CN210503156U

CN210503156U - Super high temperature resistant heat protection structure and aircraft thereof

Info

Publication number: CN210503156U
Application number: CN201921038436.4U
Authority: CN
Inventors: 杨斌; 高庆福; 熊熙; 李勇
Original assignee: Hunan Ronglan Intelligent Technology Co ltd
Current assignee: Hunan Ronglan Intelligent Technology Co ltd
Priority date: 2019-07-05
Filing date: 2019-07-05
Publication date: 2020-05-12
Anticipated expiration: 2029-07-05

Abstract

The utility model provides a super high temperature resistant thermal protection structure and an aircraft thereof, wherein the thermal protection structure is a composite layer structure and comprises a protection layer, an aircraft shell and a thermal insulation layer; the insulation layer is arranged between the protective layer and the aircraft shell; the protective layer is made of a silicon carbide plate with the thickness of 3-5 mm, the heat insulation layer is made of an alumina aerogel heat insulation composite material with the thickness of 7-12 mm, and the aircraft shell is made of an alloy plate with the thickness of 2-5 mm. The utility model provides a hot protective structure of resistant super high temperature and aircraft thereof can effectively be applied to ultra-high temperature (1800 ℃) and harsh hot gas flow and erode the environment.

Description

Super high temperature resistant heat protection structure and aircraft thereof

Technical Field

The utility model relates to an aircraft thermal protection technical field specifically is a hot protective structure of resistant super high temperature and aircraft thereof.

Background

The front edge part of the ultra-high speed aircraft and the engine nozzle can be subjected to severe aerodynamic heating in the working process, and the maximum temperature of the local surface exceeds 1800 ℃. In order to ensure that the aircraft is stable in ultra-high temperature long-time working state, the metal cabin body is heated to deform, the mechanical property is within a safety margin, and a high-efficiency thermal protection structure is required to be installed on the surface of the metal cabin section of the aircraft, so that the metal cabin section always works within the safe alloy use range. The traditional ultra-high temperature thermal protection structure mainly comprises a heat-proof layer (silicon carbide and graphite), a heat-insulating layer (carbon felt, ceramic fiber felt and glass fiber), a reflecting layer (carbon paper and a metal layer) and the like. The heat insulation effect is poor, the hot surface temperature of the hot protective structure is 1800 ℃, and when the thickness is 40mm, the cold surface temperature reaches 1100 ℃ in 600 seconds.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an ultra-temperature resistant hot protective structure can effectively be applied to ultra-temperature (1800 ℃), harsh hot gas flow erodees the environment.

In order to solve the above problem, the utility model adopts the technical scheme that:

the utility model provides an ultra-high temperature resistant thermal protection structure, which is a composite layer structure and comprises a protection layer, an aircraft shell and a thermal insulation layer; the insulation layer is arranged between the protective layer and the aircraft shell; the protective layer is made of a silicon carbide plate with the thickness of 3-5 mm, the heat insulation layer is made of an alumina aerogel heat insulation composite material with the thickness of 7-12 mm, and the aircraft shell is made of an alloy plate with the thickness of 2-5 mm; the thickness of the protective layer and the thermal insulation layer of the thermal protection structure is 14-17 mm.

Optionally, the protective layer is a 4mm silicon carbide plate, the thermal insulation layer is a 10mm alumina aerogel thermal insulation composite material, and the aircraft shell is a 3mm alloy plate.

Optionally, the protective layer adopts a 4mm silicon carbide plate, the thermal insulation layer adopts a 12mm alumina aerogel thermal insulation composite material, and the aircraft shell adopts a 3mm alloy plate.

Optionally, the silicon carbide plate is replaced by a graphite plate with the thickness of 2-3 mm.

Optionally, 1-2 mm carbon cloth is arranged between the graphite plate and the alumina aerogel heat insulation composite material, and the thickness of a protective layer, a heat insulation layer and the carbon cloth of the heat protection structure is 14-17 mm.

Optionally, the protective layer adopts a 3mm graphite plate, the thermal insulation layer adopts a 10mm alumina aerogel thermal insulation composite material, the aircraft shell adopts a 3mm alloy plate, and 1mm carbon cloth is arranged between the graphite plate and the alumina aerogel thermal insulation composite material.

The utility model also provides an aircraft, including the aforesaid hot protective structure.

The beneficial effects of the utility model reside in that:

1. the utility model discloses compound silicon carbide and the thermal-insulated combined material of aluminium oxide aerogel, make composite construction, can effectively reduce hot protective structure density to 0.6g/cm³The effect of reducing weight and increasing range is achieved.

2. The utility model discloses a hot protective structure only needs inoxidizing coating and insulating layer and carbon cloth thickness to reach 14 ~ 17mm and can fall the cold side temperature to below 1000 ℃ under the circumstances of outside 1800 ℃, and thickness can fall its cold side temperature to below 800 ℃ at 16 ~ 17mm, and the space of aircraft has been saved greatly to the thickness attenuate, and the lower temperature of cold side has improved the selection range of high temperature alloy board simultaneously.

3. The utility model discloses an aircraft ultra-high temperature thermal protection structure's thin walled, lightweight can improve the mobility and the flight time of aircraft, and the service temperature of this kind of structure superalloy board reduces simultaneously, reduces the manufacturing cost of whole aircraft.

4. The utility model provides an ultra-high temperature resistant hot protective structure can effectively be applied to long term (600 seconds), ultra-high temperature (1800 ℃), harsh hot gas flow erodees the environment. The utility model discloses can also alleviate hot protective structure weight of aircraft, the hot protective structure thickness of attenuate, improve the design safety margin of aircraft, enlarge orbit motion range.

Drawings

Fig. 1 is a schematic view of an ultra-high temperature resistant thermal protection structure provided by an embodiment of the present invention;

fig. 2 is a schematic view of another ultra-high temperature resistant thermal protection structure provided by an embodiment of the present invention;

fig. 3 is a schematic view of an experimental result after the thermal protection structure protective layer is heated and examined.

Reference numerals:

1, graphite plates; 2, an alumina aerogel heat-insulating composite material; 3 alloy plate; 4 carbon cloth; 5 a silicon carbide plate.

Detailed Description

The conception, specific structure, and technical effects of the present invention will be described clearly and completely with reference to the following embodiments, so that the objects, features, and effects of the present invention can be fully understood. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and other embodiments obtained by those skilled in the art without inventive labor based on the embodiments of the present invention all belong to the protection scope of the present invention.

Example 1

The embodiment 1 of the utility model provides an ultra-high temperature resistant thermal protection structure, which is a composite layer structure and comprises a protection layer, an aircraft shell and a thermal insulation layer; the insulation layer is arranged between the protective layer and the aircraft shell;

the protective layer is a 4mm silicon carbide plate 5, the thermal insulation layer is a 10mm alumina aerogel thermal insulation composite material 2, and the aircraft shell is a 3mm alloy plate 3. As shown in fig. 2.

Example 2

The embodiment 2 of the utility model provides a hot protective structure of super high temperature resistance, in this embodiment, the inoxidizing coating adopts 3 mm's graphite cake 1, the insulating layer adopts 10 mm's alumina aerogel thermal-insulated combined material 2, the aircraft casing adopts 3 mm's alloy board, graphite cake 1 with be provided with 1 mm's carbon cloth 4 between the alumina aerogel thermal-insulated combined material 2. As shown in fig. 1.

The other structures are the same as those of embodiment 1, and are not described herein again.

Example 3

The embodiment 3 of the utility model provides a hot protective structure of super high temperature resistance, the inoxidizing coating adopts 4mm carborundum board 5, the insulating layer adopts 12mm aluminium oxide aerogel thermal-insulated combined material 2, the aircraft casing adopts 3mm alloy plate 3. As shown in fig. 2.

It should be noted that in embodiments 1-3 of the present invention, the alumina aerogel thermal insulation composite 2 can be made of high temperature resistant alumina aerogel thermal insulation composite made by patent CN101041770A (patent No. 200710034510.0, patent name: a high temperature resistant alumina aerogel thermal insulation composite and its preparation method); the density of the alumina aerogel heat-insulation composite material 2 is 0.29-0.35 g/cm³And can resist temperature of 1500 ℃.

The silicon carbide plate 5 may be a carbon fiber-reinforced silicon carbide composite material obtained by the method disclosed in patent No. CN102249721B (patent No. CN102249721B, patent name: method for producing carbon fiber-reinforced silicon carbide composite material).

The graphite plate 1 can be made of graphite in the prior art, and the carbon cloth 4 can be made of carbon fiber cloth in the prior art.

The alloy plate 3 is usually made of a high-temperature alloy, and typically made of a titanium alloy, a nickel alloy, or the like, such as: alloy materials of GH220, GH128, GH131, K4169, FGH95 and the like can be adopted.

Example 4

An embodiment of the utility model provides an aircraft, aircraft includes the resistant ultra-high temperature's of above-mentioned arbitrary hot protective structure.

In order to verify the utility model discloses hot protective structure's validity, its verification method is: the test is carried out for 600 seconds at 1800 ℃, and the test mode is that a protective layer heat-proof layer of the heat protection structure is directly ablated by oxyacetylene flame. The oxygen-acetylene high-temperature flame is generated by controlling the flow rate and pressure of oxygen and the flow rate and pressure of acetylene, and the examination time is 600 seconds. In the checking process, the surface temperature of the heat-proof layer of the heat protection structure (the temperature measuring range of the infrared thermometer is between room temperature and 2500 ℃) and the surface temperature of the aircraft shell (the temperature is measured by a thermocouple, and the temperature is between room temperature and 1200 ℃) are measured. The surface temperature of the protective layer is the hot surface temperature, and the surface temperature of the aircraft shell (alloy plate) is the cold surface temperature.

Will the utility model discloses embodiment 3's hot protective structure adopts above-mentioned examination mode to heat the examination, produces the high temperature air current that exceeds 1800 ℃ in inoxidizing coating surface department. The hot face temperature of its protective coating was then measured, as well as the cold face temperature of the aircraft shell (alloy plate), and the results are shown in fig. 3.

The embodiment 3 of the utility model provides a hot protective structure, inoxidizing coating and insulating layer thickness are 16mm,1800 ℃ examination 600 seconds, and alloy plate 3's cold surface temperature 748 ℃, thermal-insulated efficiency is showing and is promoting.

The embodiment 1 of the utility model provides a hot protective structure, inoxidizing coating and thermal-insulated layer thickness are 14mm,1800 ℃ examination 600 seconds, and alloy plate 3's cold surface temperature (890 ℃), thermal-insulated efficiency is showing and is promoting.

The embodiment 2 of the utility model provides a hot protective structure, inoxidizing coating and insulating layer to and carbon cloth thickness is 14mm,1800 ℃ examination 600 seconds, and alloy plate 3's cold surface temperature (950 ℃), thermal-insulated efficiency is showing and is promoting.

It should be noted that, throughout the specification, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

The principles and embodiments of the present invention have been explained herein using specific examples, which are presented only to assist in understanding the methods and their core concepts. It should be noted that there are infinite trial ways due to the limited character expression, and those skilled in the art can make some improvements, decorations or changes without departing from the principle of the present invention, and can also combine the above technical features in a proper way; the application of these modifications, variations or combinations, or the application of the concepts and solutions of the present invention in other contexts without modification, is not intended to be considered as a limitation of the present invention.

Claims

1. The ultra-high temperature resistant thermal protection structure is characterized in that the thermal protection structure is a composite layer structure and comprises a protection layer, an aircraft shell and a thermal insulation layer; the insulation layer is arranged between the protective layer and the aircraft shell;

the protective layer is made of a silicon carbide plate (5) with the thickness of 3-5 mm, the heat insulation layer is made of an alumina aerogel heat insulation composite material (2) with the thickness of 7-12 mm, and the aircraft shell is made of an alloy plate (3) with the thickness of 2-5 mm;

the thickness of the protective layer and the thermal insulation layer of the thermal protection structure is 14-17 mm.

2. The thermal protection structure according to claim 1, characterized in that said protective layer is a 4mm silicon carbide plate (5), said insulation layer is a 10mm alumina aerogel insulation composite (2), and said aircraft shell is a 3mm alloy plate (3).

3. The thermal protection structure according to claim 1, characterized in that said protective layer is made of 4mm silicon carbide plates (5), said thermal insulation layer is made of 12mm alumina aerogel thermal insulation composite (2), and said aircraft shell is made of 3mm alloy plates (3).

4. The thermal protection structure according to claim 1, characterized in that said silicon carbide plates (5) are replaced by graphite plates (1) of 2-3 mm.

5. The thermal protection structure according to claim 4, characterized in that 1-2 mm carbon cloth (4) is arranged between the graphite plate (1) and the alumina aerogel thermal insulation composite material (2), and the thickness of the protective layer, the thermal insulation layer and the carbon cloth (4) of the thermal protection structure is 14-17 mm.

6. The thermal protection structure according to claim 5, characterized in that said protective layer is made of 3mm graphite plates (1), said thermal insulation layer is made of 10mm alumina aerogel thermal insulation composite (2), said aircraft shell is made of 3mm alloy plates (3), and 1mm carbon cloth (4) is arranged between said graphite plates (1) and said alumina aerogel thermal insulation composite (2).

7. An aircraft, characterized in that it comprises a thermal protection structure according to any one of claims 1 to 6.