阅读说明：本技术 一种适用于负曲率外形的防隔热一体化热防护结构 (A kind of anti-heat-insulation integrative thermal protection structure suitable for negative cruvature shape ) 是由 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 于 2019-09-30 设计创作，主要内容包括：本发明公开了一种适用于负曲率外形的防隔热一体化热防护结构,属于高超声速临近空间飞行器热防护技术领域。包括：承力壳体；热防护层,热防护层包括隔热层和防热层,防热层内壁设置有网格状的防热层加强筋,所述隔热层设置在防热层加强筋的网格内,隔热层表面设有隔热层包覆蒙皮；防热层、隔热层包覆蒙皮、防热层加强筋在预浸料状态即与隔热层通过缝合线缝合成一体,再整体高温固化为防隔热一体化结构；粘接层位于承力壳体和热防护层之间,粘接层为具有耐高温和热匹配性能的粘接剂。本发明采用防隔热一体化热防护层并用耐高温粘接剂粘接在承力壳体上,可避免飞行器热防护结构负曲率部位出现界面分离。(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.)

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.

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.