An aerospace fire blocking and retarding fixture assembly

Abstract

The utility model relates to the technical field of fire -retardant and discloses an aerospace fire -retardant fixing mechanism assembly, including two casing, two casing splicing form connecting space, pipeline cover is established in connecting space, at least two sets of limiting piece, set up on the inner wall of casing, be provided with the connecting channel of communication with connecting space on limiting piece, be provided with the support end on limiting piece, and the end of support end forms contact top end, and contact top end is opposite with the outer wall of pipeline;The fire -retardant cover is covered on the outer wall of casing;The utility model can make the fixed state of line contact or surface contact between support end and pipeline, cooperate the connecting space under vacuum state, make it not easy to form heat conduction path, prevent the heat generated by pipeline from diffusing to the surrounding components, form the phenomenon of temperature aggregation.

Description

Technical Field

[0001] This utility model relates to the field of fireproof and flame-retardant technology, specifically to an aerospace fireproof and flame-retardant fixing mechanism component. Background Technology

[0002] In the aerospace field, critical areas such as engine compartments, fuel pipeline compartments, and cable channels are prone to fires due to high temperatures, fuel leaks, and electrical faults. Fixing mechanisms are core components that support pipelines, cables, and equipment.

[0003] Currently, existing fixing mechanisms often use metal materials such as stainless steel and titanium alloy to wrap around the fuel lines inside the engine compartment. Although this can meet the basic fixing strength requirements, it has significant drawbacks. When the fuel lines generate high temperatures, the high thermal conductivity of the metal material easily forms a heat conduction path, causing the heat to spread rapidly to surrounding components and resulting in temperature accumulation. Utility Model Content

[0004] This utility model provides an aerospace fireproof and flame-retardant fixing mechanism assembly. Through the cooperation of a limiting component, a supporting end, and a flame-retardant sleeve, the supporting end and the pipeline are made to form a fixed state of line contact or surface contact in a vacuum state. This solves the problem mentioned in the background art that the pipeline is prone to forming a heat conduction path, which causes heat to spread rapidly to the surrounding components and form a temperature accumulation phenomenon.

[0005] This utility model provides the following technical solution: An aerospace fireproof and flame-retardant fixing mechanism assembly includes two housings joined together to form a connecting space, with a pipeline sleeved within the connecting space. It also includes at least two sets of limiting members disposed on the inner walls of the housings, wherein each limiting member has a connecting channel communicating with the connecting space, and a supporting end on each limiting member, the end of which forms a contact tip abutting against the outer wall of the pipeline; and a flame-retardant sleeve sleeved on the outer wall of the housings.

[0006] As a preferred technical solution of this utility model, the support end includes an arc-shaped top end disposed at the end of the limiting member, and the arc-shaped surface of the arc-shaped top end forms surface contact with the outer wall of the pipeline.

[0007] As a preferred embodiment of this utility model, the support end includes a conical top end disposed at the end of the limiting member, and the tip of the conical top end abuts against the outer wall of the pipeline.

[0008] As a preferred embodiment of this utility model, the length ratio of the limiting member to the supporting end is 3:1.

[0009] As a preferred embodiment of this utility model, an end is fixedly connected to the housing, a connecting groove is provided on the end, and a sealing ring is provided on the connecting groove.

[0010] As a preferred embodiment of this utility model, a sealing groove is provided on the housing, and a sealing strip is provided on the sealing groove, and the sealing groove is adapted to the connecting groove.

[0011] As a preferred embodiment of this utility model, the flame-retardant sleeve has an opening, and the two ends of the opening form free ends, which are connected by Velcro.

[0012] As a preferred embodiment of this utility model, the inner wall of the flame-retardant sleeve is provided with an inner cladding layer.

[0013] Compared with the prior art, this utility model provides an aerospace fireproof and flame-retardant fixing mechanism component, which has the following beneficial effects: 1. In this aerospace fireproof and flame-retardant fixing mechanism component, two support end forms are adapted to different pipeline scenarios, which can enable the support end and the pipeline to form a fixed state of line contact or surface contact. Combined with the connection space in a vacuum state, it is not easy to form a heat conduction path, preventing the heat generated by the pipeline from spreading to the surrounding components and forming a temperature accumulation phenomenon.

[0014] The parts not covered in this device are the same as or can be implemented using existing technology. This utility model can make the support end and the pipeline form a fixed state of line contact or surface contact. Combined with the connection space under vacuum, it makes it difficult to form a heat conduction path and prevents the heat generated by the pipeline from spreading to the surrounding components and forming a temperature accumulation phenomenon. Attached Figure Description

[0015] To more clearly illustrate the specific embodiments of this utility model or the technical solutions in the prior art, the accompanying drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. In all the drawings, the elements or parts are not necessarily drawn to actual scale.

[0016] Figure 1 This is a schematic diagram of the entire utility model; Figure 2 This is a schematic diagram of the interior of the casing of this utility model; Figure 3 This is a schematic diagram of the flame-retardant sleeve of this utility model; Figure 4 This is a schematic diagram of the arc-shaped top end of this utility model; Figure 5 This is a schematic diagram of the conical tip of this utility model.

[0017] In the diagram: 1. Housing; 101. Connecting ear; 102. Bolt; 2. End; 3. Connecting groove; 4. Sealing ring; 5. Sealing groove; 6. Sealing strip; 7. Limiting component; 8. Support end; 9. Connecting channel; 10. Flame retardant sleeve; 11. Inner cladding; 12. Velcro; 801. Arc-shaped top; 802. Conical top. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0019] Example: Reference Figures 1-5 This utility model provides an aerospace fireproof and flame-retardant fixing mechanism component. Its basic components mainly include two shells 1, which are spliced ​​together to form a connecting space. The pipeline is sleeved in the connecting space and is adapted to aviation fuel pipelines with a diameter of 50-80mm. In this device, the diameter is 70mm. Both shells 1 are semi-cylindrical structures and are integrally molded from alumina ceramic fiber reinforced resin matrix composite material. This material has a low thermal conductivity, which is more than 65% lower than that of traditional stainless steel, and a compressive strength ≥300MPa, which meets the fixing strength requirements. The inner diameter of the shell 1 is adapted to the outer diameter of the pipeline to be fixed. The splicing surface of the two shells 1 is provided with a sealing groove 5 along the axial direction, and a sealing strip 6 is provided on the sealing groove 5 to keep the two shells 1 in a sealed state when spliced.

[0020] Connecting lugs 101 are also provided on the housing 1. After splicing, they are fastened by four sets of high-strength ceramic bolts 102 to form a cylindrical connecting space with excellent sealing performance. The pipeline is coaxially sleeved in the connecting space. End heads 2 are provided at both ends of the housing 1. The end heads 2 are made of the same composite material as the housing 1. The connection parts with the housing 1 are reinforced by carbon fiber cloth to ensure the connection strength. A connecting groove 3 is opened on the end face of the end head 2. A graphite-reinforced sealing ring 4 is installed in the connecting groove 3. The sealing ring 4 has a circular cross-section. When the two housings 1 are spliced, the sealing ring 4 is squeezed and fills the gap between the connecting groove 3 and the two housings 1.

[0021] Specifically, the device is equipped with five to twenty sets of limiting components 7, of which ten sets are used in this device. They are circumferentially spaced on the inner walls of the two housings 1. The bottom of the limiting component 7 is a cuboid structure made of silicon nitride ceramic material. It is bonded to the inner wall of the housing 1 with high-temperature structural adhesive. The bonding surface is coated with a 2mm thick silane coupling agent to improve adhesion. A connecting channel 9 is provided between two adjacent sets of limiting components 7. When it is necessary to evacuate the connecting space, the channel can achieve the connection effect between two adjacent limiting components 7. A support end 8 is integrally formed at the end of the limiting component 7. The length ratio of the limiting component 7 to the support end 8 is 3:1, that is, the length of the support end 8 is 20mm and the length of the limiting component 7 is 60mm. This can reduce the contact area between the support structure and the pipeline while ensuring the stability of the support and reducing the heat conduction efficiency.

[0022] The support end 8 provides two implementation forms. For main fuel lines with a fixed diameter, an arc-shaped top end 801 is adopted, whose inner wall curvature radius is consistent with the outer wall curvature radius of the line (e.g., the curvature radius of the arc-shaped top end 801 is 30mm for a 60mm diameter line), so that the contact area reaches more than 85% of the inner wall area of ​​the arc-shaped top end 801.

[0023] For branch pipes with a diameter error of ±2mm, a tapered tip 802 can be used. The tip angle is 60° and the tip is blunted (0.5mm radius). This avoids scratching the outer wall of the pipe and allows for flexible adaptation through line contact to accommodate minor changes in pipe diameter. At the same time, the guiding effect of the tapered structure can assist in the quick positioning and installation of the pipe. Under normal operating conditions, this component is fixed to the pipe through surface contact or line contact via the support end 8. Meanwhile, a vacuum is drawn in the connection space to isolate the high temperature generated by the pipe from the external environment as much as possible, forming a relatively independent space. Furthermore, the two support end 8 forms can adapt to different pipe scenarios, allowing the support end 8 to form a fixed state of line contact with the pipe. Combined with the connection space under vacuum, it is not easy to form a heat conduction path, preventing the heat generated by the pipe from spreading to surrounding components and causing temperature accumulation.

[0024] Furthermore, a flame-retardant sleeve 10 is detachably connected to the outer wall of the housing 1 via Velcro 12. The flame-retardant sleeve 10 is made of silicone rubber composite glass fiber material with a thickness of 12mm. The outer layer is a flame-retardant silicone rubber layer (temperature resistance 300℃), and the inner layer is a ceramic fiber inner cladding layer 11 (temperature resistance 800℃). The inner cladding layer 11 is bonded and fixed to the outer wall of the housing 1 with high-temperature pressure-sensitive adhesive to prevent the flame-retardant sleeve 10 from shifting under vibration. The flame-retardant sleeve 10 has an opening along the axial direction, and Velcro 12 is sewn to the two free ends of the opening. The length of the pile layer and the barbed layer of the Velcro is the same, and the overlap bonding length can be adjusted according to the outer diameter of the housing 1 (when adapting to the housing 1 with a pipe diameter of 50-80mm, the overlap length is 30-60mm). The peel strength after bonding is ≥5N / cm, which meets the requirements of quick installation and disassembly and facilitates later maintenance.

[0025] In addition, the outer surface of the flame-retardant sleeve 10 is coated with a 0.5mm thick aluminum foil reflective layer, which can reflect more than 80% of radiant heat, further reducing the heating temperature of the shell 1.

[0026] Components not described in detail in this article are existing technologies.

[0027] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. An aerospace fireproof and flame-retardant fixing mechanism assembly, comprising two housings (1), the two housings (1) being joined to form a connecting space, and pipelines being sleeved within the connecting space, characterized in that, Also includes: At least two sets of limiting members (7) are provided on the inner wall of the housing (1). Among them, the limiting member (7) is provided with a connecting channel (9) that communicates with the connecting space, and the limiting member (7) is provided with a support end (8). The end of the support end (8) forms a contact top, and the contact top abuts against the outer wall of the pipeline. Flame-retardant sleeve (10) is fitted onto the outer wall of the shell (1).

2. The aerospace fireproof and flame-retardant fixing mechanism assembly according to claim 1, characterized in that, The support end (8) includes an arc-shaped top end (801) disposed at the end of the limiting member (7), and the arc-shaped surface of the arc-shaped top end (801) forms a surface contact with the outer wall of the pipeline.

3. The aerospace fireproof and flame-retardant fixing mechanism assembly according to claim 1, characterized in that, The support end (8) includes a conical top end (802) disposed at the end of the limiting member (7), the tip of the conical top end (802) abutting against the outer wall of the pipeline.

4. An aerospace fireproof and flame-retardant fixing mechanism assembly according to claim 2 or 3, characterized in that, The length ratio of the limiting member (7) to the supporting end (8) is 3:

1.

5. The aerospace fireproof and flame-retardant fixing mechanism assembly according to claim 1, characterized in that, An end (2) is fixedly connected to the housing (1), and a connecting groove (3) is provided on the end (2), and a sealing ring (4) is provided on the connecting groove (3).

6. The aerospace fireproof and flame-retardant fixing mechanism assembly according to claim 5, characterized in that, The housing (1) has a sealing groove (5) and a sealing strip (6) is provided on the sealing groove (5). The sealing groove (5) is adapted to the connecting groove (3).

7. The aerospace fireproof and flame-retardant fixing mechanism assembly according to claim 1, characterized in that, The flame-retardant sleeve (10) has an opening, and the two ends of the opening form free ends, which are connected by Velcro (12).

8. The aerospace fireproof and flame-retardant fixing mechanism assembly according to claim 7, characterized in that, The inner wall of the flame-retardant sleeve (10) is provided with an inner cladding layer (11).

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