CN113978696B - Spacecraft and thermal resistance type end cap mounting structure thereof - Google Patents
Spacecraft and thermal resistance type end cap mounting structure thereof Download PDFInfo
- Publication number
- CN113978696B CN113978696B CN202111315339.7A CN202111315339A CN113978696B CN 113978696 B CN113978696 B CN 113978696B CN 202111315339 A CN202111315339 A CN 202111315339A CN 113978696 B CN113978696 B CN 113978696B
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- Prior art keywords
- heat
- end cap
- cabin section
- heat insulation
- mounting structure
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Links
- 238000009413 insulation Methods 0.000 claims abstract description 38
- 230000004888 barrier function Effects 0.000 claims abstract description 19
- 230000005855 radiation Effects 0.000 claims abstract description 18
- 239000012212 insulator Substances 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 11
- 239000000565 sealant Substances 0.000 claims description 8
- 239000004744 fabric Substances 0.000 claims description 5
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 3
- 239000004964 aerogel Substances 0.000 claims description 3
- 239000005011 phenolic resin Substances 0.000 claims description 3
- 229920001568 phenolic resin Polymers 0.000 claims description 3
- 238000012546 transfer Methods 0.000 abstract description 13
- 238000007789 sealing Methods 0.000 abstract description 8
- 239000010410 layer Substances 0.000 description 17
- 238000000034 method Methods 0.000 description 6
- 239000000956 alloy Substances 0.000 description 4
- 239000003292 glue Substances 0.000 description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 3
- 238000002679 ablation Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 210000001503 joint Anatomy 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000003032 molecular docking Methods 0.000 description 2
- 238000009991 scouring Methods 0.000 description 2
- 235000012239 silicon dioxide Nutrition 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 229910052681 coesite Inorganic materials 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 229910052906 cristobalite Inorganic materials 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 239000010453 quartz Substances 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 229910052682 stishovite Inorganic materials 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 229910052905 tridymite Inorganic materials 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- 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
- 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
- B64C1/403—Arrangement of fasteners specially adapted therefor, e.g. of clips
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Thermal Insulation (AREA)
Abstract
The application relates to a spacecraft and thermal resistance formula end cap mounting structure thereof, it includes: the end cap is internally provided with a first heat insulation piece; a rear cabin section; the second heat insulation piece is arranged between the end cap and the rear cabin section to form a heat radiation barrier layer; a third heat insulator disposed between the tip cap and the rear compartment section to form a heat conduction barrier layer covering the heat radiation barrier layer; and the connecting piece penetrates through the first heat insulating piece and the third heat insulating piece and connects the end cap with the rear cabin section. The formed heat radiation barrier layer prevents heat radiation, and the heat conduction barrier layer covers the heat radiation barrier layer, so that the end cap and the rear cabin section are in indirect contact when connected, and heat radiation is isolated while heat conduction is isolated; the first thermal shield separates the connector from the tip cap portion to reduce heat transfer from the connector to achieve sealing and thermal protection goals under harsh thermal operating environment conditions.
Description
Technical Field
The application relates to the field of aerospace thermal protection, in particular to a spacecraft and a thermal resistance type end cap mounting structure thereof.
Background
The working environment of the nose cone part of the aerospace craft is very harsh, the temperature is high, the heat flow is large, and the scouring is serious, so that the nose cone material is required to have good anti-ablation, anti-erosion and anti-heat load performances, so that the nose cone material can bear the scouring damage strongly caused by high-temperature ablation and high-speed airflow, and the tip of the aerospace craft is often made of a high-temperature alloy material with excellent high-temperature resistance.
In some related technologies, the nose cone part of the aerospace craft and the rear cabin section are in butt joint through a connecting structure to form a whole, but the following problems exist:
the nose cone part of the aerospace craft made of the superalloy material generally has high heat conductivity, and a large amount of heat can be transferred when the nose cone part is directly in butt joint with the rear cabin section in the aerospace, so that a single machine in the rear cabin section fails and other faults are caused, and therefore a certain heat protection design is needed to block the heat transfer.
Disclosure of Invention
The embodiment of the application provides a spacecraft and a thermal resistance type end cap mounting structure thereof, which are used for solving the problem that equipment in a rear cabin section is failed due to the fact that a nose cone part of the spacecraft made of a high-temperature alloy material transfers heat to the rear cabin section in the related technology.
In a first aspect, there is provided a thermal resistance tip cap mounting structure comprising:
the end cap is internally provided with a first heat insulation piece;
a rear cabin section;
the second heat insulation piece is arranged between the end cap and the rear cabin section to form a heat radiation barrier layer;
a third heat insulator disposed between the tip cap and the rear compartment section to form a heat conduction barrier layer covering the heat radiation barrier layer;
and the connecting piece penetrates through the first heat insulating piece and the third heat insulating piece and connects the end cap with the rear cabin section.
In some embodiments, a mounting groove is formed on the end of the end cap or the rear cabin section, and the second heat insulation member is arranged in the mounting groove.
In some embodiments, the mounting groove comprises an annular groove and a circular groove, the annular groove and the circular groove are concentrically arranged, and a radius of the annular groove is greater than a radius of the circular groove;
the second heat insulation piece comprises sealant and a heat insulation block, wherein the sealant is filled in the annular groove, and the heat insulation block is positioned in the circular groove.
In some embodiments, the sealant is a high temperature putty material and the insulation block is an aerogel.
In some embodiments, the third insulation covers the end of the tip cap or rear section and is a thermal cloth.
In some embodiments, the connector is a high strength bolt with one end having a head located within the tip cap;
the first heat insulating piece is provided with a sinking groove for accommodating the head part of the high-strength bolt.
In some embodiments, a flexible gasket is also included, the flexible gasket disposed between the first insulation and the inner wall of the tip cap.
In some embodiments, the rear cabin section is externally coated with a heat-proof layer, and the sum of the end areas of the heat-proof layer and the rear cabin section is equal to the end area of the end cap;
the third insulation covers an end of the rear deck section.
In some embodiments, the heat protective layer is a phenolic resin based heat protective material.
In a second aspect, there is provided a spacecraft comprising: a thermal resistance type end cap mounting structure.
The beneficial effects that technical scheme that this application provided brought include:
the embodiment of the application provides a thermal resistance type end cap mounting structure, wherein a second heat insulation piece is arranged between the end cap and the end part of a rear cabin section, which is in direct contact, so that a heat radiation barrier layer is formed, and a space between the end cap and the rear cabin section is blocked, and heat radiation is avoided; the third heat insulation piece is arranged between the end cap and the rear cabin section to form a heat conduction barrier layer, and the heat conduction barrier layer covers the heat radiation barrier layer, so that when the end cap and the rear cabin section are connected by the connecting piece, the end cap and the rear cabin section are in indirect contact, heat conduction is not carried out, heat radiation is isolated while heat conduction is isolated, and the heat blocking effect is further enhanced.
In addition, as the connecting piece extends into the rear cabin section and has certain heat conduction, the first heat insulation piece separates the connecting piece from the end cap part so as to reduce heat transfer, and the heat transfer of the end cap to the rear cabin section can be greatly reduced by adopting the mounting structure.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural diagram of a thermal resistance type end cap mounting structure according to an embodiment of the present application.
In the figure: 1. an end cap; 2. a first heat insulating member; 3. a rear cabin section; 4. a mounting groove; 41. an annular groove; 42. a circular groove; 5. a second heat insulating member; 6. a third heat insulating member; 7. a connecting piece; 8. a flexible gasket; 9. and a heat-resistant layer.
Detailed Description
For the purposes of making the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present application based on the embodiments herein.
The embodiment of the application provides a spacecraft and a thermal resistance type end cap mounting structure thereof, which are used for solving the problem that equipment in a rear cabin section is failed due to the fact that a nose cone part of the spacecraft made of a high-temperature alloy material transfers heat to the rear cabin section in the related technology.
Referring to fig. 1, a thermal resistance type end cap mounting structure includes an end cap 1, a first heat insulating member 2, a rear compartment section 3, a second heat insulating member 5, a third heat insulating member 6, and a connecting member 7;
wherein the end cap 1 is hollow, and the end part is provided with an opening, which is a high-temperature alloy material with good high-temperature resistance; the inside of the rear cabin section 3 is hollow, and the end part for contacting with the end cap 1 is also provided with an opening, so that the weight reduction problem of the aircraft is considered, and therefore, the heat transfer of the end cap 1 into the rear cabin section 3 is in two forms, one is that the end cap 1 is directly contacted with the rear cabin section 3, and the direct conduction is carried out through structural materials; the other is that after the spaces in the end cap 1 and the rear cabin section 3 are communicated, heat transfer is performed in the form of heat radiation.
For the former case, where heat transfer is performed directly, there is another case where, since the end cap 1 and the rear compartment 3 are connected by the connection member 7, a part of the connection member 7 is extended into the bulkhead of the rear compartment 3, and heat is transferred to the rear compartment through the connection member 7.
The following specific settings were thus made:
the second heat insulation member 5 is arranged between the end cap 1 and the rear cabin section 3 to form a heat radiation barrier layer; a third thermal insulation 6 is provided between the end cap 1 and the rear section 3 to form a heat conduction barrier layer covering the heat radiation barrier layer. The connection member 7 penetrates the first and third heat insulating members 2 and 6 and connects the end cap 1 and the rear compartment section 3 to insulate heat from direct conduction and heat radiation.
The first heat insulating piece 2 is arranged in the end cap 1, the first heat insulating piece 2 reduces the contact between the connecting piece 7 and the inner wall of the end cap 1, and the vast majority of the connecting piece 7 at one end of the end cap 1 is wrapped, so that the heat transfer area is reduced, and the heat transfer is reduced.
The number of the connectors 7 can be plural and distributed on a circle centered on the center of the end face of the end cap 1 and uniformly spaced. The number of first heat insulating members 2 corresponds to the number of connecting members 7.
Therefore, through the structural arrangement, the heat transferred from the end cap 1 to the rear cabin section 3 is greatly reduced, the structure is simple, the original connection mode of the end cap 1 and the rear cabin section 3 is not affected, and the heat resistance reliability is stable.
In some preferred embodiments, to facilitate the installation of the second insulation 5 and the docking of the end cap 1 with the rear section 3, a mounting groove 4 is provided on the end of the end cap 1 or the rear section 3, which does not require docking during installation, saving the steps of installation.
Further, wherein the mounting groove 4 includes an annular groove 41 and a circular groove 42, the annular groove 41 and the circular groove 42 are concentrically arranged, and a radius of the annular groove 41 is larger than a radius of the circular groove 42; the opening on the end of the end cap 1 or the rear section 3 is located in the circular groove 42;
the second heat insulating piece 5 comprises sealing glue and a heat insulating block, the sealing glue is filled in the annular groove 41, the heat insulating block is positioned in the circular groove 42, so that the sealing glue can ensure the tightness of the joint between the end cap 1 and the rear cabin section 3, heat transfer can be reduced, the heat insulating block separates the space between the end cap 1 and the rear cabin section 3, and due to the arrangement of the circular groove 42 and the annular groove 41, the heat insulating block and the sealing glue are placed in advance when the end cap 1 and the rear cabin section 3 are connected, and then only the joint is needed.
The sealant is a high-temperature putty material, has high temperature resistance and sealing performance, and the heat insulation block is a SiO2 aerogel material with excellent heat insulation property;
further, a third heat insulating member 6 covers the end of the end cap 1 or the rear cabin section 3, and is a heat insulating cloth, and can be connected with the rear cabin section 3 in a sealing manner through a sealant, and the heat insulating block is fixed in the circular groove 42. The heat insulation cloth is B-type quartz fiber cloth with excellent heat insulation performance, so that the end cap 1 and the rear cabin section 3 are not directly connected.
In some preferred embodiments, the connection 7 may be a high strength bolt, one end of which has a head located within the tip cap 1; the first heat insulation piece 2 is provided with a sinking groove for accommodating the head part of the high-strength bolt, namely the sinking groove is a hexagonal groove; the first heat insulating piece 2 can enclose the side edge and one side of the high-strength bolt, so that heat transfer is avoided.
Further, the mounting structure further comprises a flexible gasket 8, wherein the flexible gasket 8 is arranged between the first heat insulation piece 2 and the inner wall of the end cap 1, the flexible gasket 8 is made of red copper material, has good ductility and is softer in texture, is mounted between the first heat insulation piece 2 and the end cap 1 and is used for adapting to thermal deformation of the end cap and preventing connection looseness.
In some preferred embodiments, the end cap 1 and the rear compartment 3 may be of the same cross-sectional area, but in this way heat may enter from the whole body of the rear compartment 3, transferring heat, plus heat generated by friction with air, and thus the following arrangement is also made:
the rear cabin section 3 is coated with a heat-proof layer 9, and the sum of the end areas of the heat-proof layer 9 and the rear cabin section 3 is equal to the end area of the end cap 1; at this time, the third heat insulating member 6 covers the end of the rear cabin section 3, but does not cover the end of the heat insulating layer 9, and the heat insulating layer 9 can be made of high-temperature resistant and ablation resistant phenolic resin heat insulating material, so that the whole body of the rear cabin section 3 can be protected and thermally isolated, and the end, which is contacted or close to the end cap 1, of the rear cabin section 3 is comprehensively thermally isolated and protected by being matched with the third heat insulating member 6, so that the heat insulating effect is greatly improved.
The application also proposes a spacecraft comprising: the thermal resistance type end cap mounting structure.
The heat transferred from the end cap 1 of the spacecraft to the rear cabin section 3 is greatly reduced, the structure is simple, the original connection mode of the end cap 1 and the rear cabin section 3 is not affected, the heat resistance reliability is stable, the butt joint of the end cap 1 and the rear cabin section 3 in the spacecraft is realized, and the sealing and heat protection targets under the severe heat working environment condition are achieved.
It should be appreciated that depending on the size of the aircraft and the tolerance to high temperatures, the mounting assemblies are designed with different structural dimensions to match for adaptation.
In the description of the present application, it should be noted that the azimuth or positional relationship indicated by the terms "upper", "lower", etc. are based on the azimuth or positional relationship shown in the drawings, and are merely for convenience of description of the present application and simplification of the description, and are not indicative or implying that the apparatus or element in question must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present application. Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.
It should be noted that in this application, relational terms such as "first" and "second" and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
The foregoing is merely a specific embodiment of the application to enable one skilled in the art to understand or practice the application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (7)
1. A thermal resistance tip cap mounting structure, comprising:
a first heat insulation piece (2) is arranged in the end cap (1);
a rear cabin section (3);
a second heat insulator (5) provided between the end cap (1) and the rear compartment section (3) to form a heat radiation barrier;
a third thermal insulation (6) arranged between the end cap (1) and the rear compartment section (3) to form a heat conduction barrier layer covering the heat radiation barrier layer;
a connecting member (7) passing through the first and third heat insulators (2, 6) and connecting the end cap (1) and the rear compartment section (3);
the first heat insulation piece (2) wraps most of one end of the connecting piece (7) positioned at the end cap (1), so that contact between the connecting piece (7) and the inner wall of the end cap (1) is reduced;
the end part of the end cap (1) or the rear cabin section (3) is provided with a mounting groove (4), and the second heat insulation piece (5) is arranged in the mounting groove (4);
the mounting groove (4) comprises an annular groove (41) and a circular groove (42), the annular groove (41) and the circular groove (42) are concentrically arranged, and the radius of the annular groove (41) is larger than that of the circular groove (42);
the second heat insulation piece (5) comprises sealant and a heat insulation block, wherein the sealant is filled in the annular groove (41), and the heat insulation block is positioned in the circular groove (42);
the heat insulation device further comprises a flexible gasket (8), wherein the flexible gasket (8) is arranged between the first heat insulation piece (2) and the inner wall of the end cap (1).
2. The thermal resistance tip cap mounting structure according to claim 1, wherein:
the sealant is a high-temperature putty material, and the heat insulation block is aerogel.
3. The thermal resistance tip cap mounting structure according to claim 1, wherein:
the third heat insulation member (6) covers the end part of the end cap (1) or the rear cabin section (3) and is heat insulation cloth.
4. The thermal resistance tip cap mounting structure according to claim 1, wherein:
the connecting piece (7) is a high-strength bolt, and one end with a head is positioned in the end cap (1);
the first heat insulating piece (2) is provided with a sinking groove for accommodating the head part of the high-strength bolt.
5. The thermal resistance tip cap mounting structure according to claim 1, wherein:
the rear cabin section (3) is externally coated with a heat-proof layer (9), and the sum of the end areas of the heat-proof layer (9) and the rear cabin section (3) is equal to the end area of the end cap (1);
the third insulation (6) covers the end of the rear compartment section (3).
6. The thermal resistance tip cap mounting structure according to claim 5, wherein:
the heat-proof layer (9) is made of phenolic resin-based heat-proof materials.
7. A spacecraft, characterized in that it comprises: a thermal resistance tip cap mounting structure according to any one of claims 1-6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111315339.7A CN113978696B (en) | 2021-11-08 | 2021-11-08 | Spacecraft and thermal resistance type end cap mounting structure thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111315339.7A CN113978696B (en) | 2021-11-08 | 2021-11-08 | Spacecraft and thermal resistance type end cap mounting structure thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113978696A CN113978696A (en) | 2022-01-28 |
| CN113978696B true CN113978696B (en) | 2024-04-09 |
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ID=79747183
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111315339.7A Active CN113978696B (en) | 2021-11-08 | 2021-11-08 | Spacecraft and thermal resistance type end cap mounting structure thereof |
Country Status (1)
| Country | Link |
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| CN (1) | CN113978696B (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05203095A (en) * | 1992-01-24 | 1993-08-10 | Natl Space Dev Agency Japan<Nasda> | Heat protecting system |
| CN106314758A (en) * | 2016-09-29 | 2017-01-11 | 湖北航天技术研究院总体设计所 | End cap heat resistance connecting device |
| CN206885331U (en) * | 2017-05-05 | 2018-01-16 | 肇庆市广应科通用航空研究院 | A kind of compound heat shield of spacecraft |
| CN109367758A (en) * | 2018-11-27 | 2019-02-22 | 北京空间技术研制试验中心 | A kind of thermal protection component and thermal protection system |
| CN109573094A (en) * | 2018-12-05 | 2019-04-05 | 湖北航天技术研究院总体设计所 | A kind of temperature barrier based on the docking of aircraft bay section |
| 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 |
| CN210364351U (en) * | 2019-08-26 | 2020-04-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Thermal protection structure |
| CN211893639U (en) * | 2019-11-25 | 2020-11-10 | 中国空气动力研究与发展中心 | Ultrahigh-temperature end heat sealing structure of hypersonic aircraft |
| CN112399744A (en) * | 2020-11-10 | 2021-02-23 | 北京动力机械研究所 | Composite high-temperature-resistant heat-resistant support structure |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005068290A1 (en) * | 2004-01-05 | 2005-07-28 | Airbus Deutschland Gmbh | Insulation package arrangement for insulating the interior of an aircraft fuselage |
| US9835425B2 (en) * | 2015-08-14 | 2017-12-05 | Raytheon Company | Metallic nosecone with unitary assembly |
-
2021
- 2021-11-08 CN CN202111315339.7A patent/CN113978696B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05203095A (en) * | 1992-01-24 | 1993-08-10 | Natl Space Dev Agency Japan<Nasda> | Heat protecting system |
| CN106314758A (en) * | 2016-09-29 | 2017-01-11 | 湖北航天技术研究院总体设计所 | End cap heat resistance connecting device |
| CN206885331U (en) * | 2017-05-05 | 2018-01-16 | 肇庆市广应科通用航空研究院 | A kind of compound heat shield of spacecraft |
| CN109367758A (en) * | 2018-11-27 | 2019-02-22 | 北京空间技术研制试验中心 | A kind of thermal protection component and thermal protection system |
| CN109573094A (en) * | 2018-12-05 | 2019-04-05 | 湖北航天技术研究院总体设计所 | A kind of temperature barrier based on the docking of aircraft bay section |
| CN210364351U (en) * | 2019-08-26 | 2020-04-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Thermal protection structure |
| CN211893639U (en) * | 2019-11-25 | 2020-11-10 | 中国空气动力研究与发展中心 | Ultrahigh-temperature end heat sealing structure of hypersonic aircraft |
| 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 |
| CN112399744A (en) * | 2020-11-10 | 2021-02-23 | 北京动力机械研究所 | Composite high-temperature-resistant heat-resistant support structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113978696A (en) | 2022-01-28 |
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