CN110524974A - A kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape - Google Patents

A kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape Download PDF

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Publication number
CN110524974A
CN110524974A CN201910942135.2A CN201910942135A CN110524974A CN 110524974 A CN110524974 A CN 110524974A CN 201910942135 A CN201910942135 A CN 201910942135A CN 110524974 A CN110524974 A CN 110524974A
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China
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thermal
heat
thermal protection
heat shield
insulation layer
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CN201910942135.2A
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CN110524974B (en
Inventor
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 form; Layered products 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 form; Layered products 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 form; Layered products 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 form; Layered products 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 form; Layered products 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
    • 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
    • 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

Abstract

The invention discloses a kind of anti-heat-insulation integrative thermal protection structures suitable for negative cruvature shape, belong to hypersonic near space vehicle thermal protection technology field.It include: load shell；Thermal protection shield, thermal protection shield include thermal insulation layer and heat shield, and heat shield inner wall is provided with latticed heat shield reinforcing rib, and the thermal insulation layer is arranged in the grid of heat shield reinforcing rib, and thermal insulation layer surface is equipped with thermal insulation layer and coats covering；Heat shield, thermal insulation layer cladding covering, heat shield reinforcing rib are sutured integrally with thermal insulation layer by suture in prepreg state, then integral high-temperature is cured as anti-heat-insulation integrative structure；For adhesive layer between load shell and thermal protection shield, adhesive layer is the bonding agent with high temperature resistant and thermal matching energy.The present invention is bonded in load shell on using anti-heat-insulation integrative thermal protection shield and with high temperature resistant adhesive, can avoid aircraft thermal protection structure negative cruvature position and interfacial separation occurs.

Description

A kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape
Technical field
The present invention relates to hypersonic near space vehicle thermal protection technology fields, are specifically related to a kind of suitable for negative The anti-heat-insulation integrative thermal protection structure of curvature shape.
Background technique
(refer generally to flying speed is more than 5 Mach to hypersonic near space vehicle, whole to fly in endoatmosphere flight Row device) due to having the characteristics that flying speed is high, penetration ability is strong, there are huge military value and potential economic value, The Main way of domestic and international weapon and spacecraft development is had become at present.Aircraft when endoatmosphere is with hypersonic flight, Aerodynamic Heating is very serious, and the thermal protection problem of aircraft outer surface is always hypersonic near space vehicle design needs Key problems-solving.
The thermal protection structure of common hypersonic aircraft outer surface is generally what thermal protection shield was combined with bearing layer Multilayered structure, thermal protection shield can be the composite construction that single layer heat shield or heat shield are combined with thermal insulation layer.Thermal protection shield generally has Two ways is compound with bearing layer: most common one is pre-fix prepreg cloth in bearing layer by modes such as windings or laying On, then with bearing layer curing molding.Another kind is by mold by the direct curing molding of thermal protection shield, then covers and be attached to load Housing outer surface is attached by adhesive layer again between thermal protection shield and bearing layer.All there is flight course in both structures In hot conditions under, the problem of heat shield, thermal insulation layer, the interface between load shell are easy to appear adhesive failure and separate； But for positive camber shape, after there is localized interface unsticking, by the restraining force of the heat shield of shape closure, between each bed boundary Still it can be bonded, thermal protection overall structure be influenced less, problem does not protrude.
To obtain higher lift resistance ratio, hypersonic near space vehicle has higher requirement to aerodynamic configuration, generally It is designed as the lifting body shape of abnormal curved surface, some need is designed with the aerodynamic configuration of negative cruvature, but negative cruvature is pneumatically outer Shape brings new challenge to the solar heat protection of hypersonic aircraft, Design on thermal insulation:
(1) under the hot conditions in flight course, heat shield, thermal insulation layer, the adhesive failure between load shell and divide From rear, for there are the thermal protection structure of negative cruvature shape, the heat shield of shape closure at negative cruvature position without restraining force, Therefore, interface separates at first between each layer in negative cruvature position；Simultaneously as the thermal expansion of load shell is than generally comparing solar heat protection The thermal expansion of layer is big, so that heat shield increases in the tensile stress of circumferencial direction, has been further exacerbated by between each layer in negative cruvature position The separation at interface.After interfacial separation occurs in negative cruvature position, under the effect of high speed pneumatic load, there is the position of interfacial separation Solar heat protection ply stress can increase rapidly, and easily destroy, and destroy so as to cause entire solar heat protection damage layer, Flight Vehicle Structure.
(2) in heat shield forming process, fiber cloth or prepreg needs are coated on load shell or tooling, for existing The thermal protection structure of negative cruvature shape during being coated with, is born since the deformability of fiber cloth or prepreg planar is poor The defects of curvature position is easy to appear fold, and molding heat shield will appear local eminence or local hole, and then influence solar heat protection Layer thermal protective performance.
(3) winding of use prepreg cloth or laying are pre-fixed on bearing layer, then with bearing layer curing molding Mode forms heat shield, other than the above problem, there is also negative cruvature position since winding, laying tensile force are difficult to control, makes Negative cruvature position heat shield material property is obtained to be difficult to ensure；Simultaneously as the thermal expansion of load shell is bigger than heat shield, solidification Load housing shrinkage is more afterwards, and interfacial separation occurs at first in the meeting between the heat shield and load shell at negative cruvature position.
Therefore, it is necessary to study be suitable for negative cruvature shape aircraft use, while have both excellent Burning corrosion resistance energy, prevent it is heat-insulated The thermal protection structure of performance and thermal matching energy.
Summary of the invention
The purpose of the invention is to overcome, interface is easy between each layer in negative cruvature position in above-mentioned background technique The deficiency now separated provides a kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape.
The present invention provides a kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape, comprising:
Load shell；
Thermal protection shield, the thermal protection shield include thermal insulation layer and heat shield, and the heat shield inner wall is provided with latticed Heat shield reinforcing rib, the thermal insulation layer are arranged in the grid of heat shield reinforcing rib, and thermal insulation layer surface is equipped with thermal insulation layer cladding and covers Skin；The thermal insulation layer cladding covering, heat shield reinforcing rib, heat shield pass through suture linear slit with thermal insulation layer under prepreg state Integrator；
Adhesive layer, between load shell and thermal protection shield, thermal protection shield is bonded the adhesive layer by the adhesive layer On load shell.
Preferred embodiment: the heat shield, thermal insulation layer cladding covering and heat shield reinforcing rib are laminated by multilayer prepreg And hot setting forms, the prepreg is made of certain thickness three-dimensional silica fiber fabric impregnated phenolic resin.
Preferred embodiment: the thermal insulation layer is aerogel composite.
Preferred embodiment: the adhesive layer is the bonding agent with high temperature resistant and thermal matching energy, is equipped in the adhesive layer Multiple through-holes.
Preferred embodiment: the axis of the through-hole is vertical with the thickness direction of the adhesive layer.
Preferred embodiment: the suture is silica fiber material.
Based on the above technical solution, compared with prior art, advantages of the present invention is as follows:
A kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape of the invention, the integration thermal protection knot Structure can be solved effectively to have the hypersonic near space vehicle negative cruvature position heat shield of negative cruvature shape, thermal insulation layer, be held The problem of interface between power shell is easy to appear separation improves aircraft under the effect of high speed pneumatic load, negative cruvature position The ability destroyed is resisted, to guarantee aircraft thermal protection structure reliably working.
1) adhesive layer of the invention is that a kind of band through-hole with good high temperature bonding performance, good thermal matching energy is viscous A layer structure is connect, to guarantee that negative cruvature position does not occur interfacial separation phenomenon, avoids under the effect of high speed pneumatic load, bears song The risk that rate position is easily destroyed.The good high temperature bonding performance of adhesive layer makes hot conditions of the aircraft in flight course Under, it is bonding secured between thermal protection shield and load shell；The good thermal matching of adhesive layer can solve aircraft and adapt to height Under the conditions of temperature, load shell and thermal protection shield compatibility of deformation problem caused by load case swells amount is bigger than thermal protection shield；Band The adhesive layer structure of through-hole can both reduce the compression modulus of adhesive layer, and then improve load shell and thermal protection shield compatibility of deformation Ability also provides exhaust passage for the gas that thermal protection shield carbonization generates under hot conditions, reduces thermal protection shield and load shell The risk removed between body due to gas internal pressure.
2) stereo fabric that heat shield of the invention, thermal insulation layer cladding covering and heat shield reinforcing rib use, has certain Deformability avoid the occurrence of fold at negative cruvature position during being coated with, and then reduce local eminence or local hole etc. Defect improves the performance of thermal protection shield.
3) thermal protection shield of the invention is equipped with thermal insulation layer and heat shield, and heat shield inner wall is provided with latticed heat shield and adds Strengthening tendons, thermal insulation layer are arranged in the grid of heat shield reinforcing rib, and thermal insulation layer surface is equipped with thermal insulation layer and coats covering；Heat shield, every Thermosphere coats covering, heat shield reinforcing rib is sutured integrally with thermal insulation layer by suture in prepreg state, then whole high Temperature is cured as anti-heat-insulation integrative structure.This thermal protection shield can avoid aircraft thermal protection structure negative cruvature position and interface point occurs From, effectively improve aircraft high speed pneumatic load effect under, negative cruvature position resist destroy ability, to guarantee aircraft Structure reliably working.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the thermal protection structure longitudinal profile of the embodiment of the present invention；
Fig. 2 is the thermal protection structure cross-sectional view of the embodiment of the present invention.
Appended drawing reference: 1- thermal protection shield, 2- adhesive layer, 3- load shell, 11- heat shield, 12- thermal insulation layer, 13- thermal insulation layer Coat covering, 14- heat shield reinforcing rib, 15- suture.
Specific embodiment
With reference to the accompanying drawing and specific embodiment the present invention is described in further detail.
Embodiment 1
Referring to figure 1 and figure 2, the embodiment of the present invention provides a kind of anti-heat-insulation integrative heat suitable for negative cruvature shape Safeguard structure, the integration thermal protection structure are made of load shell 3, thermal protection shield 1 and adhesive layer 2.
Wherein, load shell 3 is the metal material of high-strength light, and load shell 3 mainly plays carrying.
Thermal protection shield 1 includes thermal insulation layer 12 and heat shield 11, and 11 inner wall of heat shield is provided with latticed heat shield and reinforces Muscle 14, thermal insulation layer 12 are arranged in the grid of heat shield reinforcing rib 14, are equipped with thermal insulation layer on 12 surface of thermal insulation layer and coat covering 13.
The grid-shaped arrangement of heat shield reinforcing rib 14, heat shield reinforcing rib 14 provide space for the arrangement of thermal insulation layer 12, Since the thermal insulation layer 12 of the present embodiment is using the heat-barrier material with low thermal conductivity, low-density, by thermal insulation layer 12 It is arranged in the grid of heat shield reinforcing rib 14, prevents thermal insulation layer 12 by external force deformation failure.
It is i.e. logical with thermal insulation layer 12 in prepreg state that thermal insulation layer coats covering 13, heat shield reinforcing rib 14 and heat shield 11 It crosses suture 15 to suture integrally, then integral high-temperature is cured as anti-heat-insulation integrative structure.
Adhesive layer 2, between load shell 3 and thermal protection shield 1, thermal protection shield 1 is bonded in adhesive layer 2 by adhesive layer 2 On load shell 3.Adhesive layer 2 is the bonding agent solidification with good thermal matching energy, high temperature bonding performance, coating processes performance It forms, multiple through-holes is offered in the adhesive layer 2, and the axis of through-hole is vertical with the thickness direction of adhesive layer 2.Adhesive layer 2 Typical performance requires to be shown in Table 1:
1 adhesive layer performance requirement of table
Serial number Parameter State Required value
1 Compression modulus (20% compression ratio) Room temperature~220 DEG C 1~10MPa
2 Shear strength Room temperature~220 DEG C ≥0.2MPa
3 Elongation rate of tensile failure Room temperature >=100%
4 Tensile strength Room temperature ≥1.5MPa
5 Viscosity When coating ≤1×105Pa.s
Working principle
A kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape of the invention, the integration thermal protection knot Structure is made of load shell 3, thermal protection shield 1 and adhesive layer 2.The integration thermal protection structure can effectively solve outside with negative cruvature The hypersonic near space vehicle negative cruvature position heat shield of shape, thermal insulation layer, the interface between load shell are easy to appear The problem of separation, improves aircraft under the effect of high speed pneumatic load, and the ability destroyed is resisted at negative cruvature position, to guarantee to fly Row device thermal protection structure reliably working.
Adhesive layer 2 of the invention is that a kind of band through-hole with good high temperature bonding performance, good thermal matching energy is viscous A layer structure is connect, to guarantee that negative cruvature position does not occur interfacial separation phenomenon, avoids under the effect of high speed pneumatic load, bears song The risk that rate position is easily destroyed.The good high temperature bonding performance of adhesive layer 2 makes high temperature item of the aircraft in flight course It is bonding secured between thermal protection shield 1 and load shell 3 under part.
The good thermal matching of adhesive layer 2 can solve aircraft and adapt under hot conditions, 3 swell increment specific heat of load shell Load shell 3 and 1 compatibility of deformation problem of thermal protection shield caused by protective layer 1 is big.The structure of adhesive layer 2 with through-hole both can be with The compression modulus of adhesive layer 2 is reduced, and then improves load shell 3 and 1 compatibility of deformation ability of thermal protection shield, also under hot conditions The gas that the carbonization of thermal protection shield 1 generates provides exhaust passage, reduces between thermal protection shield 1 and load shell 3 due in gas The risk pressed and removed.
Thermal protection shield 1 of the invention is equipped with thermal insulation layer 12 and heat shield 11, and 11 inner wall of heat shield is provided with latticed anti- Thermosphere reinforcing rib 14, thermal insulation layer 12 are arranged in the grid of heat shield reinforcing rib 14, and 12 surface of thermal insulation layer is coated equipped with thermal insulation layer Covering 13；Heat shield 11, thermal insulation layer cladding covering 13, heat shield reinforcing rib 14 pass through seam with thermal insulation layer 12 in prepreg state Zygonema 15 sutures integrally, then integral high-temperature is cured as anti-heat-insulation integrative structure.It is anti-that this thermal protection shield 1 can avoid aircraft heat There is interfacial separation in protection structure negative cruvature position, effectively improves aircraft under the effect of high speed pneumatic load, negative cruvature position is supported The ability of collapse resistance, to guarantee Flight Vehicle Structure reliably working.
Embodiment 2
Referring to figure 1 and figure 2, the embodiment of the present invention provides a kind of anti-heat-insulation integrative heat suitable for negative cruvature shape Safeguard structure, the present embodiment the difference from embodiment 1 is that: the heat shield 11 of this thermal protection shield 1, thermal insulation layer cladding covering 13 and Heat shield reinforcing rib 14 is to be laminated by multilayer prepreg and hot setting forms, and prepreg is by certain thickness three-dimensional quartz Fabric impregnated phenolic resin is made.The specific thickness of three-dimensional silica fiber fabric and the specific type those skilled in the art of phenolic resin Member's specific setting according to actual needs.
Heat shield 11, thermal insulation layer cladding covering 13 and the heat shield reinforcing rib 14 of thermal protection shield 1 can be as needed using not The stereo fabric of stack pile, different types of resin are prepared respectively.
The stereo fabric that heat shield 11, thermal insulation layer cladding covering 13 and heat shield reinforcing rib 14 use, has certain change Shape ability avoids the occurrence of fold at negative cruvature position, and then reduce local eminence or local hole etc. and lack during being coated with It falls into, improves the performance of thermal protection shield 1.
Embodiment 3
Referring to figure 1 and figure 2, the embodiment of the present invention provides a kind of anti-heat-insulation integrative heat suitable for negative cruvature shape Safeguard structure, the present embodiment the difference from embodiment 1 is that: the heat shield 11 of this thermal protection shield 1 be equipped with multilayer, heat shield 11 The specific number of plies is increased and decreased according to specific design requirement.Multilayer heat shield 11 is overlapped into setting thickness, and multilayer heat shield 11 passes through Suture 15 and thermal insulation layer 12 suture integrally.Integral thermal protection will have been sutured in multilayer heat shield 11 and embodiment 1 Suture is integral again for layer 1, prevents occurring interfacial separation between layers.
Preferably, suture 15 uses the silica fiber material of high temperature resistant property.Silica fiber material has heat-resisting, corrosion resistant Erosion and flexibility.Strength retention height, dimensionally stable, thermal shock resistance, chemical stability, translucency and electrical insulating property at high temperature It is good.Silica fiber material high temperature resistance is higher than high silica fiber, and long-term use temperature can reach 1200 DEG C, and softening point temperature is high Up to 1700 DEG C, while there is high electrical insulation capability, resistance to ablation, anti-thermal shock, excellent dielectric properties and good chemical stabilization Property etc..
This thermal protection shield 1 using suture 15 by the thermal insulation layer of thermal protection shield 1 cladding covering 13, heat shield reinforcing rib 14, Integral structure is stitched into using suture 15 between thermal insulation layer 12 and heat shield 11, is still able to maintain at 1200 DEG C of high temperature The excellent properties of strength retention height, dimensionally stable, are not in the defect of deformation and fracture.This thermal protection shield 1 is ensured Thermal insulation layer coats the globality between covering 13, heat shield reinforcing rib 14, thermal insulation layer 12 and heat shield 11, prevents between layers There is interfacial separation.
Preferably, it is the lower material of thermal coefficient, such as aerogel composite that thermal insulation layer 12, which is selected,.Aeroge is compound Material is a kind of ideal transparent heat-insulated material, has extraordinary heat insulation, is 2-5 times of traditional insulation materials.Using gas Heat-barrier material of the gel complex material as this thermal insulation layer 12, the device that can effectively sock in is in endoatmosphere with hypersonic The Aerodynamic Heating generated when flight enters aircraft inside cabin, provides works fine environment for aircraft below deck equipment.
A kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape of the embodiment of the present invention be referred to The preparation of lower section method:
Step 101: thermal protection shield 1 makes.The thermal insulation layer that setting thickness is laid with first in mold coats covering 13, secondly It sets up defences thermosphere reinforcing rib 14 on thermal insulation layer cladding 13 upper berth of covering, heat shield reinforcing rib 14 is in net on thermal insulation layer cladding covering 13 Trellis arrangement.Next in the grid of heat shield reinforcing rib 14 be laid with thermal insulation layer 12, then heat shield reinforcing rib 14 and every The top of thermosphere 12 is laid with heat shield 11, and heat shield 11, thermal insulation layer 12, thermal insulation layer are finally coated covering 13 using suture 15 Integral structure and the curing molding in mold are stitched into heat shield reinforcing rib 14.
Step 102: load shell 3 is surface-treated.It is polished and is cleared up on the surface of load shell 3 first, it is ensured that load The rough surface no-sundries of shell 3, then on the surface of load shell 3, coating viscosifies silane coupling agent and dries.
Step 103: coating adhesive layer 2.First in the shaft of the surface of load shell 3 arrangement setting quantity, shaft Preferably steel wire；Secondly adhesive layer 2 is uniformly coated on the surface in load shell 3, it is ensured that adhesive layer 2 can fill full thermal protection shield Gap between 1 and load shell 3；Next the thermal protection shield of curing molding 1 is sleeved on to the surface of load shell 3, to viscous It connects when layer 2 is in semi-cured state and extracts the shaft in adhesive layer 2 out to form gas vent, be finally in complete to adhesive layer 2 After solidification, integration thermal protection structure preparation is completed.
Those skilled in the art can carry out various modifications to the embodiment of the present invention and modification, if these modifications and change For type within the scope of the claims in the present invention and its equivalent technologies, then these modifications and variations are also in protection scope of the present invention Within.
The prior art that the content being not described in detail in specification is known to the skilled person.

Claims (6)

1. a kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape characterized by comprising
Load shell (3)；
Thermal protection shield (1), the thermal protection shield (1) include thermal insulation layer (12) and heat shield (11), heat shield (11) inner wall It is provided with latticed heat shield reinforcing rib (14), the thermal insulation layer (12) is arranged in the grid of heat shield reinforcing rib (14), Thermal insulation layer (12) surface is equipped with thermal insulation layer cladding covering (13)；Thermal insulation layer cladding covering (13), heat shield reinforcing rib (14), Heat shield (11) is i.e. integral by suture (15) suture with thermal insulation layer (12) under prepreg state；
Adhesive layer (2), the adhesive layer (2) are located between load shell (3) and thermal protection shield (1), and the adhesive layer (2) will be hot Protective layer (1) is bonded on load shell (3).
2. a kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape as described in claim 1, feature exist In:
The heat shield (11), thermal insulation layer cladding covering (13) and heat shield reinforcing rib (14) are laminated simultaneously by multilayer prepreg Hot setting forms, and the prepreg is made of certain thickness three-dimensional silica fiber fabric impregnated phenolic resin.
3. a kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape as described in claim 1, feature exist In:
The thermal insulation layer (12) is aerogel composite.
4. a kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape as described in claim 1, feature exist In:
The adhesive layer (2) is the bonding agent with high temperature resistant and thermal matching energy, is equipped in the adhesive layer (2) multiple logical Hole.
5. a kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape as claimed in claim 4, feature exist In:
The axis of the through-hole is vertical with the thickness direction of the adhesive layer (2).
6. a kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape as described in claim 1, feature exist In:
The suture (15) is silica fiber material.
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