CN110524974B - Prevent thermal-insulated integrative hot protective structure suitable for negative curvature appearance - Google Patents

Prevent thermal-insulated integrative hot protective structure suitable for negative curvature appearance Download PDF

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CN110524974B
CN110524974B CN201910942135.2A CN201910942135A CN110524974B CN 110524974 B CN110524974 B CN 110524974B CN 201910942135 A CN201910942135 A CN 201910942135A CN 110524974 B CN110524974 B CN 110524974B
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layer
heat
thermal
thermal protection
proof
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CN110524974A (en
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范开春
胡善刚
陈兴峰
王辉
郭辉荣
林雪峰
杨攀
程昌
王盛龙
朱璇
马治
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General Designing Institute of Hubei Space Technology Academy
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General Designing Institute of Hubei Space Technology Academy
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/06—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by a fibrous or filamentary layer mechanically connected, e.g. by needling to another layer, e.g. of fibres, of paper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/18—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by features of a layer of foamed material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/245—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it being a foam layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
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    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/40—Sound or heat insulation, e.g. using insulation blankets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C30/00—Supersonic type aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2266/00—Composition of foam
    • B32B2266/12—Gel
    • B32B2266/126—Aerogel, i.e. a supercritically dried gel
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/306—Resistant to heat

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  • Aviation & Aerospace Engineering (AREA)
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Abstract

The invention discloses an anti-heat insulation integrated thermal protection structure suitable for a negative curvature shape, and belongs to the technical field of thermal protection of hypersonic proximity space vehicles. The method comprises the following steps: a force bearing shell; the thermal protection layer comprises a thermal insulation layer and a thermal protection layer, wherein latticed thermal protection layer reinforcing ribs are arranged on the inner wall of the thermal protection layer, the thermal insulation layer is arranged in the grids of the thermal protection layer reinforcing ribs, and a thermal insulation layer coating skin is arranged on the surface of the thermal insulation layer; the heat-proof layer, the skin coated by the heat-proof layer and the heat-proof layer reinforcing ribs are sewn with the heat-proof layer into a whole through sewing lines in a prepreg state and then integrally cured at high temperature to form an integrated heat-proof and heat-proof structure; the adhesive layer is positioned between the bearing shell and the thermal protection layer, and the adhesive layer is adhesive with high temperature resistance and thermal matching performance. The invention adopts the heat-proof integrated heat protection layer and bonds the heat-proof integrated heat protection layer on the bearing shell by using the high-temperature resistant adhesive, thereby avoiding the interface separation at the negative curvature part of the aircraft heat protection structure.

Description

Prevent thermal-insulated integrative hot protective structure suitable for negative curvature appearance
Technical Field
The invention relates to the technical field of thermal protection of hypersonic-velocity near space aircrafts, in particular to an anti-heat-insulation integrated thermal protection structure suitable for negative curvature shapes.
Background
The hypersonic near space aircraft (generally, an aircraft with the flight speed exceeding mach 5 and flying in the atmosphere in the whole process) has great military value and potential economic value due to the characteristics of high flight speed, strong penetration resistance and the like, and is the main direction for developing domestic and foreign weapons and spacecrafts at present. When the aircraft flies at the hypersonic speed in the atmosphere, pneumatic heating is very serious, and the problem of thermal protection of the outer surface of the aircraft is always the problem that needs to be mainly solved in the design of the hypersonic speed adjacent space aircraft.
The thermal protection structure on the outer surface of the common hypersonic aircraft is generally a multilayer structure formed by compounding a thermal protection layer and a bearing layer, and the thermal protection layer can be a single-layer heat protection layer or a composite structure formed by combining the heat protection layer and a heat insulation layer. The thermal protection layer is generally compounded with the bearing layer in two ways: the most common one is to fix the pre-soaked cloth on the bearing layer by winding or laying, and then to solidify and form the pre-soaked cloth along with the bearing layer. The other method is that the thermal protection layer is directly solidified and molded through a mold and then sleeved on the outer surface of the bearing shell, and the thermal protection layer is connected with the bearing layer through an adhesive layer. The two structures have the problem that the interfaces among the heat-proof layer, the heat-insulating layer and the bearing shell are easy to be bonded and fail to separate under the high-temperature condition in the flight process; however, for the positive curvature shape, after local interface debonding occurs, the interfaces of all layers can still be attached by virtue of the constraint force of the heat protection layer closed by the shape, so that the influence on the whole heat protection structure is small, and the problem is not obvious.
In order to obtain a higher lift-drag ratio, the hypersonic near space vehicle has higher requirements on the aerodynamic shape, the hypersonic near space vehicle is generally designed into the shape of a lifting body with a special-shaped curved surface, and some hypersonic near space vehicles need to be designed into the aerodynamic shape with negative curvature, but the aerodynamic shape with negative curvature brings new challenges to the heat-proof and heat-insulation design of the hypersonic near space vehicle:
(1) under the high temperature condition in the flight process, after the bonding among the heat-proof layer, the heat-insulating layer and the bearing shell fails and is separated, for the heat protection structure with the negative curvature shape, the heat-proof layer with the closed shape has no constraint force at the negative curvature part, so that the interfaces among all layers of the negative curvature part are separated firstly; meanwhile, the thermal expansion ratio of the bearing shell is generally larger than the thermal expansion of the heat-proof layer, so that the tensile stress of the heat-proof layer in the circumferential direction is increased, and the separation of the interface between each layer of the negative curvature part is further intensified. After the negative curvature part has interface separation, under the action of high-speed pneumatic load, the thermal protection layer stress of the part with the interface separation is rapidly increased, and the part is easy to damage, so that the whole thermal protection layer and the aircraft structure are damaged.
(2) In the forming process of the heat-proof layer, fiber cloth or prepreg needs to be paved on a bearing shell or a tool, and for a heat protection structure with a negative curvature appearance, because the fiber cloth or prepreg has poor deformability in a plane, folds are easy to appear at the negative curvature part in the paving process, and the formed heat-proof layer has the defects of local bulges, local holes and the like, so that the heat protection performance of the heat-proof layer is influenced.
(3) For the heat-proof layer formed by winding or pre-fixing a pre-impregnated cloth on a bearing layer and then curing and forming the pre-impregnated cloth and the bearing layer, in addition to the problems, the negative curvature part has the problem that the performance of the heat-proof layer material at the negative curvature part is difficult to ensure due to the difficulty in controlling the tension of the winding and the laying layer; meanwhile, as the thermal expansion of the bearing shell is larger than that of the heat-proof layer, the bearing shell shrinks more after being cured, and the heat-proof layer at the negative curvature part and the bearing shell are separated from each other on the interface first.
Therefore, there is a need to develop a thermal protection structure suitable for an aircraft with a negative curvature profile, and having excellent ablation resistance, heat insulation performance and thermal matching performance.
Disclosure of Invention
The invention aims to overcome the defect that the interfaces between layers at the negative curvature part are easy to separate in the background technology, and provides an anti-heat-insulation integrated heat protection structure suitable for negative curvature shapes.
The invention provides a heat-insulation integrated heat protection structure suitable for negative curvature shapes, which comprises:
a force bearing shell;
the thermal protection layer comprises a thermal insulation layer and a thermal protection layer, wherein latticed thermal protection layer reinforcing ribs are arranged on the inner wall of the thermal protection layer, the thermal insulation layer is arranged in the grids of the thermal protection layer reinforcing ribs, and a thermal insulation layer coating skin is arranged on the surface of the thermal insulation layer; the thermal insulation layer covers the skin, the thermal insulation layer reinforcing ribs and the thermal insulation layer are sewn with the thermal insulation layer into a whole through sewing threads in a prepreg state;
the adhesive layer is positioned between the bearing shell and the thermal protection layer, and the thermal protection layer is adhered to the bearing shell through the adhesive layer.
The preferred scheme is as follows: the heat-proof layer, the thermal insulation layer coating skin and the heat-proof layer reinforcing rib are all formed by laminating and curing a plurality of layers of prepreg, and the prepreg is prepared by impregnating three-dimensional quartz fabric with phenolic resin.
The preferred scheme is as follows: the thermal-insulating layer is made of aerogel composite materials.
The preferred scheme is as follows: the bonding layer is an adhesive with high temperature resistance and thermal matching performance, wherein the high temperature resistance means that the temperature environment of the aircraft in the flight process can be resisted, the thermal matching performance is used for solving the problem of deformation coordination of the bearing shell and the thermal protection layer caused by the fact that the thermal expansion amount of the bearing shell is larger than that of the thermal protection layer, and a plurality of through holes are formed in the bonding layer.
The preferred scheme is as follows: the axis of the through hole is perpendicular to the thickness direction of the bonding layer.
The preferred scheme is as follows: the suture line is made of quartz fiber materials.
On the basis of the technical scheme, compared with the prior art, the invention has the following advantages:
the integrated heat protection structure suitable for the negative curvature shape can effectively solve the problem that the interfaces among the heat protection layer, the heat insulation layer and the bearing shell at the negative curvature part of the hypersonic-velocity near space aircraft with the negative curvature shape are easy to separate, and improves the capability of the negative curvature part of the aircraft in resisting damage under the action of high-speed pneumatic load, thereby ensuring the reliable work of the heat protection structure of the aircraft.
1) The bonding layer has a through hole bonding layer structure with good high-temperature bonding performance and good thermal matching performance, so that the phenomenon of interface separation of a negative curvature part is avoided, and the risk that the negative curvature part is easy to damage under the action of high-speed pneumatic load is avoided. The good high-temperature bonding performance of the bonding layer ensures that the bonding between the thermal protection layer and the bearing shell is firm under the high-temperature condition in the flight process of the aircraft; the good thermal matching performance of the bonding layer solves the problem that the bearing shell and the thermal protection layer are deformed and coordinated due to the fact that the bearing shell has larger expansion amount than the thermal protection layer when the aircraft can adapt to high temperature conditions; the adhesive layer structure with the through holes can reduce the compression modulus of the adhesive layer, further improve the deformation coordination capacity of the bearing shell and the thermal protection layer, provide an exhaust channel for gas generated by carbonization of the thermal protection layer under a high-temperature condition, and reduce the risk of peeling between the thermal protection layer and the bearing shell due to internal pressure of the gas.
2) The three-dimensional fabric adopted by the heat-proof layer, the thermal insulation layer coating skin and the heat-proof layer reinforcing rib has certain deformability, and wrinkles are avoided at the negative curvature part in the paving process, so that the defects of local bulges or local holes and the like are reduced, and the performance of a heat-proof layer is improved.
3) The heat protection layer is provided with a heat insulation layer and a heat protection layer, wherein latticed heat protection layer reinforcing ribs are arranged on the inner wall of the heat protection layer, the heat insulation layer is arranged in a grid of the heat protection layer reinforcing ribs, and a heat insulation layer coating skin is arranged on the surface of the heat insulation layer; the heat-proof layer, the skin coated by the heat-proof layer and the reinforcing ribs of the heat-proof layer are sewn with the heat-proof layer into a whole through sewing threads in a prepreg state, and then the whole is cured at high temperature to form the heat-proof integrated structure. The thermal protection layer can avoid interface separation at the negative curvature part of the thermal protection structure of the aircraft, effectively improves the capability of the aircraft for resisting damage at the negative curvature part under the action of high-speed pneumatic load, and further ensures the reliable work of the aircraft structure.
Drawings
FIG. 1 is a schematic structural view in longitudinal section of a thermal protection structure according to an embodiment of the present invention;
fig. 2 is a schematic cross-sectional view of a thermal protection structure according to an embodiment of the invention.
Reference numerals: 1-thermal protection layer, 2-adhesive layer, 3-bearing shell, 11-heat protection layer, 12-heat insulation layer, 13-heat insulation layer coating skin, 14-heat protection layer reinforcing rib and 15-suture line.
Detailed Description
The invention is described in further detail below with reference to the figures and the embodiments.
Example 1
Referring to fig. 1 and 2, the embodiment of the invention provides an integrated heat protection structure suitable for heat insulation of a negative curvature shape, and the integrated heat protection structure consists of a force bearing shell 3, a heat protection layer 1 and an adhesive layer 2.
Wherein, the bearing shell 3 is made of light high-strength metal material, and the bearing shell 3 mainly plays a bearing role.
The thermal protection layer 1 comprises a thermal insulation layer 12 and a thermal protection layer 11, wherein latticed thermal protection layer reinforcing ribs 14 are arranged on the inner wall of the thermal protection layer 11, the thermal insulation layer 12 is arranged in the grids of the thermal protection layer reinforcing ribs 14, and a thermal insulation layer coating skin 13 is arranged on the surface of the thermal insulation layer 12.
This thermal-protective layer strengthening rib 14 is latticed and arranges, and thermal-protective layer strengthening rib 14 provides the space for arranging of insulating layer 12, because the insulating layer 12 of this embodiment adopts the thermal-insulating material that has low coefficient of thermal conductivity, low density, consequently sets up insulating layer 12 in the net of thermal-protective layer strengthening rib 14, prevents that insulating layer 12 from receiving the external force deformation to become invalid.
The thermal insulation layer coating skin 13, the thermal insulation layer reinforcing ribs 14 and the thermal insulation layer 11 are sewn with the thermal insulation layer 12 into a whole in a prepreg state through sewing threads 15, and then the whole is cured at high temperature to form a thermal insulation integrated structure.
The adhesive layer 2 is positioned between the bearing shell 3 and the thermal protection layer 1, and the thermal protection layer 1 is adhered to the bearing shell 3 through the adhesive layer 2. The adhesive layer 2 is formed by curing an adhesive with good thermal matching performance, high-temperature adhesive performance and coating process performance, a plurality of through holes are formed in the adhesive layer 2, and the axes of the through holes are perpendicular to the thickness direction of the adhesive layer 2. Typical performance requirements for the adhesive layer 2 are given in table 1:
TABLE 1 bond layer Performance requirements
Serial number Parameter(s) Status of state Required value
1 Compression modulus (20% compression) Normal temperature to 220 DEG C 1～10MPa
2 Shear strength Normal temperature to 220 DEG C ≥0.2MPa
3 Elongation at Break At normal temperature ≥100％
4 Tensile strength At normal temperature ≥1.5MPa
5 Viscosity of the oil During coating ≤1×105Pa.s
Principle of operation
The invention relates to an anti-heat insulation integrated thermal protection structure suitable for a negative curvature shape, which consists of a bearing shell 3, a thermal protection layer 1 and an adhesive layer 2. This integrative hot protective structure can effectively solve the hypersonic speed that has the negative curvature appearance and close on the problem that the separation appears easily in the interface between space vehicle negative curvature position thermal protection layer, insulating layer, the load casing, improves the aircraft under the high-speed pneumatic load effect, and the ability of negative curvature position resistance to destruction to guarantee the reliable work of aircraft hot protective structure.
The bonding layer 2 is a bonding layer structure with a through hole and has good high-temperature bonding performance and good thermal matching performance, so that the phenomenon of interface separation of a negative curvature part is avoided, and the risk that the negative curvature part is easy to damage under the action of high-speed pneumatic load is avoided. The good high-temperature bonding performance of the bonding layer 2 ensures that the bonding between the thermal protection layer 1 and the bearing shell 3 is firm under the high-temperature condition in the flight process of the aircraft.
The good thermal matching performance of the adhesive layer 2 solves the problem that the bearing shell 3 and the thermal protection layer 1 deform and coordinate due to the fact that the expansion amount of the bearing shell 3 is larger than that of the thermal protection layer 1 when the aircraft can adapt to high temperature conditions. The structure of the adhesive layer 2 with the through holes can reduce the compression modulus of the adhesive layer 2, further improve the deformation coordination capacity of the bearing shell 3 and the thermal protection layer 1, provide an exhaust channel for gas generated by carbonization of the thermal protection layer 1 under a high-temperature condition, and reduce the risk of peeling between the thermal protection layer 1 and the bearing shell 3 due to internal pressure of the gas.
The heat protection layer 1 is provided with a heat insulation layer 12 and a heat protection layer 11, wherein the inner wall of the heat protection layer 11 is provided with latticed heat protection layer reinforcing ribs 14, the heat insulation layer 12 is arranged in grids of the heat protection layer reinforcing ribs 14, and the surface of the heat insulation layer 12 is provided with a heat insulation layer coating skin 13; the heat-proof layer 11, the heat-insulating layer coating skin 13 and the heat-proof layer reinforcing ribs 14 are integrally sewn with the heat-insulating layer 12 in a prepreg state through sewing threads 15, and then the whole is cured at high temperature to form a heat-proof and heat-insulating integrated structure. This thermal protection layer 1 can avoid the hot protective structure negative curvature position of aircraft to appear interface separation, effectively improves the aircraft under high-speed pneumatic load effect, and negative curvature position resists the ability of destruction to guarantee the reliable work of aircraft structure.
Example 2
Referring to fig. 1 and fig. 2, an embodiment of the present invention provides an integrated heat protection structure with heat insulation and protection suitable for a negative curvature profile, and the present embodiment is different from embodiment 1 in that: the heat-proof layer 11, the heat-proof layer coating skin 13 and the heat-proof layer reinforcing ribs 14 of the heat-proof layer 1 are all formed by laminating multiple layers of prepreg and curing at high temperature, wherein the prepreg is prepared by impregnating a certain thickness of three-dimensional quartz fabric with phenolic resin. The specific thickness of the cubic quartz fabric and the specific kind of the phenolic resin are specifically set by those skilled in the art according to actual needs.
The heat-proof layer 11, the heat-insulating layer coating skin 13 and the heat-proof layer reinforcing ribs 14 of the heat-protective layer 1 can be respectively prepared from three-dimensional fabrics with different thicknesses and different types of resins according to requirements.
The three-dimensional fabric adopted by the heat-proof layer 11, the thermal insulation layer coating skin 13 and the heat-proof layer reinforcing ribs 14 has certain deformability, and wrinkles are avoided at negative curvature positions in the laying process, so that the defects of local bulges or local holes and the like are reduced, and the performance of the heat-proof layer 1 is improved.
Example 3
Referring to fig. 1 and fig. 2, an embodiment of the present invention provides an integrated heat protection structure with heat insulation and protection suitable for a negative curvature profile, and the present embodiment is different from embodiment 1 in that: the heat-proof layer 11 of the heat-protective layer 1 is provided with a plurality of layers, and the specific number of the layers of the heat-proof layer 11 is increased or decreased according to the specific design requirement. The multilayer heat-proof layer 11 is laminated to a set thickness, and the multilayer heat-proof layer 11 is integrally sewed with the heat-insulating layer 12 through a sewing thread 15. The multilayer heat-protective layer 11 and the heat-protective layer 1 which is integrally sewn in the embodiment 1 are sewn again to prevent the interfacial separation between the layers.
Preferably, the sewing thread 15 is made of quartz fiber material with high temperature resistance. The quartz fiber material has heat resistance, corrosion resistance and flexibility. High strength retention rate at high temperature, stable dimension, thermal shock resistance, chemical stability, light transmission and good electrical insulation. The quartz fiber material has high temperature resistance, high long-term use temperature up to 1200 deg.c, softening point temperature up to 1700 deg.c, high electric insulating performance, high ablation resistance, high heat shock resistance, excellent dielectric performance, high chemical stability, etc.
The thermal protection layer 1 adopts the suture 15 to sew the thermal insulation layer coating skin 13, the thermal protection layer reinforcing ribs 14, the thermal insulation layer 12 and the thermal protection layer 11 of the thermal protection layer 1 into an integrated structure by the suture 15, so that the excellent performances of high strength retention rate and stable size can be still maintained at high temperature of 1200 ℃, and the defects of deformation and fracture cannot occur. The integrity among the heat-insulating layer coating skin 13, the heat-proof layer reinforcing ribs 14, the heat-insulating layer 12 and the heat-proof layer 11 of the heat-protective layer 1 is guaranteed, and the interface separation between layers is prevented.
Preferably, the insulating layer 12 is selected to be a material with a low thermal conductivity, such as an aerogel composite. The aerogel composite material is an ideal transparent heat insulation material, has a very good heat insulation effect, and is 2-5 times of the traditional heat insulation material. The aerogel composite material is used as the heat insulation material of the heat insulation layer 12, so that aerodynamic heat generated when the aircraft flies at hypersonic speed in the atmosphere can be effectively prevented from entering the inner cabin of the aircraft, and a good working environment is provided for equipment in the inner cabin of the aircraft.
The heat-insulation integrated heat protection structure suitable for the negative curvature shape can be prepared by the following method:
step 101: and (4) manufacturing a thermal protection layer 1. Firstly, a thermal insulation layer coated skin 13 with a set thickness is laid in a mould, secondly, thermal insulation layer reinforcing ribs 14 are laid on the thermal insulation layer coated skin 13, and the thermal insulation layer reinforcing ribs 14 are arranged on the thermal insulation layer coated skin 13 in a grid shape. Next, the heat insulation layer 12 is laid in the grid of the heat insulation layer reinforcing ribs 14, then the heat insulation layer 11 is laid on the top of the heat insulation layer reinforcing ribs 14 and the heat insulation layer 12, and finally the heat insulation layer 11, the heat insulation layer 12, the heat insulation layer coating skin 13 and the heat insulation layer reinforcing ribs 14 are sewn into an integrated structure through the sewing lines 15 and are cured and formed in a mold.
Step 102: and (3) surface treatment of the bearing shell 3. Firstly, the surface of the bearing shell 3 is polished and cleaned to ensure that the surface of the bearing shell 3 is rough and free of impurities, and then the surface of the bearing shell 3 is coated with a tackifying primer and dried.
Step 103: the adhesive layer 2 is applied. Firstly, arranging a set number of rod-shaped objects on the surface of the bearing shell 3, wherein the rod-shaped objects are preferably steel wires; secondly, uniformly coating the adhesive layer 2 on the surface of the bearing shell 3 to ensure that the adhesive layer 2 can be filled in the gap between the thermal protection layer 1 and the bearing shell 3; and then sleeving the cured thermal protection layer 1 on the surface of the bearing shell 3, drawing out the rod-shaped object in the bonding layer 2 to form an exhaust hole when the bonding layer 2 is in a semi-cured state, and finally completing the preparation of the integrated thermal protection structure after the bonding layer 2 is completely cured.
Various modifications and variations of the embodiments of the present invention may be made by those skilled in the art, and they are also within the scope of the present invention, provided they are within the scope of the claims of the present invention and their equivalents.
What is not described in detail in the specification is prior art that is well known to those skilled in the art.

Claims (4)

1. The utility model provides a prevent thermal-insulated integrative hot protective structure suitable for negative curvature appearance which characterized in that includes:
a bearing shell (3);
the thermal protection layer (1) comprises a thermal insulation layer (12) and a thermal protection layer (11), wherein latticed thermal protection layer reinforcing ribs (14) are arranged on the inner wall of the thermal protection layer (11), the thermal insulation layer (12) is arranged in grids of the thermal protection layer reinforcing ribs (14), and a thermal insulation layer coating skin (13) is arranged on the surface of the thermal insulation layer (12); the thermal insulation layer coating skin (13), the thermal insulation layer reinforcing ribs (14) and the thermal insulation layer (11) are sewn into a whole with the thermal insulation layer (12) through sewing threads (15) in a prepreg state;
the adhesive layer (2) is positioned between the bearing shell (3) and the thermal protection layer (1), and the thermal protection layer (1) is adhered to the bearing shell (3) through the adhesive layer (2);
adhesive linkage (2) is for having the adhesive of high temperature resistant and heat matching performance, and wherein high temperature resistant indicates can tolerate the temperature environment of aircraft flight in-process, and heat matching performance is used for solving the big and bearing casing and the thermal protection layer deformation coordination problem that leads to of bearing casing thermal expansion volume than thermal protection layer thermal expansion volume, be equipped with a plurality of through-holes in adhesive linkage (2), the axis of through-hole with the thickness direction of adhesive linkage (2) is perpendicular.
2. An integrated thermal protection structure adapted for negative curvature profiles for protection against heat insulation as claimed in claim 1 wherein:
the heat-proof layer (11), the heat-insulating layer coating skin (13) and the heat-proof layer reinforcing ribs (14) are all formed by laminating and curing multiple layers of prepreg, and the prepreg is prepared by impregnating three-dimensional quartz fabric with phenolic resin.
3. An integrated thermal protection structure adapted for negative curvature profiles for protection against heat insulation as claimed in claim 1 wherein:
the heat insulation layer (12) is made of aerogel composite materials.
4. An integrated thermal protection structure adapted for negative curvature profiles for protection against heat insulation as claimed in claim 1 wherein:
the suture line (15) is made of quartz fiber materials.
CN201910942135.2A 2019-09-30 2019-09-30 Prevent thermal-insulated integrative hot protective structure suitable for negative curvature appearance Active CN110524974B (en)

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CN111409814B (en) * 2020-03-02 2021-09-14 北京空天技术研究所 Thermal bridge blocking structure for aircraft and preparation method thereof
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