CN109736972B - Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method - Google Patents
Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method Download PDFInfo
- Publication number
- CN109736972B CN109736972B CN201910152770.0A CN201910152770A CN109736972B CN 109736972 B CN109736972 B CN 109736972B CN 201910152770 A CN201910152770 A CN 201910152770A CN 109736972 B CN109736972 B CN 109736972B
- Authority
- CN
- China
- Prior art keywords
- propellant
- cooling
- heat
- wall plate
- thermal protection
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000007788 liquid Substances 0.000 title claims abstract description 42
- 238000000034 method Methods 0.000 title claims abstract description 14
- 238000001816 cooling Methods 0.000 claims abstract description 135
- 239000002826 coolant Substances 0.000 claims abstract description 43
- 239000003380 propellant Substances 0.000 claims description 122
- 238000002485 combustion reaction Methods 0.000 claims description 28
- 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
- 239000010439 graphite Substances 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 7
- 239000000463 material Substances 0.000 description 10
- 238000002679 ablation Methods 0.000 description 6
- 238000010438 heat treatment Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000002699 waste material Substances 0.000 description 3
- 210000001503 joint Anatomy 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
- 230000001681 protective effect Effects 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 230000001172 regenerating effect Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 239000011203 carbon fibre reinforced carbon Substances 0.000 description 1
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 238000005979 thermal decomposition reaction Methods 0.000 description 1
- 239000011215 ultra-high-temperature ceramic Substances 0.000 description 1
Landscapes
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention relates to the field of carrier rocket thermal protection, and particularly provides a rocket bottom thermal protection panel, a liquid rocket bottom thermal protection system and a liquid rocket bottom thermal protection method. Rocket bottom thermal protection panel locates rocket bottom, includes: an inner wall plate positioned at one side close to the object to be protected; the outer wall plate is positioned at 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 a heat conducting medium, and the cooling pipeline is internally provided with a circulating cooling medium for exchanging heat with the heat conducting medium. The heat protection structure adopts active cooling, has better heat protection effect than the traditional passive protection, improves heat exchange efficiency by combining efficient heat conduction and active cooling, and realizes efficient cooling of the heat protection structure by fewer pipelines.
Description
Technical Field
The invention relates to the field of carrier rocket thermal protection, in particular to a rocket bottom thermal protection panel, a liquid rocket bottom thermal protection system and a liquid rocket bottom thermal protection method.
Background
The bottom of the carrier rocket is heated by air and radiation generated by jet flow of the rocket engine, and thermal protection measures are needed to be adopted for protecting engine pipelines, electric equipment and the like at the bottom of the rocket. The bottom of the existing disposable rocket is generally made of glass fiber reinforced plastic, high-flexibility Wen Jue hot cloth and other composite materials. The reusable rocket is subjected to double effects of atmospheric pneumatic heating and jet heating in the process of returning and reentering, the thermal environment is obviously higher than that of the traditional one-time-use carrier rocket, and the bottom thermal protection faces huge technical challenges.
The traditional passive heat protection is realized by utilizing the material ablation principle or the high temperature resistance and low heat conductivity of the material, and the ablation material has serious ablation and ablation problems under the conditions of high heat flow and high dynamic pressure in the reentry process, so that the thickness of a heat protection structure needs to be improved to meet the reentry section heat protection performance, thereby bringing about great weight improvement, and the heat protection layer needs to be replaced after each return, so that the repeated use cannot be realized. The high-performance non-ablative high-temperature resistant materials (such as novel C/SiC, C/C, ultrahigh-temperature ceramics and the like) are high in processing difficulty, high in cost, small in damage tolerance, large in brittleness and the like, and are easy to damage under the condition of repeated use. Therefore, a reusable carrier rocket is highly demanded for a heat protection structure which is good in reusability, light in weight and efficient.
Disclosure of Invention
The invention provides a rocket bottom thermal protection panel with active cooling and good protection effect, which aims to solve the technical problems of low thermal protection efficiency, easy ablation and ablation, high cost and poor reusability of the traditional rocket bottom passive thermal protection structure.
Meanwhile, in order to solve the technical problems, the invention provides a liquid rocket bottom heat protection system for actively cooling the rocket bottom by using a propellant.
Furthermore, in order to solve the technical problems, the invention provides a liquid rocket bottom heat protection method for actively cooling the rocket bottom by using a propellant.
In a first aspect, the present invention provides a rocket base thermal protection panel comprising:
An inner wall plate positioned at one side close to the object to be protected;
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 cooling pipeline is internally provided with a circulating cooling medium for exchanging heat with the heat conducting medium.
The cooling pipeline comprises a plurality of coolant flow channels 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 plurality of coolant flow channels.
The coolant flow channels are sequentially arranged in a ring shape around the rocket engine.
The cooling pipeline is positioned at one side close to the outer wall plate.
The thermally conductive medium comprises at least one of highly thermally conductive carbon/carbon and highly thermally conductive graphite.
In a second aspect, the present invention provides a liquid rocket bottom thermal protection system comprising:
The rocket bottom thermal protection panel is characterized in that the inlet end of the cooling pipeline is connected to the 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 with the 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 with the 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 with the propellant conveying system, the downstream of the propellant conveying system is connected with the 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 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 entering the combustion system to participate in combustion, or
And the low-temperature propellant enters a propellant conveying system, is mixed with low-temperature propellant, and enters a thrust chamber cooling system to cool the thrust chamber.
The technical scheme of the invention has the following beneficial effects:
1) The invention provides a rocket bottom heat protection panel which is arranged at the bottom of a rocket and comprises an inner wall plate, an outer wall plate and a cooling pipeline, wherein a heat conducting medium is filled between the inner wall plate and the outer wall plate, the cooling pipeline is wrapped by the heat conducting medium, and the cooling pipeline is internally provided with a circulating cooling medium for exchanging heat with the heat conducting medium. The cooling pipeline and the outer wall plate indirectly exchange heat through the heat conducting medium, the temperature of the external environment of the cooling pipeline is constant everywhere, the heat exchange efficiency is improved, meanwhile, the heat protection panel realizes the temperature equalization of the cooling pipeline which are not contacted with each other through the heat conducting medium, the heat exchange effect is better, the active cooling efficiency is greatly improved, the density of the cooling pipeline can be correspondingly reduced, and the recycling 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 thermally protect 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 active cooling principle is adopted to protect the bottom of the rocket, so that 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 reusable performance is better.
2) The invention provides a rocket bottom thermal protection panel, a cooling pipeline comprises a plurality of coolant flow channels uniformly distributed between an inner wall plate and an outer wall plate, liquid collectors are arranged at the inlet end and the outlet end of the cooling pipeline, the liquid collectors are communicated with the plurality of coolant flow channels, and the liquid collectors collect and shunt cooling media in the plurality of flow channels at the same time, so that the flow of the cooling media is increased, and the heat exchange efficiency is further improved.
3) According to the rocket bottom thermal protection panel provided by the invention, the cooling pipeline is positioned on one side close to the outer wall plate, the outer side of the outer wall plate is in a high-temperature environment, the cooling pipeline is arranged on one side close to the high-temperature environment, the heat exchange efficiency is higher, and the protection effect on the protection side is better.
4) According to the liquid rocket bottom thermal protection system provided by the invention, the inlet end of the cooling pipeline is connected to the propellant conveying pipeline, the propellant conveying pipeline conveys the propellant into the cooling pipeline, the propellant is used as a cooling medium in the cooling pipeline, and the thermal protection system is in butt joint with the cooling system in the rocket, so that the structure is optimized, and the cost is reduced.
5) According to the liquid rocket bottom thermal protection system provided by the invention, the outlet end of the cooling pipeline can be connected with the thrust chamber cooling system/the combustion system/the propellant conveying system according to different temperatures of the propellant, so that the high-efficiency utilization of the cooled propellant is realized, the waste of the propellant is avoided, and the regenerative cooling of the system is realized.
6) The invention provides a liquid rocket bottom thermal protection method, which comprises the following steps: the propellant conveying pipeline conveys 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 enters the propellant conveying system, and enters the cooling system of the thrust chamber to cool the thrust chamber after being mixed with the low-temperature propellant. According to the method, the active cooling principle is adopted to protect the bottom of the rocket, so that the thermal protection performance of the bottom of the carrier rocket is greatly improved, the thermal protection system is in butt joint with the cooling system in the rocket, the efficient utilization of cooling propellant is realized, the waste of the propellant is avoided, and the cost is reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view showing a cross-sectional front view of a thermal protection panel according to an embodiment of the present invention;
FIG. 2 is a schematic top view 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 one 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 in accordance with yet another embodiment of the present invention.
Reference numerals illustrate:
10-a thermal protection panel; 11-an inner wall panel; 12-an outer wall plate; 2-a heat conducting medium; 3-coolant flow channels; 4-a cooling medium; 5-liquid collector.
Detailed Description
The following description of the embodiments of the present invention will be made more apparent and fully hereinafter with reference to the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present invention without making any inventive effort, are intended to fall within the scope of the present invention. In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
The invention provides a rocket bottom heat protection panel, which adopts an active cooling protection structure and can be used for heat protection in high-temperature environments, and the structure of the heat protection panel in one embodiment is shown in fig. 1 and 2.
As shown in fig. 1, in the present embodiment, heat protection panel 10 is an integrated panel that is added to the outer layer of the rocket base shield or serves as the rocket base shield. The panel structure comprises 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 the structure to be protected in the rocket, and the outer side of the outer wall plate 12 is a high-temperature environment of pneumatic heating and radiation heating generated by jet flow of the rocket engine. The 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 made of high heat conducting material, such as high heat conducting carbon/carbon, high heat conducting graphite and the like, so that after the outer wall plate 12 exchanges heat with the external high temperature environment, the heat conducting medium 2 exchanges heat with the outer wall plate 12, and heat is transferred to the heat conducting medium 2, and isothermal of the panel structure is realized.
The heat conducting medium 2 is internally 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 heat exchange with the heat conducting medium 2 is realized 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 a loop 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 liquid collectors 5, the liquid collectors 5 are respectively communicated with a plurality of coolant flow channels 3, and the cooling medium 4 is distributed or collected in the cooling pipeline through the liquid collectors 5, so that the flow of the cooling medium is improved, and the heat exchange capacity is further improved. In the present embodiment, as shown in fig. 1, since the outside of the outer wall plate 12 is a high-temperature environment, in order to further improve the heat exchange efficiency of the cooling medium 4, the cooling pipe is provided on the side closer to the outer wall plate 12. The shape and structure of the coolant flow channel 3 may be set according to the specific location of the rocket engine, which is not limited in the present invention.
In the present 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 passage 3 may be made of a high temperature resistant material having a good damage tolerance such as titanium alloy or stainless steel, so that the reusability of the panel is improved. In the present embodiment, the protection principle of the heat protection panel 10 is: the outer wall plate 12 transfers the heat of the outside high-temperature environment to the internal heat conducting medium 2, and as the outer wall of the coolant flow channel 3 is wrapped by the heat conducting medium 2, the circumference of the wall of the coolant flow channel 3 is isothermal everywhere, and the cooling pipeline can effectively cool the outer wall plate 12 without contacting the wall surface of the outer wall plate 12, so that the heat exchange efficiency is maximized. Meanwhile, the panel structure of the embodiment realizes the homogenization of cooling pipelines which are not contacted with each other through the heat conducting medium 2, compared with the traditional active cooling structure, the heat exchange efficiency is obviously improved, the whole cooling of the whole rocket bottom panel can be realized without dense arrangement of the panel inner coolant flow channels 3, and the structure weight is reduced. Preferably, the inner wall plate 11 is close to one side of the rocket interior to be protected, and in order to improve the protection effect, the inner wall plate 11 may be made of a nonmetallic material with good heat insulation effect, such as high temperature resistant glass, high temperature resistant ceramic, and the like.
In this embodiment, the thermal protection panel 10 is used as a carrier rocket bottom protection panel of a liquid rocket engine, and the cooling system of the thermal protection 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, and is 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, and the low-temperature propellant is used as a cooling medium 4 of the protective panel, thereby correspondingly simplifying the structure of a cooling system and reducing the cost.
As shown in fig. 3 to 5, the downstream of the cooling line can be connected to different downstream systems according to the temperature of the cooling medium 4 at the outlet end, so that the high-efficiency utilization of the propellant is realized.
In the embodiment shown in fig. 3, the cooling line of the thermal protection panel 10 is arranged upstream of the thrust chamber cooling system of the engine, i.e. the outlet end of the cooling line communicates to the thrust chamber cooling system. The cooling medium 4 (propellant) cools the bottom of the carrier rocket which is relatively low in thermal environment, and then cools the engine thrust chamber which is more severe in 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, flows into the inlet of the cooling system of the thrust chamber, cools the thrust chamber with higher thermal environment, and flows into the downstream system, for example, the combustion system to participate in combustion.
In the embodiment shown in fig. 4, the cooling lines of the thermal protection panel 10 are arranged upstream of the combustion system, i.e. the outlet ends of the cooling lines communicate to the combustion system. The cooling medium 4 (propellant) cools and exchanges heat to the bottom of the carrier rocket, and then enters the 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, flows out through the outlet end, and 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, exchanges heat with the heat protection panel 10, flows out through the outlet end, and is further connected with the outlet end of the propellant conveying system, and after the high-temperature propellant after heat exchange flowing out of the outlet end of the cooling pipeline is mixed with the low-temperature propellant of the propellant conveying system for cooling, the high-temperature propellant and the low-temperature propellant enter the thrust chamber cooling system together to cool the thrust chamber with higher thermal environment, and the propellant after heat exchange enters the downstream system, for example, enters the combustion system to participate in combustion.
According to the thermal protection system provided by the invention, the liquid rocket propellant is used as the cooling medium 4, so that the thermal protection performance of the bottom of the carrier rocket is greatly improved, and the applicable thermal environment range of the thermal protection system is far beyond that of a traditional passive 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, so that the utilization efficiency of the propellant is improved, the waste of the propellant is avoided, and a regenerative cooling system of the rocket engine is realized.
In another aspect, the present invention further provides a method for thermal protection of a bottom of a liquid rocket, which can be used for the thermal protection structure or the thermal protection panel, and includes the following steps:
The propellant conveying pipeline conveys 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 entering the combustion system to participate in combustion, or
And the low-temperature propellant enters a propellant conveying system, is mixed with low-temperature propellant, and enters a thrust chamber cooling system to cool the thrust chamber.
Specifically, the flow direction of the propellant after heat exchange in the heat protection panel 10 is determined by the propellant temperature at the outlet end, and when the propellant temperature at the outlet end is not higher than the preset temperature of the thrust chamber cooling system, the propellant still meets the requirement of cooling the thrust chamber with more severe 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 may continue to participate in the thrust chamber cooling when the temperature of the propellant in the cooling circuit rises no more than 150-250 ℃. When the temperature of the propellant in the cooling pipeline is 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 be mixed with the propellant in the cooling system of the thrust chamber to form a cooling medium with lower temperature to continuously participate in the cooling of the thrust chamber.
In the liquid rocket thermal protection panel, the system and the method provided by the invention, the flow rate of the cooling medium is determined by the thermal environment state and is suitable for the liquid rocket engine and the turbopump capacity. The temperature rise of the cooling medium after heat exchange cannot exceed the allowable temperature, and the maximum allowable temperature is the boiling point for some propellants (such as liquid oxygen and the like), and the thermal decomposition or thermochemical decomposition temperature for some propellants (such as liquid kerosene lamp).
For a thermal protection structure, the wall temperature of the structure must not exceed the allowable temperature of the material, the temperature of the thermal wall must not exceed the allowable temperature of the thermal stability condition of the corresponding material, the temperature of the cold wall must not cause the cooling medium 4 to boil or crack in a film state, and the wall temperature distribution of the cooling structure is adapted to the allowable strength of the material.
In some alternative embodiments, the inner panel 11 and the outer panel 12 of the thermal protection panel 10 may be made of a suitable material of construction according to the specific aerodynamic load requirements of the launch vehicle, thermal environmental conditions, and physical properties of the propellant, and the like, as the invention is not limited in this regard. Furthermore, the heat protection structure can adopt an integral integrated panel or a mode of splicing a plurality of panels, and each panel is provided with an independent cooling pipeline which is respectively connected with the propellant conveying pipeline and the downstream system.
It should be apparent that the above embodiments are merely examples for clarity of illustration and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.
Claims (5)
1. A liquid rocket bottom thermal protection system, comprising: rocket bottom thermal protection panel, propellant conveying pipeline, thrust chamber cooling system, combustion system and propellant conveying system, rocket bottom thermal protection panel locates the rocket bottom, includes:
An inner wall plate (11) positioned on a side close to the object to be protected;
An outer wall plate (12) positioned at one side close to the 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);
The cooling pipeline is arranged between the inner wall plate (11) and the outer wall plate (12) and is positioned at one side close to the outer wall plate (12), the outside of the cooling pipeline is wrapped by the heat conducting medium (2), the inside of the cooling pipeline is provided with a circulating cooling medium (4) for exchanging heat with the heat conducting medium (2), the cooling pipeline comprises a plurality of coolant flow channels (3) uniformly distributed between the inner wall plate (11) and the outer wall plate (12), liquid collectors (5) are respectively arranged at the inlet end and the outlet end of the cooling pipeline, and the liquid collectors (5) are communicated with the plurality of coolant flow channels (3);
The inlet end of the cooling pipeline is connected to a propellant conveying pipeline, and the propellant conveying pipeline conveys propellant into the cooling pipeline, and the propellant is used as the cooling medium (4) in the cooling pipeline;
The outlet end of the cooling pipeline is connected to one of a thrust chamber cooling system, a combustion system and a propellant conveying system, when the outlet end of the cooling pipeline is communicated with the thrust chamber cooling system, the propellant exchanges heat with the heat conducting medium (2) and then flows to the thrust chamber cooling system to cool the thrust chamber, when the outlet end of the cooling pipeline is communicated with the combustion system, the propellant exchanges heat with the heat conducting medium (2) and then flows to the combustion system to participate in combustion, and when the outlet end of the cooling pipeline is communicated with the propellant conveying system, the propellant exchanges heat with the heat conducting medium (2) and then flows to the propellant conveying system.
2. A liquid rocket bottom thermal protection system according to claim 1,
The coolant flow channels (3) are sequentially arranged in a ring shape around the rocket engine.
3. A liquid rocket bottom thermal protection system according to claim 1 or 2, wherein the thermally conductive medium (2) comprises at least one of highly thermally conductive carbon/carbon, highly thermally conductive graphite.
4. A liquid rocket bottom thermal protection system according to claim 1,
When the outlet end of the cooling pipeline is communicated with the propellant conveying system, the downstream of the propellant conveying system is connected with the 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.
5. A method for protecting the bottom of a liquid rocket, which is applied to the liquid rocket bottom thermal protection system of claim 1, and comprises the following steps:
The propellant conveying pipeline conveys 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 entering the combustion system to participate in combustion, or
And the low-temperature propellant enters a propellant conveying system, is mixed with low-temperature propellant, and enters a thrust chamber cooling system to cool the thrust chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910152770.0A CN109736972B (en) | 2019-02-28 | 2019-02-28 | Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910152770.0A CN109736972B (en) | 2019-02-28 | 2019-02-28 | Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109736972A CN109736972A (en) | 2019-05-10 |
| CN109736972B true CN109736972B (en) | 2024-06-07 |
Family
ID=66368941
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910152770.0A Active CN109736972B (en) | 2019-02-28 | 2019-02-28 | Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109736972B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111874273A (en) * | 2020-07-01 | 2020-11-03 | 北京坤飞航天科技有限公司 | Propellant filling system and propellant filling method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006212705A (en) * | 2006-02-06 | 2006-08-17 | Jfe Steel Kk | Heat insulating plate for induction heating device and induction heating device |
| CN101633405A (en) * | 2009-09-02 | 2010-01-27 | 北京航空航天大学 | Round pipe sandwich heat-preventing component |
| CN111630944B (en) * | 2007-06-15 | 2011-12-21 | 清华大学 | Rocket thrust chamber with sectional sintering porous wall surface |
| CN207850149U (en) * | 2017-11-10 | 2018-09-11 | 中冶赛迪装备有限公司 | A kind of cooling structure |
| CN209991872U (en) * | 2019-02-28 | 2020-01-24 | 北京星际荣耀空间科技有限公司 | Rocket bottom thermal protection panel and liquid rocket bottom thermal protection system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9493228B2 (en) * | 2012-11-28 | 2016-11-15 | The Boeing Company | High heat transfer rate reusable thermal protection system |
-
2019
- 2019-02-28 CN CN201910152770.0A patent/CN109736972B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006212705A (en) * | 2006-02-06 | 2006-08-17 | Jfe Steel Kk | Heat insulating plate for induction heating device and induction heating device |
| CN111630944B (en) * | 2007-06-15 | 2011-12-21 | 清华大学 | Rocket thrust chamber with sectional sintering porous wall surface |
| CN101633405A (en) * | 2009-09-02 | 2010-01-27 | 北京航空航天大学 | Round pipe sandwich heat-preventing component |
| CN207850149U (en) * | 2017-11-10 | 2018-09-11 | 中冶赛迪装备有限公司 | A kind of cooling structure |
| CN209991872U (en) * | 2019-02-28 | 2020-01-24 | 北京星际荣耀空间科技有限公司 | Rocket bottom thermal protection panel and liquid rocket bottom thermal protection system |
Non-Patent Citations (1)
| Title |
|---|
| 贾瑛.《大学化学》.2015,第226页. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109736972A (en) | 2019-05-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP3176537U (en) | High temperature graphite heat exchanger | |
| CN112431675B (en) | Combined scramjet engine cooling circulation system | |
| US10161691B2 (en) | Multi-channel cooling plenum | |
| CN206040826U (en) | A thermal management system for high altitude unmanned aerial vehicle fuel cell module | |
| CN108899442A (en) | Dynamic lithium battery bracket | |
| CN105914427A (en) | Average-temperature structure applied to energy storage device and device | |
| CN115837292B (en) | High-flow high-temperature heating system of hypersonic wind tunnel | |
| CN109736972B (en) | Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method | |
| CN110963084B (en) | Thermal control device suitable for space nuclear thermal propulsion system | |
| WO2023066259A1 (en) | Battery pack and energy storage system | |
| CN209991872U (en) | Rocket bottom thermal protection panel and liquid rocket bottom thermal protection system | |
| CN208862064U (en) | Battery pack structure | |
| CN206116564U (en) | Be applied to energy memory's samming structure and device | |
| CN109264030B (en) | Convection cooling active heat protection structure | |
| CN111237087B (en) | Micro-pore plate active and passive composite cooling structure for aerospace power and cooling method | |
| CN105870538A (en) | Electric automobile battery pack heat management structure | |
| CN109736974B (en) | Thermal protection device and liquid carrier rocket | |
| CN210106023U (en) | Thermal protection device and liquid carrier rocket | |
| CN215060132U (en) | Novel energy-saving heat preservation pipe | |
| CN218274667U (en) | Temperature control device for electric pile test system | |
| CN216481616U (en) | Heat accumulation type high-temperature high-pressure hot blast stove | |
| CN115013156B (en) | Near-field thermophotovoltaic power generation device for recovering waste heat of aviation turbojet engine | |
| Jianqing et al. | Study on heat dissipation performance of polymer electrolyte membrane fuel cell reactor based on ultra-thin uniform temperature plate | |
| CN110224196B (en) | Liquid cooling structure of square power battery | |
| CN208569296U (en) | A kind of heat exchange cooling device and litho machine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Applicant after: Beijing Star glory Space Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Applicant before: BEIJING I-SPACE TECHNOLOGY Co.,Ltd. |
|
| CB02 | Change of applicant information | ||
| GR01 | Patent grant |