CN113955077A

CN113955077A - A supersonic aircraft head surface heat insulation structure

Info

Publication number: CN113955077A
Application number: CN202111299914.9A
Authority: CN
Inventors: 肖珊珊; 潘剑锋; 王继坤; 范宝伟
Original assignee: Jiangsu University
Current assignee: Jiangsu University
Priority date: 2021-11-04
Filing date: 2021-11-04
Publication date: 2022-01-21
Anticipated expiration: 2041-11-04
Also published as: CN113955077B

Abstract

The invention provides a hypersonic aircraft head surface heat insulation structure which comprises an outer surface lead structure layer and a honeycomb heat insulation layer, wherein the honeycomb heat insulation layer is connected with the surface of an aircraft head; the outer surface lead structure layer comprises a honeycomb framework and a lead layer, the lead layer covers the honeycomb of the honeycomb framework, and when the lead layer is melted, the lead layer can flow out along the channel honeycomb; the honeycomb framework is connected with the honeycomb heat insulation layer. The invention ensures that the thermal insulation layer on the surface of the hypersonic aircraft head has better thermal insulation effect.

Description

Super high sound speed aircraft head surface heat insulation structure

Technical Field

The invention relates to the technical field of aircraft heat insulation, in particular to a hypersonic aircraft head surface heat insulation structure.

Background

Hypersonic aircraft are relatively common nowadays, but the temperature of the head can rise to 1500-2000 ℃ instantaneously during the flight process, so that the heat insulation of the head is particularly important in order to protect the head structure and internal instruments of the aircraft and ensure the normal flight. At present, the use of a high-temperature-resistant heat insulation layer is common, but the heat insulation layer still has a space for optimizing and improving, so that the heat insulation layer has a better heat insulation effect.

At present, what a good insulating layer adopted is a honeycomb, and on high temperature resistant thermal insulation material's basis, honeycomb makes during air gets into the hole, has increased heat conduction thermal resistance for he has reached better thermal-insulated effect. At present, the heat insulation material applied to the field of high-temperature aviation is generally zirconium diboride, and the material can resist the high temperature of 3246 ℃, and has the characteristics of high strength at normal temperature and high temperature, good thermal shock resistance, small resistance, oxidation resistance at high temperature and the like. However, the existing insulation layers have the disadvantage that if new insulation strength is required, a new high temperature resistant material is required. And the ease of processing into honeycomb structures, as well as the cost, must be considered. The insulation structure needs to be optimized.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides the hypersonic aircraft head surface heat insulation structure, so that the hypersonic aircraft head surface heat insulation layer has a better heat insulation effect.

The present invention achieves the above-described object by the following technical means.

The hypersonic aircraft head surface heat insulation structure comprises an outer surface lead structure layer and a honeycomb heat insulation layer, wherein the honeycomb heat insulation layer is connected with the surface of the aircraft head; the outer surface lead structure layer comprises a honeycomb framework and a lead layer, the lead layer covers the honeycomb of the honeycomb framework, and when the lead layer is melted, the lead layer can flow out along the channel honeycomb; the honeycomb framework is connected with the honeycomb heat insulation layer.

Further, the honeycomb heat-insulating layer comprises a honeycomb inner core, a honeycomb heat-insulating layer lower panel, an outer side sealing layer and a honeycomb heat-insulating layer upper panel; the honeycomb inner core is hermetically wrapped by a lower honeycomb heat-insulating layer panel, an outer side sealing layer and an upper honeycomb heat-insulating layer panel; the lower panel of the honeycomb thermal insulation layer is bonded with the surface of the head of the aircraft through an epoxy polyamide adhesive; the lower surface of the honeycomb framework is bonded with the upper panel of the honeycomb heat-insulating layer through an epoxy polyamide adhesive.

Furthermore, the honeycomb inner core is formed by closely arranging a plurality of hexahedral core grids to form densely-distributed cavities.

Further, the side length of a core lattice of the honeycomb inner core is 6-10 mm, and the thickness of the honeycomb inner core is 200-300 mm.

Further, the material of the honeycomb inner core is zirconium diboride.

Further, the core lattices of the honeycomb inner core are filled with heat insulating materials.

Further, the material of the honeycomb framework is C/SiC.

Furthermore, the honeycomb framework is formed by closely arranging a plurality of hexahedral core grids to form densely-distributed cavities, a lead layer covers the cavities, and the side length of the core grids of the honeycomb framework is 4-6 mm.

The invention has the beneficial effects that:

according to the hypersonic aircraft head surface heat insulation structure, in the process of hypersonic aircraft flying, the surface rubs with the atmosphere to generate a large amount of heat, the temperature of the head can be instantly raised to 1500-2000 ℃, the deformation of the aircraft head caused by high temperature often can affect the stability and safety of the aircraft to a certain degree, in order to avoid the situation, the head heat insulation layer is optimized, a layer of lead is attached to the original honeycomb type heat insulation layer, and the boiling point of the lead is 1740 ℃. In the flying process of the aircraft, the high temperature of the head enables the lead to be sublimated instantly, and a large amount of heat can be taken away by sublimation, so that the heat insulation effect is greatly enhanced. Lead is embedded into the C/SiC honeycomb framework, so that the melted lead is ensured to flow out along the grooves, and the flying is not influenced by splashing everywhere.

Drawings

FIG. 1 is a cross-sectional view of a hypersonic aircraft head surface insulation structure in accordance with the present invention.

Fig. 2 is a schematic view of a honeycomb core according to the present invention.

In the figure:

1-a honeycomb framework; 2-epoxy polyamide adhesive; 3-a honeycomb inner core; 4-a honeycomb thermal insulation layer; 5-honeycomb thermal insulation layer lower panel; 6-outer sealing layer; 7-honeycomb thermal insulation layer upper panel; 9-lead layer.

Detailed Description

The invention will be further described with reference to the following figures and specific examples, but the scope of the invention is not limited thereto.

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "axial," "radial," "vertical," "horizontal," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present invention and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

As shown in fig. 1 and 2, the hypersonic aircraft head surface thermal insulation structure comprises an outer surface lead structural layer and a honeycomb thermal insulation layer 4, wherein the honeycomb thermal insulation layer 4 is connected with the surface of the aircraft head; the outer surface lead structure layer comprises a honeycomb framework 1 and a lead layer 9, the lead layer 9 covers the honeycomb of the honeycomb framework 1, and when the lead layer 9 is melted, the lead layer can flow out along the honeycomb, so that the melted lead is prevented from splashing around to influence flight; the honeycomb framework 1 is connected with the honeycomb heat insulation layer 4. The material of the honeycomb framework 1 is C/SiC. The honeycomb framework 1 is formed by densely arranging a plurality of hexahedral core grids to form a densely-distributed cavity, a lead layer 9 covers the cavity, and the side length of the core grids of the honeycomb framework 1 is 4-6 mm.

The honeycomb heat insulation layer 4 comprises a honeycomb inner core 3, a honeycomb heat insulation layer lower panel 5, an outer side sealing layer 6 and a honeycomb heat insulation layer upper panel 7; the honeycomb inner core 3 is hermetically wrapped by a honeycomb heat-insulating layer lower panel 5, an outer side sealing layer 6 and a honeycomb heat-insulating layer upper panel 7; the lower panel 5 of the honeycomb thermal insulation layer is bonded with the surface of the head of the aircraft through an epoxy polyamide adhesive 2; the lower surface of the honeycomb framework 1 is bonded with the honeycomb heat-insulating layer upper panel 7 through the epoxy polyamide adhesive 2. The honeycomb inner core 3 is formed by closely arranging a plurality of hexahedral core grids to form a densely-distributed cavity. The side length of the core lattice of the honeycomb inner core 3 is 6-10 mm, and the thickness of the honeycomb inner core 3 is 200-300 mm. The material of the honeycomb inner core 3 is zirconium diboride. The core lattice of the honeycomb inner core 3 can be filled with heat insulation materials, so that heat insulation can be further realized.

The working principle is as follows:

the invention takes away the pneumatic heat mainly according to the change of the state of the metal lead. When the flying speed of the aircraft is low, the temperature of the head of the aircraft is lower than the melting point temperature of lead, the thermal load of the head of the aircraft is small, the stability of the aircraft cannot be influenced, and the heat insulation structure can meet the heat insulation requirement of the head of the aircraft; when the aircraft flies at a high speed, the temperature of the head of the aircraft is higher than the melting point temperature of lead and lower than the boiling point temperature of lead, at the moment, the lead in the honeycomb heat insulation layer absorbs heat and melts, and the molten lead flows out through the honeycomb channel to take away heat, so that the function of cooling the head of the aircraft is realized; when the aircraft flies at ultrahigh sound speed, the temperature of the head of the aircraft rises instantly, the lead is converted from a solid state to a gaseous state to absorb a large amount of heat, the gaseous lead flows out through the honeycomb runner, and a large amount of heat generated by friction with air is taken away, so that the temperature of the surface 7 is reduced, and the heat insulation pressure is reduced. Meanwhile, in consideration of the fact that liquid lead melted by the lead layer can flow into gaps of the honeycomb structure and influence the heat insulation effect of the heat insulation layer, the outer side sealing layer 6 is added on the basis of the honeycomb inner core 3, and the outer side sealing layer 6 is bonded with the honeycomb inner core 3 through the epoxy polyamide adhesive 2. In order to prevent the molten lead from splashing around, the lead layer 9 is fixed by the C/SiC honeycomb framework 1, and the molten lead liquid flows out along the honeycomb.

It should be understood that although the present description has been described in terms of various embodiments, not every embodiment includes only a single embodiment, and such description is for clarity purposes only, and those skilled in the art will recognize that the embodiments described herein may be combined as suitable to form other embodiments, as will be appreciated by those skilled in the art.

The above-listed detailed description is only a specific description of a possible embodiment of the present invention, and they are not intended to limit the scope of the present invention, and equivalent embodiments or modifications made without departing from the technical spirit of the present invention should be included in the scope of the present invention.

Claims

1. a supersonic aircraft head surface heat insulation structure, is characterized in that, comprises outer surface lead structure layer and honeycomb heat insulation layer (4), and described honeycomb heat insulation layer (4) is connected with aircraft head surface; The outer surface lead structure layer includes a honeycomb skeleton (1) and a lead layer (9). outflow; the honeycomb skeleton (1) is connected with the honeycomb thermal insulation layer (4).

2. The supersonic aircraft head surface heat insulation structure according to claim 1, wherein the honeycomb heat insulation layer (4) comprises a honeycomb inner core (3) and a honeycomb heat insulation layer lower panel (5) , the outer sealing layer (6) and the upper panel (7) of the honeycomb heat insulation layer; the honeycomb inner core (3) is covered by the lower panel (5) of the honeycomb heat insulation layer, the outer sealing layer (6) and the upper panel of the honeycomb heat insulation layer (7) Sealing and wrapping; the lower panel (5) of the honeycomb heat insulation layer and the surface of the aircraft head are bonded by an epoxy polyamide adhesive (2); the lower surface of the honeycomb skeleton (1) is insulated from the honeycomb The upper panel (7) is bonded by epoxy polyamide adhesive (2).

3 . The surface heat insulation structure of the head of a hypersonic aircraft according to claim 2 , wherein the honeycomb inner core ( 3 ) consists of a number of hexahedral core cells that are closely arranged to form dense cavities. 4 .

4 . The surface heat insulation structure of the head of a hypersonic aircraft according to claim 3 , wherein the honeycomb inner core ( 3 ) has a core lattice side length of 6 to 10 mm, and the honeycomb inner core ( 3 ) Thickness 200 ~ 300mm.

5 . The surface heat insulation structure of the head of a hypersonic aircraft according to claim 2 , wherein the core cells of the honeycomb inner core ( 3 ) are filled with heat insulation material. 6 .

6 . The surface heat insulation structure of the supersonic aircraft head according to claim 2 , wherein the material of the honeycomb inner core ( 3 ) is zirconium diboride. 7 .

7 . The surface heat insulation structure of the head of a hypersonic aircraft according to claim 1 , wherein the material of the honeycomb skeleton ( 1 ) is C/SiC. 8 .

8 . The surface heat insulation structure of the head of a hypersonic aircraft according to claim 1 , wherein the honeycomb skeleton ( 1 ) is composed of several hexahedral cores closely arranged to form a dense cavity, and the cavity is covered with A lead layer (9) is provided, and the side length of the core lattice of the honeycomb skeleton (1) is 4-6 mm.