CN213138084U

CN213138084U - Fireproof structure

Info

Publication number: CN213138084U
Application number: CN202021234117.3U
Authority: CN
Inventors: 许良
Original assignee: Shenzhen Fuxiang Aviation Technology Co ltd
Current assignee: Shenzhen Fuxiang Aviation Technology Co ltd
Priority date: 2020-06-29
Filing date: 2020-06-29
Publication date: 2021-05-07
Anticipated expiration: 2030-06-29

Abstract

A fireproof structure comprises a fireproof layer, a metal layer and a heat insulation layer, wherein the fireproof layer comprises a first carbon fiber layer, a second carbon fiber layer and a porous material layer, the fireproof layer is provided with a first part and a second part, the two second parts are respectively positioned on two opposite sides of the first part, the first part is provided with the first carbon fiber layer and the second carbon fiber layer which are sequentially laminated, and the second part is provided with the first carbon fiber layer, the porous material layer and the second carbon fiber layer which are sequentially laminated; the heat insulation layer is arranged between the fire-proof layer and the metal layer, and the fire-proof structure is composed of a multi-layer structure and has the characteristics of high temperature resistance and light weight.

Description

Fireproof structure

Technical Field

The utility model relates to a fireproof structure of a light airplane; in particular to a fireproof structure arranged between an engine compartment and a cab.

Background

The engine of the light aircraft is known to provide the flight power of the light aircraft, and because the engine of the light aircraft is easy to generate high temperature during operation, in order to ensure the safety of other equipment at the rear of the engine compartment and personnel in the cockpit of the light aircraft, the engine is generally arranged in the engine compartment separated from the cockpit.

In addition, a fire-proof structure is required to be disposed between the engine compartment and the cockpit for effectively isolating a heat source and further ensuring flight safety, the fire-proof structure is made of a material having high temperature resistance, and generally has a light weight characteristic so as not to increase the load of the light aircraft, and the use of the fire-proof structure at present cannot meet the requirements of the light aircraft on safety and light weight. Therefore, the existing fire-proof structure still needs to be improved.

SUMMERY OF THE UTILITY MODEL

In view of the above, an object of the present invention is to provide a fireproof structure, which has the characteristics of high temperature resistance and light weight.

In order to achieve the above object, the present invention provides a fire protection structure for a light aircraft, the light aircraft has a cabin and an engine compartment, the fire protection structure is disposed between the cabin and the engine compartment to separate the cabin and the engine compartment, it is characterized in that the fireproof structure comprises a fireproof layer, a metal layer and a heat insulation layer, the fireproof layer comprises a first carbon fiber layer, a second carbon fiber layer and a porous material layer, the fire-proof layer is provided with a first part and two second parts which are respectively positioned at two opposite sides of the first part, the first part has the first carbon fiber layer and the second carbon fiber layer laminated in this order, the second part has the first carbon fiber layer, the porous material layer and the second carbon fiber layer laminated in this order; the heat insulation layer is arranged between the fireproof layer and the metal layer.

According to the above concept, the fire-proof layer includes a third carbon fiber layer disposed on the first portion, and the first portion has the first carbon fiber layer, the second carbon fiber layer and the third carbon fiber layer stacked one on another.

According to the above concept, the lightweight aircraft includes an engine mount, the fire protection structure has a plurality of mounting holes for mounting the engine mount, and the plurality of mounting holes penetrate the first portion of the fire protection layer, the thermal insulation layer, and the metal layer.

According to the above concept, the first carbon fiber layer, the second carbon fiber layer and the third carbon fiber layer respectively comprise a carbon fiber prepreg.

According to the above concept, the weight per unit area of the carbon fiber prepreg is 150g/m or more²And not more than 200g/m²。

According to the above concept, the thicknesses of the first carbon fiber layer, the second carbon fiber layer and the third carbon fiber layer respectively satisfy the condition of being greater than or equal to 0.4mm and less than or equal to 1.0 mm.

According to the above concept, the porous material layer comprises a foamed sheet or a hollow honeycomb sheet, and the maximum thickness of the porous material layer is greater than or equal to 2mm and less than or equal to 4 mm.

According to the above concept, the thermal insulation layer comprises a cork material with resin, and the thickness of the thermal insulation layer is greater than or equal to 12mm and less than or equal to 20 mm.

According to the above concept, the density of the thermal insulation layer is greater than or equal to 140Kg/cm³。

According to the above concept, the longitudinal section of the porous material layer of each of the second portions of the fire-retardant layer is trapezoidal.

The utility model has the advantages of, fire resistive construction comprises multilayer structure, has high temperature resistant and lightweight characteristic concurrently.

Drawings

Fig. 1 is a perspective view of a fire protection structure according to a preferred embodiment of the present invention.

FIG. 2 is a schematic side view of the fire protection structure of the preferred embodiment.

Fig. 3(a), 3(b), 3(c), and 3(d) are schematic views of the flame retardant layer according to the preferred embodiment.

FIG. 4 is a sectional view taken along line A-A of FIG. 3 (a).

FIG. 5 is a sectional view taken along line B-B of FIG. 3 (B).

FIG. 6 is a schematic top view of the fire protection structure of the preferred embodiment.

Fig. 7 is a perspective view of the fire protection structure of the preferred embodiment.

Description of the reference numerals

[ the utility model ]

1: fireproof structure

1 a: mounting hole

10: fire-proof layer

102: first carbon fiber layer

104: second carbon fiber layer

106: third carbon fiber layer

108: porous material layer

20: thermal insulation layer

30: metal layer

A1: the first part

A2: the second part

2: light airplane

3: die set

4: engine mount

R: cabin

Detailed Description

In order to explain the present invention more clearly, the following detailed description will be given with reference to the accompanying drawings. Referring to fig. 1 to 7, a fire protection structure 1 according to a preferred embodiment of the present invention is used for a light aircraft 2, the light aircraft 2 has a cabin R and an engine compartment (not shown), the fire protection structure is disposed between the cabin R and the engine compartment to separate the cabin R and the engine compartment, and the engine compartment is provided with an engine (not shown), and the fire protection structure 1 includes a fire protection layer 10, a thermal insulation layer 20 and a metal layer 30, as shown in fig. 2, the thermal insulation layer 20 is disposed between the fire protection layer 10 and the metal layer 30.

The fire-proof layer 10 comprises a first carbon fiber layer 102, a second carbon fiber layer 104, a third carbon fiber layer 106 and a porous material layer 108, the fire-proof layer 10 is provided with a first part A1 and two second parts A2, the two second parts A2 are respectively positioned at two opposite sides of the first part A1, the first part A1 is provided with the first carbon fiber layer 102, the second carbon fiber layer 104 and the third carbon fiber layer 106 which are sequentially stacked, and the second part A2 is provided with the first carbon fiber layer 102, the porous material layer 108 and the second carbon fiber layer 104 which are sequentially stacked.

In this embodiment, as shown in fig. 3(a), 3(b), 3(c), and 3(d), the fire-retardant layer 10 is laminated in the order of first providing the first carbon fiber layer 102 on a mold 3 (see fig. 4), then providing the porous material layer 108 on each of the second portions a2 to cover the first carbon fiber layer 102, then providing the second carbon fiber layer 104 to cover the first carbon fiber layer 102 and the porous material layer 108, and finally providing the third carbon fiber layer 106 on the first portion a1 to cover the second carbon fiber layer 104. It is worth mentioning that, as shown in fig. 5, the longitudinal section of the porous material layer 108 of each second portion a2 of the fire-retardant layer 10 is trapezoidal.

Wherein the first carbon fiber layer 102, the second carbon fiber layer 104 and the third carbon fiber layer 106 respectively comprise a carbon fiber prepreg, and the fiber unit area weight of the carbon fiber prepreg is greater than or equal to 150g/m²And not more than 200g/m²In this embodiment, the thicknesses of the first carbon fiber layer 102, the second carbon fiber layer 104 and the third carbon fiber layer 106 are 0.7mm as an example, and in practice, the thicknesses of the first carbon fiber layer 102, the second carbon fiber layer 104 and the third carbon fiber layer 106 may be different from each other.

The porous material layer 108 comprises a foamed sheet or a hollow honeycomb sheet, such as

Series of PVC foaming materials. The maximum thickness of the porous material layer 108 is equal to or greater than 2mm and equal to or less than 4mm, and in the present embodiment, the maximum thickness of the porous material layer 108 is illustrated as 3 mm.

The thermal insulation layer 20 comprises a cork material with resin, the thickness of the thermal insulation layer 20 is greater than or equal to 12mm and less than or equal to 20mm, and the density of the thermal insulation layer 20 is greater than or equal to 140Kg/cm³In the present embodiment, the thermal insulation layer 20 is illustrated by CORE cock NL10, and the density thereof is equal to 140Kg/cm³In other embodiments, it is not excluded that the thermal insulation layer 20 is made of other materials, for example, the thermal insulation layer 20 may be made of CORK material of CORE corrk NL11 or may be made of two or more different materials. In this embodiment, the metal layer 30 is a titanium alloy metal plate with a thickness of 0.4mm, but in other embodiments, it is not excluded that the metal layer 30 can be a metal plate made of stainless steel or other materials, for example.

Referring to fig. 6 and 7, the light aircraft 2 includes an engine frame 4, the engine frame 4 is used for connecting the engine, the fire protection structure 1 has a plurality of mounting holes 1a for mounting the engine frame 4, and the mounting holes 1a penetrate through the first carbon fiber layer 102, the second carbon fiber layer 104 and the third carbon fiber layer 106 of the first portion a1 of the fire protection layer 10, the thermal insulation layer 20 and the metal layer 30.

In summary, the multi-layer structure of the fire-proof structure 1 can achieve the effects of high temperature resistance and light weight, and can not only meet the requirements of light aircraft on safety performance, but also achieve the technical requirements of load reduction.

The above description is only a preferred embodiment of the present invention, and all equivalent changes and modifications to the application of the present invention and the claims should be considered to be included in the scope of the present invention.

Claims

1. A fire protection structure for a light aircraft having a cabin and an engine compartment, said fire protection structure being disposed between said cabin and said engine compartment to separate said cabin from said engine compartment,

the fire protection structure comprises:

a fire barrier layer;

a metal layer; and

the heat insulation layer is arranged between the fire-proof layer and the metal layer;

the fireproof layer comprises a first carbon fiber layer, a second carbon fiber layer and a porous material layer, the fireproof layer is provided with a first portion and two second portions, the two second portions are located on two opposite sides of the first portion respectively, the first portion is provided with the first carbon fiber layer and the second carbon fiber layer which are sequentially stacked, and the second portion is provided with the first carbon fiber layer, the porous material layer and the second carbon fiber layer which are sequentially stacked.

2. The fire protection structure of claim 1, wherein said fire protection layer comprises a third carbon fiber layer disposed on said first portion, said first portion having said first carbon fiber layer, said second carbon fiber layer and said third carbon fiber layer stacked one on another.

3. A fire protection architecture as claimed in claim 1, wherein said lightweight aircraft includes an engine mount, said fire protection architecture having a plurality of mounting holes for mounting said engine mount, said plurality of mounting holes extending through said first portion of said fire protection layer, said insulating layer and said metal layer.

4. The fire protection structure of claim 2, wherein each of said first carbon fiber layer, said second carbon fiber layer and said third carbon fiber layer comprises a carbon fiber prepreg.

5. The fire protection structure of claim 4, wherein said carbon fiber prepreg has a fiber basis weight of 150g/m or more²And not more than 200g/m²。

6. The fire protection structure of claim 5, wherein the thicknesses of the first carbon fiber layer, the second carbon fiber layer and the third carbon fiber layer respectively satisfy the condition of 0.4mm or more and 1.0mm or less.

7. The fire protection structure of claim 1, wherein said porous material layer comprises a foamed sheet or a hollow honeycomb sheet, and a maximum thickness of said porous material layer is greater than or equal to 2mm and less than or equal to 4 mm.

8. The fire protection structure of claim 1, wherein said insulation layer comprises a cork material with resin, said insulation layer having a thickness of 12mm or more and 20mm or less.

9. Fire protection architecture as claimed in claim 8, characterized in that said insulating layer has a density equal to or greater than 140Kg/cm 3.

10. A fire-barrier construction as claimed in claim 1, wherein the longitudinal cross-section of the porous material layer in each of the second portions of the fire-barrier layer is trapezoidal.