CN111531321B - Method for repairing spacecraft thrust chamber jacket and spacecraft thrust chamber - Google Patents
Method for repairing spacecraft thrust chamber jacket and spacecraft thrust chamber Download PDFInfo
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- CN111531321B CN111531321B CN202010654327.6A CN202010654327A CN111531321B CN 111531321 B CN111531321 B CN 111531321B CN 202010654327 A CN202010654327 A CN 202010654327A CN 111531321 B CN111531321 B CN 111531321B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/21—Bonding by welding
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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
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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Abstract
The invention discloses a method for repairing a jacket of a spacecraft thrust chamber and the spacecraft thrust chamber, and provides the thrust chamber, wherein the thrust chamber comprises an outer wall, an inner wall and convex ribs, the inner wall is welded and connected with the outer wall through the convex ribs, and a plurality of channels for flowing of a coolant are limited between the inner wall and the outer wall after the outer wall and the inner wall are welded by the convex ribs; pressing the channel, checking the debonding part between the outer wall and the convex rib, and enabling the position of the outer wall corresponding to the debonding part to be protruded by pressing; an imaging negative film is arranged on the inner side of the inner wall; irradiating the bulge through rays to enable the convex rib corresponding to the bulge to form a first image on the imaging negative film; comparing the first image with the position relation of the bulges and the convex ribs on the imaging negative film, and determining a track to be welded on the outer wall; and carrying out laser welding on the outer wall along the track to finish the repair of the thrust chamber jacket. The whole process is reasonable in design and saves cost.
Description
Technical Field
The invention relates to the technical field of spacecraft engines, in particular to a method for repairing a jacket of a thrust chamber of a spacecraft and the thrust chamber of the spacecraft.
Background
The technology of spacecraft engines is rapidly upgraded with the development of the aerospace industry. As a main component of the engine, the thrust chamber is a key component for performing energy conversion of the propellant and generating thrust. The thrust chamber body is a component which is used for mixing and burning fuel in the spacecraft engine to generate high-temperature and high-pressure fuel gas, and then the fuel gas is accelerated and discharged through the throat part to obtain reverse thrust. The body of the thrust chamber is of a Laval profile structure, and the thrust chamber can be cooled by adopting a regenerative cooling technology. The thrust chamber is composed of a milled groove inner wall and a milled groove outer wall, a plurality of cooling channels are arranged between the milled groove inner wall and the milled groove outer wall, and the two inner parts do not have any leakage defect under the pressure up to 60 MPa.
The invention provides a method for repairing a jacket of a thrust chamber of a spacecraft and the thrust chamber of the spacecraft, which can be used for welding and repairing the inner wall and the outer wall of the spacecraft when the inner wall and the outer wall of a milling groove have debonding and unwelding defects, so that a repaired product meets the use requirement, the cost is saved, and the safe use of the thrust chamber of the spacecraft is ensured.
Disclosure of Invention
The invention aims to provide a method for repairing a jacket of a thrust chamber of a spacecraft and the thrust chamber of the spacecraft, which have the advantages of reasonable design and simple operation when the inner wall and the outer wall of a milling groove have the defects of debonding and unwelding, so that a repaired product meets the use requirement, the cost is saved, the safe use of the thrust chamber of the spacecraft is ensured, and the like.
In order to achieve the purpose, the invention provides the following technical scheme: a method of repairing a spacecraft thrust chamber jacket comprising:
providing a thrust chamber, wherein the thrust chamber comprises an outer wall, an inner wall and a convex rib, the inner wall is connected with the outer wall in a welding mode through the convex rib, and a plurality of channels for flowing coolant are defined between the inner wall and the outer wall after the outer wall and the inner wall are welded;
pressing the channel, checking a debonding part between the outer wall and the convex rib, and enabling the position of the outer wall corresponding to the debonding part to be protruded through pressing;
arranging an imaging negative film on the inner side of the inner wall;
irradiating the bulge through rays to enable the convex rib corresponding to the bulge to form a first image on the imaging negative film;
comparing the first image with the position relation of the bulges and the convex ribs on the imaging negative film, and determining a track to be welded on the outer wall;
and carrying out laser welding on the outer wall along the track, and further completing the repair of the thrust chamber jacket.
Further, before the projection is irradiated by the ray, the projection is pressed down to one side of the convex rib by a pressure head, so that the projection and the convex rib are mutually attached.
Furthermore, after the protrusions and the convex ribs are tightly attached to each other, lead mark belts are attached to the upper portion and the lower portion of the protrusions along the axial direction.
Further, the lead label tape is bonded by lead block arrows, lead wires and adhesive tapes, and the actual distance of each lead block arrow is measured by a micrometer before use to carry out labeling.
Further, the distance between the upper part and the lower part of the bulge along the axial direction is A, and when A is larger than or equal to 100mm, the number of the lead label tapes is increased between the upper part and the lower part of the bulge.
Furthermore, through the ray irradiation protruding, make correspond protruding fin is in form first image after on the formation of image film, follow the inner wall takes out the formation of image film, compare first image with protruding with the fin is in the position relation on the formation of image film, correspondingly the outer wall surface draw each with protruding each fin that overlaps on the formation of image film is in corresponding mark point on the outer wall connects each mark point, obtains the welding track.
Further, irradiating the bump and the lead label tape by rays to enable the lead label tape to form a second image on the imaging negative film; and obtaining each marking point and welding track by comparing the position relation between the lead label tape on the outer wall and the bulge and the relation between the second image of the lead label tape on the imaging negative film and the first image.
Furthermore, when the convex ribs and the protrusions are welded by laser, the convex ribs are welded with the protrusions one by one.
Further, the thickness of the outer wall is B, when B is larger than or equal to 8mm, the thickness of the bulge is processed to be less than 5mm, the bulge and the convex rib are subjected to laser welding through laser welding, and then the wall thickness of the processed bulge is equal to the wall thickness of the thrust chamber through a surfacing welding mode.
The invention also provides a spacecraft thrust chamber which is prepared by adopting the method for repairing the jacket of the spacecraft thrust chamber.
Compared with the prior art, the invention has the beneficial effects that: the convex rib is positioned between the outer wall and the inner wall, so that the observation is inconvenient, the convex rib corresponding to the convex rib is enabled to form a first image on the imaging negative by irradiating the convex rib on the outer wall through rays, so that the shape and the trend of the convex rib can be obtained from the imaging negative, and the track to be welded between the convex rib and the convex rib is determined on the outer wall by comparing the first image with the position relation of the convex rib and the position relation of the convex rib on the imaging negative; and laser welding the outer wall and the convex ribs by a laser welding machine along the track so as to complete the repair of the thrust chamber jacket. In the whole process, when the inner wall and the outer wall of the milling groove have debonding and unwelded defects, the welding defects of the inner wall and the outer wall can be reliably repaired and welded, so that the production cost is saved, and the safe use of the rocket engine thrust chamber is ensured.
Drawings
FIG. 1 is a flow chart of a repair method of the present invention;
FIG. 2 is a schematic view of the thrust chamber configuration of the present invention;
FIG. 3 is a schematic view of the structure of the outer wall, inner wall and ribs of the present invention;
FIG. 4 is a schematic view of the construction of the ram, outer wall, inner wall and ribs of the present invention;
FIG. 5 is a schematic structural view of an arrow of a lead label tape and a lead block according to the present invention;
FIG. 6 is a schematic view of the structure of the radiation irradiating projection of the present invention;
FIG. 7 is a diagram illustrating a first image according to the present invention;
FIG. 8 is a schematic structural view of rib position marking points and laser welding trajectories according to the present invention;
FIG. 9 is a schematic illustration of laser welding of the present invention;
FIG. 10 is a schematic view of the fusion depth and fusion width of the present invention when the outer wall, the inner wall and the ribs are connected.
Description of reference numerals:
1 thrust chamber 2 outer wall
3 inner wall 4 ribs
5 pressure head 6 lead label
7 lead block arrow 8 film support plate
9 imaging negative film 10 ray source
12-rib position marking point of 11 clamping tool device
13 track 14 robot arm
15 welding head
Detailed Description
For the purpose of promoting a clear understanding of the objects, aspects and advantages of the embodiments of the invention, reference will now be made to the drawings and detailed description, wherein there are shown in the drawings and described in detail, various modifications of the embodiments described herein, and other embodiments of the invention will be apparent to those skilled in the art.
The exemplary embodiments of the present invention and the description thereof are provided to explain the present invention and not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.
As used herein, the terms "first," "second," …, etc., do not denote any order or sequence, nor are they used to limit the present invention, but rather are used to distinguish one element from another or from another element or operation described in the same technical language.
With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.
As used herein, "and/or" includes any and all combinations of the described items.
As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. Generally, the range of slight variations or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.
Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.
After the production of the body of the thrust chamber is completed, the body is first subjected to an inner and outer wall joint strength test. For example, the test can be performed by filling a high pressure liquid into the interlayer between the inner wall and the outer wall of the milled groove. If the inner wall and the outer wall of the milling groove are debonded (a gap exists at the joint of the outer wall and the convex rib, and the outer wall at the gap is raised when high pressure is borne), a protrusion can be formed at the debonding part of the outer wall, which also means that the body test of the thrust chamber fails. In order to ensure the safety of the space engine, the thrust chamber body which fails the test is often abandoned.
The embodiment of the invention provides a method for repairing a thrust chamber jacket. As shown in figures 1, 2, 3, 4, 6, 7 and 9,
providing a thrust chamber 1, wherein the thrust chamber 1 comprises an outer wall 2, an inner wall 3 and convex ribs 4, the inner wall 3 is connected with the outer wall 2 in a welding mode through the convex ribs 4, and a plurality of channels for flowing coolant are defined between the inner wall 3 and the outer wall 2 after the outer wall 2 and the inner wall 3 are welded; the repair method of the thrust chamber jacket comprises the following steps:
s1: and (3) pressing the channel, inspecting the debonding part between the outer wall 2 and the convex rib 4, and making the position of the outer wall 2 corresponding to the debonding part bulge by pressing.
S2: an imaging negative 9 is provided on the inner side of the inner wall 3.
S3: the projection is irradiated by the ray, so that the convex rib 4 corresponding to the projection forms a first image on the imaging negative film 9.
S4: comparing the first image with the position of the projections and ribs 4 on the imaging plate 9 determines the path 13 to be welded on the outer wall 2.
S5: the outer wall 2 is laser welded along the trajectory 13, and the repair of the thrust chamber jacket is completed.
Since the rib 4 is located between the outer wall 2 and the inner wall 3, it is inconvenient to observe the welding effect, which affects the precise welding. In the embodiment, the projection on the outer wall 2 is irradiated by the ray, so that the convex rib 4 corresponding to the projection forms a first image on the imaging film 9, so as to accurately obtain the shape and the trend of the convex rib 4 from the imaging film 9, and the track 13 to be welded between the projection and the convex rib 4 is determined on the outer wall 2 by comparing the position relationship between the first image and the projection and the position relationship between the projection and the convex rib 4 on the imaging film 9. After the welding track 13 is determined, the outer wall 2 can be laser welded along the track 13, thereby completing the repair of the thrust chamber jacket. When the inner wall of the milling groove and the outer wall are debonded (the outer wall and the convex rib are partially separated) and are not welded, the repairing method of the embodiment of the application can reliably repair the welding defect of the inner wall and the outer wall, saves production cost and ensures safe use of the thrust chamber of the rocket engine.
It should be noted that, as shown in fig. 4 and 6, in order to facilitate the welding connection between the protrusion and the protruding rib 4 and to accurately position the protrusion with a defective connection with the protruding rib 4, for example, before the protrusion is irradiated with the radiation, the pressing head 5 may be used to press the protrusion toward the protruding rib 4, so that the protrusion and the protruding rib 4 are tightly attached to each other. According to the repairing method provided by the embodiment of the application, the convex ribs 4 and the bulges are tightly attached to each other, so that the imaging errors of the convex ribs and the bulges on an imaging negative film can be avoided, and the positioning effect on welding defects is improved.
As shown in fig. 5, 6 and 7, in order to facilitate the positioning of the projections and the marking, for example, after the projections and the ribs 4 are closely attached to each other, a lead label tape 6 is attached above and below the projections in the axial direction. The lead label tape 6 can accurately determine the parts to be welded of the outer wall 2 and the convex ribs 4 by imaging on the imaging film 9 according to the relation between the lead label tape and the convex ribs 4 on the imaging film 9 and the relation between the lead label tape and the convex ribs 4 on the outer wall 2. For example, the lead label tape 6 may be disposed along the circumferential direction of the outer wall of the thrust chamber, and closely attached to the surface of the thrust chamber, so that the rib between the inner wall and the outer wall may be more accurately positioned.
Further, in order to ensure that the lead label tape 6 accurately positions the to-be-welded protruding rib and the protrusion, for example, the lead label tape 6 may be bonded by a lead block arrow 7, a lead wire and an adhesive tape, that is, the lead block arrow 7, the lead wire and the adhesive tape. The lead mark belt 6 is provided with scales, the function of the lead mark belt is similar to that of a measuring scale, and the position to be welded can be accurately positioned by comparing the position relation of an imaging object and a real object. And forming a second image on the imaging negative by the lead label tape 6 through rays, and obtaining each marking point and each welding track by comparing the position relation of the lead label tape on the outer wall and the bulge and the relation of the two images of the lead label tape 6 on the imaging negative 9 and the first image. For example, the second image defines the up-and-down position of the projection (along the axial direction of the outer wall), and the second image (the lead label tape 6 on the imaging film) intersects with the first image (the convex rib on the imaging film), so that the position of the welding defect between the convex rib 4 and the outer wall 2 can be accurately determined on one hand, and the number of the convex ribs passing through the projection can be clearly determined on the other hand, and the subsequent welding is facilitated. For example, the first image has 5 to 10 convex ribs on the imaging film, the convex ribs correspond to corresponding scales of the second image on the imaging film (the scales of the second image formed by the lead label tape correspond to the scales of the lead label tape on the real object), and the convex ribs and the length corresponding to the protrusions can be reversely marked on the outer wall of the thrust chamber according to the corresponding relation between the lead label tape and the actual scales of the protrusions.
Specifically, as shown in fig. 5, 6, 7, 8 and 10, the pictures with the first image and the second image are compared with the outer wall 2. For example, the second image (the graphic of the lead label 6 projected on the imaging negative) is attached to the actual lead label 6 on the outer wall so that the second image of the lead label 6 on the imaging negative is coincident with the lead label 6. Extending two ends of a first image (a pattern of the convex rib projected on the imaging film), drawing rib position marking points 12 on the outer sides of two actual lead label tapes 6 which are far away from each other, then taking down the imaging film and the lead label tapes 6, connecting the two rib position marking points 12 to obtain a welding track 13 of the convex rib 4 on the outer wall 2, and then welding the outer wall along the track. In order to ensure that the welding is tight and firm, and ensure that the welded outer wall and the convex ribs meet the design requirements, for example, the laser welding parameters are corresponding parameters of selecting the melting depth (E mark point) as the thickness of the outer wall, adding 0.5mm-2mm of depth, and the melting width (F mark point) as the width of 0.5-2 mm. In addition, the number of the rib position marking points 12 is at least two, and in order to accurately determine the to-be-welded track of the convex rib, the number of the marking points 12 can be increased. In the present embodiment, in order to further improve the measurement accuracy, the actual distance of each lead arrow 7 is measured by a micrometer before use and marked.
When the bumps are irradiated with radiation, in order to accurately obtain the positions of the bumps and the lead label tape 6, for example, the radiation source 10 emitting the radiation is located on the outer side of the side wall, and the radiation source 10 is located in the direction perpendicular to the bumps. The radiation source 10 can irradiate the projections at a plurality of positions which form certain included angles with the direction vertical to the projections in the process of irradiating the projections and the lead label tape 6 to obtain images of a plurality of different convex ribs and the lead label tape 6 on an imaging negative film. By comprehensive comparison, the average value of the positions of the convex ribs and the lead label tape 6 in the imaging negative film is obtained (the lead block arrow and the lead wire in the lead label tape 6 play a role of a graduated scale, and the value of each position is marked on the imaging negative film). The average is marked on an imaging negative and the points are connected in the manner described above to determine the path of the ribs to be welded. According to the thrust chamber jacket repairing method, the image of the light source irradiation error can be eliminated by adjusting the irradiation angle of the light source, the positioning precision of the convex is improved, and the repairing effect of the thrust chamber jacket is improved.
It should be reminded that when the area of the protrusion is too large, for example, the distance between the upper part and the lower part of the protrusion in the axial direction is a, and when a is greater than or equal to 100mm, the number of the lead label tapes 6 can be increased between the upper part and the lower part of the protrusion, so as to facilitate the determination of the position of the convex rib 4.
It should be noted that, in order to improve the repairing efficiency and save the repairing time, for example, when the convex rib 4 and the protrusion are welded by a laser welder, the convex rib 4 is welded with the protrusion one by one.
It should be noted that, when the outer wall of the thrust chamber 1 is too thick, the welding range of the laser welder is exceeded, and the outer wall 2 and the rib 4 may be welded insufficiently firmly. For example, the thickness of the outer wall of the thrust chamber 1 is B, and when B is more than or equal to 8m, in order to meet the use requirement of a laser welding machine and ensure that the outer wall and the convex rib are welded tightly and fixed firmly, the thickness of the bulge can be firstly processed to be less than 5 mm. Like this, can be when repairing welding protruding with fin 4 laser through laser welder for outer wall 2 is inseparabler with the welding of fin 4, and welding defect's repairing effect is better. The processed wall thickness of the bulge is equal to the outer wall thickness of the thrust chamber 1 through a build-up welding mode after the bulge and the convex rib 4 are subjected to laser welding, so that the thrust chamber after repair welding can meet the use requirement. The surfacing mode can be specifically operated as follows: for example, after the protrusion is processed to 5mm in thickness and welding is completed, the upper portion of the protrusion is filled with a plurality of layers of alloy plates and laser welding is adopted to tightly connect each layer of copper alloy plate with the outer wall and the copper alloy plates close to each other, so that the protrusion filled with the plurality of layers of alloy plates is equal to the thickness of the outer wall.
In order to make the imaging film 9 tightly attached to the inner wall 3, avoid the imaging film 9 from falling off from the inner wall 3 and improve the imaging precision of the lead label tape and the convex ribs on the imaging film 9, a clamping tool device 11 can be adopted to match with the film support plate 8 to fix the imaging film 9 on the inner wall 3. Referring to fig. 6, the clamping tooling device 11 is substantially in the shape of a truncated cone, and both the clamping tooling device 11 and the film support plate 8 are positioned on the inner side of the inner wall 3 of the thrust chamber. The clamping tooling device 11 supports one side of the film support plate 8, and the other side of the film support plate 8 presses the imaging film 9 on the surface of the inner wall 3 close to the axis of the thrust chamber. According to the thrust chamber sleeving welding repair method, the imaging negative film can be limited by the aid of the tool, so that the imaging angle between the ray light source and the imaging negative film is ensured, and the imaging precision of the lead label tape is improved.
The number of the machine arms 14 of the welding machine can be increased according to actual needs, for example, the welding ribs to be welded can be welded simultaneously through a plurality of the machine arms 14 of the welding machine, so that the deformation of the thrust chamber in the welding process is reduced, and the repair effect of the jacket is improved. In addition, when the welding head 15 is in contact with the bulge, an air supply device is arranged on one side of the welding head and used for blowing away smoke around the welding head 15, so that protective gas is formed outside the welding point, and the repair effect of the thrust chamber jacket is improved.
The radiation source of the present application may be an X-ray source.
The above embodiments may be combined with each other with corresponding technical effects.
The invention also provides a spacecraft thrust chamber which is prepared by adopting the method for repairing the jacket of the spacecraft thrust chamber.
The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.
Claims (10)
1. A method for repairing a jacket of a thrust chamber of a spacecraft is characterized in that,
providing a thrust chamber, the thrust chamber includes outer wall, inner wall and fin, the inner wall pass through the fin with outer wall welded connection, the fin is in the outer wall with the inner wall welds the back and prescribes a limit to many passageways that supply the coolant circulation between inner wall and the outer wall, include:
pressing the channel, checking a debonding part between the outer wall and the convex rib, and enabling the position of the outer wall corresponding to the debonding part to be protruded through pressing;
arranging an imaging negative film on the inner side of the inner wall;
irradiating the bulge through rays to enable the convex rib corresponding to the bulge to form a first image on the imaging negative film;
comparing the first image with the position relation of the bulges and the convex ribs on the imaging negative film, and determining a track to be welded on the outer wall;
and carrying out laser welding on the outer wall along the track, and further completing the repair of the thrust chamber jacket.
2. The method for repairing a spacecraft thrust chamber jacket according to claim 1, wherein before said projections are irradiated with rays, said projections are pressed down toward said convex rib side with a pressing head so that said projections and said convex rib are closely attached to each other.
3. The method for repairing a spacecraft thrust chamber jacket according to claim 2, wherein after the protrusions and the ribs are tightly adhered to each other, lead tapes are respectively adhered above and below the protrusions in the axial direction of the thrust chamber.
4. The method for repairing a spacecraft thrust chamber jacket according to claim 3, wherein the lead label tape is bonded together by lead block arrows, lead wires and adhesive tapes, and the actual distance of each lead block arrow is measured and marked by a micrometer before use.
5. The method for repairing a spacecraft thrust chamber jacket according to claim 3, wherein a distance A between an upper side and a lower side of the protrusion in the axial direction is provided, and when A is not less than 100mm, the number of the lead label tape is increased between the upper side and the lower side of the protrusion.
6. The method according to claim 3, wherein after the projection is irradiated by the ray to form a first image on the imaging negative plate by the convex rib corresponding to the projection, the imaging negative plate is taken out from the inner wall, the positional relationship between the first image and the projection and the convex rib on the imaging negative plate is compared, and accordingly, the corresponding mark points on the outer wall of each convex rib overlapped with the projection on the imaging negative plate are drawn on the surface of the outer wall, and the mark points are connected to obtain the welding track.
7. The method of repairing a spacecraft thrust cell jacket of claim 6, wherein said projection and lead straps are irradiated by radiation to cause said lead straps to form a second image on said imaging plate; and obtaining each marking point and welding track by comparing the position relation between the lead label tape on the outer wall and the bulge and the relation between the second image of the lead label tape on the imaging negative film and the first image.
8. The method for repairing a spacecraft thrust chamber jacket of claim 1, wherein said ribs are welded to said protrusions one by one while said ribs and said protrusions are laser welded.
9. The method for repairing the thrust chamber jacket of the spacecraft as claimed in claim 1, wherein the thickness of the outer wall is B, when B is greater than or equal to 8mm, the thickness of the bulge is processed to be less than 5mm, the bulge and the convex rib are subjected to laser welding through laser welding, and then the wall thickness of the processed bulge is equal to the wall thickness of the thrust chamber through a build-up welding mode.
10. A spacecraft thrust chamber, characterized in that it is produced by a method for repairing a spacecraft thrust chamber jacket according to any one of claims 1 to 9.
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| 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 |
| CN117754101B (en) * | 2023-12-21 | 2024-07-23 | 河北志成束源科技有限公司 | Un-welded repair tool and method for Laval nozzle of gas pressure diffusion welding |
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| WO2008010748A1 (en) * | 2006-07-19 | 2008-01-24 | Volvo Aero Corporation | Method for manufacturing a wall structure |
| CN107430894A (en) * | 2015-03-24 | 2017-12-01 | 阿海珐核能公司 | Nuclear reactor cover inner surface restorative procedure, the nuclear reactor cover obtained by this method |
| CN106113871A (en) * | 2016-06-22 | 2016-11-16 | 江苏华尚汽车玻璃工业有限公司 | A kind of automobile sandwich-glass bubble eliminates technique |
| 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 |
| CN109834396A (en) * | 2019-03-04 | 2019-06-04 | 北京蓝箭空间科技有限公司 | Composite tooling and thrust chamber welding procedure for thrust chamber welding |
| 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 |
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