CN209991872U - Rocket bottom thermal protection panel and liquid rocket bottom thermal protection system - Google Patents
Rocket bottom thermal protection panel and liquid rocket bottom thermal protection system Download PDFInfo
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- CN209991872U CN209991872U CN201920261386.XU CN201920261386U CN209991872U CN 209991872 U CN209991872 U CN 209991872U CN 201920261386 U CN201920261386 U CN 201920261386U CN 209991872 U CN209991872 U CN 209991872U
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- 238000001816 cooling Methods 0.000 claims abstract description 125
- 239000002826 coolant Substances 0.000 claims abstract description 44
- 239000003380 propellant Substances 0.000 claims description 101
- 238000002485 combustion reaction Methods 0.000 claims description 24
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 9
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 229910002804 graphite Inorganic materials 0.000 claims description 3
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- 230000001681 protective effect Effects 0.000 abstract description 18
- 238000000034 method Methods 0.000 description 11
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- 238000010438 heat treatment Methods 0.000 description 6
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- 230000007613 environmental effect Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002633 protecting effect Effects 0.000 description 2
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- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
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- 239000011152 fibreglass Substances 0.000 description 1
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- 239000001257 hydrogen Substances 0.000 description 1
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- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
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Abstract
The utility model relates to a carrier rocket heat protection field specifically provides a hot protective plate in rocket bottom and hot protective system in liquid rocket bottom. Rocket bottom heat protection panel locates the rocket bottom, includes: the inner wall plate is positioned at one side close to the object to be protected; the outer wall plate is positioned on one side close to the high-temperature environment, a heat-conducting medium is filled between the inner wall plate and the outer wall plate, and the heat-conducting medium is used for exchanging heat with the outer wall plate; and the cooling pipeline is arranged between the inner wall plate and the outer wall plate, the outside of the cooling pipeline is wrapped by the heat-conducting medium, and the inside of the cooling pipeline is provided with the circulating cooling medium for exchanging heat with the heat-conducting medium. The utility model discloses a hot protective structure adopts the active cooling, and hot protective effect is better than traditional passive form protection, and utilizes high-efficient heat conduction and active cooling's combination to improve heat exchange efficiency to less pipeline realizes hot protective structure's high-efficient cooling.
Description
Technical Field
The utility model relates to a carrier rocket heat protection field, concretely relates to hot protective panel in rocket bottom and hot protective system in liquid rocket bottom.
Background
The bottom of the carrier rocket needs to take thermal protection measures for protecting engine pipelines, electrical equipment and the like at the bottom of the rocket due to pneumatic heating and radiation heating generated by rocket engine jet flow. The bottom of the existing disposable rocket is generally made into a thermal protection structure by adopting composite materials such as glass fiber reinforced plastics, flexible high-temperature heat-insulating cloth and the like. The reusable rocket is subjected to the double effects of atmospheric pneumatic heating and jet flow heating in the process of returning and re-entering, the thermal environment is obviously higher than that of the traditional disposable carrier rocket, and the bottom thermal protection faces huge technical challenges.
Traditional passive thermal protection utilizes the material ablation principle or the characteristic of high temperature resistance, low thermal conductivity of material itself to realize, and serious ablation, the degradation problem can appear in the high heat flow of reentry process, high dynamic pressure condition to the ablation class material, for satisfying reentry section thermal protection performance, needs to improve the thickness of hot protective structure, therefore brings the promotion greatly of weight, and need change the thermal protection layer after returning at every turn, can't realize repeatedly usable. And high-performance non-ablative high-temperature-resistant materials (such as novel C/SiC, C/C, ultrahigh-temperature ceramics and the like) are difficult to process, high in cost, small in damage tolerance, high in brittleness and the like, and are easy to damage under the condition of repeated use. Therefore, a reusable carrier rocket urgently needs a heat protection structure with good reusability, light weight and high efficiency.
SUMMERY OF THE UTILITY MODEL
For the hot protective efficiency who solves the passive form hot protective structure in traditional rocket bottom is low, ablation, degradation easily appear, with high costs, the poor technical problem of used repeatedly ability simultaneously, the utility model provides a rocket bottom hot protective panel that active cooling and protecting effect are good.
And simultaneously, for solving above-mentioned technical problem, the utility model provides an utilize propellant to carry out initiative refrigerated liquid rocket bottom thermal protection system to the rocket bottom.
Furthermore, in order to solve the technical problem, the utility model provides a propellant carries out active cooling's liquid rocket bottom thermal protection method to the rocket bottom.
In a first aspect, the present invention provides a rocket bottom thermal protection panel, including:
the inner wall plate is positioned at one side close to the object to be protected;
the outer wall plate is positioned on one side close to a high-temperature environment, and a heat-conducting medium is filled between the inner wall plate and the outer wall plate and is used for exchanging heat with the outer wall plate; and
and the cooling pipeline is arranged between the inner wall plate and the outer wall plate, the outside of the cooling pipeline is wrapped by the heat-conducting medium, and a circulating cooling medium is arranged in the cooling pipeline and used for exchanging heat with the heat-conducting medium.
The cooling pipeline comprises a plurality of coolant flow channels which are uniformly distributed between the inner wall plate and the outer wall plate, liquid collectors are arranged at the inlet end and the outlet end of the cooling pipeline, and the liquid collectors are communicated with the coolant flow channels.
The plurality of coolant flow passages are sequentially arranged in a ring shape around the rocket engine.
The cooling pipeline is located at one side close to the outer wall plate.
The heat-conducting medium comprises at least one of high-heat-conductivity carbon/carbon and high-heat-conductivity graphite.
In a second aspect, the present invention provides a thermal protection system for bottom of liquid rocket, including:
in the rocket bottom thermal protection panel, the inlet end of the cooling pipeline is connected to a propellant conveying pipeline, the propellant conveying pipeline conveys propellant into the cooling pipeline, and the propellant is used as the cooling medium in the cooling pipeline.
The outlet end of the cooling pipeline is communicated to a thrust chamber cooling system, and the propellant exchanges heat with the heat-conducting medium and then flows to the thrust chamber cooling system to cool the thrust chamber.
The outlet end of the cooling pipeline is communicated to a combustion system, and the propellant exchanges heat with the heat-conducting medium and then flows to the combustion system to participate in combustion.
The outlet end of the cooling pipeline is communicated to a propellant conveying system, the downstream of the propellant conveying system is connected with a thrust chamber cooling system, the propellant exchanges heat with the heat-conducting medium and then flows to the propellant conveying system, and the propellant is mixed with the low-temperature propellant in the propellant conveying system and then flows to the thrust chamber cooling system to cool the thrust chamber.
In a third aspect, the present invention provides a liquid rocket bottom thermal protection method, applied to the rocket bottom thermal protection system, comprising the following steps:
the propellant conveying pipeline conveys the propellant in the cooling pipeline, and the propellant exchanges heat with the heat-conducting medium;
when the temperature of the propellant after heat exchange is not higher than the preset temperature of a thrust chamber cooling system, the propellant enters the thrust chamber cooling system to cool a thrust chamber;
when the temperature of the propellant after heat exchange is higher than the preset temperature of the cooling system of the thrust chamber,
the propellant enters a combustion system to participate in combustion, or
The mixed gas enters a propellant conveying system, is mixed with a low-temperature propellant and then enters a thrust chamber cooling system to cool a thrust chamber.
The technical scheme of the utility model, following beneficial effect has:
1) the utility model provides a rocket bottom heat protection panel locates the rocket bottom, including interior wallboard, outer wallboard and cooling line, fill heat-conducting medium between interior wallboard and the outer wallboard, the cooling line is outside by heat-conducting medium parcel, its inside cooling medium that has the circulation for with the heat-conducting medium heat transfer. The cooling pipeline and the outer wall plate indirectly exchange heat through the heat-conducting medium, so that the temperature of the external environment of the cooling pipeline is constant, the heat exchange efficiency is improved, meanwhile, the heat protection panel realizes the uniform temperature of the cooling pipeline which is not in contact with each other through the heat-conducting medium, the heat exchange effect is better, the active cooling efficiency is greatly improved, the intensity of the cooling pipeline can be correspondingly reduced, and the reutilization performance of the heat protection structure is improved. The heat protection panel can be additionally arranged on the outer layer of the rocket bottom shielding plate to carry out heat protection on the bottom shielding plate, and can also be directly used as an actively-cooled bottom shielding plate structure to realize the multiple purposes of the heat protection panel. The rocket bottom is protected by adopting an active cooling principle, the thermal protection performance of the bottom of the carrier rocket is greatly improved, the applicable thermal environment range exceeds that of the traditional passive thermal protection structure, and the reusability is better.
2) The utility model provides a hot protection panel in rocket bottom, many coolant flow channels between wallboard and the outer wall board including the equipartition cooling line, cooling line's entry end and exit end all are equipped with the liquid trap, many coolant flow channels of liquid trap intercommunication, and the liquid trap carries out the mass flow and shunts to the coolant in many runners simultaneously, increases coolant's flow, and then improves heat exchange efficiency.
3) The utility model provides a hot protective panel in rocket bottom, cooling pipeline are located the one side that is close to the out-wainscot, and the out-wainscot outside is high temperature environment, and one side that is close to high temperature environment is located to the cooling pipeline, and heat exchange efficiency is higher, and the protective effect to the protection side is better simultaneously.
4) The utility model provides a hot protection system in liquid rocket bottom, cooling line's entry end is connected to propellant conveying line, and propellant conveying line carries the propellant in to cooling line, utilizes the propellant as the coolant in the cooling line, and hot protection system and the inside cooling system butt joint of rocket optimize structure, reduce cost.
5) The utility model provides a hot protection system in liquid rocket bottom, thrust room cooling system/combustion system propellant conveying system can be connected according to the temperature difference of propellant to the exit end of cooling line, realizes cooling propellant's high-efficient utilization, avoids the propellant extravagant, realizes the regeneration cooling of system.
6) The utility model provides a liquid rocket bottom thermal protection method, including following step: the propellant conveying pipeline conveys the propellant in the cooling pipeline, and the propellant exchanges heat with the heat-conducting medium; when the temperature of the propellant after heat exchange is not higher than the preset temperature of a thrust chamber cooling system, the propellant enters the thrust chamber cooling system to cool a thrust chamber; when the temperature of the propellant after heat exchange is higher than the preset temperature of the cooling system of the thrust chamber, the propellant enters the combustion system to participate in combustion, or enters the propellant conveying system to be mixed with the low-temperature propellant and then enters the cooling system of the thrust chamber to cool the thrust chamber. The utility model discloses a method adopts the active cooling principle to protect the rocket bottom, greatly promotes the hot barrier propterty in carrier rocket bottom, and hot barrier propterty docks with the inside cooling system of rocket, realizes cooling propellant high efficiency and utilizes, avoids propellant extravagant, reduce cost.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic front sectional view of a thermal protection panel according to an embodiment of the present invention;
FIG. 2 is a schematic top view of a cross-sectional structure of a thermal protection panel according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a thermal protection system in accordance with an embodiment of the present invention;
FIG. 4 is a schematic diagram of a thermal protection system in accordance with another embodiment of the present invention;
fig. 5 is a schematic diagram of a thermal protection system according to yet another embodiment of the present invention.
Description of reference numerals:
10-a heat protection panel; 11-inner wall panel; 12-an outer wall panel; 2-a heat-conducting medium; 3-coolant flow channels; 4-a cooling medium; and 5-a liquid collector.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some examples of the present invention, but not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work all belong to the protection scope of the present invention. Furthermore, the technical features mentioned in the different embodiments of the invention described below can be combined with each other as long as they do not conflict with each other.
The utility model provides a hot protective panel in rocket bottom, this panel structure adopt active cooling's protective structure, can be used to the hot protection of high temperature environment, show the structure of hot protective panel in an embodiment in figure 1, figure 2.
As shown in fig. 1, in the present embodiment, the heat shield panel 10 is an integrated panel, and is provided in the outer layer of the rocket bottom cover or serves as the rocket bottom cover. The panel structure includes an inner wall plate 11, an outer wall plate 12, and a heat transfer medium 2 filled between the inner and outer wall plates. The thermal protection panel 10 is arranged at the bottom of the rocket, the inner wall plate 11 is positioned at one side close to a structure to be protected in the rocket, and the outer side of the outer wall plate 12 is a high-temperature environment for pneumatic heating and radiation heating generated by rocket engine jet flow. Fill between interior wallboard 11 and the outer wall board 12 and be heat-conducting medium 2, heat-conducting medium 2 is high heat conduction material, for example high carbon/carbon, high graphite etc. of leading to outer wallboard 12 and external high temperature environment heat transfer back, heat-conducting medium 2 carries out the heat transfer to outer wallboard 12, makes heat transfer to heat-conducting medium 2, realizes panel structure's isothermal.
The heat-conducting medium 2 is embedded with a cooling pipeline, a flowing cooling medium 4 is arranged in the cooling pipeline, the cooling medium 4 is low-temperature cooling liquid, and the heat exchange with the heat-conducting medium 2 is carried out in the flowing process, so that the heat protection panel 10 is cooled. As shown in fig. 1 and 2, in the present embodiment, the cooling line includes a plurality of coolant flow passages 3, and the plurality of coolant flow passages 3 are arranged in an annular order around the rocket engine between the inner and outer wall plates. The inlet end and the outlet end of the cooling pipeline are provided with a liquid collector 5, the liquid collector 5 is respectively communicated with the plurality of coolant flow channels 3, and cooling media 4 are divided or collected in the cooling pipeline through the liquid collector 5, so that the flow of the cooling media is improved, and further the heat exchange capacity is improved. In the present embodiment, as shown in fig. 1, since the outside of the outer wall plate 12 is in a high-temperature environment, the cooling pipe is provided on the side closer to the outer wall plate 12 in order to further improve the heat exchange efficiency of the cooling medium 4. It should be noted that the coolant flow channel 3 may be configured according to the position of the rocket engine body, and the present invention is not limited thereto.
In this embodiment, the heat protection panel 10 is used as a rocket bottom heat protection panel, and the inner wall plate 11, the outer wall plate 12, and the pipe wall of the coolant flow channel 3 can be made of high temperature resistant materials with good damage tolerance, such as titanium alloy and stainless steel, so as to improve the reusability of the panel. In the present embodiment, the protection principle of the heat protection panel 10 is: the heat transfer of outer wallboard 12 with outside high temperature environment to inside heat-conducting medium 2, because the outer wall of coolant runner 3 is wrapped up by heat-conducting medium 2, so the pipe wall circumference of coolant runner 3 is isothermal everywhere, and the wall that the cooling line does not contact outer wallboard 12 can effectively cool off outer wallboard 12, realizes the heat exchange efficiency maximize. Simultaneously, the panel structure of the embodiment realizes the temperature equalization of the cooling pipelines which are not in contact with each other through the heat-conducting medium 2, compared with the traditional active cooling structure, the heat exchange efficiency is obviously improved, the coolant flow channels 3 in the panel can realize the integral cooling of the panel at the bottom of the whole rocket without intensive arrangement, and the structure weight is reduced. Preferably, the inner wall plate 11 is close to one side of the structure to be protected inside the rocket, and in order to improve the protection effect, the inner wall plate 11 may be made of a non-metallic material with a good heat insulation effect, such as high temperature resistant glass, high temperature resistant ceramic, and the like.
In this embodiment, the heat shield panel 10 serves as a bottom shield panel of a launch vehicle of a liquid rocket engine, and the cooling system of the heat shield panel 10 is connected to the cooling system of the liquid rocket engine. Specifically, the inlet end of the cooling pipeline is connected with a propellant conveying pipeline of the liquid rocket engine, the propellant conveying pipeline conveys low-temperature propellant into the cooling pipeline, the propellant is coolant and fuel of the liquid rocket engine, generally low-temperature liquid such as liquid hydrogen, low-temperature kerosene, liquid methane and the like, so that the protective panel is connected with the propellant conveying pipeline, the low-temperature propellant is used as a cooling medium 4 of the protective panel, the structure of the cooling system is correspondingly simplified, and the cost is reduced.
As shown in fig. 3 to 5, the downstream of the cooling pipeline can be connected to different downstream systems according to the temperature of the cooling medium 4 at the outlet end, so that the efficient utilization of the propellant is realized.
In the embodiment shown in fig. 3, the cooling line of the heat protection panel 10 is arranged upstream of the thrust compartment cooling system of the engine, i.e. the outlet end of the cooling line is connected to the thrust compartment cooling system. The cooling medium 4 (propellant) cools the bottom of the launch vehicle, which has a relatively low thermal environment, and then cools the engine thrust chamber, which has a more severe thermal environment. Specifically, as shown in fig. 3, the cooling medium 4 flows into the heat protection panel 10 through the inlet end, exchanges heat with the heat protection panel 10, flows out through the outlet end, and further flows into the inlet of the thrust chamber cooling system to cool the thrust chamber with a higher thermal environment, and the propellant after heat exchange flows into the downstream system again, for example, enters the combustion system to participate in combustion.
In the embodiment shown in fig. 4, the cooling line of the heat protection panel 10 is arranged upstream of the combustion system, i.e. the outlet end of the cooling line is connected to the combustion system. And the cooling medium 4 (propellant) cools and exchanges heat with the bottom of the carrier rocket and then enters a combustion system to participate in combustion. Specifically, as shown in fig. 4, the cooling medium 4 flows into the heat protection panel 10 through the inlet end, exchanges heat with the heat protection panel 10, and then flows out through the outlet end, and further enters the combustion system together with the propellant at the outlet end of the thrust chamber cooling system.
In the embodiment shown in fig. 5, the outlet end of the cooling pipeline is communicated with the propellant conveying system, and the downstream of the propellant conveying system is connected with the thrust chamber cooling system, namely, the high-temperature propellant at the outlet of the cooling pipeline and the low-temperature propellant of the propellant conveying system are mixed and then enter the thrust chamber cooling system. Specifically, as shown in fig. 5, the cooling medium 4 flows into the heat protection panel 10 through the inlet end, flows out through the outlet end after exchanging heat with the heat protection panel 10, and then is connected with the outlet end of the propellant conveying system, the high-temperature propellant after exchanging heat, which flows out from the outlet end of the cooling pipeline, is mixed with the low-temperature propellant of the propellant conveying system to be cooled, and then enters the thrust chamber cooling system together to cool the thrust chamber with higher thermal environment, and then the propellant after exchanging heat enters the downstream system, for example, enters the combustion system to participate in combustion.
The utility model provides a hot protection system utilizes the liquid rocket propellant as coolant 4, has greatly promoted carrier rocket bottom thermal protection performance, and the hot environmental scope of its applicable far exceeds traditional passive form thermal protection structure. Meanwhile, the cooling system of the thermal protection panel can be communicated to different downstream systems according to the temperature of the outlet end, the utilization efficiency of the propellant is improved, the propellant waste is avoided, and the regenerative cooling system of the rocket engine is realized.
On the other hand, the utility model also provides a liquid rocket bottom heat protection method, this method can be used to foretell heat protection structure or heat protection panel, and it includes following step:
the propellant conveying pipeline conveys the propellant in the cooling pipeline, and the propellant exchanges heat with the heat-conducting medium;
when the temperature of the propellant after heat exchange is not higher than the preset temperature of the thrust chamber cooling system, the propellant enters the thrust chamber cooling system to cool the thrust chamber;
when the temperature of the propellant after heat exchange is higher than the preset temperature of the cooling system of the thrust chamber,
the propellant enters the combustion system to participate in combustion, or
The mixed gas enters a propellant conveying system, is mixed with a low-temperature propellant and then enters a thrust chamber cooling system to cool a thrust chamber.
Particularly, the flow direction of the propellant after heat exchange in the heat protection panel 10 is determined by the temperature of the propellant at the outlet end, and when the temperature of the propellant at the outlet end is not higher than the preset temperature of the thrust chamber cooling system, the propellant still meets the requirement of more severe thrust chamber cooling to the thermal environment, so that the outlet end of the heat protection panel 10 is communicated with the thrust chamber cooling system, and the utilization efficiency of the propellant is improved. For example, in one exemplary embodiment, the propellant can continue to participate in the thrust chamber cooling when the temperature of the propellant in the cooling circuit does not rise above 150-250 ℃. When the temperature of the propellant in the cooling pipeline is increased to be higher than the preset temperature of the cooling system of the thrust chamber, the propellant cannot directly participate in the cooling of the thrust chamber at the moment, and can directly enter the combustion system to participate in combustion, or is mixed with the propellant in the cooling system of the thrust chamber to form a cooling medium with a lower temperature, and the cooling medium continuously participates in the cooling of the thrust chamber.
It should be noted that in the liquid rocket thermal protection panels, systems, and methods provided by the present invention, the flow rate of the cooling medium is determined by the thermal environment conditions, while being compatible with the liquid rocket engine and the turbopump capabilities. The temperature rise of the cooling medium after heat exchange cannot exceed the allowable temperature, the maximum allowable temperature being the boiling point for some propellants (e.g. liquid oxygen, etc.) and the thermal or thermochemical decomposition temperature for some propellants (e.g. liquid kerosene lamp).
For the thermal protection structure, the structure wall temperature of the thermal protection structure does not exceed the allowable temperature of the material, the hot wall temperature does not exceed the allowable temperature of the corresponding material under the thermal stability condition, the cold wall temperature does not cause film boiling or cracking of the cooling medium 4, and the wall temperature distribution of the cooling structure is adapted to the allowable strength of the material.
In some alternative embodiments, the inner wall panel 11 and the outer wall panel 12 of the thermal protection panel 10 may be selected from suitable structural materials according to the specific aerodynamic bearing requirements of the launch vehicle, thermal environmental conditions, propellant physical properties, and the like, without limitation. Furthermore, the thermal protection structure may be an integral panel or a plurality of panels may be joined together, each panel having an independent cooling circuit connected to the propellant feed line and downstream systems.
It should be understood that the above embodiments are only examples for clearly illustrating the present invention, and are not intended to limit the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications can be made without departing from the scope of the invention.
Claims (9)
1. The utility model provides a rocket bottom heat protection panel locates the rocket bottom, its characterized in that includes:
an inner wall plate (11) positioned at one side close to the object to be protected;
the outer wall plate (12) is positioned on one side close to a high-temperature environment, a heat-conducting medium (2) is filled between the inner wall plate (11) and the outer wall plate (12), and the heat-conducting medium (2) is used for exchanging heat with the outer wall plate (12); and
and the cooling pipeline is arranged between the inner wall plate (11) and the outer wall plate (12), the outside of the cooling pipeline is wrapped by the heat-conducting medium (2), and the inside of the cooling pipeline is provided with a circulating cooling medium (4) for exchanging heat with the heat-conducting medium (2).
2. A rocket bottom thermal protection panel according to claim 1,
the cooling pipeline comprises a plurality of coolant flow channels (3) which are uniformly distributed between the inner wall plate (11) and the outer wall plate (12), liquid collectors (5) are arranged at the inlet end and the outlet end of the cooling pipeline, and the liquid collectors (5) are communicated with the coolant flow channels (3).
3. A rocket bottom thermal protection panel according to claim 2,
the plurality of coolant flow channels (3) are sequentially arranged in a ring shape around the rocket engine.
4. Rocket bottom thermal protection panel according to any one of claims 1 to 3, wherein said cooling lines are located on the side close to said outer wall plate (12).
5. Rocket bottom thermal protection panel according to any one of claims 1 to 3, wherein said heat conducting medium (2) comprises at least one of highly heat conducting carbon/carbon, highly heat conducting graphite.
6. A liquid rocket bottom thermal protection system, comprising:
rocket bottom thermal protection panel according to any one of claims 1 to 5, the inlet end of the cooling circuit being connected to a propellant feed line which feeds propellant into said cooling circuit as said cooling medium (4) in said cooling circuit.
7. The liquid rocket bottom thermal protection system of claim 6,
the outlet end of the cooling pipeline is communicated to a thrust chamber cooling system, and the propellant exchanges heat with the heat-conducting medium (2) and then flows to the thrust chamber cooling system to cool the thrust chamber.
8. The liquid rocket bottom thermal protection system of claim 6,
the outlet end of the cooling pipeline is communicated to a combustion system, and the propellant exchanges heat with the heat-conducting medium (2) and then flows to the combustion system to participate in combustion.
9. The liquid rocket bottom thermal protection system of claim 6,
the outlet end of the cooling pipeline is communicated to a propellant conveying system, the downstream of the propellant conveying system is connected with a thrust chamber cooling system, the propellant exchanges heat with the heat-conducting medium (2) and then flows to the propellant conveying system, and the propellant is mixed with the low-temperature propellant in the propellant conveying system and then flows to the thrust chamber cooling system to cool the thrust chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920261386.XU CN209991872U (en) | 2019-02-28 | 2019-02-28 | Rocket bottom thermal protection panel and liquid rocket bottom thermal protection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920261386.XU CN209991872U (en) | 2019-02-28 | 2019-02-28 | Rocket bottom thermal protection panel and liquid rocket bottom thermal protection system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209991872U true CN209991872U (en) | 2020-01-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920261386.XU Withdrawn - After Issue CN209991872U (en) | 2019-02-28 | 2019-02-28 | Rocket bottom thermal protection panel and liquid rocket bottom thermal protection system |
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| CN (1) | CN209991872U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109736972A (en) * | 2019-02-28 | 2019-05-10 | 北京星际荣耀空间科技有限公司 | Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method |
| CN109736972B (en) * | 2019-02-28 | 2024-06-07 | 北京星际荣耀空间科技股份有限公司 | Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method |
-
2019
- 2019-02-28 CN CN201920261386.XU patent/CN209991872U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109736972A (en) * | 2019-02-28 | 2019-05-10 | 北京星际荣耀空间科技有限公司 | Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method |
| CN109736972B (en) * | 2019-02-28 | 2024-06-07 | 北京星际荣耀空间科技股份有限公司 | Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method |
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