CN109736972A - 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
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- CN109736972A CN109736972A CN201910152770.0A CN201910152770A CN109736972A CN 109736972 A CN109736972 A CN 109736972A CN 201910152770 A CN201910152770 A CN 201910152770A CN 109736972 A CN109736972 A CN 109736972A
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- 239000007788 liquid Substances 0.000 title claims abstract description 34
- 238000000034 method Methods 0.000 title abstract description 10
- 238000001816 cooling Methods 0.000 claims abstract description 127
- 239000002826 coolant Substances 0.000 claims abstract description 43
- 239000003380 propellant Substances 0.000 claims description 109
- 238000002485 combustion reaction Methods 0.000 claims description 15
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 9
- 238000002156 mixing Methods 0.000 claims description 8
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 239000003795 chemical substances by application Substances 0.000 claims description 6
- 229910002804 graphite Inorganic materials 0.000 claims description 3
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- 230000000694 effects Effects 0.000 abstract description 6
- 239000000463 material Substances 0.000 description 10
- 238000010438 heat treatment Methods 0.000 description 6
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- 238000009835 boiling Methods 0.000 description 2
- 239000004744 fabric 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
- 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
- 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
- 239000000110 cooling liquid Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
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- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
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Abstract
The present invention relates to carrier rocket thermal protection field, a kind of rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method are specifically provided.Thermal protection panel in rocket bottom is set to rocket bottom, comprising: inside panel, positioned at close to the side to fender；Exterior panel is filled with heat-conducting medium positioned at the side close to hot environment between inside panel and exterior panel, heat-conducting medium is used to exchange heat with exterior panel；And cooling line, it is set between inside panel and exterior panel, and wrapped up outside cooling line by heat-conducting medium, the internal cooling medium with circulation, for exchanging heat with heat-conducting medium.Thermal protection structure of the invention uses active cooling, and it is more preferable that thermal protection effect compares traditional passive type protection, and improves heat exchange efficiency using the combination of high-efficiency heat conduction and active cooling, and the efficient cooling of thermal protection structure is realized with less pipeline.
Description
Technical field
The present invention relates to carrier rocket thermal protection fields, and in particular to a kind of rocket bottom thermal protection panel, liquid rocket
Bottom thermal protection system and method.
Background technique
The Aerodynamic Heating and radiant heating that carrier rocket bottom is generated due to rocket engine jet flow, to protect rocket bottom
Engine pipelines and electrical equipment etc., need to take thermal protection measure to rocket bottom.Existing disposable rocket
Bottom generally uses the composite materials such as glass reinforced plastic, flexible high temperature adiabatic cloth that thermal protection structure is made.Reusable rocket exists
Return reenter during by atmosphere Aerodynamic Heating and jet flow heating double influence, thermal environment, which is apparently higher than, traditional disposably to be made
With carrier rocket, Base Heat protection is faced with huge technological challenge.
Traditional passive type thermal protection is the high temperature resistant for utilizing material ablation principle or material itself, the spy of lower thermal conductivity
Property realize, and ablation class material will appear serious ablation under the conditions of the high hot-fluid for the process that reenters, high dynamic pressure, degrade and ask
Topic, to meet reentry stage thermal protective performance, needs to improve the thickness of thermal protection structure, thus brings greatly promoting for weight, and
It needs to replace thermal protection shield after returning every time, cannot achieve reusable.And high performance non-ablative high temperature resistant material
Expect (such as novel C/SiC, C/C, superhigh temperature ceramics etc.) difficulty of processing it is big, cost is very high, small, brittleness that there are damage tolerances compared with
The problems such as big, is easily damaged under the conditions of reuse.Therefore reusable carrier rocket repeats there is an urgent need to one kind and makes
With property is good, thermal protection structure of efficient and light weight.
Summary of the invention
For the thermal protection low efficiency for solving traditional rocket bottom passive type thermal protection structure, easily there is ablation, degrades, simultaneously
Technical problem that is at high cost, reusing ability difference, the present invention provides a kind of active cooling and the good rocket bottoms of protection effect
Portion's thermal protection panel.
Meanwhile in order to solve the above technical problems, rocket bottom is carried out actively using propellant the present invention provides a kind of
Cooling liquid rocket bottom thermal protection system.
Further more, in order to solve the above technical problems, the present invention provides a kind of propellants to carry out active cooling to rocket bottom
Liquid rocket Base Heat means of defence.
In a first aspect, the present invention provides a kind of rocket bottom thermal protection panels, comprising:
Inside panel, positioned at close to the side to fender；
Exterior panel fills heat-conducting medium between the inside panel and the exterior panel positioned at the side close to hot environment,
The heat-conducting medium is used to exchange heat with the exterior panel；With
Cooling line is set between the inside panel and the exterior panel, and by described thermally conductive outside the cooling line
Medium package, the internal cooling medium with circulation, for exchanging heat with the heat-conducting medium.
The cooling line includes a plurality of coolant flow passages being evenly arranged between the inside panel and the exterior panel, described
The arrival end of cooling line and outlet end are equipped with liquid trap, and the liquid trap is connected to a plurality of coolant flow passages.
The a plurality of coolant flow passages are set gradually in a ring around rocket engine.
The cooling line is located at close to the side of the exterior panel.
The heat-conducting medium includes at least one of highly-conductive hot carbon/carbon, high thermal conductivity graphite.
Second aspect, the present invention provides a kind of liquid rocket bottom thermal protection systems, comprising:
Above-mentioned rocket bottom thermal protection panel, the arrival end of cooling line is connected to propellant energy properties pipeline, described to push away
Propellant is conveyed into the cooling line into agent transfer pipeline, the propellant is as the cooling in the cooling line
Medium.
The outlet end of the cooling line is connected to thrust chamber cooling system, and the propellant and the heat-conducting medium exchange heat
Afterwards, the thrust chamber cooling system is circulated to cool down thrust chamber.
The outlet end of the cooling line is connected to combustion system, after the propellant and the heat-conducting medium exchange heat, stream
It passes to the combustion system and participates in burning.
The outlet end of the cooling line is connected to propellant transfer system, and the propellant transfer system downstream connection pushes away
After power chamber cooling system, the propellant and heat-conducting medium heat exchange, it is circulated to the propellant transfer system, is pushed away with described
The thrust chamber cooling system is circulated to after into the cryogenic propellant blending in agent transportation system to cool down thrust chamber.
The third aspect, the present invention provides a kind of liquid rocket Base Heat means of defences, applied to above-mentioned rocket bottom
Thermal protection system comprising following steps:
Propellant energy properties pipeline is that propellant is conveyed in cooling line, and propellant and heat-conducting medium exchange heat；
Propellant temperature after heat exchange is not higher than thrust chamber cooling system preset temperature, and the propellant enters institute
Thrust chamber cooling system is stated, thrust chamber is cooled down；
Propellant temperature after heat exchange is higher than thrust chamber cooling system preset temperature,
The propellant enters combustion system and participates in burning, or
It is cold to thrust chamber progress to enter thrust chamber cooling system after into propellant transfer system, with cryogenic propellant blending
But.
Technical solution of the present invention has the following beneficial effects:
1) thermal protection panel in rocket bottom provided by the invention is set to rocket bottom, including inside panel, exterior panel and cooling
Pipeline is filled heat-conducting medium, is wrapped up outside cooling line by heat-conducting medium between inside panel and exterior panel, internal to have circulation
Cooling medium, be used for and heat-conducting medium exchange heat.Cooling line and exterior panel realize cooling tube by heat-conducting medium indirect heat exchange
External environment isothermal everywhere in road improves heat exchange efficiency, while thermal protection panel realizes non-touching cooling by heat-conducting medium
The samming of pipeline, heat transfer effect is more preferable, greatly improves active cooling efficiency, can accordingly reduce the closeness of cooling line, mention
The reusable performance of high thermal protection structure.Thermal protection panel can be added in rocket bottom shield outer layer, carry out heat to bottom shield
Protection can also realize the multipurpose of thermal protection panel directly as the bottom shield structure of active cooling.Using active cooling principle
Rocket bottom is protected, significant increase carrier rocket bottom thermal protective performance, the thermal environment range being applicable in is more than tradition
Passive type thermal protection structure, and reusable performance is more preferable.
2) thermal protection panel in rocket bottom provided by the invention, cooling line include being evenly arranged between inside panel and exterior panel
A plurality of coolant flow passages, the arrival end of cooling line and outlet end be equipped with liquid trap, and liquid trap is connected to a plurality of coolant flow
Road, liquid trap carry out afflux and shunting to the cooling medium in a plurality of runner simultaneously, increase the flow of cooling medium, and then improve
Heat exchange efficiency.
3) thermal protection panel in rocket bottom provided by the invention, cooling line are located at close to the side of exterior panel, exterior panel
Outside is hot environment, and cooling line is provided close to the side of hot environment, and heat exchange efficiency is higher, while the protection to protection side
Effect is more preferable.
4) arrival end of liquid rocket bottom provided by the invention thermal protection system, cooling line is connected to propellant energy properties
Pipeline, propellant energy properties pipeline convey propellant into cooling line, using propellant as the cooling medium in cooling line,
Thermal protection system is docked with the cooling system inside rocket, and optimization structure reduces cost.
5) outlet end of liquid rocket bottom provided by the invention thermal protection system, cooling line can be according to the temperature of propellant
Different connection thrust chamber cooling system/combustion system/propellant transfer systems are spent, the efficient utilization of cooling propellant is realized, keeps away
Exempt from propellant waste, realizes the re-generatively cooled of system.
6) liquid rocket Base Heat means of defence provided by the invention, comprising the following steps: propellant energy properties pipeline is cold
But propellant is conveyed in pipeline, propellant and heat-conducting medium exchange heat；Propellant temperature after heat exchange is not higher than thrust chamber
Cooling system preset temperature, the propellant enter the thrust chamber cooling system, cool down to thrust chamber；After heat exchange
The propellant temperature is higher than thrust chamber cooling system preset temperature, and the propellant enters combustion system and participates in burning, or into
Enter propellant transfer system, thrust chamber is cooled down with thrust chamber cooling system is entered after cryogenic propellant blending.The present invention
Method rocket bottom is protected using active cooling principle, significant increase carrier rocket bottom thermal protective performance, heat is anti-
Protecting system is docked with the cooling system inside rocket, realizes that cooling propellant efficiently utilizes, propellant is avoided to waste, reduce at
This.
Detailed description of the invention
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art be briefly described, it should be apparent that, it is described below
Attached drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not making the creative labor
It puts, is also possible to obtain other drawings based on these drawings.
Fig. 1 is the main view the schematic diagram of the section structure of thermal protection panel in one embodiment of the present invention；
Fig. 2 is the top view cross section structural schematic diagram of thermal protection panel in one embodiment of the present invention；
Fig. 3 is the schematic diagram of thermal protection system in one embodiment of the present invention；
Fig. 4 is the schematic diagram of thermal protection system in another embodiment of the present invention；
Fig. 5 is the schematic diagram of thermal protection system in another embodiment of the present invention.
Description of symbols:
10- thermal protection panel；11- inside panel；12- exterior panel；2- heat-conducting medium；3- coolant flow passages；4- cooling medium；
5- liquid trap.
Specific embodiment
Technical solution of the present invention is clearly and completely described below in conjunction with attached drawing, it is clear that described implementation
Mode is a part of the embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, this field is general
Logical technical staff every other embodiment obtained without making creative work, belongs to protection of the present invention
Range.As long as in addition, the non-structure each other of technical characteristic involved in invention described below different embodiments
It can be combined with each other at conflict.
The present invention provides a kind of rocket bottom thermal protection panel, which uses the safeguard structure of active cooling,
It can be used for the thermal protection of hot environment, a kind of structure of thermal protection panel in embodiment shown in Fig. 1, Fig. 2.
As shown in Figure 1, in the present embodiment, thermal protection panel 10 is integrated panel, add in outside rocket bottom shield
Layer or as rocket bottom shield.Panel construction includes inside panel 11, exterior panel 12 and is filled in thermally conductive between inside and outside siding
Medium 2.Thermal protection panel 10 is set to rocket bottom, and inside panel 11 is located at the side inside rocket to safeguard structure, outer wall
The outside of plate 12 is the hot environment of the Aerodynamic Heating that rocket engine jet flow generates and radiant heating.Inside panel 11 and exterior panel
Be filled with heat-conducting medium 2 between 12, heat-conducting medium 2 is highly heat-conductive material, such as it is high lead carbon/carbon, height leads graphite etc., thus outer wall
After plate 12 and the heat exchange of external high temperature environment, heat-conducting medium 2 exchanges heat to exterior panel 12, makes heat transfer to heat-conducting medium 2, real
The isothermal of existing panel construction.
Heat-conducting medium 2, which is embedded in, is equipped with cooling line, and the cooling medium 4 of flowing, cooling medium 4 are equipped in cooling line
It for cryogenic liquid, exchanges heat in flow process with heat-conducting medium 2, to realize the cooling to thermal protection panel 10.As Fig. 1,
Shown in Fig. 2, in the present embodiment, cooling line includes a plurality of coolant flow passages 3, and a plurality of coolant flow passages 3 are in interior exterior panel
Between be annularly arranged successively around rocket engine.The arrival end of cooling line and outlet end are provided with liquid trap 5, liquid trap
5 are respectively communicated with a plurality of coolant flow passages 3, and cooling medium 4 is shunted in cooling line by liquid trap 5 or afflux, improves cooling
Rate-of flow, and then improve exchange capability of heat.Runner in the present embodiment, as shown in Figure 1, due on the outside of exterior panel 12 be high temperature
Cooling line is set to closer to the side of exterior panel 12 by environment for the heat exchange efficiency for further increasing cooling medium 4.It needs
Illustrate, 3 shape and structure of coolant flow passages can be configured according to rocket engine specific location, and the present invention does not limit this
System.
In the present embodiment, thermal protection panel 10 be used as rocket bottom thermal protection panel, inside panel 11, exterior panel 12,
And the good heat-resisting material of titanium alloy, stainless steel equivalent damage tolerance can be used in the tube wall of coolant flow passages 3, improves the weight of panel
Multiple service performance.In the present embodiment, the preventing principle of thermal protection panel 10 are as follows: exterior panel 12 is by the warm of outside hot environment
Amount is transferred to internal heat-conducting medium 2, since the outer wall of coolant flow passages 3 is wrapped up by heat-conducting medium 2, coolant flow passages 3
Tube wall circumferential isothermal, the wall surface that cooling line does not contact exterior panel 12 everywhere can effectively cool down exterior panel 12, realize
Maximum heat exchange efficiency.The panel construction of present embodiment realizes non-touching cooling line by heat-conducting medium 2 simultaneously
Samming compares traditional active cooling structure, and heat exchange efficiency is obviously improved, and panel itself coolant flow passages 3 are not necessarily to intensive cloth
The entirety cooling that can be realized to entire rocket bottom panel is set, construction weight is reduced.Preferably, inside panel 11 is in rocket
Portion waits for the side of safeguard structure, and to improve protection effect, the nonmetallic materials of good heat-insulation effect are can be used in inside panel 11, such as resistance to
High temp glass, refractory ceramics etc..
In the present embodiment, carrier rocket foot guard panel of the thermal protection panel 10 as liquid-propellant rocket engine,
The cooling system of thermal protection panel 10 is connected to the cooling system of liquid-propellant rocket engine.Specifically, the entrance of cooling line
The propellant energy properties piping connection at end and liquid-propellant rocket engine, propellant energy properties pipeline transporting low temperature into cooling line promote
Agent, propellant are the coolant and fuel of liquid-propellant rocket engine, the generally Low Temperature Liquids such as liquid hydrogen, low temperature kerosene, liquid methane
Body, thus by protection face board and propellant energy properties piping connection, using cryogenic propellant as the cooling medium 4 of protection face board,
Corresponding simplified cooling system structure, reduces cost.
As shown in Figures 3 to 5, the downstream of cooling line can be connected to according to the temperature height of the cooling medium 4 of outlet end
Different down-stream systems realizes that the high efficiency of propellant utilizes.
In the embodiment shown in fig. 3, the thrust chamber cooling of engine is arranged in the cooling line of thermal protection panel 10
System upstream, the i.e. outlet end of cooling line are connected to thrust chamber cooling system.Cooling medium 4 (propellant) is first to thermal environment phase
Low carrier rocket bottom is cooled down, then the more harsh motor power room of thermal environment is cooled down.Specifically,
As shown in figure 3, cooling medium 4 flows into thermal protection panel 10 through arrival end, flowed out after exchanging heat to thermal protection panel 10 through outlet end,
And then thrust chamber cooling system entrance is flowed into, the higher thrust chamber of thermal environment is cooled down, the propellant after heat exchange flows into again
Down-stream system, such as participate in burning into combustion system.
In embodiment shown in Fig. 4, the cooling line of thermal protection panel 10 is arranged in combustion system upstream, i.e., cooling
The outlet end of pipeline is connected to combustion system.After cooling medium 4 (propellant) carries out cooling heat transferring to carrier rocket bottom, enter
Combustion system participates in burning.Specifically, as shown in figure 4, cooling medium 4 flows into thermal protection panel 10 through arrival end, to hot anti-
Protection slab 10 flows out after exchanging heat through outlet end, and then enters burning system together with the propellant of the outlet end of thrust chamber cooling system
System.
In embodiment shown in Fig. 5, the outlet end of cooling line is connected to propellant transfer system, propellant energy properties system
System downstream connection thrust chamber cooling system, the i.e. high-temperature propellant of cooling line outlet and the low temperature of propellant transfer system promote
Enter thrust chamber cooling system after agent blending.Specifically, as shown in figure 5, cooling medium 4 flows into thermal protection panel through arrival end
10, it is flowed out after exchanging heat to thermal protection panel 10 through outlet end, and then be connected with the outlet end of propellant transfer system, cooling line
It is common to enter after the cryogenic propellant blending cooling of high-temperature propellant and propellant transfer system after the heat exchange of outlet end outflow
Thrust chamber cooling system cools down the higher thrust chamber of thermal environment, and then the propellant after heat exchange enters downstream downstream system
System, such as participate in burning into combustion system.
Thermal protection system provided by the invention, using liquid rocket propellant as cooling medium 4, significant increase delivery
Rocket bottom thermal protective performance, the passive type thermal protection structure of the applicable remote ultra-traditional of thermal environment range.Thermal protection face simultaneously
The cooling system of plate can be connected to different down-stream systems according to discharge-end temperature, improve propellant utilization efficiency, avoid propellant
Waste, realizes the re-generatively cooled system of rocket engine.
On the other hand, the present invention also provides a kind of liquid rocket Base Heat means of defence, this method can be used for above-mentioned
Thermal protection structure or thermal protection panel comprising following steps:
Propellant energy properties pipeline is that propellant is conveyed in cooling line, and propellant and heat-conducting medium exchange heat；
Propellant temperature after heat exchange is not higher than thrust chamber cooling system preset temperature, and it is cooling that propellant enters thrust chamber
System cools down thrust chamber；
Propellant temperature after heat exchange is higher than thrust chamber cooling system preset temperature,
Propellant enters combustion system and participates in burning, or
It is cold to thrust chamber progress to enter thrust chamber cooling system after into propellant transfer system, with cryogenic propellant blending
But.
Specifically, the flow direction of the propellant after exchanging heat in thermal protection panel 10 is determined by the propellant temperature of outlet end
Fixed, when outlet end propellant temperature is not higher than thrust chamber cooling system preset temperature, propellant still meets to thermal environment more
For the cooling requirement of harsh thrust chamber, therefore the outlet end of thermal protection panel 10 is connected to thrust chamber cooling system, raising
Propellant utilization efficiency.Such as in an illustrative embodiment, when the propellant temperature rise in cooling line is not higher than 150
~250 DEG C, it is cooling that propellant can continue to participate in thrust chamber.And when the propellant temperature rise in cooling line is cooling higher than thrust chamber
When systemic presupposition temperature, propellant can not directly participate in thrust chamber cooling at this time, can be directly entered combustion system and participate in burning, or
The cooling medium to form lower temperature is blended with the propellant in thrust chamber cooling system, and it is cooling to continue to participate in thrust chamber.
It should be noted that in liquid rocket thermal protection panel provided by the invention, system and method, cooling medium
Flow determined by thermal environment state, while being adapted with liquid-propellant rocket engine and turbine pump capacity.Cooling medium is exchanging heat
Afterwards, temperature rise is no more than allowable temperature, and maximum allowable temperature is boiling point for certain propellants (such as liquid oxygen etc.), certain
A little propellants (such as liquid kerosene lamp) are then thermal decomposition or Thermochemical Decomposition temperature.
For thermal protection structure, structure wall temperature must not exceed material allowable temperature, and hot wall temperature must not exceed respective material
The temperature of thermal stability condition allowed, cold wall Wen Buying make cooling medium 4 film boiling or cracking, and cooling knot occur
The wall temperature distribution of structure and the allowable strength of material are adapted.
In some alternative embodiments, the inside panel 11 of thermal protection panel 10 and exterior panel 12 can have according to carrier rocket
The suitable structural material of the selections such as aerodynamic force bearing requirements, thermal environment condition and propellant physical property of body, the present invention do not make this
Limitation.Further more, the integral panel of an entirety can be used in thermal protection structure, the form of multiple panel splicings can also be used,
Each panel has independent cooling line, is connected respectively with propellant energy properties pipeline and down-stream system.
Obviously, above embodiment is only intended to clearly illustrate example, and does not limit the embodiments.
For those of ordinary skill in the art, other various forms of variations can also be made on the basis of the above description
Or it changes.There is no necessity and possibility to exhaust all the enbodiments.And obvious variation extended from this
Or it changes still within the protection scope of the invention.
Claims (10)
1. a kind of rocket bottom thermal protection panel is set to rocket bottom characterized by comprising
Inside panel (11), positioned at close to the side to fender；
Exterior panel (12) is filled between the inside panel (11) and the exterior panel (12) positioned at the side close to hot environment
Have heat-conducting medium (2), the heat-conducting medium (2) is used to exchange heat with the exterior panel (12)；With
Cooling line is set between the inside panel (11) and the exterior panel (12), and by described outside the cooling line
Heat-conducting medium (2) package, the internal cooling medium (4) with circulation, for exchanging heat with the heat-conducting medium (2).
2. thermal protection panel in rocket bottom according to claim 1, which is characterized in that
The cooling line includes a plurality of coolant flow passages being evenly arranged between the inside panel (11) and the exterior panel (12)
(3), the arrival end of the cooling line and outlet end are equipped with liquid trap (5), and the liquid trap (5) is connected to a plurality of cooling
Agent runner (3).
3. thermal protection panel in rocket bottom according to claim 2, which is characterized in that
The a plurality of coolant flow passages (3) set gradually in a ring around rocket engine.
4. thermal protection panel in rocket bottom according to any one of claims 1 to 3, which is characterized in that the cooling line
Positioned at the side close to the exterior panel (12).
5. thermal protection panel in rocket bottom according to any one of claims 1 to 3, which is characterized in that the heat-conducting medium
It (2) include at least one of highly-conductive hot carbon/carbon, high thermal conductivity graphite.
6. a kind of liquid rocket bottom thermal protection system characterized by comprising
Thermal protection panel in rocket bottom according to any one of claims 1 to 5, the arrival end of cooling line are connected to propulsion
Agent transfer pipeline, the propellant energy properties pipeline convey propellant into the cooling line, and the propellant is as described cold
But the cooling medium (4) in pipeline.
7. liquid rocket bottom according to claim 6 thermal protection system, which is characterized in that
The outlet end of the cooling line is connected to thrust chamber cooling system, and the propellant and the heat-conducting medium (2) exchange heat
Afterwards, the thrust chamber cooling system is circulated to cool down thrust chamber.
8. liquid rocket bottom according to claim 6 thermal protection system, which is characterized in that
The outlet end of the cooling line is connected to combustion system, after the propellant and the heat-conducting medium (2) exchange heat, circulation
Burning is participated in the combustion system.
9. liquid rocket bottom according to claim 6 thermal protection system, which is characterized in that
The outlet end of the cooling line is connected to propellant transfer system, the propellant transfer system downstream connection thrust chamber
After cooling system, the propellant and the heat-conducting medium (2) heat exchange, it is circulated to the propellant transfer system, is pushed away with described
The thrust chamber cooling system is circulated to after into the cryogenic propellant blending in agent transportation system to cool down thrust chamber.
10. a kind of liquid rocket Base Heat means of defence, which is characterized in that be applied to rocket Base Heat as claimed in claim 6
Guard system comprising following steps:
Propellant energy properties pipeline is that propellant is conveyed in cooling line, and propellant and heat-conducting medium exchange heat；
Propellant temperature after heat exchange is not higher than thrust chamber cooling system preset temperature, pushes away described in the propellant entrance
Power chamber cooling system, cools down thrust chamber；
Propellant temperature after heat exchange is higher than thrust chamber cooling system preset temperature,
The propellant enters combustion system and participates in burning, or
Enter thrust chamber cooling system after into propellant transfer system, with cryogenic propellant blending to cool down thrust chamber.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910152770.0A CN109736972B (en) | 2019-02-28 | 2019-02-28 | Rocket bottom thermal protection panel, liquid rocket bottom thermal protection system and method |
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| 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 |
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| CN109736972A true CN109736972A (en) | 2019-05-10 |
| CN109736972B CN109736972B (en) | 2024-06-07 |
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Cited By (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 |
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