CN109367758A - A kind of thermal protection component and thermal protection system - Google Patents
A kind of thermal protection component and thermal protection system Download PDFInfo
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- CN109367758A CN109367758A CN201811427161.3A CN201811427161A CN109367758A CN 109367758 A CN109367758 A CN 109367758A CN 201811427161 A CN201811427161 A CN 201811427161A CN 109367758 A CN109367758 A CN 109367758A
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- thermal protection
- cover board
- protection component
- thermal
- insulation layer
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- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Thermal Insulation (AREA)
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Abstract
The present invention relates to a kind of thermal protection component and thermal protection systems, wherein thermal protection component, including cover board (111), and it is set to the cover board bearing (112) on the cover board (111), and the heat insulation structural (113) being connected with cover board bearing (112)；The cover board (111) is ceramic matric composite plate, and its side for supporting (112) far from the cover board is provided with antioxidant coating.Thermal protection component of the invention has the advantages that reusable, structural module, light weight, at low cost, easily changeable, so that the present invention is had broad application prospects in hypersonic aircraft field, meets aircraft simultaneously for the strict demand for preventing heat-insulated, lightweight, carrying and shock resistance etc..Further make the applicability that has a wide range of application of the invention higher.
Description
Technical field
The present invention relates to thermal protection system design field more particularly to a kind of thermal protection components and thermal protection system.
Background technique
Hypersonic aircraft surface is acted on by harsh Aerodynamic Heating, and the major function of thermal protection system (TPS) is solution
Certainly hypersonic cruise reenters the Aerodynamic Heating problem faced in return course, and maintaining bottom main structure is allowed
Within the temperature range of, and ensure Cang Nei mechanism, electrical, control device normal operation circumstances.Reusable launch vehicles are flying
During row, in the high temperature for emitting with being then subjected to l670 DEG C or more in return course, isolation is up to the noise of 167dB, resists greatly
The washing away of various particles, the radiation for resisting various rays etc. in gas.Therefore, lightweight, durable, easy to operate, reusable heat are anti-
The development of protecting system and optimization design are the key that advanced hypersonic aircraft and weapon system success or failure.
The Metallic Thermal Protection Systems of current research have many advantages, such as high reliablity, good toughness, with the same of anti-heat function
When there is certain bearing capacity, but limited by metal material performance, metal TPS is generally only applied to be about 980 DEG C using temperature
Region in temperature range.And for hypersonic aircraft, it usually needs using the thermal protection system of more operation at high temperature range
System.In addition, Metallic Thermal Protection Systems can be such that mass of system obviously increases using high temperature alloy matrix composite, there is also thermal expansions
Coefficient is big, leads to the problem of being unfavorable for clearance seal and thermally matched design.
Summary of the invention
The purpose of the present invention is to provide a kind of thermal protection component and thermal protection systems, solve existing thermal protection system application
The problem that temperature range is not high enough, thermal expansion is serious.
For achieving the above object, the present invention provides a kind of thermal protection component, including cover board, and is set to the lid
Cover board bearing on plate, and the heat insulation structural being connected is supported with the cover board；
The cover board is ceramic matric composite plate, and it is provided with anti-oxidant painting far from the side that the cover board supports
Layer.
According to an aspect of the present invention, the cover board bearing includes supporting part and coupling part；
The supporting part is circumferential wall, and one end is mutually connected vertically with the coupling part, the other end and institute
It states cover board and is mutually permanently connected and constitute groove structure.
According to an aspect of the present invention, the cover board is trapezoidal plate, has the first edge and second being parallel to each other
Edge；
The second edge extends to the direction far from the supporting part constitutes the first convex eaves structure；
The first edge is overlapped on the end face of the supporting part and constitutes step structure.
According to an aspect of the present invention, the coupling part is annular plate-like body；
The supporting part with the ring edge on the inside of the coupling part is orthogonal is fixedly connected.
According to an aspect of the present invention, the heat insulation structural includes: first thermal insulation layer, second thermal insulation layer, glass fibre
Layer and radiation shield；
The first thermal insulation layer, second thermal insulation layer, glass layer and the radiation shield use bonding agent and sizing
Adhesive tape assembling；
The radiation shield is set between adjacent thermal insulation layer.
According to an aspect of the present invention, the second thermal insulation layer is two layers；
The first thermal insulation layer is alumina fibre composite layer, and the second thermal insulation layer is nano silicon oxide composite layer.
For achieving the above object, the present invention provides a kind of thermal protection system of thermal protection component, comprising: multiple heat are anti-
Protecting assembly, sealing element and connection component；
The first convex eaves structure between the two neighboring thermal protection component mutually overlaps and adjacent two with step structure
Coupling part between a thermal protection component, which mutually overlaps, constitutes accommodating cavity；
In the sealing element setting and the accommodating cavity；
The connection component and the coupling part are connected with each other.
According to an aspect of the present invention, the gap between the cover board of the two neighboring thermal protection component be 0.5mm~
2mm；
Gap filling between the cover board of the two neighboring thermal protection component has solar heat protection putty.
According to an aspect of the present invention, the connection component includes: multiple brackets, connector, the first heat insulating washer, and
Two heat insulating washers, adjusting washer, lock washer and pedestal；
Multiple first engaging lugs, first heat insulating washer, the pedestal, second heat insulating washer, adjusting pad
Circle and lock washer are sequentially connected in series setting by the connector；
According to an aspect of the present invention, the bracket has the first engaging lug and the second connection of mutual dislocation setting
Ear；
First engaging lug and the pedestal are connected with each other, and second engaging lug is mutually interconnected with the coupling part
It connects.
The bracket is flexible alloy components.
A kind of scheme according to the present invention, thermal protection component of the invention have reusable, structural module, quality
Gently, at low cost, easily changeable advantage makes the present invention have broad application prospects in hypersonic aircraft field, meets and flies
Row device is simultaneously for the strict demand for preventing heat-insulated, lightweight, carrying and shock resistance etc..Further make application of the invention
The wide applicability of range is higher.
A kind of scheme according to the present invention, the present invention are cover-plate type thermal protection systems using ceramic matric composite (CMC)
Heatproof is higher, bearing capacity is stronger, it is lower to make large-size components, maintenance cost.Thermal protection system of the invention is by dividing
Block designs and thermal expansion coefficient is used to be much smaller than the ceramic matric composite of metal, and thermal expansion coefficient is only the 1/2-1/ of metal
3, it can effectively solve thermally matched in thermal protection conceptual design and thermal stress problem, improve the reliability of thermal protection system design.
In addition, main body of the present invention uses high temperature resistant, high specific strength, the relatively lower ceramic matric composite of density, it can be by entire machine
Body structural member total weight reduces 30-40%, and antioxygenic property is also superior to C/C composite material；Structure of the invention is not easy to take off simultaneously
It falls, not hygroscopic, rain-proof, the sealing for being unlikely to deform and being conducive to gap.
Entire cover board is arranged to trapezoidal panel by a kind of scheme according to the present invention, is effectively prevented because of different cover boards
Between gap area the drawbacks of leading to aerodynamic characteristic difference and local Aerodynamic Heating at longer longitudinal joint, thus to guaranteeing to use this hair
Internal structure, the normal work of component of bright aircraft are advantageous.
A kind of scheme according to the present invention by setting multilayered structure for heat insulation structural, and is provided with different heat-insulated
The thermal insulation layer of effect not only takes full advantage of the excellent performance of different thermal insulation layers, realizes the gradient separation of heat, and is conducive to
Reduce the cost of entire heat insulation structural.Radiation shield is arranged between different thermal insulation layers further reduced previous thermal insulation layer
The heat of transmitting, it is advantageous to the performance for guaranteeing latter thermal insulation layer, radiation shield especially is set in the link position of each thermal insulation layer
Layer, so avoid temperature shock cause latter thermal insulation layer surface damage the drawbacks of, to guarantee heat insulation structural stable structure and
Good heat insulation is beneficial.
A kind of scheme according to the present invention, after the assembling of adjacent heat guard assembly, the first convex eaves structure and step structure are mutual
Overlap joint constitutes the first seal structures in seaming position to realize, the air-flow for avoiding aircraft surface is straight from seaming position
It connects and is flowed into inside thermal protection system of the invention, the coupling part between two neighboring thermal protection component, which mutually overlaps, not only to be increased
The strong intensity of link position and accommodating cavity for sealing element installation is constituted between two neighboring thermal protection component, lead to
The effect for crossing sealing element further constitutes the second seal structures, and then enhances the leakproofness and heat-resisting quantity of link position
Can, it is advantageous to the leakproofness and high temperature resistance that guarantee present invention entirety.
A kind of scheme according to the present invention, by the gap setting between the cover board of two neighboring thermal protection component in 0.5mm
It is also cover board expanded by heating there are sufficient surplus in the case where ensure that sealing effect of the invention in the range of~2mm,
Damage caused by adjacent cover board expanded by heating and mutual extrusion is avoided, ensure that job stability of the invention.In addition, connecing
It stitches position and fills heat release putty, the infiltration of high-temperature gas during aircraft flight from seaming position is further avoided, into one
Step ensure that the good leakproofness of the present invention.
Detailed description of the invention
Fig. 1 schematically shows a kind of structure chart of the thermal protection component of embodiment according to the present invention；
Fig. 2 schematically shows a kind of cover board of embodiment according to the present invention and the connection figure of cover board bearing；
Fig. 3 schematically shows a kind of cover board of embodiment according to the present invention and the bottom view of cover board bearing；
Fig. 4 schematically shows a kind of structure chart of embodiment heat insulation structural according to the present invention；
Fig. 5 schematically shows a kind of structure chart of embodiment thermal protection system according to the present invention；
Fig. 6 schematically shows a kind of connection structure diagram of embodiment thermal protection system according to the present invention；
Fig. 7 schematically shows a kind of structure chart of embodiment connection component according to the present invention.
Specific embodiment
It, below will be to embodiment in order to illustrate more clearly of embodiment of the present invention or technical solution in the prior art
Needed in attached drawing be briefly described.It should be evident that the accompanying drawings in the following description is only of the invention some
Embodiment for those of ordinary skills without creative efforts, can also be according to these
Attached drawing obtains other attached drawings.
When being described for embodiments of the present invention, term " longitudinal direction ", " transverse direction ", "upper", "lower", " preceding ",
" rear ", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", orientation or positional relationship expressed by "outside" are based on phase
Orientation or positional relationship shown in the drawings is closed, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore above-mentioned term cannot
It is interpreted as limitation of the present invention.
The present invention is described in detail with reference to the accompanying drawings and detailed description, embodiment cannot go to live in the household of one's in-laws on getting married one by one herein
It states, but therefore embodiments of the present invention are not defined in following implementation.
In conjunction with shown in Fig. 1, Fig. 2 and Fig. 3, a kind of embodiment according to the present invention, a kind of thermal protection component of the invention
Including cover board 111, cover board bearing 112 and heat insulation structural 113.In the present embodiment, cover board 111, cover board bearing 112 and heat-insulated
Structure 113 is set gradually, and is mutually permanently connected.In the present embodiment, cover board 111 selects the material for being resistant to 1700 DEG C of high temperature
Material.In the present embodiment, cover board 111 uses ceramic matric composite (such as C/S iC material), and it is supported far from cover board
112 side is provided with antioxidant coating.In the present embodiment, cover board 111 and cover board support 112 sides interconnected also
It is provided with reinforcing rib structure 111a.In the present embodiment, cover board 111 and cover board bearing 112 are integrally formed, and structure is steady
Fixed, intensity is high.Certainly, cover board 111 and cover board bearing 112 are detachably connected.By above-mentioned setting, by cover board
111 are set as with reinforcing rib 111a refractory ceramics based composites, and not only its structural strength is high, but also in aircraft high speed
High temperature resistance in flight course is more excellent, and expanded by heating deflection is small, to guarantee aircraft in high-speed flight
Stabilization aerodynamic configuration in journey is advantageous.Meanwhile using refractory ceramics based composites, its heat-conductive characteristic is low, effectively blocks
The heat internally conducted during aircraft flight, it is advantageous to the internal component, the steady operation of structure that guarantee aircraft.Lid
The surface quality of cover board 111 can be effectively ensured in the outside setting antioxidant coating of plate 111, especially during high-speed flight
Hot environment under, the surface quality of cover board 111 is further ensured that by antioxidant coating, guarantees thermal protection component of the invention
Service life is advantageous.
In conjunction with shown in Fig. 2 and Fig. 3, a kind of embodiment according to the present invention, cover board bearing 112 includes supporting part 1121
With coupling part 1122.In the present embodiment, supporting part 1121 is circumferential wall, and one end and coupling part 1122 are mutual
Vertical connection, the other end and cover board 111 are mutually permanently connected and constitute groove structure.In the present embodiment, coupling part
1122 be annular plate-like body.The ring edge of 1122 inside of supporting part 1121 and coupling part is orthogonal to be fixedly connected.
In conjunction with shown in Fig. 2 and Fig. 3, a kind of embodiment according to the present invention, cover board 111 is trapezoidal plate.In this embodiment party
In formula, cover board 111 has with the first edge 1111 and second edge 1112 that are parallel to each other and cover board 111 to be mutually inclined
Third edge 1113 and the 4th edge 1114.In the present embodiment, it is separate to be fixedly supported upon supporting part 1121 for cover board 111
One end of coupling part 1122.Second edge 1112 extends to the direction far from supporting part 1121 constitutes the first convex eaves structure
114, i.e. side of the second edge 1112 of cover board 111 beyond supporting part 1121, the protrusion part of cover board 111 constitutes first
Convex eaves structure 114.In the present embodiment, first edge 1111 is overlapped on the end face of supporting part 1121 and constitutes step structure
115, i.e. side of the first edge 1111 without departing from supporting part 1121, the first edge 1111 and supporting part of cover board 111
1121 end face constitutes step structure 115.In the present embodiment, third edge 1113 and the 4th edge 1114 equally also divide
Not mutually the direction far from supporting part 1121, which does not extend, constitutes convex eaves structure, i.e. the third edge 1113 and the 4th edge of cover board 111
1114 exceed the side of supporting part 1121 respectively, and the protrusion part of cover board 111 constitutes convex eaves structure.By above-mentioned setting,
Entire cover board 111 is arranged to trapezoidal panel, is effectively prevented because the gap area between different cover boards 111 is at longer longitudinal joint
And the drawbacks of leading to aerodynamic characteristic difference and local Aerodynamic Heating, thus to the internal structure, the group that guarantee using aircraft of the invention
The normal work of part is advantageous.
As shown in figure 4, a kind of embodiment according to the present invention, heat insulation structural 113 includes: first thermal insulation layer 1131,
Two thermal insulation layers 1132, glass layer 1133 and radiation shield 1134.In the present embodiment, first thermal insulation layer 1131,
Two thermal insulation layers 1132, glass layer 1133 and radiation shield 1134 are assembled using bonding agent and shaping glue band.In this implementation
In mode, the heat insulation of first thermal insulation layer 1131 is greater than the heat insulation of second thermal insulation layer 1132.In the present embodiment,
One thermal insulation layer 1131 uses alumina fibre composite material, and second thermal insulation layer 1132 uses nano oxidized silicon composite.Referring to
Shown in Fig. 4, in the present embodiment, second thermal insulation layer 1132 is two layers.The setting of radiation shield 1134 and adjacent thermal insulation layer
Between, i.e., radiation shield 1134 is set between first thermal insulation layer 1131 and second thermal insulation layer 1132, second thermal insulation layer 1132
Between second thermal insulation layer 1132.Certainly, second thermal insulation layer 1132 may be arranged as other quantity (for example, three layers, four layers or
Person is more).Likewise, first thermal insulation layer 1131 may be set to be (for example, two layers, three layers etc.) of multilayer.It is set by above-mentioned
It sets, by setting multilayered structure for heat insulation structural 113, and is provided with the thermal insulation layer of different heat insulation, it is not only sufficiently sharp
With the excellent performance of different thermal insulation layers, the gradient separation of heat is realized, play the solar heat protection of a variety of materials itself to greatest extent
And thermal insulation benefits, maximum heat-insulating efficiency is obtained, and advantageously reduce the cost of entire heat insulation structural 113.It is different every
Radiation shield 1134 is arranged between thermosphere further reduced the heat of previous thermal insulation layer transmitting, to the latter thermal insulation layer of guarantee
Performance is advantageous, radiation shield 1134 especially is arranged in the link position of each thermal insulation layer, and then avoid temperature shock and cause
The drawbacks of latter thermal insulation layer surface is damaged, it is beneficial to the stable structure and good heat insulation that guarantee heat insulation structural 113.
In conjunction with shown in Fig. 1, Fig. 5 and Fig. 6, a kind of embodiment according to the present invention, a kind of thermal protection system of the invention
It include: multiple thermal protection components 11, sealing element 12 and connection component 13.In the present embodiment, pass through multiple thermal protection components
11 are mutually spliced to form the guard system for aircraft, are formed and are flown after the mutually splicing of the cover board 111 on thermal protection component 11
The aerodynamic configuration of row device.In the present embodiment, the first convex eaves knot between airflow direction, two neighboring thermal protection component 11
The coupling part 1122 of structure 114 and step structure 115 mutually between overlap joint and two neighboring thermal protection component 11 mutually overlaps
Constitute accommodating cavity 14.In the present embodiment, sealing element 12 is strip main body made of heat-resisting material, and form is arranged
Match with accommodating cavity 14, i.e., what sealing element 12 was matched with accommodating cavity 14 is mounted in accommodating cavity 14.In this implementation
In mode, coupling part 1122 and connection component 13 on thermal protection component 11 are connected with each other, to realize that heat of the invention is anti-
The assembling of protecting system.By above-mentioned setting, after adjacent heat guard assembly 11 assembles, the first convex eaves structure 114 and step structure 115
Mutually overlap joint constitutes the first seal structures in seaming position to realize, avoids the air-flow of aircraft surface from seam position
It sets and is fed directly to inside thermal protection system of the invention, the coupling part 1122 between two neighboring thermal protection component 11 is mutual
Overlap joint not only increases the intensity of link position and constitutes between two neighboring thermal protection component 11 pacifies for sealing element 12
The accommodating cavity 14 of dress further constitutes the second seal structures by the effect of sealing element 12, and then enhances link position
Leakproofness and high temperature resistance, to guaranteeing that the whole leakproofness of the present invention and high temperature resistance are advantageous.
A kind of embodiment according to the present invention, after multiple thermal protection components 11 are connected with each other, two neighboring thermal protection group
Gap between the cover board 111 of part 11 is 0.5mm~2mm.In the present embodiment, the cover board of two neighboring thermal protection component 11
Gap filling between 111 has solar heat protection putty.It, will be between the cover board 111 of two neighboring thermal protection component 11 by above-mentioned setting
Gap setting ensure that sealing effect of the invention in the range of 0.5mm~2mm in the case where, it is also heated for cover board 111
Expansion avoids damage caused by adjacent 111 expanded by heating of cover board and mutual extrusion, ensure that the present invention there are sufficient surplus
Job stability.In addition, filling heat release putty in seaming position, high-temperature gas during aircraft flight is further avoided
From the infiltration of seaming position, the good leakproofness of the present invention is further ensured.
As shown in fig. 7, a kind of embodiment according to the present invention, connection component 13 includes: multiple brackets 131, connector
132, the first heat insulating washer 133, the second heat insulating washer 134, adjusting washer 135, lock washer 136 and pedestal 137.In this implementation
In mode, bracket 131 is provided with the first engaging lug 1311, the second engaging lug 1312, and for connecting the first engaging lug 1311
With 1312 middleware 1313 of the second engaging lug, middleware 1313 is a strip plate body, and its section is arcuation, passes through this
Kind setting guarantees the bonding strength of bracket 131 to enhance the structural strength of middleware 1313.First engaging lug 1311 and
Two engaging lugs 1312 are respectively arranged at the opposite both ends of middleware 1313, and the first engaging lug 1311 and the second engaging lug
The 1312 two sides dislocation for being located at middleware 1313 are arranged in parallel.Divide on the first engaging lug 1311 and the second engaging lug 1312
It is not provided with through-hole, is passed through for connector.First engaging lug 1311 is used to be connected with each other with pedestal 137, the second engaging lug
1312 are connected with each other by connector and coupling part 1122.
As shown in fig. 7, in the present embodiment, bracket 131, the first heat insulating washer 133, the second heat insulating washer 134, adjustment
Washer 135 and lock washer 136 are mounted on pedestal 137 by connector 132.In the present embodiment, multiple brackets 131
On the first engaging lug 1311 be stacked with, and connected by connector 132.In the present embodiment, multiple first engaging lugs
1311, the first heat insulating washer 133, pedestal 137, the second heat insulating washer 134, adjusting washer 135 and lock washer 136 pass through connection
Part 132 (such as screw bolt and nut) is sequentially connected in series.In the present embodiment, it is in zigzag shape structure that pedestal 137 is whole.
In the present embodiment, bracket 131 uses high-temperature alloy material, and has elasticity.Similarly.Connector 132
Also it is made of high-temperature alloy material.By setting flexible alloy material piece for bracket 131, to be conducive to alleviate
The disadvantage of thermal protection component 11 upper cover plate 111 and unequal power distribution caused by several thermal dilation differences of aircraft body structure
End, effectively increases the structural stability of thermal protection system of the invention.Meanwhile alloy material is set by connector 132, also
Be conducive to the drawbacks of eliminating connector 132 and 131 thermal mismatching of bracket.
Above content is only the example of concrete scheme of the invention, for the equipment and structure of wherein not detailed description, is answered
When being interpreted as that the existing common apparatus in this field and universal method is taken to be practiced.
The foregoing is merely a schemes of the invention, are not intended to restrict the invention, for the technology of this field
For personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of thermal protection component, which is characterized in that including cover board (111), and the cover board being set on the cover board (111)
It supports (112), and the heat insulation structural (113) being connected with cover board bearing (112)；
The cover board (111) is ceramic matric composite plate, and its side for supporting (112) far from the cover board is provided with antioxygen
Change coating.
2. thermal protection component according to claim 1, which is characterized in that the cover board bearing (112) includes supporting part
(1121) and coupling part (1122)；
The supporting part (1121) is circumferential wall, and one end is mutually connected vertically with the coupling part (1122), another
One end and the cover board (111), which are mutually permanently connected, constitutes groove structure.
3. thermal protection component according to claim 2, which is characterized in that the cover board (111) is trapezoidal plate, with phase
Mutually parallel first edge (1111) and second edge (1112)；
The second edge (1112) extends to the direction far from the supporting part (1121) constitutes the first convex eaves structure
(114)；
The first edge (1111) is overlapped on composition step structure (115) on the end face of the supporting part (1121).
4. thermal protection component according to claim 2, which is characterized in that the coupling part (1122) is annular plate-like
Body；
The supporting part (1121) with the ring edge on the inside of the coupling part (1122) is orthogonal is fixedly connected.
5. thermal protection component according to claim 1, which is characterized in that the heat insulation structural (113) includes: first heat-insulated
Layer (1131), second thermal insulation layer (1132), glass layer (1133) and radiation shield (1134)；
The first thermal insulation layer (1131), second thermal insulation layer (1132), glass layer (1133) and the radiation shield
(1134) it is assembled using bonding agent and shaping glue band；
The radiation shield (1134) is set between adjacent thermal insulation layer.
6. thermal protection component according to claim 5, which is characterized in that the second thermal insulation layer (1132) is two layers；
The first thermal insulation layer (1131) is alumina fibre composite layer, and the second thermal insulation layer (1132) is multiple for nano silicon oxide
Close layer.
7. a kind of thermal protection system of the thermal protection component using any one of claim 1 to 6 characterized by comprising multiple
Thermal protection component (11), sealing element (12) and connection component (13)；
The first convex eaves structure (114) and step structure (115) between the two neighboring thermal protection component (11) mutually overlap,
And the mutually overlap joint of the coupling part (1122) between the two neighboring thermal protection component (11) constitutes accommodating cavity (14)；
In sealing element (12) setting and the accommodating cavity (14)；
The connection component (13) and the coupling part (1122) are connected with each other.
8. thermal protection system according to claim 7, which is characterized in that the lid of the two neighboring thermal protection component (11)
Gap between plate (111) is 0.5mm~2mm；
Gap filling between the cover board (111) of the two neighboring thermal protection component (11) has solar heat protection putty.
9. thermal protection system according to claim 7 or 8, which is characterized in that the connection component (13) includes: multiple
Frame (131), connector (132), the first heat insulating washer (133), the second heat insulating washer (134), adjusting washer (135), locking pad
Enclose (136) and pedestal (137)；
It is multiple first engaging lugs (1311), first heat insulating washer (133), the pedestal (137), described second heat-insulated
Washer (134), adjusting washer (135) and lock washer (136) are sequentially connected in series setting by the connector (132).
10. thermal protection system according to claim 9, which is characterized in that the bracket (131) is arranged with mutual dislocation
The first engaging lug (1311) and the second engaging lug (1312)；
First engaging lug (1311) and the pedestal (137) are connected with each other, second engaging lug (1312) and the company
Socket part point (1122) is connected with each other.
The bracket (131) is flexible alloy components.
Priority Applications (1)
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| CN201811427161.3A CN109367758B (en) | 2018-11-27 | 2018-11-27 | Thermal protection assembly and thermal protection system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811427161.3A CN109367758B (en) | 2018-11-27 | 2018-11-27 | Thermal protection assembly and thermal protection system |
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| CN109367758B CN109367758B (en) | 2020-05-15 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110834712A (en) * | 2019-10-17 | 2020-02-25 | 中国运载火箭技术研究院 | Be applicable to high temperature resistant thermal plug structure of dismantling |
| CN113978696A (en) * | 2021-11-08 | 2022-01-28 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
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