CN117365783A - High-performance liquid rocket engine thrust chamber head-body connection method - Google Patents
High-performance liquid rocket engine thrust chamber head-body connection method Download PDFInfo
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- CN117365783A CN117365783A CN202311414214.9A CN202311414214A CN117365783A CN 117365783 A CN117365783 A CN 117365783A CN 202311414214 A CN202311414214 A CN 202311414214A CN 117365783 A CN117365783 A CN 117365783A
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- connecting layer
- performance liquid
- rocket engine
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- 238000000034 method Methods 0.000 title claims abstract description 33
- 239000007788 liquid Substances 0.000 title claims abstract description 24
- 239000000919 ceramic Substances 0.000 claims abstract description 52
- 238000005266 casting Methods 0.000 claims abstract description 7
- 230000007704 transition Effects 0.000 claims abstract description 5
- 239000010410 layer Substances 0.000 claims description 58
- 239000000956 alloy Substances 0.000 claims description 20
- 229910045601 alloy Inorganic materials 0.000 claims description 19
- 238000005245 sintering Methods 0.000 claims description 18
- 239000000463 material Substances 0.000 claims description 15
- 230000008569 process Effects 0.000 claims description 11
- 239000002002 slurry Substances 0.000 claims description 11
- 229910001092 metal group alloy Inorganic materials 0.000 claims description 9
- 238000007747 plating Methods 0.000 claims description 8
- 239000004576 sand Substances 0.000 claims description 7
- 239000003431 cross linking reagent Substances 0.000 claims description 6
- 239000002270 dispersing agent Substances 0.000 claims description 6
- 239000002245 particle Substances 0.000 claims description 6
- 238000012545 processing Methods 0.000 claims description 6
- WGTYBPLFGIVFAS-UHFFFAOYSA-M tetramethylammonium hydroxide Chemical group [OH-].C[N+](C)(C)C WGTYBPLFGIVFAS-UHFFFAOYSA-M 0.000 claims description 6
- 238000003723 Smelting Methods 0.000 claims description 5
- 238000006356 dehydrogenation reaction Methods 0.000 claims description 5
- 238000004108 freeze drying Methods 0.000 claims description 5
- 238000007710 freezing Methods 0.000 claims description 5
- 230000008014 freezing Effects 0.000 claims description 5
- 238000001755 magnetron sputter deposition Methods 0.000 claims description 5
- 239000000843 powder Substances 0.000 claims description 5
- 238000007158 vacuum pyrolysis Methods 0.000 claims description 5
- 238000001513 hot isostatic pressing Methods 0.000 claims description 4
- KHYBPSFKEHXSLX-UHFFFAOYSA-N iminotitanium Chemical group [Ti]=N KHYBPSFKEHXSLX-UHFFFAOYSA-N 0.000 claims description 4
- 229910001000 nickel titanium Inorganic materials 0.000 claims description 4
- RMAQACBXLXPBSY-UHFFFAOYSA-N silicic acid Chemical compound O[Si](O)(O)O RMAQACBXLXPBSY-UHFFFAOYSA-N 0.000 claims description 4
- 238000013461 design Methods 0.000 claims description 3
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 claims description 3
- 229910052863 mullite Inorganic materials 0.000 claims description 3
- ZIUHHBKFKCYYJD-UHFFFAOYSA-N n,n'-methylenebisacrylamide Chemical group C=CC(=O)NCNC(=O)C=C ZIUHHBKFKCYYJD-UHFFFAOYSA-N 0.000 claims description 3
- 238000004321 preservation Methods 0.000 claims description 3
- 238000007670 refining Methods 0.000 claims description 3
- 239000002344 surface layer Substances 0.000 claims description 3
- 229910052845 zircon Inorganic materials 0.000 claims description 3
- GFQYVLUOOAAOGM-UHFFFAOYSA-N zirconium(iv) silicate Chemical compound [Zr+4].[O-][Si]([O-])([O-])[O-] GFQYVLUOOAAOGM-UHFFFAOYSA-N 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims description 2
- 230000001070 adhesive effect Effects 0.000 claims description 2
- 239000013077 target material Substances 0.000 claims description 2
- 239000002184 metal Substances 0.000 abstract description 16
- 229910052751 metal Inorganic materials 0.000 abstract description 16
- 238000005495 investment casting Methods 0.000 abstract description 3
- 238000000016 photochemical curing Methods 0.000 abstract description 3
- 239000011247 coating layer Substances 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 235000015895 biscuits Nutrition 0.000 description 2
- 238000005219 brazing Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 239000011153 ceramic matrix composite Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000002513 implantation Methods 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The invention provides a high-performance liquid rocket engine thrust chamber head and body connecting method, which is characterized in that a strengthened and toughened SiC ceramic body is prepared through photo-curing forming and gel casting, a transition layer is plated on the surface of a ceramic connecting layer, and investment precision casting is carried out on the transition layer, so that the high-reliability connection between a thrust chamber metal head and the ceramic body is realized. The complex structure of the connecting layer provides more interfaces for the connection of ceramics and metal, improves the combination stability, improves the fatigue performance of the connection of the head and the body, and meets the requirements of high performance and multiple ignition of the attitude control engine.
Description
Technical Field
The invention relates to the advanced manufacturing field, in particular to a high-performance liquid rocket engine thrust chamber head and body connecting method.
Background
Because of the advantages of light weight, high temperature ablation resistance and the like, the C/SiC ceramic matrix composite is considered as an ideal material for realizing the light weight of the thrust chamber jet pipe of the attitude and orbit control engine. At present, ceramic is gradually adopted as a jet pipe material for a domestic and foreign attitude and orbit control engine thrust chamber, but a thrust chamber head injector is usually made of an alloy material, and the integral processing of the head and the jet pipe is difficult to realize.
This is because the atomic bonding mode, thermal expansion coefficient, thermal conductivity, electrical conductivity, microstructure, etc. of ceramics and metals are different, so that there is a difficulty in connecting the two. In addition, along with the continuous improvement of the requirements of the high-performance liquid rocket attitude and orbit control engine on the chamber pressure of the thrust chamber, the heat flow density and the pressure born by the spray pipe in the working process of the engine are further increased, and the connection of the ceramic spray pipe and the metal head becomes an important factor for limiting the improvement of the chamber pressure of the thrust chamber of the liquid rocket engine.
The ceramic body part and the metal alloy head part of the thrust chamber of the current attitude and orbit control engine are mainly connected by adopting a transient liquid phase diffusion brazing method, but the ceramic-metal connection strength realized by the method can not meet the performance requirement of a high-performance engine, and the problems of high residual stress, low connection strength and the like exist. To achieve the improvement of the performance such as the specific impulse and the chamber pressure of the engine, the problem of high-strength connection between the ceramic spray pipe and the metal head needs to be solved.
Disclosure of Invention
The invention solves the technical problems that: in order to overcome the defects of the prior art, the method for connecting the head and the body of the thrust chamber of the high-performance liquid rocket engine is provided, the residual stress is reduced, and the connection strength is improved.
The technical scheme of the invention is as follows: after the SiC ceramic body is structurally designed, a connecting layer is structurally designed on the surface of the body, so that the connecting layer has a multi-element arrangement structure;
forming a wax film according to the designed SiC ceramic body and the connecting layer, and processing the body and the connecting layer wax film to obtain a SiC ceramic body and connecting layer combination;
plating an alloy film on the connecting layer, and performing vacuum sintering and dehydrogenation sintering on the connecting layer after plating the alloy film; then putting the ceramic body and connecting layer combination into PSB powder, and forming on the connecting layer to obtain a metal alloy head wax film; and (3) processing the metal alloy head wax film to obtain the thrust chamber blank with the alloy head and the SiC ceramic body integrated.
Further, the multi-element arrangement structure of the connecting layer is a zigzag structure or a multi-layer framework structure or a special-shaped staggered structure.
Further, the process of treating the body and the tie layer wax film includes: preparing SiC ceramic slurry; pouring SiC ceramic slurry into the body and the connecting layer wax film, solidifying the slurry, and performing freeze drying and vacuum pyrolysis to obtain a ceramic blank; and performing hot isostatic pressing sintering on the ceramic blank to obtain the body and connecting layer combination.
Still further, the slurry comprises ceramic particles, a cross-linking agent and a dispersing agent, wherein the purity of the ceramic particles is more than or equal to 99.99%, the particle size is 5-20 mu m, the cross-linking agent is methylene bisacrylamide, the adding amount is 1-5wt.% of the total mass, the dispersing agent is tetramethyl ammonium hydroxide solution, and the adding amount is 0.2-1wt.% of the total mass.
The freezing temperature of freeze drying is minus 40 ℃ to minus 50 ℃, the freezing time is 5h to 6h, the temperature is slowly increased to 560 ℃ to 620 ℃ according to the speed of 2 ℃/min in the vacuum pyrolysis process, and the temperature is kept at 560 ℃ to 620 ℃ for 50 min to 80min.
The pressure is 18-24 MPa, and the sintering temperature is 1450-1550 ℃.
Further, the target material of the alloy plating magnetron sputtering for the connecting layer blank is Ni-Ti alloy, the vacuum sintering temperature is 980-1050 ℃, the time is 25-35 min, the dehydrogenation sintering temperature is 820-860 ℃, and the heat preservation time is 85-100 min.
Further, the process for treating the metal alloy head wax film comprises the following steps: preparing a shell on the outer surface of the wax mould of the metal alloy head; dewaxing the wax mould and roasting the dewaxed shell; and smelting and casting the shell by using alloy liquid.
Still further, the binder of the mold shell is silica sol, the viscosity is 38-55s, the surface layer material and the transition material are zircon sand, the grain size of sand grains is 80/100 meshes, the back layer material is mullite sand, and the mesh size is 200 meshes.
Dewaxing is carried out after the dwell time is 8-12min under the conditions that the temperature is 160-180 ℃ and the dwell pressure is 0.55-0.70MPa, the roasting temperature is 980-1020 ℃, and the roasting time is more than or equal to 4 hours.
During smelting and casting, the alloy is liquefied and then heated to 1500-1530 ℃ for refining, and then cooled to 1450+/-5 ℃ for casting, and the vacuum degree is kept to be less than 7.5X10-2 Torr (10 Pa) in the process.
Compared with the prior art, the invention has the advantages that: the diffusion brazing connection of traditional attitude control engine thrust chamber metal head and ceramic body is broken through, the toughened SiC ceramic body is prepared through photocuring forming and gel casting, and the high-reliability connection of the thrust chamber metal head and the ceramic body is realized through plating a connecting layer on the ceramic surface and investment precision casting on the connecting layer.
(1) The complex structure of the connecting layer provides more interfaces for the connection of ceramics and metal, and improves the combination stability;
(2) The structure of the ceramic connecting layer is metallurgically bonded with the head metal, so that part of cracks can be dispersed on the microstructure to inhibit the expansion of macroscopic cracks;
(3) The matching of different ceramics and metals can be adapted by regulating the thickness of the connecting layer, so that creep cracks are inhibited;
(4) The fatigue performance of the connection of the head and the body is improved, and the requirements of high performance and multiple ignition of the attitude control engine are met.
Drawings
FIG. 1 is a schematic view of a rocket engine thrust chamber of the present invention;
FIG. 2 is a flow chart of the connection method of the present invention;
FIG. 3 is a schematic view of a zigzag connecting layer according to the present invention;
FIG. 4 is a schematic view of a multi-layer skeletal connecting layer structure of the present invention;
fig. 5 is a schematic view of the structure of the special-shaped staggered connection layer of the present invention.
Detailed Description
In order to better understand the technical scheme of the present invention, the following specific description of the embodiments of the present invention is provided with reference to the accompanying drawings.
The embodiment of the invention is a liquid rocket engine thrust chamber, and as shown in fig. 1, the liquid rocket engine thrust chamber is mainly formed by connecting a thrust chamber head part 1 and a thrust chamber body part 2 through a connecting layer 3. The head material is high-temperature alloy, and can be GH4169, GH4202 and the like, and the body material is SiC ceramic material. The connecting part between the body and the head is provided with a connecting layer which can adopt a zigzag structure (shown in figure 3), can be in triangular zigzag continuous arrangement, or a multi-layer framework structure (shown in figure 4), can be in repeated arrangement of square units, or is in a special-shaped staggered structure (shown in figure 5) and is in strip interweaving arrangement. The surface of the connecting layer is coated with a metal coating layer with the activity similar to that of the metal material.
The implementation steps are as follows:
step 1: the three-dimensional modeling is carried out on the die of the thrust chamber body 2 by using computer aided design software, the connecting layer 3 is designed on the surface of the thrust chamber body 2, and the three-dimensional model of the connecting layer 3 is designed into a plurality of staggered frameworks.
Step 2: and (3) forming the wax patterns of the thrust chamber body part 2 and the connecting layer 3 by adopting a photo-curing method according to the three-dimensional model designed in the step (1).
Step 3: the SiC ceramic slurry is prepared by adopting high-purity non-spherical SiC ceramic powder with the purity of 99.99 percent and the grain diameter of 5-20 mu m, methylene bisacrylamide as a cross-linking agent and tetramethylammonium hydroxide solution as a dispersing agent. The amount of the cross-linking agent is 1-5wt.% of the total amount, and the amount of the dispersing agent is 0.2-1wt.% of the total amount.
Step 4: pouring the SiC ceramic slurry prepared in the step 3 into the wax mould prepared in the step 2, freeze-drying for 5-6 hours at a freezing temperature of minus 40 ℃ to minus 50 ℃ after the slurry is completely solidified, slowly heating to 600 ℃ at a speed of 2 ℃/min, then preserving heat for 60min at 600 ℃, and carrying out vacuum pyrolysis to obtain ceramic biscuit of the thrust chamber body 2 and the connecting layer 3;
step 5: and (3) performing hot isostatic pressing sintering on the ceramic biscuit prepared in the step (4), wherein the hot isostatic pressing pressure is 20MPa, and the sintering temperature is 1500 ℃. The thrust chamber body and the connecting layer 3SiC ceramic were obtained.
Step 6: preparing a connecting layer 3Ni-Ti coating layer between the ceramic of the thrust chamber body 2 and the metal of the thrust chamber head 1. The magnetron sputtering process is adopted inThe ceramic skeleton of the connecting layer 3 is plated with a Ni film, and the magnetron sputtering target is Ni alloy. And (3) placing the connecting layer 3 subjected to magnetron sputtering coating into a vacuum sintering furnace for high-temperature vacuum sintering at the temperature of 1000 ℃ for 30 minutes. Followed by implantation of TiH 2 The powder is subjected to high-temperature vacuum sintering and titanizing dehydrogenation, the sintering temperature is 850 ℃, and the heat preservation time is 90 minutes. A bonded body of the thrust chamber body 2SiC ceramic and the ni—ti film-plated connection layer 3 was obtained.
Step 7: the wax film of the thrust chamber head 1 is molded. The combined body of the SiC ceramic of the thrust chamber body part 2 and the Ni-Ti connecting layer 3 is placed into a laser selective forming device, a designed head three-dimensional model is led into a device system, the forming material is PSB powder, proper parameters such as laser power, scanning speed, scanning path and the like are selected, and a wax model of the thrust chamber head 1 is formed on the connecting layer 3 plated with the Ni-Ti film by adopting a laser selective forming process.
Step 8: step 7, preparing a shell on the outer surface of the wax mould of the thrust chamber head 1, wherein the shell is a silica sol shell, and the adhesive is silica sol and has the viscosity of 38-55s; the surface layer material and the transition material are zircon sand, the grain size is 80/100 meshes, the back layer material is mullite sand, and the grain size is 200 meshes.
Step 9: the shell obtained in the step 8 is heated to 160-180 ℃; the pressure of the pressure maintaining is 0.55-0.70MPa; removing the wax mould after the dwell time is 8-12min, and roasting the dewaxed shell at 980-1020 ℃; the roasting time is not less than 4 hours. After firing, the shell of the thrust chamber head 1 is obtained.
Step 10: smelting high-temperature alloy, heating to 1500-1530 ℃ for refining after liquefying the high-temperature alloy, cooling to 1450+/-5 ℃ for pouring, and pouring into a shell of the thrust chamber head 1, wherein the vacuum degree is kept to be less than 7.5X10-2 Torr (10 Pa) in the process.
Step 11: and polishing to remove the shell of the thrust chamber head 1, and obtaining the metal and ceramic integrated thrust chamber blank.
Step 12: and processing the blank of the thrust chamber, and performing performance tests such as liquid flow and hydraulic strength tests to obtain the thrust chamber meeting the design requirements.
In conclusion, the liquid rocket engine thrust chamber head-body connecting layer prepared by the method breaks through the traditional method that the ceramic/metal connection only depends on materials to realize the connection of the thrust chamber head-body, and the high-temperature alloy and the SiC ceramic are connected in a high-reliability manner through the combination of ceramic surface structural design and metal coating layer plating and investment precision casting.
It will be understood that the invention has been described by way of example only, and that various changes in the features and examples may be made, or equivalents may be substituted, by way of illustration, without departing from the spirit and scope of the invention. In addition, many modifications may be made to adapt a particular situation to the teachings of the invention without departing from its spirit and scope. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this invention, but that the invention will include all embodiments falling within the scope of the appended claims.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Claims (11)
1. The method for connecting the head and the body of the thrust chamber of the high-performance liquid rocket engine is characterized by comprising the following steps of:
carrying out structural design on the connecting layer on the surface of the SiC ceramic body part to enable the connecting layer to have a multi-element arrangement structure;
forming a wax film according to the designed SiC ceramic body and the connecting layer, and processing the body and the connecting layer wax film to obtain a SiC ceramic body and connecting layer combination;
plating an alloy film on the connecting layer, and performing vacuum sintering and dehydrogenation sintering on the connecting layer after plating the alloy film; then putting the ceramic body and connecting layer combination into PSB powder, and forming on the connecting layer to obtain a metal alloy head wax film; and (3) processing the metal alloy head wax film to obtain the thrust chamber blank with the alloy head and the SiC ceramic body integrated.
2. The method for connecting the thrust chamber head and the body of the high-performance liquid rocket engine according to claim 1, wherein the multi-element arrangement structure of the connecting layer is a zigzag structure or a multi-layer framework structure or a special-shaped staggered structure.
3. A method of connecting a thrust chamber head and body of a high performance liquid rocket engine as recited in claim 1, wherein the step of treating the body and the connecting layer wax film comprises: preparing SiC ceramic slurry; pouring SiC ceramic slurry into the body and the connecting layer wax film, solidifying the slurry, and performing freeze drying and vacuum pyrolysis to obtain a ceramic blank; and performing hot isostatic pressing sintering on the ceramic blank to obtain the body and connecting layer combination.
4. The method for connecting the thrust chamber head and the body of the high-performance liquid rocket engine according to claim 3, wherein the slurry comprises ceramic particles, a cross-linking agent and a dispersing agent, the purity of the ceramic particles is more than or equal to 99.99%, the particle size is 5-20 mu m, the cross-linking agent is methylene bisacrylamide, the adding amount is 1-5wt.% of the total mass, the dispersing agent is tetramethyl ammonium hydroxide solution, and the adding amount is 0.2-1wt.% of the total mass.
5. A method for connecting a thrust chamber head and a body of a high-performance liquid rocket engine according to claim 3, wherein the freezing temperature of freeze drying is-40 ℃ to-50 ℃, the freezing time is 5h to 6h, the vacuum pyrolysis process is slowly heated to 560 ℃ to 620 ℃ at a speed of 2 ℃/min, and the heat is preserved for 50 min to 80min at 560 ℃ to 620 ℃.
6. A method for connecting a thrust chamber and a head body of a high-performance liquid rocket engine according to claim 3, wherein the pressure is 18-24 MPa, and the sintering temperature is 1450-1550 ℃.
7. The method for connecting the thrust chamber head and the body of the high-performance liquid rocket engine according to claim 1, wherein the target material for magnetron sputtering of the alloy plating alloy of the blank of the connecting layer is Ni-Ti alloy, the vacuum sintering temperature is 980-1050 ℃, the time is 25-35 min, the dehydrogenation sintering temperature is 820-860 ℃, and the heat preservation time is 85-100 min.
8. A method of connecting a thrust chamber head and body of a high performance liquid rocket engine as recited in claim 1, wherein the process of treating the metallic alloy head wax film comprises: preparing a shell on the outer surface of the wax mould of the metal alloy head; dewaxing the wax mould and roasting the dewaxed shell; and smelting and casting the shell by using alloy liquid.
9. The method for connecting the thrust chamber head and the body of the high-performance liquid rocket engine according to claim 8, wherein the adhesive of the shell is silica sol, the viscosity is 38-55s, the surface layer material and the transition material are zircon sand, the grain size is 80/100 meshes, the back layer material is mullite sand, and the mesh size is 200 meshes.
10. The method for connecting the head and the body of the thrust chamber of the high-performance liquid rocket engine according to claim 8, wherein dewaxing is carried out after 8-12min of dwell time under the conditions that the temperature is 160-180 ℃ and the dwell pressure is 0.55-0.70MPa, and the roasting temperature is 980-1020 ℃ and the roasting time is more than or equal to 4 hours.
11. The method for connecting a thrust chamber and a head body of a high-performance liquid rocket engine according to claim 8, wherein during smelting and casting, the temperature of the liquefied alloy is raised to 1500-1530 ℃ for refining, then the temperature is lowered to 1450+/-5 ℃, and the vacuum degree is kept to be less than 7.5X10-2 Torr (10 Pa) during the process.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311414214.9A CN117365783A (en) | 2023-10-27 | 2023-10-27 | High-performance liquid rocket engine thrust chamber head-body connection method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311414214.9A CN117365783A (en) | 2023-10-27 | 2023-10-27 | High-performance liquid rocket engine thrust chamber head-body connection method |
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