CN114251195A - Thrust chamber head structure and thrust chamber start many times - Google Patents
Thrust chamber head structure and thrust chamber start many times Download PDFInfo
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- CN114251195A CN114251195A CN202111481508.4A CN202111481508A CN114251195A CN 114251195 A CN114251195 A CN 114251195A CN 202111481508 A CN202111481508 A CN 202111481508A CN 114251195 A CN114251195 A CN 114251195A
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- top cover
- thrust chamber
- reinforcing rib
- welding
- ribs
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- 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
Abstract
The invention discloses a repeatedly started thrust chamber head structure and a thrust chamber, wherein in the repeatedly started thrust chamber head structure, on the premise that a bearing cone keeps a conical upward contraction configuration, a liquid oxygen top cover, the bearing cone and a reinforcing rib can be integrally designed by adopting a compact design of two hole seats and adopting non-contact electron beam welding or laser welding to replace the traditional argon arc welding or flange connection of the two hole seats. Compared with the traditional split type welding structure, the invention effectively reduces the number of welding seams and welding heat input, reduces the welding procedure after welding detection, and simultaneously reduces the influence on the deformation of the injector.
Description
Technical Field
The invention belongs to the technical field of liquid rocket engines, and particularly relates to a repeatedly started thrust chamber head structure and a thrust chamber.
Background
The oxyhydrogen rocket engine takes liquid hydrogen and liquid oxygen as propellants, has the advantages of high specific impulse, no pollution and the like, and is one of mainstream propulsion technologies adopted by superior engines, deep space detectors and the like in the world at present. During operation, fuel hydrogen and oxidant liquid oxygen are respectively distributed to the nozzle through the hydrogen head cavity and the oxygen head cavity, the hydrogen and the oxygen are mixed in the outlet area of the nozzle and then combusted, chemical energy is converted into heat energy and pressure potential energy, and then combustion products are extruded and discharged through the throat part and the spray pipe to generate thrust.
The head of the oxyhydrogen rocket engine is provided with hundreds or even hundreds of nozzles, and because welding seams such as a plurality of nozzle brazing seams in the head assembly are used for blocking the oxyhydrogen front-view function, detailed detection of the welding seams and the like in the injector is needed to ensure that the oxyhydrogen does not generate cavity explosion and the nozzle circumferential seams meet the design requirements and do not generate local ablation. The active engine generally needs to assemble and braze the gunpowder nozzle, the first base and the second base to form the injector assembly, and then carry out subsequent welding processing to form the head. The engine head structure is relatively complex, and the disassembly step causes that the injector still has more welding procedures after the brazing detection, so that the injector is deformed, and the difficulty of ensuring design indexes such as a nozzle circumferential seam and the like is brought.
The upper-level oxyhydrogen rocket engine generally requires a multi-ignition starting function, and the common scheme at present adopts 2 powder igniters to be arranged on a two-hole seat provided with 2 mounting holes to realize multi-starting. Considering the compactness of the spatial layout, the small internal space between the head oxygen top cover and the bearing cone is required to be used for installing the cartridge igniter. And because the volume of the two-hole seat is larger than that of the single-ignition adapter, the bearing cone and the liquid oxygen top cover are required to be designed separately in the traditional upper-level hydrogen-oxygen rocket engine, so that the two-hole seat and the liquid oxygen top cover can be conveniently welded or the flange butt joint surface can be conveniently processed after welding. In addition, in order to ensure weldability, external split welding ribs are designed for the traditional bearing cone. This further introduces a welding process that causes further distortion of the injector, which adversely affects the quality of the injector product.
Disclosure of Invention
The invention aims to overcome the defects and provides a repeatedly started thrust chamber head structure and a thrust chamber, wherein in the repeatedly started thrust chamber head structure, on the premise that a bearing cone keeps a conical upward contraction configuration, a non-contact electron beam welding or laser welding is adopted to replace the traditional argon arc welding or flange connection of the two hole seats through the compact design of the two hole seats, so that the liquid oxygen top cover, the bearing cone and the reinforcing ribs can be integrally designed. Compared with the traditional split type welding structure, the invention effectively reduces the number of welding seams and welding heat input, reduces the welding procedure after welding detection, and simultaneously reduces the influence on the deformation of the injector.
In order to achieve the above purpose, the invention provides the following technical scheme:
the invention relates to a repeatedly started thrust chamber head structure, which comprises an integrated top cover, an injector component, a hydrogen collector and two hole seats, wherein the injector component is arranged on the top cover;
the integrated top cover comprises an integrally formed bearing cone, an oxygen cavity top cover and an integrated reinforcing structure unit; the top end of the bearing cone is provided with a flange used for being connected with an engine frame, the flange is provided with a fabrication hole used as a welding window, the bearing cone is of a hollow structure, the bottom end of the bearing cone is connected with an oxygen cavity top cover, the oxygen cavity top cover is provided with a boss, and an integrated reinforcing structure unit is arranged inside the integrated top cover;
after the integrated top cover and the injector assembly are welded, the hydrogen collector is welded outside the integrated top cover and the injector assembly;
the two-hole seat comprises an integrally formed mounting base and a main body part positioned above the mounting base, the diameter phi A of the mounting base is larger than the diameter phi B of the main body part and smaller than the diameter phi C of a process hole arranged on the flange, an electron beam or a laser beam enters from the process hole and avoids the main body part from reaching the connecting part of the mounting base and a boss arranged on the oxygen cavity top cover, the electron beam or the laser welding of the two-hole seat and the integrated top cover is realized, and a complete thrust chamber head structure is formed.
Furthermore, the difference value between the diameter phi A of the mounting base and the diameter phi B of the main body part is larger than the width of a welding seam of electron beam welding or laser welding, and the difference value between the diameter phi C of the process hole and the diameter phi A of the mounting base is larger than the width of the welding seam of electron beam welding or laser welding.
Furthermore, the integrated reinforcing structure unit comprises a conical reinforcing rib arranged on the inner wall of the force bearing cone, a top cover outer surface reinforcing rib arranged on the upper surface of the oxygen cavity top cover, and a vertical rib connecting the conical reinforcing rib and the top cover outer surface reinforcing rib; the top cover outer surface reinforcing rib comprises a radial reinforcing rib and a circumferential arc reinforcing rib.
Furthermore, the position where one end of the vertical rib is connected with the conical reinforcing rib is positioned at the length of the conical reinforcing rib
The other end of the vertical rib is connected with one end of a radial reinforcing rib in the reinforcing ribs on the outer surface of the top cover, and the other end of the radial reinforcing rib extends to a boss arranged on the top cover of the oxygen cavity.
Furthermore, the circumferential arc-shaped reinforcing ribs in the reinforcing ribs on the outer surface of each top cover are equal in thickness; the thickness of each conical reinforcing rib is equal.
Furthermore, the bearing cone side wall of the integrated top cover is provided with an oxygen inlet and 2 operation windows positioned on two sides of the oxygen inlet, the 2 operation windows are used for realizing the installation and replacement of the cartridge igniter on the two-hole seat, one end of a circumferential arc-shaped reinforcing rib in the reinforcing rib on the outer surface of the top cover is connected with the radial reinforcing rib, and the other end of the circumferential arc-shaped reinforcing rib extends to the operation.
Furthermore, in the reinforcing ribs on the outer surface of the top cover, the included angles beta of the radial reinforcing ribs on two sides of the operation window are 2-5 degrees larger than the central angle corresponding to the radian occupied by the operation window;
furthermore, the height of the circumferential arc-shaped reinforcing rib in the reinforcing rib on the outer surface of the top cover is gradually reduced from one end connected with the radial reinforcing rib to one end extending to the operation window, and the occupied central angle of the circumferential arc-shaped reinforcing rib is smaller than half of the included angle beta of the radial reinforcing ribs positioned on the two sides of the operation window.
Furthermore, in the reinforcing ribs on the outer surface of the top cover, the thickness of the radial reinforcing ribs positioned on two sides of the oxygen inlet is greater than that of the rest radial reinforcing ribs; the radial reinforcing ribs extend to the height of one end of the boss arranged on the oxygen cavity top cover and are flush with the upper end of the fillet of the outer brim of the boss.
Furthermore, the integral type reinforced structure unit is 4 groups, and every two adjacent groups of reinforced structure units are symmetrically distributed under the overlooking visual angle.
A multi-start thrust chamber comprises the multi-start thrust chamber head structure and the multi-start thrust chamber tail structure.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention relates to a repeatedly started thrust chamber head structure, which is characterized in that a two-hole seat is compactly designed aiming at the problems of multiple welding procedures and large heat input of a traditional structure, so that non-contact electron beam welding or laser welding can replace traditional argon arc welding or flange connection to realize the installation of the two-hole seat on an oxygen cavity top cover, the problem that the oxygen cavity top cover, a bearing cone and a reinforcing rib need to be designed separately is solved, the oxygen cavity top cover, the bearing cone and the reinforcing rib can be integrally processed and formed, the processing precision and the process flexibility are effectively improved, and the production cost is reduced;
(2) in the repeatedly started thrust chamber head structure, the integrated top cover is internally provided with the integrated reinforcing structure unit, so that the structure is more compact compared with the traditional external reinforcing rib, and the trouble that the traditional external welding rib needs to be welded after the head body of the thrust chamber is butted can be avoided;
(3) in the repeatedly started thrust chamber head structure, the specific structure and size of the integrated reinforced structure unit are designed, so that the integrated reinforced structure unit can meet the requirements of weight reduction and strength;
(4) the repeatedly started thrust chamber head structure can reduce the head welding process and heat input after welding detection of the injector, reduce the guarantee difficulty of the head product design index and improve the working reliability of an engine.
Drawings
FIG. 1 is a schematic view of a multi-start thrust chamber head of the present invention, wherein (a) is a general view and (b) is a schematic view of an integrated top cover and two hole seats; in the figure, 1 is an integrated top cover, 2 is a two-hole seat, 3 is a gunpowder spray pipe, 4 is two bottoms, 5 is a hydrogen collector, and 6 is one bottom; 7 is a hydrogen cavity; 8 is a nozzle; 9 is a hydrogen nozzle circular seam; 10 is a combustion chamber; 11 is an oxygen chamber; 12 is a cartridge igniter, and 13 is an operation window;
FIG. 2 is a schematic structural view of the integral top cover of the present invention, wherein (a) is a top view and (b) is a sectional view taken along the line A-A in FIG. A; in the figure, 4 is a conical reinforcing rib, 15 is a vertical rib, and 16 is a reinforcing rib on the outer surface of the top cover.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The invention aims to provide a repeatedly-started thrust chamber head structure which can be used for a head of an oxyhydrogen rocket engine and solves the problems of multiple welding procedures and large deformation influence after welding detection of an injector in the traditional structure. According to the repeatedly started thrust chamber head structure, on the premise that the bearing cone keeps a conical upward contraction configuration, the integrated design of the liquid oxygen top cover, the bearing cone and the reinforcing rib can be realized through the compact design of the two hole seats 2 and the non-contact electron beam welding or laser welding is adopted to replace the traditional argon arc welding (or flange connection) of the two hole seats 2. As shown in fig. 1(a), the newly designed integrated top cover 1 is a traditional aggregate of oxygen chamber top cover, force bearing cone, reinforcing rib, oxygen inlet and the like. In the production process of the engine, the gunpowder nozzle 3, the two bottoms 4, the nozzle 8 and the one bottom 6 are assembled and welded to form the injector assembly. And then, carrying out brazing seam quality detection to ensure that the medium in the hydrogen cavity 7 cannot leak through the brazing seam between the two bottoms 4 and the nozzle 8, thereby generating the risk of hydrogen-oxygen serial cavities. And after the hydrogen nozzle circumferential weld 9 is detected to be qualified, the integrated top cover 1 and the injector assembly are assembled and welded into a whole through an inner weld seam and an outer weld seam to form a closed oxygen cavity 11. And after the inner and outer welding seams of the oxygen cavity 11 are detected to be qualified, the hydrogen collector 5 and the two hole seats 2 are welded in sequence to form the head of the thrust chamber. When the engine works, two gunpowder igniters 12 are arranged in the thrust chamber to realize 2 times of starting, oxygen is distributed to a plurality of nozzles 8 through the oxygen chamber 11 to enter the combustion chamber 10 to be mixed with hydrogen supplied through the hydrogen chamber 7 and the hydrogen nozzle circumferential seam 9, and then the combustion is stabilized to generate the thrust.
The two-hole base 2 is a three-way adapter, and through compact design, the diameter phi C of the process hole of the integrated top cover 1, the diameter phi A of the installation base and the diameter phi B of the main body part are ensured, and the difference value of the phi A, the phi B and the phi C is slightly larger than the width of an electron beam welding or laser welding seam, so that finally, the non-contact electron beam welding or laser welding of the two-hole base 2 in a compact space becomes possible.
As shown in fig. 1(b), the integrated top cover 1 is an assembly of a liquid oxygen top cover, a force bearing cone and a reinforcing rib, and the whole is of a hollow conical structure. The top end of the integrated top cover 1 is provided with a flange and a process hole, and the flange is used for connecting the thrust chamber with the engine frame; the inner diameter of the fabrication hole is phi C, so that the fabrication hole can reduce weight on one hand, and a welding window is mainly provided for electron beam welding or laser welding. Operation windows 13 are provided on both sides of the oxygen inlet of the integrated top cap 1 for the installation and replacement of the cartridge 12, etc. The inner wall of the conical surface of the bearing cone in the integrated top cover 1 is provided with the built-in conical surface reinforcing rib 14, the structure is more compact compared with the traditional external reinforcing rib, and the trouble that the traditional external welding rib needs to be welded after the head body of the thrust chamber is butted can be avoided.
As shown in fig. 2(a), the outer surface of the oxygen chamber 11, i.e. the top cover upper surface of the oxygen chamber, is provided with top cover outer surface reinforcing ribs 16, and the top cover outer surface reinforcing ribs 16 include radial reinforcing ribs and circumferential arc-shaped reinforcing ribs extending to the operating window 13 in the circumferential direction.
The conical surface reinforcing rib 14, the top cover outer surface reinforcing rib 16 and the vertical rib 15 form an integrated reinforcing structure unit, as shown in fig. 2, the vertical rib 15 is located between R1 and R2 and within a circumferential radian gamma range, and the integrated reinforcing structure unit penetrates through the oxygen cavity top cover outer surface and extends to the inner surface of the force bearing cone.
The axial reinforcing rib of the top cover outer surface reinforcing rib 16 of each integrated reinforcing structure unit is designed to be equal in thickness, the thickness of the axial reinforcing rib is delta 3, and the central angle corresponding to the radian extending to the operation window 13 is alpha. The circumferential arc-shaped reinforcing rib is designed into a non-equal height structure for reducing weight, and the height of the circumferential arc-shaped reinforcing rib is gradually reduced from h1 to h2 from the outside of the range of the radian gamma.
As shown in fig. 2(b), the radial middle section of the integrated reinforcing structure unit is in a shape of a boot, and the toe part of the boot (i.e. one end of the radial reinforcing rib in the reinforcing rib 16 on the outer surface of the top cover) extends to a circular boss at the center of the oxygen chamber top cover, and the height of the circular boss is flush with the upper end of the boss outer eave fillet R3, namely h3 is equal to R3.
As shown in fig. 2(a), the total number of the integrated reinforcing structure units is 4, the top view is symmetrical in the up-down, left-right and vertical arrangement, the included angle of the radial reinforcing rib in the reinforcing rib 16 on the outer surface of the top cover on the side of the operation window 13 is beta, and the specific value is 2-5 degrees larger than the central angle corresponding to the radian occupied by the operation window. To control the weight of the outer surface ribs 16 of the top cover, α < β/2. In order to compensate the structure weakening effect of the conical surface notch on the oxygen inlet side, the thickness delta 2 of the 2 groups of radial reinforcing ribs close to the oxygen inlet side is larger than the thickness delta 1 of the radial reinforcing ribs on the other side.
Integral type top cap 1 can adopt processes such as 3D printing, casting to carry out integrated into one piece machine-shaping, carries out the follow-up welding of head etc. again, has that part quantity is few, welding deformation influences advantages such as little.
The repeatedly started thrust chamber head structure can reduce the head welding process and heat input after welding detection of the injector, reduce the guarantee difficulty of the head product design index and improve the working reliability of an engine. The invention can be used for the head of the thrust chamber of the oxyhydrogen rocket engine with the starting requirement of more than 2 times, and can also be popularized and applied to other liquid rocket engines with the starting requirement of more than 2 times.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (11)
1. A multi-start thrust chamber head structure is characterized by comprising an integrated top cover (1), an injector component, a hydrogen collector (5) and a two-hole seat (2);
the integrated top cover (1) comprises an integrally formed bearing cone, an oxygen cavity top cover and an integrated reinforcing structure unit; the top end of the bearing cone is provided with a flange used for being connected with an engine frame, the flange is provided with a fabrication hole used as a welding window, the bearing cone is of a hollow structure, the bottom end of the bearing cone is connected with an oxygen cavity top cover, the oxygen cavity top cover is provided with a boss, and an integrated reinforcing structure unit is arranged inside the integrated top cover (1);
after the integrated top cover (1) and the injector assembly are welded, the hydrogen collector (5) is welded outside the integrated top cover (1) and the injector assembly;
the two-hole seat (2) comprises an integrally formed mounting base and a main body part positioned above the mounting base, the diameter phi A of the mounting base is larger than the diameter phi B of the main body part and smaller than the diameter phi C of a process hole arranged on the flange, an electron beam or a laser beam is incident from the process hole and avoids the main body part from reaching the connecting part of the mounting base and a boss arranged on the oxygen cavity top cover, the electron beam or the laser welding of the two-hole seat (2) and the integrated top cover (1) is realized, and a complete thrust chamber head structure is formed.
2. The multiple start thrust chamber head structure of claim 1, wherein the difference between the mounting base diameter Φ a and the main body portion diameter Φ B is greater than the weld width of electron beam welding or laser welding, and the difference between the tooling hole diameter Φ C and the mounting base diameter Φ a is greater than the weld width of electron beam welding or laser welding.
3. The multi-start thrust chamber head structure of claim 1, wherein the integrated reinforcing structure unit comprises a conical reinforcing rib (14) arranged on the inner wall of the force bearing cone, a top cover outer surface reinforcing rib (16) arranged on the upper surface of the top cover of the oxygen cavity, and a vertical rib (15) connecting the conical reinforcing rib (14) and the top cover outer surface reinforcing rib (16); the top cover outer surface reinforcing ribs (16) comprise radial reinforcing ribs and circumferential arc-shaped reinforcing ribs.
4. The multiple start thrust chamber head structure according to claim 3, wherein the position where one end of the vertical rib (15) is connected to the tapered reinforcing rib (14) is located along the length of the tapered reinforcing rib (14)
The other end of the vertical rib (15) is connected with one end of a radial reinforcing rib in the reinforcing ribs (16) on the outer surface of the top cover, and the other end of the radial reinforcing rib extends to a boss arranged on the top cover of the oxygen cavity.
5. A multiple start thrust chamber head structure as claimed in claim 3 or 4, wherein the circumferential ribs of said top cover outer surface ribs (16) are of equal thickness; the conical reinforcing ribs (14) are equal in thickness.
6. The multiple start thrust chamber head structure of claim 3 or 4, wherein the force bearing conical side wall of the integrated top cover (1) is provided with an oxygen inlet and 2 operation windows (13) positioned at two sides of the oxygen inlet, the 2 operation windows (13) are used for realizing the installation and replacement of the cartridge (12) on the two-hole seat (2), one end of a circumferential arc-shaped reinforcing rib in the reinforcing rib (16) on the outer surface of the top cover is connected with the radial reinforcing rib, and the other end of the circumferential arc-shaped reinforcing rib extends to the operation window (13).
7. The multiple start thrust chamber head structure of claim 6, wherein in the top cover outer surface reinforcing rib (16), the included angle β of the radial reinforcing ribs on both sides of the operation window (13) is 2-5 ° larger than the central angle corresponding to the radian occupied by the operation window (13).
8. A multiple start thrust cell header assembly as set forth in claim 6 wherein said top cover outer surface ribs (16) have circumferentially curved ribs which taper from their connection to the radial ribs to their height extending to the end of the operating window (13) at a central angle less than half the angle β of the radial ribs on either side of the operating window (13).
9. The multiple start thrust chamber head structure of claim 6, wherein of said top cover outer surface reinforcing ribs (16), the radial ribs located on both sides of the oxygen inlet have a thickness greater than that of the remaining radial ribs; the radial reinforcing ribs extend to the height of one end of the boss arranged on the oxygen cavity top cover and are flush with the upper end of the fillet of the outer brim of the boss.
10. The multiple start thrust chamber head structure of claim 1, wherein said integral stiffening structure units are 4 groups, and each two adjacent groups of stiffening structure units are symmetrically distributed in a top view.
11. A multi-start thrust cell comprising a multi-start thrust cell head structure according to any of claims 1 to 10.
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| CN202111481508.4A CN114251195B (en) | 2021-12-06 | 2021-12-06 | Thrust chamber head structure and thrust chamber start many times |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111481508.4A CN114251195B (en) | 2021-12-06 | 2021-12-06 | Thrust chamber head structure and thrust chamber start many times |
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| CN114251195A true CN114251195A (en) | 2022-03-29 |
| CN114251195B CN114251195B (en) | 2023-04-14 |
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| US4811892A (en) * | 1986-03-08 | 1989-03-14 | Messerschmitt-Boelkow-Blohm Gmbh | Method for diffusion welding under isostatic pressure |
| US6107596A (en) * | 1999-02-04 | 2000-08-22 | Otkrytoe Aktsionernoe Obschestvo "Nauchno-Proizvodstvennoe Obiedinenie "Energomash"Imeni Akademika V.P. Glushko" | Method for producing a welded-brazed combustion chamber |
| CN103982332A (en) * | 2014-06-06 | 2014-08-13 | 葛明龙 | Rocket thrust chamber with fuel switching function and supply system of rocket thrust chamber |
| CN106735829A (en) * | 2016-11-30 | 2017-05-31 | 湖北三江航天江北机械工程有限公司 | The welding method of many designs of part of liquid rocket engine thrust chamber head injector |
| CN111633339A (en) * | 2020-06-03 | 2020-09-08 | 蓝箭航天空间科技股份有限公司 | Rocket engine thrust chamber laser welding process and rocket engine thrust chamber |
| CN113600994A (en) * | 2021-07-26 | 2021-11-05 | 湖北明匠机电有限公司 | Multi-part structure welding method for liquid rocket engine thrust chamber head injector |
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2021
- 2021-12-06 CN CN202111481508.4A patent/CN114251195B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4811892A (en) * | 1986-03-08 | 1989-03-14 | Messerschmitt-Boelkow-Blohm Gmbh | Method for diffusion welding under isostatic pressure |
| US6107596A (en) * | 1999-02-04 | 2000-08-22 | Otkrytoe Aktsionernoe Obschestvo "Nauchno-Proizvodstvennoe Obiedinenie "Energomash"Imeni Akademika V.P. Glushko" | Method for producing a welded-brazed combustion chamber |
| CN103982332A (en) * | 2014-06-06 | 2014-08-13 | 葛明龙 | Rocket thrust chamber with fuel switching function and supply system of rocket thrust chamber |
| CN106735829A (en) * | 2016-11-30 | 2017-05-31 | 湖北三江航天江北机械工程有限公司 | The welding method of many designs of part of liquid rocket engine thrust chamber head injector |
| CN111633339A (en) * | 2020-06-03 | 2020-09-08 | 蓝箭航天空间科技股份有限公司 | Rocket engine thrust chamber laser welding process and rocket engine thrust chamber |
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