CN110553554A - Light thermal protection structure for hypersonic missile - Google Patents
Light thermal protection structure for hypersonic missile Download PDFInfo
- Publication number
- CN110553554A CN110553554A CN201910829947.6A CN201910829947A CN110553554A CN 110553554 A CN110553554 A CN 110553554A CN 201910829947 A CN201910829947 A CN 201910829947A CN 110553554 A CN110553554 A CN 110553554A
- Authority
- CN
- China
- Prior art keywords
- layer
- thermal protection
- composite material
- temperature
- protection structure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000002131 composite material Substances 0.000 claims abstract description 29
- 238000009413 insulation Methods 0.000 claims abstract description 23
- 239000011248 coating agent Substances 0.000 claims abstract description 18
- 238000000576 coating method Methods 0.000 claims abstract description 18
- 229910052751 metal Inorganic materials 0.000 claims abstract description 17
- 239000002184 metal Substances 0.000 claims abstract description 17
- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 12
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000000919 ceramic Substances 0.000 claims abstract description 5
- 229910016006 MoSi Inorganic materials 0.000 claims abstract description 4
- 239000004965 Silica aerogel Substances 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 6
- 229910052799 carbon Inorganic materials 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 4
- 239000004964 aerogel Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 239000010453 quartz Substances 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 241000405147 Hermes Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000004260 weight control Methods 0.000 description 1
Classifications
-
- 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
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different 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
- B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
-
- 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
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
-
- 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
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/005—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile
-
- 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
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different 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
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B9/041—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- 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
- B32B2255/00—Coating on the layer surface
- B32B2255/20—Inorganic coating
-
- 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
- B32B2307/304—Insulating
-
- 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
-
- 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
- B32B2307/70—Other properties
- B32B2307/714—Inert, i.e. inert to chemical degradation, corrosion
Abstract
The invention discloses a light thermal protection structure for a hypersonic missile, which comprises a high-temperature-resistant coating, a high-strength composite material layer, a heat insulation layer and a light metal layer which are sequentially arranged from outside to inside, wherein the high-temperature-resistant coating is SiC + MoSi 2, the high-strength composite material layer is a ceramic-based composite material, the heat insulation layer 3 is silica aerogel, and the light metal layer is a titanium alloy.
Description
Technical Field
The invention relates to the technical field of hypersonic missiles, in particular to a light thermal protection structure for a hypersonic missile.
Background
the design of a thermal protection structure is one of key technologies for solving the problem of pneumatic heating, wherein the thermal protection technology of a reentry warhead, a recoverable satellite, a space shuttle and a manned spacecraft is mature, but the volume and the weight of the thermal protection structure are larger, and the structure is complex; for example, the thermal protection system of the space shuttle accounts for 20% of the weight of the system, and brings a serious challenge to the structural design and weight control, so that the thermal protection structure determines the safety, the effective load and the economical efficiency of the aircraft, which are also important directions for the technical development of the missile, and the volume and the weight of the missile tend to be miniaturized; the light thermal protection structure is adopted on the hypersonic missile, the design of the thermal protection structure of the missile can be effectively simplified, and the weight of the missile is reduced, so that the light thermal protection structure has wide application prospects in the aspects of hypersonic missiles, hypersonic aircrafts in adjacent spaces and the like. In addition, the light thermal protection structure is improved and designed, and can also be applied to thermal protection structures of missiles or other aircrafts with low flying speed, thereby having important significance on the safety and the economy of the aircrafts;
At present, the thermal protection of hypersonic aerodynamic heat at home and abroad is mainly based on high-temperature resistant materials and composite materials, and the high-temperature resistant materials and the composite materials are combined to form various thermal protection structures, wherein the thermal protection structure of the American space shuttle is as follows: the outer layer is advanced carbon/carbon thermal structure, the middle is superalloy honeycomb and insulating layer, the inside is titanium alloy multilayer wall, british hot space shuttle's thermal protection structure does: the outer layer is a carbon/carbon thermal structure, the middle is a high-temperature alloy tile and a heat insulation felt, and the inner part is a titanium alloy multilayer wall; the heat protection structure of the German SANGER space shuttle is as follows: the outer layer is a carbon/carbon thermal structure, the middle is a high-temperature alloy tile, and the inner part is a titanium alloy multilayer wall; the heat protection structure of the French HERMES space shuttle is as follows: the outer layer is made of C/SiC composite material, the middle part is made of ceramic tiles, and the inner part is made of flexible heat insulation felt; and the traditional hot protective structure of domestic adoption comprises main structure, glue film, inner layer structure, heat insulation layer and skin etc. and the material of its each layer mainly has: in practical application, some layers of materials can be repeatedly superposed, the number of layers of the total materials can reach 5-7, and in addition, some domestic thermal protection structures are additionally provided with supporting plates, so that the structure and the forming process are complex, the volume is large, the weight is heavy, and the price is expensive;
Chinese patent (publication No. CN103770954A) discloses a large-area thermal protection device for hypersonic aircraft, which comprises an outer thermal insulation layer, an inner thermal insulation layer, and a titanium alloy layer, wherein: the outer heat-insulating layer and the inner heat-insulating layer are made of quartz composite materials, the outer heat-insulating layer is made of aerogel materials, namely one layer of aerogel is sandwiched between two layers of quartz composite materials, the structural strength of the quartz composite materials is utilized to enable the aerogel layer to be formed, the titanium alloy layer is utilized as a main bearing structure, although the patent can play a certain role in protecting aerodynamic heat, the patent depends on the titanium alloy layer as the main bearing structure, and the integral structural strength of the patent is insufficient.
Disclosure of Invention
In order to overcome the defects in the background art, the invention discloses a light thermal protection structure for a hypersonic missile.
In order to achieve the purpose, the invention adopts the following technical scheme:
A light thermal protection structure for a hypersonic missile comprises a high-temperature-resistant coating, a high-strength composite material layer, a heat insulation layer and a light metal layer which are sequentially arranged from outside to inside, wherein the high-temperature-resistant coating is SiC + MoSi 2, the high-strength composite material layer is a ceramic-based composite material, the heat insulation layer is silica aerogel, the light metal layer is a titanium alloy, and the thickness ratio of each layer of the high-temperature-resistant coating, the high-strength composite material layer, the heat insulation layer and the light metal layer is 1: 4-5: 5-4: 2.
Preferably, the thickness ratio of each layer of the high-temperature-resistant coating, the high-strength composite material layer, the heat insulation layer and the light metal layer is 1:4:5: 2.
Preferably, the thickness ratio of each layer of the high-temperature-resistant coating, the high-strength composite material layer, the heat insulation layer and the light metal layer is 1:5:4: 2.
due to the adoption of the technical scheme, the invention has the following beneficial effects:
The light thermal protection structure for the hypersonic missile, disclosed by the invention, has the advantages of simple structure, good thermal insulation effect, simpler and more convenient processing technology and forming, easiness in realization of technology, smaller deformation during compression resistance, light weight, higher strength, capability of bearing long-time pneumatic load and capability of reducing the influence of pneumatic heat on internal components of the missile; the high-strength composite material is used as a structural support, the requirement of bearing the pneumatic load generated by hypersonic flight of the missile can be met, and the deformation is small; the high-temperature resistant coating material can withstand high-temperature heat flow and can radiate partial heat energy outwards; the thermal insulation material can retard the transfer of heat energy to the inside of the missile body, and the influence of the aerodynamic heat generated by the flight of the hypersonic missile on the load in the missile body is reduced; the light metal layer is titanium alloy, and the titanium alloy has the excellent properties of high strength, good corrosion resistance, high heat resistance and the like, and can play a main supporting role on parts in the missile; the light thermal protection structure can be widely applied to thermal protection structures of air-to-air missiles, air-to-ground missiles and other hypersonic aircrafts flying at high speed or hypersonic speed; in addition, the invention can also be used for the thermal protection of a hypersonic speed aircraft in a near space or other high-speed aircraft.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
fig. 2 is an enlarged schematic view of a portion a of fig. 1.
In the figure: 1. a high temperature resistant coating; 2. a high strength composite layer; 3. a thermal insulation layer; 4. a light metal layer.
Detailed Description
The present invention will be explained in detail by the following examples, which are disclosed for the purpose of protecting all technical improvements within the scope of the present invention.
The light thermal protection structure for the hypersonic missile comprises a high-temperature-resistant coating 1, a high-strength composite material layer 2, a thermal insulation layer 3 and a light metal layer 4 which are sequentially arranged from outside to inside, wherein the high-temperature-resistant coating 1 is SiC + MoSi 2 and can bear high temperature and radiate partial energy to the outside so as to reduce the transmission of high-temperature heat to the inside, the high-strength composite material layer 2 is a ceramic-based composite material which has high strength and rigidity and can play a supporting role, namely, the missile body can be kept basically not deformed when the high-temperature-and-pressure combined action of high-speed airflow is applied, the thermal insulation layer 3 is silica aerogel and can effectively retard the transmission of the high-temperature heat to the inside and prolong the heat conduction time, the light metal layer 4 is titanium alloy and plays a main supporting role for parts inside the missile, the thickness ratio of the high-temperature-resistant coating 1 to the high-strength composite material layer 2 to the thermal insulation layer 3 to the light metal layer 4 is 1: 4-5: 5-4: 2, and the thickness ratio of the high-strength composite material layer 2 to the thermal insulation layer 2 is adjustable when the high-temperature-and the high-temperature-resistant coating 1 to-and the high-strength composite material 2 is overloaded under normal flight conditions as required.
The light thermal protection structure for the hypersonic missile is implemented only by manufacturing the light thermal protection structure into a shell of a body to be protected by the thermal protection structure.
The present invention is not described in detail in the prior art.
Claims (3)
1. A light thermal protection structure for a hypersonic missile is characterized by comprising a high-temperature-resistant coating (1), a high-strength composite material layer (2), a heat insulation layer (3) and a light metal layer (4) which are sequentially arranged from outside to inside, wherein the high-temperature-resistant coating (1) is SiC + MoSi 2, the high-strength composite material layer (2) is a ceramic-based composite material, the heat insulation layer 3 is silica aerogel, the light metal layer (4) is a titanium alloy, and the thickness ratio of each layer of the high-temperature-resistant coating (1), the high-strength composite material layer (2), the heat insulation layer (3) and the light metal layer (4) is 1: 4-5: 5-4: 2.
2. The lightweight thermal protection structure of claim 1, further characterized by: the thickness ratio of each layer of the high-temperature-resistant coating (1), the high-strength composite material layer (2), the heat insulation layer (3) and the light metal layer (4) is 1:4:5: 2.
3. The lightweight thermal protection structure of claim 1, further characterized by: the thickness ratio of each layer of the high-temperature-resistant coating (1), the high-strength composite material layer (2), the heat insulation layer (3) and the light metal layer (4) is 1:5:4: 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910829947.6A CN110553554A (en) | 2019-09-03 | 2019-09-03 | Light thermal protection structure for hypersonic missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910829947.6A CN110553554A (en) | 2019-09-03 | 2019-09-03 | Light thermal protection structure for hypersonic missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110553554A true CN110553554A (en) | 2019-12-10 |
Family
ID=68738910
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910829947.6A Pending CN110553554A (en) | 2019-09-03 | 2019-09-03 | Light thermal protection structure for hypersonic missile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110553554A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901885A (en) * | 2019-12-23 | 2020-03-24 | 湖北航天技术研究院总体设计所 | Thermal protection system of aircraft |
| CN113466894A (en) * | 2021-06-09 | 2021-10-01 | 航天恒星科技有限公司 | Protection system of emergency positioning transmitter |
| CN113804065A (en) * | 2020-06-12 | 2021-12-17 | 北京星途探索科技有限公司 | Novel heat insulation patch applied to supersonic missile |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4939038A (en) * | 1986-01-22 | 1990-07-03 | Inabata Techno Loop Corporation | Light metallic composite material and method for producing thereof |
| US20040258900A1 (en) * | 2003-04-24 | 2004-12-23 | Simon Reinhard A. | Multi-layer ceramic composite material with a thermal-protective effect |
| CN101648598A (en) * | 2009-09-10 | 2010-02-17 | 国营江北机械厂 | Novel inorganic thermal protection structure and manufacturing 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 |
| CN103727357A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Ultrathin high-temperature-resistant thermal insulation material structure |
| CN103770954A (en) * | 2013-09-30 | 2014-05-07 | 中国人民解放军国防科学技术大学 | Large-area thermal protection device of hypersonic flight vehicle |
| US20140287641A1 (en) * | 2013-03-15 | 2014-09-25 | Aerogel Technologies, Llc | Layered aerogel composites, related aerogel materials, and methods of manufacture |
| CN107081941A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | Structure and its application of a kind of metal surface with thermal protection coating material |
| CN108911760A (en) * | 2018-08-08 | 2018-11-30 | 航天材料及工艺研究所 | The non-ablative type thermally protective materials of carbon fiber-reinforced resin gradient carbonization and preparation method |
| CN109823510A (en) * | 2019-03-06 | 2019-05-31 | 中南大学 | Hypersonic aircraft and its thermal protection structure and coolant circulating system |
| CN211234149U (en) * | 2019-09-03 | 2020-08-11 | 中国空空导弹研究院 | Light thermal protection structure for hypersonic missile |
-
2019
- 2019-09-03 CN CN201910829947.6A patent/CN110553554A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4939038A (en) * | 1986-01-22 | 1990-07-03 | Inabata Techno Loop Corporation | Light metallic composite material and method for producing thereof |
| US20040258900A1 (en) * | 2003-04-24 | 2004-12-23 | Simon Reinhard A. | Multi-layer ceramic composite material with a thermal-protective effect |
| CN101648598A (en) * | 2009-09-10 | 2010-02-17 | 国营江北机械厂 | Novel inorganic thermal protection structure and manufacturing method thereof |
| US20140287641A1 (en) * | 2013-03-15 | 2014-09-25 | Aerogel Technologies, Llc | Layered aerogel composites, related aerogel materials, and methods of manufacture |
| 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 |
| CN103727357A (en) * | 2013-09-11 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Ultrathin high-temperature-resistant thermal insulation material structure |
| CN103770954A (en) * | 2013-09-30 | 2014-05-07 | 中国人民解放军国防科学技术大学 | Large-area thermal protection device of hypersonic flight vehicle |
| CN107081941A (en) * | 2016-02-16 | 2017-08-22 | 中国科学院大连化学物理研究所 | Structure and its application of a kind of metal surface with thermal protection coating material |
| CN108911760A (en) * | 2018-08-08 | 2018-11-30 | 航天材料及工艺研究所 | The non-ablative type thermally protective materials of carbon fiber-reinforced resin gradient carbonization and preparation method |
| CN109823510A (en) * | 2019-03-06 | 2019-05-31 | 中南大学 | Hypersonic aircraft and its thermal protection structure and coolant circulating system |
| CN211234149U (en) * | 2019-09-03 | 2020-08-11 | 中国空空导弹研究院 | Light thermal protection structure for hypersonic missile |
Non-Patent Citations (1)
| Title |
|---|
| 侯党社等: "硅钼含量对C/C复合材料SiC-MoSi_2涂层结构和高温抗氧化性能的影响", 固体火箭技术, vol. 31, no. 3, pages 283 - 287 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901885A (en) * | 2019-12-23 | 2020-03-24 | 湖北航天技术研究院总体设计所 | Thermal protection system of aircraft |
| CN110901885B (en) * | 2019-12-23 | 2021-11-30 | 湖北航天技术研究院总体设计所 | Thermal protection system of aircraft |
| CN113804065A (en) * | 2020-06-12 | 2021-12-17 | 北京星途探索科技有限公司 | Novel heat insulation patch applied to supersonic missile |
| CN113466894A (en) * | 2021-06-09 | 2021-10-01 | 航天恒星科技有限公司 | Protection system of emergency positioning transmitter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110553554A (en) | Light thermal protection structure for hypersonic missile | |
| CN202955418U (en) | Steam direct buried pipe composite thermal insulation structure | |
| CN202946516U (en) | Screw thermal protection device | |
| CN101854131B (en) | High-temperature-resistant selective solar energy-absorbing film and preparation method thereof | |
| US6676077B1 (en) | High temperature resistant airfoil apparatus for a hypersonic space vehicle | |
| CN105888885B (en) | The new Joining Structure of rocket engine composite jet pipe extension and short nozzle thrust room | |
| CN109437951A (en) | A kind of lightweight heat-insulation integrative of resistance to ablation structure | |
| CN211234149U (en) | Light thermal protection structure for hypersonic missile | |
| CN109466130A (en) | A kind of moderate temperature integral structure of resistance to thermal current | |
| CN108995792A (en) | The airvane of composite structure | |
| CN212046202U (en) | Phase-change heat-insulation composite thermal protection structure of hypersonic aircraft | |
| CN105020540A (en) | Glass fiber composite thermal insulation felt with hollow microspheres as basic core and preparation method thereof | |
| CN103009717A (en) | Lightweight high-temperature resistant carbon fiber and metal mixed laminate | |
| CN104862687A (en) | Preparation method of surface coating layer of metal heat shielding structure | |
| CN111775511B (en) | Integrated bullet structure formed by composite filling dot matrix interlayer | |
| CN114180026B (en) | Composite flexible heat protection structure for dredging phase change and application of composite flexible heat protection structure in deformable aircraft | |
| CN203515812U (en) | Gas exhausting device with multilayered heat preservation and insulation layer of gas turbine | |
| CN203032022U (en) | High temperature resistant light carbon fiber-metal mixed laminate | |
| CN108248825A (en) | A kind of aircraft aerofoil structure | |
| CN204433029U (en) | A kind of structure solar heat protection configuration | |
| CN109216880B (en) | Antenna window assembly suitable for long-term pneumatic thermal environment and design method thereof | |
| CN202466863U (en) | High-temperature-resistant phenolic foam composite thermal-insulating body | |
| CN207246665U (en) | High performance vapor utilidor | |
| CN106394938A (en) | Thermal protection device of attitude control system for hypersonic-speed and large-attack-angle reentry vehicle | |
| CN208901754U (en) | Dry garden stuff processing energy saving baking room |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |