GB2616149A - Method for processing double-layer structure of thrust chamber, and spacecraft thrust chamber - Google Patents
Method for processing double-layer structure of thrust chamber, and spacecraft thrust chamber Download PDFInfo
- Publication number
- GB2616149A GB2616149A GB2307694.6A GB202307694A GB2616149A GB 2616149 A GB2616149 A GB 2616149A GB 202307694 A GB202307694 A GB 202307694A GB 2616149 A GB2616149 A GB 2616149A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wall
- double
- layer structure
- thrust chamber
- processing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 59
- 238000012545 processing Methods 0.000 title claims abstract description 44
- 238000011282 treatment Methods 0.000 claims description 41
- 238000002485 combustion reaction Methods 0.000 claims description 35
- 238000005520 cutting process Methods 0.000 claims description 14
- 125000006850 spacer group Chemical group 0.000 claims description 6
- 239000002826 coolant Substances 0.000 claims description 4
- 230000008569 process Effects 0.000 abstract description 15
- 238000004519 manufacturing process Methods 0.000 abstract description 14
- 238000003672 processing method Methods 0.000 abstract 1
- 238000003466 welding Methods 0.000 description 11
- 238000010586 diagram Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 3
- 238000003801 milling Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000605 extraction Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005323 electroforming Methods 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/418—Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS], computer integrated manufacturing [CIM]
- G05B19/41875—Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS], computer integrated manufacturing [CIM] characterised by quality surveillance of production
-
- 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
- F02K9/97—Rocket nozzles
- F02K9/972—Fluid cooling arrangements for nozzles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- 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
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/30—Nc systems
- G05B2219/32—Operator till task planning
- G05B2219/32368—Quality control
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
Abstract
A method for processing a double-layer structure of a spacecraft thrust chamber comprises: providing a first wall structure (1), a second wall structure (2) and ribs (4); bringing the first wall structure (1) and the second wall structure (2) close to each other, and closing the ends of the first wall structure (1) and the second wall structure (2), thereby forming an assembly structure composed of the first wall structure (1), the second wall structure (2) and the ribs (4), the inside of the assembly structure being a closed space; making the closed space to be at a negative pressure, then performing first pressurizing processing on the assembly structure, and next, performing second pressurizing processing in the case where the closed space is in communication with the outside, wherein the maximum pressure of the second pressurizing processing is greater than the maximum pressure of the first pressurizing processing, so that the assembly structure is welded into a whole, and a double-layer structure is obtained. The processing method is simple in process, short in manufacturing cycle and low in cost.
Description
Description
METHOD FOR PROCESSING DOUBLE-LAYER STRUCTURE OF THRUST
CHAMBER, AND SPACECRAFT THRUST CHAMBER
Technical Field
The present invention relates to the technical field of spacecraft engines, in particular to a method for processing double-layer structure of thrust chamber and a spacecraft thrust chamber.
Background Art
to The spacecraft engine technology has been rapidly upgraded with the development of the aerospace industry. As a main component of the engine, the thrust chamber is the key component to complete the energy conversion of the propellant and generate thrust. Among them, the thrust chamber body is the part responsible for the mixed combustion of fuel in the spacecraft engine to generate high-temperature and high-pressure gas, and then the gas is accelerated and discharged through a throat to obtain reverse thrust. The thrust chamber body is a Laval-profile structure, and the thrust chamber can usually be cooled by regenerative cooling technology. The thrust chamber is composed of an outer wall and an inner wall with milling grooves, and a plurality of cooling channels are located between the outer wall and the inner wall with milling grooves. Under normal circumstances, there must not be any leakage defects inside the two under a pressure of up to 60MPa.
At present, there are two methods for connecting the outer wall and the inner wall with milling grooves. One is the instantaneous liquid phase diffusion brazing and electroforming nick& process, but this process has the disadvantages of complicated process, expensiveness and long cycle time. The other is that the thrust chamber is prepared by adopting copper-steel dissimilar alloy hot isostatic pressure diffusion welding in the process. However, in the process of manufacturing the thrust chamber, it often happens that the convex ribs on the inner wall cannot withstand the high pressure and are bent, which makes the channels collapse. But, if the pressure is too low, it is impossible to complete a reliable connection between the convex ribs and the outer wall.
Description
To address the above problems, the present invention provides a welding method for processing a thrust chamber body components and a spacecraft thrust chamber, which have the advantages of simple process, short manufacturing cycle, cost-saving, being applicable for mass production, and increased production capacity.
Summary of the Invention
The object of the present invention is to provide a method for processing double-layer structure of spacecraft thrust chamber, which has the advantages of simple process, short manufacturing cycle, cost saving, being applicable for mass production, and increased production capacity.
In order to achieve the above object, the present invention provides the following technical solutions: a method for processing a double-layer structure of a spacecraft thrust chamber, characterized in that, the double-layer structure includes an outer wall, an inner wall and a spacer, wherein the outer wall and the inner wall constitute at least a part of a spacecraft thrust chamber body, the spacer is fixed between the outer wall and the inner wall and configured to provide a channel between the outer wall and the inner wall for coolant flow; the method comprises the following steps: (t) providing a first wall structure, a second wall structure and a convex rib, wherein the first wall structure and the second wall structure are close to each other in an inner-outer fitting manner to form at least a part of the spacecraft thrust chamber body, and the convex rib is located between the first wall structure and the second wall structure; (2) closing the first wall structure and the second wall structure at their ends, thereby forming a combined structure with a closed space inside, wherein the combined structure is composed of the first wall structure, the second wall structure and the convex rib; and (3) making the closed space a negative pressure, and then performing a first pressurization treatment on the combined structure from outside, and then performing a second pressurization treatment on the combined structure under a condition that the closed space communicates with outside, thereby welding the combined structure into one piece and obtaining the double-layer structure, wherein the maximum pressure of the second pressurization treatment is greater than that of the first pressurization treatment.
Description
According to the method for processing double-layer structure of spacecraft thrust chamber of the present invention, preferably, an intensity of pressure A satisfies 11\113a < A < 20MPa, a pressurization time B satisfies 0.2h < B < 10h, and a temperature C satisfies 300V < C < 1300V during the first pressurization treatment.
According to the method for processing double-layer structure of spacecraft thrust chamber of the present invention, preferably, an intensity of pressure D satisfies 2MPa < D < 120MPa, a pressurization time E satisfies 0.1h < E < 10h, and a temperature F satisfies 300C < F < 1400C during the second pressurization treatment According to the method for processing double-layer structure of spacecraft thrust chamber of the present invention, preferably, the pressure in the closed space is controlled by an air guide assembly, and the air guide assembly includes an air guide duct and an annular groove, the annular groove communicates with a distal end of the air guide duct and is provided on one side of the first wall structure, further preferably, the method comprises an evacuating device for connecting with the air guide duct.
According to the method for processing double-layer structure of spacecraft thrust chamber of the present invention, preferably, the method further comprises a step of cutting off the air guide assembly.
According to the method for processing double-layer structure of spacecraft thrust chamber of the present invention, preferably, the double-layer structure comprises a first double-layer structure and a second double-layer structure constituting the thrust chamber body, the first double-layer structure and the second double-layer structure are a combustion chamber or an expansion section independently, and the method comprises a first processing step to obtain the first double-layer structure and a second processing step to obtain the second double-layer structure, wherein the first processing step and the second processing step are performed simultaneously or sequentially.
According to the method for processing double-layer structure of spacecraft thrust chamber of the present invention, preferably, in step (I), one side of the convex rib is fixed to the second wall structure, and the other side of the convex rib is in close contact with a surface of the first wall structure, so that the convex rib is formed into the spacer after step (3).
Description
According to the method for processing double-layer structure of spacecraft thrust chamber of the present invention, preferably, the method further comprises steps of providing an end cover and removing the end cover, wherein the end cover is connected to an end of the first wall structure and an end of the second wall structure when providing the end cover, so that the first wall structure and the second wall structure are closed at the ends thereof, and the step of removing the end cover includes cutting off the end cover along a radial direction of the double-layer structure.
According to the method for processing double-layer structure of spacecraft thrust chamber of the present invention, preferably, one end of the first wall structure penetrates one end of the second wall structure and connects with the end of the second wall structure as a whole, the circumferential surface of the other end of the second wall structure is connected to the first wall structure ring through the convex ribs.
According to the method for processing double-layer structure of spacecraft thrust chamber of the present invention, preferably, the combined structure is subjected to a pressurization treatment by a high-pressure container.
The present invention also provides a spacecraft thrust chamber, which is obtained according to the above method.
Compared with the prior art, the beneficial effects of the present invention are: the first pressurization process is performed by putting the combined structure composed of the outer wall, the inner wall and the end cover after vacuuming into the high-pressure container, so that the convex ribs are joined to the outer wall. The channels are kept unblocked from the outside air through the air guide duct, and when the outer wall and the inner wall are put into the high-pressure container again for the second pressurization treatment, the high-pressure gas enters the channels through the air guide duct. On one hand, the convex ribs are supported to prevent the convex ribs from collapsing due to excessive pressure, and on the other hand, by making the maximum pressure of the second pressurization treatment greater than that of the first pressurization treatment, the air bubbles presented in the gaps when the convex ribs are connected to the outer wall are squeezed out, making the connection between the convex ribs and the outer wall more tightly and firmly. The structure of the thrust chamber body formed by the outer wall and the inner wall is obtained by cutting off the end cover and the part of the
Description
outer wall matching the air guide duct. The whole method has the advantages of simple process, short manufacturing cycle, cost saving, being applicable for mass production, and increased production capacity.
Brief Description of the Drawings
Fig. I is a schematic diagram illustrating a thrust chamber part of a rocket engine of the present invention; Fig. 2 is a schematic diagram illustrating a combustion chamber assembly of the present invention before welding; to Fig 3 is a perspective view illustrating the combustion chamber of the present invention; Fig 4 is a schematic diagram illustrating an expansion section of the present invention; Fig. 5 is a perspective view illustrating the connection between the combustion chamber and the expansion section of the present invention; Fig. 6 is a structural diagram illustrating the connection between the combustion chamber and the expansion section of the present invention; Fig. 7 is a structural schematic diagram illustrating the thinning process for the outer wall ring and the connecting duct fitting performed after the connection between the combustion chamber and the expansion section of the present invention; Fig. 8 is a schematic cross-sectional view illustrating the connection of the outer wall, the inner wall, the air guide duct, and the convex ribs of the present invention; Fig. 9 is a structural diagram illustrating the combustion chamber of the present invention cut along the radial direction of the combustion chamber; Fig. 10 is a perspective view illustrating the outer wall and the annular groove of the present invention; Fig. 11 is a structural schematic diagram illustrating the connecting duct fitting when connected with the combustion chamber and the expansion section in the present invention.
Fig. 12 is a process flowchart of the present invention.
Explanation of reference signs:
Description
D
I, outer wall 3, air guide duct 5, end cover 7, expansion section 9, outer wall ring 2, inner wall 4, convex rib 6, combustion chamber 8, annular groove 10, connecting duct fitting
Detailed Description of Embodiments
In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the following will clearly illustrate the spirit of the content disclosed in the application with the accompanying drawings and detailed descriptions. Any person skilled in the art can change and modify the content of the application on the basis of the technology taught by the content of the present application after understanding the embodiments of the content of the present application, which does not depart from the spirit and scope of the content of the present application.
The exemplary embodiments and descriptions thereof of the present application are used to explain the present application, but not to limit the present application. In addition, elements/members with the same or similar numerals used in the drawings and the embodiments are used to represent the same or similar parts.
The terms "first", "second", ... etc. used herein do not specifically refer to a sequence or order, nor are they used to limit the present application, but are only used to distinguish elements or operations described with the same technical terms.
Regarding the directional terms used herein, such as up, down, left, right, front, rear, only refer to the directions of the drawings. Accordingly, the directional terms used are for illustration and not for limitation of the present invention.
As used herein, "comprising", "including", "having", "containing" and so on are all open terms, meaning including but not limited to.
As used herein, "and/or" includes any or all combinations of the stated things.
The terms "approximately", "about", and the like used herein are used to modify any quantity or error that may vary slightly, but these slight changes or errors will not change its essence. Generally speaking, the range of slight changes or errors modified by such terms may
Description
be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments or other numerical values. Those skilled in the art should understand that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.
Certain terms used to describe the present application are discussed below or elsewhere in this description to provide those skilled in the art with additional guidance in describing the present application.
The embodiment of the present invention provides a welding method for processing a thrust chamber body components, as shown in Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 8, Fig. 9 and Fig. 12, and provides an outer wall 1, an inner wall 2 and an air guide duct 3, wherein convex ribs 4 are provided on an outer side of the inner wall 2, and the other side of the convex ribs 4 is used for close connection with the inner surface of the outer wall 1. After the outer wall 1 and the inner wall 2 are connected, the convex ribs 4 define between the outer wall 1 and the inner wall 2 a plurality of channels for coolant flow. The specific steps are as foil ows: Si: setting an end cover at both ends of the outer wall 1 and the inner wall 2 to form a combined structure, so that a closed space is formed between the outer wall 1 and the inner wall 2; S2: vacuuming the closed space through the air guide duct 3; S3: putting the combined structure composed of the outer wall 1, the inner wall 2 and the end cover 5 after vacuuming into a high-pressure container for a first pressurization treatment; S4: taking out the combined structure from the high-pressure container, and keeping the channels unblocked from the outside air through the air guide duct 3; S5: putting the outer wall 1 and the inner wall 2 into the high-pressure container again for a second pressurization treatment, wherein a maximum pressure of the second pressurization treatment is greater than that of the first pressurization treatment; S6: taking out the combined structure after the second pressurization treatment, cutting off the end cover 5 and a part of the outer wall I matching the air guide duct 3, to obtain a thrust chamber body structure comprising the outer wall 1 and the inner wall 2.
Description
Specifically, by putting the combined structure composed of the outer wall 1, the inner wall 2 and the end cover 5 after vacuuming into the high-pressure container for the first pressurization treatment, the convex ribs 4 and the outer wall 1 are connected together. Due to the air guide duct 3, the channels are kept unblocked from the outside air. When the outer wall 1 and inner wall 2 are put into the high-pressure container again for the second pressurization treatment, the high-pressure gas enters the channels via the air guide duct 3. On one hand, it is used to support the convex ribs 4, prevent the convex ribs 4 from collapsing due to excessive pressure, and facilitate the uniform flow of the coolant in the channels. On the other hand, the maximum pressure of the second pressurization treatment is greater than that of the first pressurization treatment, so that the air bubbles presented, when the convex ribs 4 are connected to the outer wall 1, in the gaps are squeezed out, and the connection between the convex ribs 4 and the outer wall I are made more tightly and firmly. After cutting off the end cover 5 and the part of the outer wall 1 matching the air guide duct 5, the thrust chamber body structure comprising the outer wall 1 and the inner wall 2 is obtained. The whole method has the advantages of simple process, short manufacturing cycle, cost saving, being applicable for mass production, and increased production capacity.
What needs to be said is that during the first pressurization treatment, in order to make the outer wall 1 and the convex ribs 4 tightly connected and fixed firmly, multiple simulation experiments were carried out on the intensity of pressure, pressurization time and temperature in the high-pressure container. When the intensity of pressure in the high-pressure container is A and satisfies 1MPa < A < 20MPa, the pressurization time is B and satisfies 0.2h < B < 10h, and the temperature in the high-pressure container is C and satisfies 3001C < C < 13001C, it is possible to make the outer wall 1 and the convex ribs 4 tightly connected, allowing atoms constituting the outer wall 1 and the convex ribs 4 to diffuse rapidly, facilitating the fixing of the two together, and improving the stability of the thrust chamber body structure.
In order to prevent the convex ribs 4 from collapsing due to excessive pressure, the air guide duct 3 keeps the channels unblocked from the outside air. During the second pressurization process, the gas inside the channels supports and fixes the convex ribs 4 to prevent the convex ribs 4 from collapse due to excessive pressure. In addition, the maximum pressure of the second pressurization treatment is greater than that of the first pressurization
Description
treatment, so that the air bubbles presented, when the outer wall I is connected to the convex ribs 4 during the first pressurization treatment, in the gaps are squeezed out, making the connection between the convex ribs 4 and the outer wall 1 more tightly and firmly, reaching the use standard of the thrust chamber.
It is to be mentioned that during the second pressurization treatment, for example, when the intensity of pressure in the high-pressure container is set as D and satisfies 2MPa < D < 120IVIPa, the pressurization time is set as E and satisfies 0.1h < E < 10h, and the temperature in the high-pressure container is set as F and satisfies 300°C < F < 1400°C, by setting parameters for the second pressurization, the bonding quality between the convex ribs on the inner wall and the outer wall can be improved, thereby improving the quality and reliability of the engine. In addition, in order to reduce air bubbles in the gap between the outer wall 1 and the convex ribs 4 when connecting with each other, for example, the second pressurization treatment can be performed multiple times. In addition, the intensity of pressure, the pressurization time and the temperature during the multiple pressurization treatments can be adjusted so that the outer wall 1 and the convex ribs 4 are connected tightly and fixed firmly.
In this embodiment, as shown in Fig. 1, Fig. 8 and Fig. 10, in order to ensure the rapid extraction of the air in the channels, for example, an annular groove 8 is provided on the inner side of the outer wall I. When vacuuming the closed space via the air guide duct 3, one end of the air guide duct 3 is connected to the annular groove 8 on the inner side of the outer wall 1, so that the channels communicate with the air guide duct 3, which facilitates the extraction of the air in the channels. During vacuuming, the closed space is evacuated by an evacuating device connected to the air guide duct, and the air in the channels is discharged from the air guide duct 3 via the annular groove 8, which has the advantages such as reasonable design, convenient operation, and easy use.
In this embodiment, as shown in Fig. 1, Fig. 2, Fig. 3 and Fig. 4, the thrust chamber body structure includes a combustion chamber 6 and an expansion section 7. The welding methods for processing the thrust chamber body components are now described separately. Taking the combustion chamber 6 as an example, the preparation process of the combustion chamber specifically includes:
Description
Vacuuming the combustion chamber 6, after the outer wall 1 and the inner wall 2 of the combustion chamber 6 are sealed by the end cover 5, to obtain a first combined structure; perfonning the first pressurization treatment on the first combined structure connecting the channels of the first combined structure to the outside via the air guide duct 3, and performing the second pressurization treatment on the first combined structure after the first pressurization treatment, to obtain the combustion chamber 6. For example, an annular groove can be provided on the inner side of the outer wall of the first combined structure, so that after the annular groove communicates with the channels between the inner and outer walls and the air guide duct respectively, the vacuuming can be performed by an evacuating device.
Taking the expansion section 7 as an example, as shown in Fig. 1, Fig. 4 and Fig. 5, the method for processing the expansion section includes: first, vacuuming the expansion section 7, after the outer wall 1 and the inner wall 2 of the expansion section 7 are sealed by the end cover 5, to obtain a second combined structure; performing the first pressurization treatment on the second combined structure; connecting the channels of the second combined structure to the outside via the air guide duct 3, and performing the second pressurization treatment on the second combined structure after the first pressurization treatment, to obtain the expansion section 7. For example, an annular groove can be provided on the inner side of the outer wall of the second combined structure, so that after the annular groove communicates with the channels between the inner and outer walls and the air guide duct respectively, the vacuuming can be performed by the evacuating device.
As shown in Fig. 2 and Fig. 3, in order to facilitate one end of the inner wall 2 of the combustion chamber (the position of the throat of the thrust chamber on the inner wall) to penetrate the outer wall, for example, the outer diameter of the outer wall 1 can be designed to be greater than the maximum diameter of the throat. In order to ensure the surface of the inner wall 2 (the position of the throat of the thrust chamber on the inner wall) is normally used, before welding the end cover at both ends of the combustion chamber 6, at the end of the combustion chamber 6 close to the expansion section 7, making one end of the inner wall 2 (the position of the throat of the thrust chamber on the inner wall) penetrates the outer wall 1 and partially exposed near the expansion section, and the circumferential surface of the exposed inner wall 2 (the position of the throat of the thrust chamber on the inner wall) is
Description
connected to an outer wall ring 9 via the convex ribs 4. The outer wall ring 9 functions as the outer wall. In order to facilitate installation, the outer wall ring 9 can be formed by docking two symmetrical semi-circular structures. In application, after one end of the inner wall 2 of the combustion chamber (the position of the throat of the thrust chamber on the inner wall) penetrates the outer wall, the outer wall ring 9 is sleeved on the outside of the convex ribs 4 first, the inner side of the outer wall ring 9 is closely connected with the convex ribs 4, and one end of the outer wall ring 9 is contacted and connected with one end of the outer wall 1.
In addition, as shown in Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 9, Fig. 10 and Fig. 11, in order to facilitate the connection between the combustion chamber 6 and the expansion section 7, for example, after the combustion chamber 6 has undergone the second pressurization treatment, cutting off the end cover 5, the air guide duct 3 and the annular groove 8 along the radial direction of the combustion chamber 6, and cutting off part of the outer wall ring 9 of the combustion chamber 6 near the end of the expansion section 7 along the radial direction, so as to obtain the combustion chamber to be welded..
Similarly, after the expansion section 7 has undergone the second pressurization treatment, cutting off the end cover, the air guide duct and the annular groove along the radial direction of the expansion section 7, and cutting off the outer wall 1 of the expansion section 7 near the end of the combustion chamber 6 along the radial direction. By the cutting of part of the outer wall ring 9 of the combustion chamber 6 and the matching cutting of the outer wall of the expansion section near the end of the combustion chamber 6, it can be ensured that the combustion chamber and the expansion section match with each other in size.
After cutting off part of the outer wall ring 9 and part of the outer wall 1 of the expansion section, the method further includes: welding the inner walls of the ends of the combustion chamber 6 and the expansion section 7 close to each other, and connecting the outer wall ring 9 and the outer wall 1 via a connecting duct fitting 10 to obtain the thrust chamber body assembly, wherein the outer wall ring 9 and the outer wall I are close to each other and both have a notch for match-welding. The whole design is ingeniously designed, which makes the combustion chamber 6 and the expansion section 7 more tightly connected without affecting the original effect. In order to reduce the weight of the thrust chamber
Description
assembly and ensure an aesthetic appearance, for example, the surfaces of the connecting duct fitting 10 and the outer wall ring 9 may be thinned.
In order to ensure that the outer wall 1, the inner wall 2 and the convex ribs 4 are clean and tidy, and reduce the impact of impurities on the welding strength, for example, the surfaces of the outer wall 1, the inner wall 2 and the convex ribs 4 need to be cleaned before use.
The thrust chamber body structure of this embodiment is mainly described with the combustion chamber 6 and the expansion section 7. In actual application, the thrust chamber body structure can also include a third portion, a fourth portion, etc., and the molding process of each portion is same with that of the combustion chamber 6 or the expansion section 7.
The above embodiments can be combined with each other and have corresponding technical effects.
The present invention also provides a spacecraft thrust chamber, which is prepared by using any one of the above-mentioned welding methods for processing the thrust chamber body components.
The above are only illustrative specific embodiments of the present invention. Without departing from the concept and principle of the present application, any equivalent changes and modifications made by those skilled in the art shall fall within the protection scope of the present application.
Claims (12)
- Claims 1. A method for processing a double-layer structure of a spacecraft thrust chamber, characterized in that, the double-layer structure includes an outer wall, an inner wall and a spacer, wherein the outer wall and the inner wall constitute at least a part of a spacecraft thrust chamber body, the spacer is fixed between the outer wall and the inner wall and configured to provide a channel between the outer wall and the inner wall for coolant flow; the method comprises the following steps: (i) providing a first wall structure, a second wall structure and a convex rib, wherein the first wall structure and the second wall structure are close to each other in an inner-outer fitting manner to form at least a part of the spacecraft thrust chamber body, and the convex rib is located between the first wall structure and the second wall structure, (2) closing the first wall structure and the second wall structure at their ends, thereby forming a combined structure with a closed space inside, wherein the combined structure is composed of the first wall structure, the second wall structure and the convex rib; and (3) making the closed space a negative pressure, and then performing a first pressurization treatment on the combined structure from outside, and then performing a second pressurization treatment on the combined structure from outside under a condition that the closed space communicates with outside, thereby forming the combined structure into one piece and obtaining the double-layer structure, wherein the maximum pressure of the second pressurization treatment is greater than that of the first pressurization treatment.
- 2. The method for processing the double-layer structure of the spacecraft thrust chamber according to claim 1, wherein an intensity of pressure A satisfies 1MPa < A < 20MPa, a pressurization time B satisfies 0.2h < B <I Oh, and a temperature C satisfies 300C < C < 1300 C during the first pressurization treatment.
- 3. The method for processing the double-layer structure of the spacecraft thrust chamber according to claim 1, wherein an intensity of pressure D satisfies 2M-Pa < D < 120MPa, a Claims pressurization time E satisfies 0.1h <E < 10h, and a temperature F satisfies 300°C < F < 1400t during the second pressurization treatment.
- 4. The method for processing the double-layer structure of the spacecraft thrust chamber according to claim 1, wherein the pressure in the closed space is controlled to be a negative pressure by an air guide assembly, and the air guide assembly includes an air guide duct and an annular groove, the annular groove communicates with a distal end of the air guide duct and is provided on one side of the first wall structure
- 5. The method for processing the double-layer structure of the spacecraft thrust chamber according to claim 4, further comprising a step of cutting off the air guide assembly.
- 6. The method for processing the double-layer structure of the spacecraft thrust chamber according to claim 1, wherein the double-layer structure comprises a first double-layer structure and a second double-layer structure, which constitute the thrust chamber body, the first double-layer structure and the second double-layer structure are a combustion chamber or an expansion section independently, and wherein the method comprises a first processing step to obtain the first double-layer structure and a second processing step to obtain the second double-layer structure, wherein the first processing step and the second processing step are performed simultaneously or sequentially.
- 7. The method for processing the double-layer structure of the spacecraft thrust chamber according to claim 1, wherein in step (i), one side of the convex rib is pre-fixed to the second wall structure, and the other side of the convex rib is in close contact with a surface of the first wall structure, so that the convex rib is formed into the spacer after step (3).Claims
- 8. The method for processing the double-layer structure of the spacecraft thrust chamber according to claim 1, further comprising steps of providing an end cover and removing the end cover, wherein the end cover is connected to an end of the first wall structure and an end of the second wall structure when providing the end cover, so that the first wall structure and the second wall structure are closed at the ends thereof, and the step of removing the end cover includes cutting off the end cover along a radial direction of the double-layer structure.
- 9. The method for processing the double-layer structure of the spacecraft thrust chamber according to claim 1, wherein one end of the first wall structure penetrates one end of the second wall structure and connects with the end of the second wall structure as a whole.
- The method for processing the double-layer structure of the spacecraft thrust chamber according to claim I, wherein the combined structure is subjected to an external pressurization treatment by a high-pressure container.
- 11 The method for processing the double-layer structure of the spacecraft thrust chamber according to claim 4, further comprising an evacuating device for connecting with the air guide duct.
- 12. A spacecraft thrust chamber, characterized in that it is obtained by the method for processing the double-layer structure of the spacecraft thrust chamber according to any one of claims 1-i 1.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011381643.7A CN112462714B (en) | 2020-12-01 | 2020-12-01 | Processing method of spacecraft thrust chamber double-layer structure |
| PCT/CN2021/134260 WO2022116955A1 (en) | 2020-12-01 | 2021-11-30 | Method for processing double-layer structure of thrust chamber, and spacecraft thrust chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB202307694D0 GB202307694D0 (en) | 2023-07-05 |
| GB2616149A true GB2616149A (en) | 2023-08-30 |
Family
ID=74806024
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2307694.6A Pending GB2616149A (en) | 2020-12-01 | 2021-11-30 | Method for processing double-layer structure of thrust chamber, and spacecraft thrust chamber |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN112462714B (en) |
| GB (1) | GB2616149A (en) |
| WO (1) | WO2022116955A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112462714B (en) * | 2020-12-01 | 2021-08-24 | 陕西蓝箭航天技术有限公司 | Processing method of spacecraft thrust chamber double-layer structure |
| CN113894453B (en) * | 2021-09-15 | 2022-06-17 | 蓝箭航天空间科技股份有限公司 | Method for processing combustion chamber structure of dissimilar metal and combustion chamber |
| CN113982786B (en) * | 2021-10-29 | 2023-06-06 | 中国人民解放军战略支援部队航天工程大学 | Rocket engine thrust chamber of red copper-stainless steel for avoiding dissimilar metal welding |
| CN116038171B (en) * | 2023-03-30 | 2023-06-27 | 北京星河动力装备科技有限公司 | Regenerative cooling thrust chamber and manufacturing method thereof |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6205661B1 (en) * | 1999-04-15 | 2001-03-27 | Peter John Ring | Method of making a rocket thrust chamber |
| WO2003052255A1 (en) * | 2001-12-18 | 2003-06-26 | Volvo Aero Corporation | A component for being subjected to high thermal load during operation and a method for manufacturing such a component |
| US8584988B1 (en) * | 2010-09-22 | 2013-11-19 | The Boeing Company | Mechanically fastened large pressurized spacecraft structure |
| CN106438109A (en) * | 2016-10-31 | 2017-02-22 | 北京航天动力研究所 | Liquid-propellant rocket engine thrust chamber interlayer structure with throat reinforcing bushing |
| CN206206011U (en) * | 2016-10-31 | 2017-05-31 | 北京航天动力研究所 | A kind of liquid rocket engine thrust chamber sandwich for strengthening bushing with throat |
| CN109759789A (en) * | 2019-01-24 | 2019-05-17 | 北京蓝箭空间科技有限公司 | The thrust chamber pressure resistance interlayer manufacturing method of liquid-propellant rocket engine |
| CN110202320A (en) * | 2019-03-15 | 2019-09-06 | 蓝箭航天技术有限公司 | Composite tooling and thrust chamber preparation process for thrust chamber preparation process |
| CN209724523U (en) * | 2019-03-13 | 2019-12-03 | 蓝箭航天技术有限公司 | A kind of thrust chamber's structure |
| CN209811495U (en) * | 2019-03-04 | 2019-12-20 | 蓝箭航天空间科技股份有限公司 | Composite tool for welding thrust chamber |
| CN209850261U (en) * | 2019-03-15 | 2019-12-27 | 蓝箭航天技术有限公司 | Composite tool for thrust chamber preparation process |
| CN111531321A (en) * | 2020-07-09 | 2020-08-14 | 蓝箭航天空间科技股份有限公司 | Method for repairing spacecraft thrust chamber jacket and spacecraft thrust chamber |
| CN112177799A (en) * | 2020-12-01 | 2021-01-05 | 蓝箭航天空间科技股份有限公司 | Welding processing method of spacecraft thrust chamber body component and spacecraft thrust chamber |
| CN112462714A (en) * | 2020-12-01 | 2021-03-09 | 陕西蓝箭航天技术有限公司 | Processing method of spacecraft thrust chamber double-layer structure |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102950351B (en) * | 2012-11-02 | 2015-10-28 | 首都航天机械公司 | Hydrogen peroxide thrust chamber body portion diffusion brazing manufacture method |
| JP5823069B1 (en) * | 2015-01-23 | 2015-11-25 | 三菱重工業株式会社 | Method for manufacturing rocket engine combustor, rocket engine combustor, and rocket engine |
| CN104924036B (en) * | 2015-06-16 | 2017-11-21 | 湖北三江航天江北机械工程有限公司 | The manufacture method of Liquid Rocket Engine Combustion Chambers |
| CN106078098B (en) * | 2016-06-29 | 2018-05-22 | 航天材料及工艺研究所 | A kind of preparation method of motor power room |
-
2020
- 2020-12-01 CN CN202011381643.7A patent/CN112462714B/en active Active
-
2021
- 2021-11-30 GB GB2307694.6A patent/GB2616149A/en active Pending
- 2021-11-30 WO PCT/CN2021/134260 patent/WO2022116955A1/en unknown
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6205661B1 (en) * | 1999-04-15 | 2001-03-27 | Peter John Ring | Method of making a rocket thrust chamber |
| WO2003052255A1 (en) * | 2001-12-18 | 2003-06-26 | Volvo Aero Corporation | A component for being subjected to high thermal load during operation and a method for manufacturing such a component |
| US8584988B1 (en) * | 2010-09-22 | 2013-11-19 | The Boeing Company | Mechanically fastened large pressurized spacecraft structure |
| CN106438109A (en) * | 2016-10-31 | 2017-02-22 | 北京航天动力研究所 | Liquid-propellant rocket engine thrust chamber interlayer structure with throat reinforcing bushing |
| CN206206011U (en) * | 2016-10-31 | 2017-05-31 | 北京航天动力研究所 | A kind of liquid rocket engine thrust chamber sandwich for strengthening bushing with throat |
| CN109759789A (en) * | 2019-01-24 | 2019-05-17 | 北京蓝箭空间科技有限公司 | The thrust chamber pressure resistance interlayer manufacturing method of liquid-propellant rocket engine |
| CN209811495U (en) * | 2019-03-04 | 2019-12-20 | 蓝箭航天空间科技股份有限公司 | Composite tool for welding thrust chamber |
| CN209724523U (en) * | 2019-03-13 | 2019-12-03 | 蓝箭航天技术有限公司 | A kind of thrust chamber's structure |
| CN110202320A (en) * | 2019-03-15 | 2019-09-06 | 蓝箭航天技术有限公司 | Composite tooling and thrust chamber preparation process for thrust chamber preparation process |
| CN209850261U (en) * | 2019-03-15 | 2019-12-27 | 蓝箭航天技术有限公司 | Composite tool for thrust chamber preparation process |
| CN111531321A (en) * | 2020-07-09 | 2020-08-14 | 蓝箭航天空间科技股份有限公司 | Method for repairing spacecraft thrust chamber jacket and spacecraft thrust chamber |
| CN112177799A (en) * | 2020-12-01 | 2021-01-05 | 蓝箭航天空间科技股份有限公司 | Welding processing method of spacecraft thrust chamber body component and spacecraft thrust chamber |
| CN112462714A (en) * | 2020-12-01 | 2021-03-09 | 陕西蓝箭航天技术有限公司 | Processing method of spacecraft thrust chamber double-layer structure |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2022116955A1 (en) | 2022-06-09 |
| CN112462714A (en) | 2021-03-09 |
| GB202307694D0 (en) | 2023-07-05 |
| CN112462714B (en) | 2021-08-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| GB2616149A (en) | Method for processing double-layer structure of thrust chamber, and spacecraft thrust chamber | |
| CN112177799B (en) | Welding processing method of spacecraft thrust chamber body component and spacecraft thrust chamber | |
| CN209724523U (en) | A kind of thrust chamber's structure | |
| US9855628B2 (en) | Manufacture of filled aerofoil | |
| US6829884B2 (en) | Rocket engine combustion chamber having multiple conformal throat supports | |
| JP5449019B2 (en) | Superconducting acceleration cavity and method of manufacturing superconducting acceleration cavity | |
| US10239141B2 (en) | Forming a complexly curved metallic sandwich panel | |
| US5375325A (en) | Method of making a rocket chamber construction | |
| CN104500157A (en) | Low-pressure cylinder of steam turbine | |
| EP2851509B1 (en) | Manufacture of hollow aerofoil | |
| US20040010900A1 (en) | Method for forming a tube-walled article | |
| JPH0647569A (en) | Method of manufacturing hollow article | |
| CN115740965A (en) | Method for manufacturing rocket engine combustion chamber with integral structure | |
| JP2013515915A (en) | Integrated aircraft engine flow path structure | |
| CN114991998A (en) | Diffusion welding body part structure of sectional type liquid rocket engine thrust chamber and welding method | |
| US20160265365A1 (en) | Manufacture of a hollow aerofoil | |
| CN112459926B (en) | Welding processing technology for body component of thrust chamber and spacecraft thrust chamber | |
| CN104289809A (en) | Vacuum diffusion welding process for groove type cylindrical surface connecting piece | |
| KR100931002B1 (en) | How to make nozzle of the combustor | |
| CN213627810U (en) | Thrust chamber body component structure and spacecraft thrust chamber | |
| CN109436377B (en) | A kind of non-uniform thickness wall surface fork ring stress spread structure and its design method | |
| CN110369729A (en) | One kind coupling manufacturing process for internal complicated multiple flow passages part powder admittedly | |
| US10415393B2 (en) | Manufacturing method | |
| CN114571053B (en) | Titanium alloy vacuum diffusion welding spray pipe and design method | |
| US11684997B2 (en) | Manufacture of a hollow aerofoil |