CN109927943A - Recoverable airship solar heat protection and carrying integral structure - Google Patents
Recoverable airship solar heat protection and carrying integral structure Download PDFInfo
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- CN109927943A CN109927943A CN201910272662.7A CN201910272662A CN109927943A CN 109927943 A CN109927943 A CN 109927943A CN 201910272662 A CN201910272662 A CN 201910272662A CN 109927943 A CN109927943 A CN 109927943A
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- heat protection
- integral structure
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Abstract
The invention discloses a kind of recoverable airship solar heat protection and carrying integral structure, comprising: heat shield, adhesive layer and bearing structure；Wherein, the heat shield is connected by the adhesive layer with the bearing structure；The bearing structure offers connecting hole, and the heat shield offers threaded hole corresponding with connecting hole, and screw sequentially passes through connecting hole and the heat shield and the bearing structure are connected with threaded hole；The bearing structure is connected with internal section structure, and for connecting interior instrument equipment.The present invention has thermal protective performance and load-carrying properties concurrently, while having the function of detachably to reuse.
Description
Technical field
The invention belongs to the recoverable airship thermal protection system technical field of the escape velocity more particularly to a kind of returns
The solar heat protection of formula airship and carrying integral structure.
Background technique
Recoverable airship is changed into the thermal energy of air with the second space flight velocity ablated configuration process, most of kinetic energy,
And these thermal energy form high Aerodynamic Heating environment in the form of boundary layer convection current and Radiation From Shock Wave in spacecraft surface, outside airship
Surface must have reliable, resistance to erosion thermal protection system, protect the equipment inside the life security and spacecraft of spacefarer.Surface
Heat insulation material structural stability and integrity demands are higher, while heat shield is connected with internal structure, it is desirable that have very high
Bearing capacity, so recoverable airship proposes requirements at the higher level to the lightweight of thermal protection system, thermal protective performance and bearing capacity.
External space shuttle mostly uses a large amount of, low-density thermal insulation tile to be spliced, and that there are structural stabilities is poor for this connecting method, pacifies
The problems such as full property is poor, assembly is complicated, the lead time is long.Domestic Shenzhou spacecraft return capsule, which is used, is directly glued to metal for heat shield
Structure type on inner casing.To solve, external heat insulation tile of shuttle spicing forming type bring is insufficient, domestic Manned reentry capsule is anti-
Hot material does not have the deficiency of bearing function, and urgent need develops a kind of solar heat protection and carrying integral structure.
Summary of the invention
Technical problem solved by the present invention is overcome the deficiencies of the prior art and provide a kind of recoverable airship solar heat protection with
Integral structure is carried, has thermal protective performance and load-carrying properties concurrently, while having the function of detachably to reuse, structure of the invention
It is more that configuration can be achieved, size range is wide, it can be achieved that integrated hood structure, integrated side wall construction, the big bottom structure of integration.
The object of the invention is achieved by the following technical programs: a kind of recoverable airship solar heat protection knot integrated with carrying
Structure, comprising: heat shield, adhesive layer and bearing structure；Wherein, the heat shield passes through the adhesive layer and the bearing structure phase
Connection；The bearing structure offers connecting hole, and the heat shield offers threaded hole corresponding with connecting hole, and screw is successively
The heat shield and the bearing structure are connected with threaded hole across connecting hole；The bearing structure and internal cabin knot
Structure is connected.
In above-mentioned recoverable airship solar heat protection and carrying integral structure, the material of the heat shield is coating material, non-burning
Lose heat insulation material or thermal-protect ablation material.
In above-mentioned recoverable airship solar heat protection and carrying integral structure, the bearing structure is wall panel structure, frame structure
Or sandwich.
In above-mentioned recoverable airship solar heat protection and carrying integral structure, the material of the wall panel structure is for metal material or again
Condensation material；The material of the frame structure is metal material or composite material.
In above-mentioned recoverable airship solar heat protection and carrying integral structure, the sandwich is X-cor sandwich, honeycomb
Sandwich, foamed sandwich structure or lattice structure.
In above-mentioned recoverable airship solar heat protection and carrying integral structure, the composite material is polymer matrix composites, gold
Metal-matrix composite material or inorganic non-metallic based composites.
In above-mentioned recoverable airship solar heat protection and carrying integral structure, the reinforcement of the composite material is carbon fiber, glass
Glass fiber, organic fiber, ceramic fibre and metallic fiber；Wherein, the carbon fiber is T300 and the above high-strength carbon fibre or M40
And the above high modulus carbon fiber；The glass fibre is E glass fibre, S glass fibre or basalt fibre；The organic fiber
For aramid fiber, ultra high molecular weight polyethylene fiber, polyimide fiber, pbo fiber or PBI fiber；The ceramic fibre is
Alumina silicate fibre and modified fibre；The metallic fiber is copper fiber or aluminum fiber.
In above-mentioned recoverable airship solar heat protection and carrying integral structure, the matrix of the polymer matrix composites is thermoplasticity
Resin or thermosetting resin, wherein the thermoplastic resin includes polypropylene, polycarbonate, polyamide and polysulfones；The thermosetting
Property resin includes epoxy resin and cyanate ester resin.
In above-mentioned recoverable airship solar heat protection and carrying integral structure, the adhesive layer is high-temperature-resisting silicon rubber.
In above-mentioned recoverable airship solar heat protection and carrying integral structure, the screw is glass reinforced plastic screw or metallic screw.
Compared with prior art, the present invention has the following advantages:
The present invention has thermal protective performance and load-carrying properties concurrently, while having the function of detachably to reuse, structure of the invention
It is more that configuration can be achieved, size range is wide, it can be achieved that integrated hood structure, integrated side wall construction, the big bottom structure of integration.
Detailed description of the invention
By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field
Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as to the present invention
Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:
Fig. 1 is the schematic diagram of recoverable airship solar heat protection provided in an embodiment of the present invention and carrying integral structure；
Fig. 2 is the Integral connection structure schematic diagram of head-shield provided in an embodiment of the present invention, side wall and outsole.
Specific embodiment
Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
It is fully disclosed to those skilled in the art.It should be noted that in the absence of conflict, embodiment in the present invention and
Feature in embodiment can be combined with each other.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the schematic diagram of recoverable airship solar heat protection provided in an embodiment of the present invention and carrying integral structure.Such as Fig. 1 institute
Show, the recoverable airship solar heat protection and carrying integral structure include: heat shield 1, adhesive layer 2 and bearing structure 3.Wherein,
Heat shield 1 is connected by adhesive layer 2 with bearing structure 3；Bearing structure 3 offers connecting hole, and heat shield 1 opens up
There is threaded hole corresponding with connecting hole, screw sequentially passes through connecting hole and heat shield 1 and bearing structure 3 are connected with threaded hole
It connects；Bearing structure 3 is connected with internal section structure.
The structural outside layers are heat shield 1, play anti-heat effect.Internal layer is bearing structure 3, plays the role of connection and carrying.
Outer layer heat insulation material and internal layer bearing structure are glued by high-temperature Resistance Adhesives becomes an entirety, and passes through spiral shell therebetween
Connect increase bonding strength.
Various interfaces and opening can be further processed on the heat shield of outer layer, for connecting solar heat protection plug screw, porthole, umbrella cabin
The functional structures such as lid.
It include connector in the bearing structure of internal layer, for connecting instrument and equipment and internal structure.
The material of the heat shield 1 is coating material, non-ablative heat insulation material or thermal-protect ablation material.
The bearing structure 3 is wall panel structure, frame structure or sandwich.Wherein, the wall panel structure or frame knot
Structure material is metal material or composite material.The sandwich is X-cor sandwich, honeycomb sandwich construction, foam layer
Structure, lattice structure.Sandwich has the advantages that lightweight, high rigidity and high intensity.
The metal material is aluminium alloy, titanium alloy and other alloy materials.
The composite material is polymer matrix composites, metal-base composites or inorganic non-metallic based composites.Institute
Stating composite material includes reinforcement and matrix.Wherein, the reinforcement of the composite material be fiber, type can be carbon fiber,
Glass fibre, organic fiber, ceramic fibre and metallic fiber etc., form can be continuous fiber or chopped strand.The carbon fiber
Dimension is T300 and the above high-strength carbon fibre or M40 and the above high modulus carbon fiber etc..The glass fibre is E glass fibre, S glass
Glass fiber, basalt fibre etc..The organic fiber be aramid fiber, ultra high molecular weight polyethylene fiber, polyimide fiber,
Pbo fiber, PBI fiber etc..The ceramic fibre is alumina silicate fibre and modified fibre.The metallic fiber is copper fiber, aluminium
Fiber etc..
The matrix of the polymer matrix composites is thermoplastic resin or thermosetting resin, wherein the thermoplastic resin
Including polypropylene, polycarbonate, polyamide and polysulfones；The thermosetting resin includes epoxy resin and cyanate ester resin.
Adhesive layer 2 is high-temperature-resisting silicon rubber.Due to the material of heat shield and the material of bearing structure, to select high temperature resistant
Silicon rubber, so that the splicing of heat shield and bearing structure is stronger.
The screw is glass reinforced plastic screw or metallic screw.Preferably, screw uses glass reinforced plastic screw, due to glass reinforced plastic spiral shell
The material of nail and the material of heat shield are close, and hot expansibility is close, so that good connecting effect.
The present embodiment additionally provides the preparation method of a kind of recoverable airship solar heat protection and carrying integral structure, this method packet
Include following steps:
(1) according to the raw material of the target capabilities of product and size selection heat shield, (raw material of heat shield be can choose
For coating material, non-ablative heat insulation material or thermal-protect ablation material).
(2) blank of heat shield is prepared according to the raw material of heat shield.
(3) the blank machine adduction of heat shield is handled to obtain the inner surface of heat shield.
(4) raw material of bearing structure are selected according to the target capabilities of product and size.
(5) bearing structure is prepared.
(6) heat shield in step (3) and the bearing structure in step (5) are passed through into adhesive layer (2) (material of adhesive layer
Can choose high-temperature-resisting silicon rubber) it is glued to be whole, and be spirally connected by screw.
(7) integral structure in assembly processing step (6), obtains target product.
In step (4), the form of bearing structure can choose wall panel structure, frame structure or sandwich.The wall
Hardened structure or frame structure material are metal material or composite material.The sandwich can be X-cor sandwich, honeycomb
Sandwich, foamed sandwich structure or lattice structure.Sandwich has the advantages that lightweight, high rigidity and high intensity.The gold
Category material is aluminium alloy, titanium alloy and other alloy materials.The composite material is polymer matrix composites, metal-based compound material
Material or inorganic non-metallic based composites.The composite material includes reinforcement and matrix.Wherein, the enhancing of the composite material
Body is fiber, and type can be carbon fiber, glass fibre, organic fiber, ceramic fibre and metallic fiber etc., and form can be company
Continuous fiber or chopped strand.The carbon fiber is T300 and the above high-strength carbon fibre or M40 and the above high modulus carbon fiber etc..Institute
Stating glass fibre is E glass fibre, S glass fibre, basalt fibre etc..The organic fiber is aramid fiber, supra polymer
Weight polyethylene fiber, polyimide fiber, pbo fiber, PBI fiber etc..The ceramic fibre is alumina silicate fibre and modified fibre
Dimension.The metallic fiber is copper fiber, aluminum fiber etc..The matrix of the polymer matrix composites is thermoplastic resin or thermosetting property
Resin, wherein the thermoplastic resin includes polypropylene, polycarbonate, polyamide and polysulfones；The thermosetting resin includes ring
Oxygen resin and cyanate ester resin.
In step (6), screw is glass reinforced plastic screw or metallic screw.Preferably, screw uses glass reinforced plastic screw, due to
The material of glass reinforced plastic screw and the material of heat shield are close, and hot expansibility is close, so that good connecting effect.
Head-shield as shown in Figure 2 can be fabricated to according to the recoverable airship solar heat protection of the present embodiment and carrying integral structure
4, side wall 5 and outsole 6.
As shown in Fig. 2, the hemisphere radius of head-shield 4 is in SR500~SR2000mm range, 20 ° of cone angle or more, total height ruler
Within very little 2m, heat shield thickness in 20~100mm range, honeycomb sandwich construction thickness in 10~80mm range, honeycomb interlayer knot
Structure plate thickness 0.1~4mm range, honeycomb sandwich construction core thickness 2~79.6mm range.
As shown in Fig. 2, the big small end rotary table radius of side wall 5 R100mm~R2000mm range, 5 °~20 ° or more of cone angle,
Within height dimension 100mm~6000mm range, heat shield thickness in 20~100mm range, honeycomb sandwich construction thickness 10
~80mm range, honeycomb sandwich construction plate thickness 0.1~4mm range, honeycomb sandwich construction core thickness 2~79.6mm model
It encloses.
As shown in Fig. 2, 2000~6000mm of diameter of phi of outsole 6, spherical crown outer profile SR1000~6000mm, height dimension
Within 100mm~1000mm range, heat shield thickness in 20~100mm range, honeycomb sandwich construction thickness in 10~80mm model
It encloses, honeycomb sandwich construction plate thickness 0.1~4mm range, honeycomb sandwich construction core thickness 2~79.6mm range.
The more detailed explanation structure preparation process of the following examples:
Outer dimension is small end radius surface R1693mm, big end radius surface R2011mm, honeycomb interlayer thickness 15mm, panel material
Material is M40J/ cyanate ester resin composite material, plate thickness 0.32mm, the integrated side wall construction of honeycomb core specification 0.03 × 3
Steps are as follows for preparation method:
(1) select heat shield raw material for lightweight thermal-protect ablation material.
(2) outer layer heat shield blank is prepared, machine adds heat insulation material inner surface and brushes 192 phenolic resin, brush coating amount (250 ±
10)g/㎡。
(3) reinforcement of the high modulus carbon fiber M40J as panel, matrix of the high temperature cyanate BS-4 as panel are selected.
Reinforcement and matrix are prepared into unidirectional pre-immersion material, thickness in monolayer 0.08mm by hot melt arrangement.It manually lays and prepares carbon fiber
Composite material face passes through vacuum bag-autoclave mode curing molding, thickness 0.32mm.
(4) heat insulation material inner surface the brushing RTV560, bondline thickness 0.15mm in step (2).It prepared by step (3)
Carbon fiber exterior skin be attached on heat insulation material inner surface high-temperature-resisting silicon rubber layer, it is solid to vacuumize pressurization by vacuum bag-baking oven
Change.
(5) it polishes and step (4) China and foreign countries' skin-surface and clears up, paste one layer of J310B glue film.Honeycomb core is spliced into target ruler
It is very little, foamed glue J245D2 connection is used between each section, is attached on the exterior skin in step (4).Foaming is wrapped up around built-in fitting
Glue J245D2 is simultaneously embedded in honeycomb core assembly in place, vacuumizes cure under pressure by vacuum bag-autoclave.
(6) it is attached in step (5) after the carbon fiber Inner Mongol subcutaneous surface of step (3) preparation being pasted one layer of J310B glue film
Honeycomb wicking surface, glue film face are contacted with honeycomb core, pass through vacuum bag-autoclave mode curing molding.
(7) NC Milling and Combined machining part height, hole location and appearance profile brush 192 in heat shield outer surface
Phenolic resin, glue amount (250 ± 10) g/ ㎡, obtains target product.
The present embodiment has thermal protective performance and load-carrying properties concurrently, while having the function of detachably to reuse, knot of the invention
Structure can realize that configuration is more, and size range is wide, it can be achieved that integrated hood structure, integrated side wall construction, the big bottom structure of integration.
Embodiment described above is the present invention more preferably specific embodiment, and those skilled in the art is in this hair
The usual variations and alternatives carried out in bright technical proposal scope should be all included within the scope of the present invention.
Claims (10)
1. a kind of recoverable airship solar heat protection and carrying integral structure, characterized by comprising: heat shield (1), adhesive layer (2) and
Bearing structure (3)；Wherein,
The heat shield (1) is connected by the adhesive layer (2) with the bearing structure (3)；
The bearing structure (3) offers connecting hole, and the heat shield (1) offers threaded hole corresponding with connecting hole, spiral shell
Nail sequentially passes through connecting hole and the heat shield (1) and the bearing structure (3) is connected with threaded hole；
The bearing structure (3) is connected with internal section structure.
2. recoverable airship solar heat protection according to claim 1 and carrying integral structure, it is characterised in that: the heat shield
(1) material is coating material, non-ablative heat insulation material or thermal-protect ablation material.
3. recoverable airship solar heat protection according to claim 1 and carrying integral structure, it is characterised in that: the carrying knot
Structure (3) is wall panel structure, frame structure or sandwich.
4. recoverable airship solar heat protection according to claim 3 and carrying integral structure, it is characterised in that: the siding knot
The material of structure is metal material or composite material；The material of the frame structure is metal material or composite material.
5. recoverable airship solar heat protection according to claim 3 and carrying integral structure, it is characterised in that: the interlayer knot
Structure is X-cor sandwich, honeycomb sandwich construction, foamed sandwich structure or lattice structure.
6. recoverable airship solar heat protection according to claim 4 and carrying integral structure, it is characterised in that: the composite wood
Material is polymer matrix composites, metal-base composites or inorganic non-metallic based composites.
7. recoverable airship solar heat protection according to claim 4 and carrying integral structure, it is characterised in that: the composite wood
The reinforcement of material is carbon fiber, glass fibre, organic fiber, ceramic fibre and metallic fiber；Wherein,
The carbon fiber is T300 and the above high-strength carbon fibre or M40 and the above high modulus carbon fiber；
The glass fibre is E glass fibre, S glass fibre or basalt fibre；
The organic fiber is aramid fiber, ultra high molecular weight polyethylene fiber, polyimide fiber, pbo fiber or PBI fine
Dimension；
The ceramic fibre is alumina silicate fibre and modified fibre；
The metallic fiber is copper fiber or aluminum fiber.
8. recoverable airship solar heat protection according to claim 6 and carrying integral structure, it is characterised in that: the resin base
The matrix of composite material is thermoplastic resin or thermosetting resin, wherein the thermoplastic resin includes polypropylene, poly- carbonic acid
Ester, polyamide and polysulfones；The thermosetting resin includes epoxy resin and cyanate ester resin.
9. recoverable airship solar heat protection according to claim 1 and carrying integral structure, it is characterised in that: the adhesive layer
It (2) is high-temperature-resisting silicon rubber.
10. recoverable airship solar heat protection according to claim 1 and carrying integral structure, it is characterised in that: the screw
For glass reinforced plastic screw or metallic screw.
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| CN201910272662.7A CN109927943B (en) | 2019-04-04 | 2019-04-04 | Heat-proof and bearing integrated structure of return airship |
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| CN201910272662.7A CN109927943B (en) | 2019-04-04 | 2019-04-04 | Heat-proof and bearing integrated structure of return airship |
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| CN109927943B CN109927943B (en) | 2022-03-04 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111016004A (en) * | 2019-12-26 | 2020-04-17 | 上海复合材料科技有限公司 | Heat-proof structure of fairing and forming method thereof |
| CN111114750A (en) * | 2019-12-20 | 2020-05-08 | 山东工业陶瓷研究设计院有限公司 | Thermal protection device and reentry vehicle |
| CN111532416A (en) * | 2020-05-12 | 2020-08-14 | 北京凌空天行科技有限责任公司 | Modular rigid ceramic tile assembly |
| CN111572822A (en) * | 2020-06-04 | 2020-08-25 | 哈尔滨工业大学 | Flexible heat-proof structure |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4002131A1 (en) * | 1990-01-25 | 1991-08-01 | Man Technologie Gmbh | High temp. resistant reflector foil - comprises highly reflective precious metal coating on ceramic support with IR-permeable stabilising layer on coating |
| EP0489531A1 (en) * | 1990-12-05 | 1992-06-10 | General Electric Company | Antenna sunshield membrane |
| US5547628A (en) * | 1993-03-09 | 1996-08-20 | Societe Europeenne De Propulsion | Method of manufacturing thermal shielding elements for space planes |
| US6663051B2 (en) * | 2001-08-06 | 2003-12-16 | Kawasaki Jukogyo Kabushiki Kaisha | Thermal protection structure |
| CN105659755B (en) * | 2003-12-18 | 2011-02-16 | 北京玻钢院复合材料有限公司 | Spacecraft reentry bluk recombination heat shield |
| CN102729482A (en) * | 2012-06-29 | 2012-10-17 | 中国人民解放军国防科学技术大学 | Composite heatproof bearing cylinder and preparation method thereof |
| CN103287568A (en) * | 2013-05-27 | 2013-09-11 | 北京玻钢院复合材料有限公司 | High-speed aircraft large-area interlayer heat protection and insulation structure and forming method thereof |
| CN203666965U (en) * | 2013-09-30 | 2014-06-25 | 中国人民解放军国防科学技术大学 | Thermal protection mechanism of hypersonic aircraft |
| CN207496916U (en) * | 2017-11-30 | 2018-06-15 | 江西洪都航空工业集团有限责任公司 | Thermal protection structure inside a kind of aircraft bay section |
| CN109367151A (en) * | 2018-10-31 | 2019-02-22 | 航天特种材料及工艺技术研究所 | A kind of heat-insulated antiscour heat shield and preparation method thereof |
| CN109454894A (en) * | 2018-10-31 | 2019-03-12 | 航天特种材料及工艺技术研究所 | A kind of compound layer of resistance to ablative thermal protection of effectively insulating and preparation method thereof |
-
2019
- 2019-04-04 CN CN201910272662.7A patent/CN109927943B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4002131A1 (en) * | 1990-01-25 | 1991-08-01 | Man Technologie Gmbh | High temp. resistant reflector foil - comprises highly reflective precious metal coating on ceramic support with IR-permeable stabilising layer on coating |
| EP0489531A1 (en) * | 1990-12-05 | 1992-06-10 | General Electric Company | Antenna sunshield membrane |
| US5547628A (en) * | 1993-03-09 | 1996-08-20 | Societe Europeenne De Propulsion | Method of manufacturing thermal shielding elements for space planes |
| US6663051B2 (en) * | 2001-08-06 | 2003-12-16 | Kawasaki Jukogyo Kabushiki Kaisha | Thermal protection structure |
| CN105659755B (en) * | 2003-12-18 | 2011-02-16 | 北京玻钢院复合材料有限公司 | Spacecraft reentry bluk recombination heat shield |
| CN102729482A (en) * | 2012-06-29 | 2012-10-17 | 中国人民解放军国防科学技术大学 | Composite heatproof bearing cylinder and preparation method thereof |
| CN103287568A (en) * | 2013-05-27 | 2013-09-11 | 北京玻钢院复合材料有限公司 | High-speed aircraft large-area interlayer heat protection and insulation structure and forming method thereof |
| CN203666965U (en) * | 2013-09-30 | 2014-06-25 | 中国人民解放军国防科学技术大学 | Thermal protection mechanism of hypersonic aircraft |
| CN207496916U (en) * | 2017-11-30 | 2018-06-15 | 江西洪都航空工业集团有限责任公司 | Thermal protection structure inside a kind of aircraft bay section |
| CN109367151A (en) * | 2018-10-31 | 2019-02-22 | 航天特种材料及工艺技术研究所 | A kind of heat-insulated antiscour heat shield and preparation method thereof |
| CN109454894A (en) * | 2018-10-31 | 2019-03-12 | 航天特种材料及工艺技术研究所 | A kind of compound layer of resistance to ablative thermal protection of effectively insulating and preparation method thereof |
Non-Patent Citations (3)
| Title |
|---|
| 史丽萍等: "金属热防护系统的研究进展", 《宇航材料工艺》 * |
| 曾昭焕: "可重复使用热防护系统防热结构", 《宇航材料工艺》 * |
| 李崇俊等: "航天飞行器热防护系统技术综述", 《高科技纤维与应用》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111114750A (en) * | 2019-12-20 | 2020-05-08 | 山东工业陶瓷研究设计院有限公司 | Thermal protection device and reentry vehicle |
| CN111016004A (en) * | 2019-12-26 | 2020-04-17 | 上海复合材料科技有限公司 | Heat-proof structure of fairing and forming method thereof |
| CN111532416A (en) * | 2020-05-12 | 2020-08-14 | 北京凌空天行科技有限责任公司 | Modular rigid ceramic tile assembly |
| CN111572822A (en) * | 2020-06-04 | 2020-08-25 | 哈尔滨工业大学 | Flexible heat-proof structure |
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| Publication number | Publication date |
|---|---|
| CN109927943B (en) | 2022-03-04 |
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