outer sides of the first clamping piece and the second clamping piece, and are connected to fix the bent skirt at the ends of the frame thermal insulation and sound insulation layer assembly. The aircraft thermal insulation and sound insulation layer fixing device utilizes a clamping component and a covering member to jointly wrap the frame thermal insulation and sound insulation layer assembly, thereby improving the thermal insulation and sound insulation performance of the frame thermal insulation and sound insulation layer assembly; and then utilizes the resilience of the clamping component itself to clamp the frame thermal insulation and sound insulation layer assembly, thereby achieving fixed installation of the frame thermal insulation and sound insulation layer assembly with good fixing effect on the basis of ensuring the thermal insulation and sound insulation performance. In view of the fact that the frame thermal insulation and sound insulation layer assembly in this embodiment has a folded skirt, a connecting member is provided to connect the skirt, thereby further fixing the frame thermal insulation and sound insulation layer assembly, thereby improving the installation stability of the frame thermal insulation and sound insulation layer assembly. Therefore, compared with traditional fixing methods such as spring clips, Velcro or tapes, the aircraft thermal insulation and sound insulation layer fixing device has good thermal insulation and sound insulation performance, good fixing effect, simple connection, and convenient assembly and disassembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.

[0020] Figure 1 It is an isometric view of a device for fixing a heat and sound insulation layer of an aircraft provided by an embodiment of the utility model;

[0021] Figure 2 It is a back view of the aircraft thermal insulation and sound insulation layer fixing device provided by an embodiment of the utility model.

[0022] In the figure:

[0023] 100, clamping assembly; 110, first clamping member; 120, second clamping member; 130, covering member; 200, connecting member; 210, nail cap; 220, nail rod; 221, annular boss; 300, protective cover. DETAILED DESCRIPTION

[0024] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only the parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0025] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0026] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0027] In the description of this embodiment, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplified operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0028] The aircraft heat insulation and sound insulation layer fixing device provided by the utility model has good heat insulation and sound insulation performance, good fixing effect, simple connection and convenient assembly and disassembly.

[0029] Specific as Figure 1 and Figure 2 As shown, the aircraft thermal insulation and sound insulation layer fixing device is used to fix the frame thermal insulation and sound insulation layer assembly wrapped on the edge of the aircraft structure frame, and includes a clamping assembly 100 and two connecting members 200. The clamping assembly 100 includes a first clamping member 110 and a second clamping member 120 that are relatively spaced and arranged, and a covering member 130 that connects the first clamping member 110 and the second clamping member 120. The first clamping member 110 and the second clamping member 120 can move away from each other under the action of an external force. When the external force is released, the first clamping member 110 and the second clamping member 120 can approach each other under the action of a rebound force to clamp the outer sides of the two ends of the frame thermal insulation and sound insulation layer assembly; the covering member 130 covers the rest of the frame thermal insulation and sound insulation layer assembly. The two connecting members 200 are respectively located on the outer sides of the first clamping member 110 and the second clamping member 120, and are connected to fix the skirt bent at the ends of the frame thermal insulation and sound insulation layer assembly. The aircraft thermal insulation and sound insulation layer fixing device utilizes the clamping assembly 100 and the covering member 130 to jointly wrap the frame thermal insulation and sound insulation layer assembly, thereby improving the thermal insulation and sound insulation performance of the frame thermal insulation and sound insulation layer assembly; and then utilizes the rebound force of the clamping assembly 100 itself to clamp the frame thermal insulation and sound insulation layer assembly, thereby achieving the fixed installation of the frame thermal insulation and sound insulation layer assembly with good fixing effect on the basis of ensuring the thermal insulation and sound insulation performance. In view of the fact that the frame thermal insulation and sound insulation layer assembly in this embodiment has a foldable skirt, the skirt is connected by providing a connecting member 200 to further fix the frame thermal insulation and sound insulation layer assembly, thereby improving the installation stability of the frame thermal insulation and sound insulation layer assembly. Therefore, compared with traditional fixing methods such as spring clips, Velcro or tape, the aircraft thermal insulation and sound insulation layer fixing device has good thermal insulation and sound insulation performance, good fixing effect, simple connection, and convenient disassembly and assembly.

[0030] Furthermore, the connecting piece 200 is also connected to the skirt of the corresponding inter-frame thermal insulation and sound insulation layer assembly, and the inter-frame thermal insulation and sound insulation layer assembly is adjacent to the frame-wrapping thermal insulation and sound insulation layer assembly, which not only further improves the fixing effect of the frame-wrapping thermal insulation and sound insulation layer assembly, but also can fix the inter-frame thermal insulation and sound insulation layer assembly.

[0031] There are many ways for the connector 200 to connect the skirt of the frame heat insulation and sound insulation layer assembly and the inter-frame heat insulation and sound insulation layer assembly. Preferably, the connector 200 is inserted through the group edge of the frame heat insulation and sound insulation layer assembly and the skirt of the inter-frame heat insulation and sound insulation layer assembly that are opposite to each other after being folded. Inserting and connecting the skirt of the frame heat insulation and sound insulation layer assembly and the inter-frame heat insulation and sound insulation layer assembly that are opposite to each other after being folded makes the contact area between the frame heat insulation and sound insulation layer assembly and the inter-frame heat insulation and sound insulation layer assembly larger and the connection strength higher.

[0032] It is worth noting that in this embodiment, mounting holes are provided on the group edge of the frame insulation and sound insulation layer assembly and the skirt of the inter-frame insulation and sound insulation layer assembly, and the connecting member 200 passes through the mounting holes to connect the group edge of the frame insulation and sound insulation layer assembly and the skirt of the inter-frame insulation and sound insulation layer assembly.

[0033] Furthermore, each connector 200 includes a nail cap 210 and a nail rod 220 connected to each other, the two nail caps 210 are respectively attached to the outside of the first clamping member 110 and the outside of the second clamping member 120, and the two nail rods 220 are passed through the group edge of the frame-wrapped heat and sound insulation layer assembly and the skirt edge of the inter-frame heat and sound insulation layer assembly in directions away from each other. The nail cap 210 can increase the contact area between the connector 200 and the first clamping member 110 or the second clamping member 120, increase the connection strength, and the nail cap 210 and the nail rod 220 have a simple structure and are easy to connect.

[0034] In this embodiment, the nail cap 210 is bonded to the outer side of the first clamping member 110 and the outer side of the second clamping member 120 .

[0035] Furthermore, in order to increase the connection strength between the edge of the frame heat insulation and sound insulation layer assembly of the nail rod 220 and the skirt of the heat insulation and sound insulation layer assembly between frames, at least two annular bosses 221 are provided along the axial direction of the nail rod 220, and the edge of the frame heat insulation and sound insulation layer assembly and the skirt of the heat insulation and sound insulation layer assembly between frames are clamped between two adjacent annular bosses 221. Exemplarily, the number of the annular bosses 221 can be two, three, four, five, etc.

[0036] In this embodiment, in order to facilitate the nail rod 220 to penetrate the group edge of the frame insulation and sound insulation layer assembly and the skirt edge of the inter-frame insulation and sound insulation layer assembly along the axis direction of the nail rod 220 away from the nail cap 210, the radial size of the annular boss 221 decreases along the axis direction of the nail rod 220 away from the nail cap 210.

[0037] The aircraft thermal insulation and sound insulation layer fixing device also includes a gasket (not shown in the figure), which is sleeved on the nail rod 220 and cooperates with the nail rod 220 to connect the group edge of the frame thermal insulation and sound insulation layer assembly and the skirt edge of the inter-frame thermal insulation and sound insulation layer assembly.

[0038] Each connector 200 further includes a protective sleeve 300, which is sleeved on the free end of the nail rod 220 to prevent the tip of the nail rod 220 from injuring an operator or damaging other parts of the aircraft. The protective sleeve 300 can be made of nylon material or the like.

[0039] Continue as Figure 1 and Figure 2 As shown, the first clamping member 110 and the second clamping member 120 are both plates, and the free ends of the first clamping member 110 and the second clamping member 120 are both curved in a direction away from the edge of the structural frame, so that the contact area of ​​the two plates is large, so that the connection strength is high; the two curved edges allow the clamping and extrusion points of the first clamping member 110 and the second clamping member 120 to smoothly transition to the free ends to prevent damage to the frame insulation and sound insulation layer assembly.

[0040] Similarly, the covering member 130 is in a continuous arc shape along the outer surface of the frame heat insulation and sound insulation layer assembly.

[0041] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the implementation methods of the present invention. For those skilled in the art, various obvious changes, readjustments and substitutions can be made without departing from the scope of protection of the present invention. It is not necessary and impossible to list all implementation methods here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention shall be included in the scope of protection of the claims of the present invention.

Claims

1. An aircraft thermal insulation and sound insulation layer fixing device, used for fixing a frame thermal insulation and sound insulation layer assembly wrapped on an aircraft structure frame edge, characterized in that: include: The clamping assembly (100) comprises a first clamping member (110) and a second clamping member (120) which are arranged at a relative interval and a covering member (130) connecting the first clamping member (110) and the second clamping member (120), wherein the first clamping member (110) and the second clamping member (120) can move away from each other under the action of an external force, and when the external force is released, the first clamping member (110) and the second clamping member (120) can move closer to each other under the action of a rebound force to clamp the outer sides of two ends of the frame heat insulation and sound insulation layer assembly, and the covering member (130) covers the rest of the frame heat insulation and sound insulation layer assembly; Two connecting members (200) are respectively located on the outer side surfaces of the first clamping member (110) and the second clamping member (120), and are connected to fix the bent skirt at the end of the frame heat insulation and sound insulation layer assembly.

2. The aircraft thermal insulation and sound insulation layer fixing device according to claim 1, characterized in that: The connecting piece (200) is also connected to the skirt of the corresponding inter-frame thermal insulation and sound insulation layer assembly, and the inter-frame thermal insulation and sound insulation layer assembly is adjacent to the frame-enclosing thermal insulation and sound insulation layer assembly.

3. The aircraft thermal insulation and sound insulation layer fixing device according to claim 2, characterized in that: The connecting piece (200) is arranged to penetrate and connect the group edge of the frame-wrapping heat and sound insulation layer assembly and the skirt edge of the inter-frame heat and sound insulation layer assembly which are folded and opposite to each other.

4. The aircraft thermal insulation and sound insulation layer fixing device according to claim 3, characterized in that: Each of the connecting members (200) comprises a nail cap (210) and a nail rod (220) connected to each other, the two nail caps (210) being respectively attached to the outside of the first clamping member (110) and the outside of the second clamping member (120), and the two nail rods (220) being passed through in directions away from each other to connect the group edge of the frame-wrapping heat insulation and sound insulation layer assembly and the skirt edge of the inter-frame heat insulation and sound insulation layer assembly.

5. The aircraft thermal insulation and sound insulation layer fixing device according to claim 4, characterized in that: At least two annular bosses (221) are provided along the axial direction of the nail rod (220), and the group edge of the frame-wrapping heat and sound insulation layer assembly and the skirt edge of the inter-frame heat and sound insulation layer assembly are clamped between two adjacent annular bosses (221).

6. The aircraft thermal insulation and sound insulation layer fixing device according to claim 5, characterized in that: The radial dimension of the annular boss (221) decreases along the axis of the nail rod (220) in a direction away from the nail cap (210).

7. The aircraft thermal insulation and sound insulation layer fixing device according to claim 4, characterized in that: The aircraft thermal insulation and sound insulation layer fixing device also includes a gasket, which is sleeved on the nail rod (220) and cooperates with the nail rod (220) to connect the group edge of the frame thermal insulation and sound insulation layer assembly and the skirt edge of the inter-frame thermal insulation and sound insulation layer assembly.

8. The aircraft thermal insulation and sound insulation layer fixing device according to claim 4, characterized in that: Each of the connecting members (200) further comprises a protective sleeve (300), wherein the protective sleeve (300) is sleeved on the free end of the nail rod (220).

9. The aircraft thermal insulation and sound insulation layer fixing device according to claim 1, characterized in that: The first clamping member (110) and the second clamping member (120) are both plate members, and the free ends of the first clamping member (110) and the second clamping member (120) are both curved in an arc shape in a direction away from the structural frame edge.

10. The aircraft thermal insulation and sound insulation layer fixing device according to claim 1, characterized in that: The covering member (130) is in a continuous arc shape along the outer surface of the frame heat insulation and sound insulation layer assembly.

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