CN111496365A - Solid rocket engine shell assembly welding tool with embedded end cover - Google Patents
Solid rocket engine shell assembly welding tool with embedded end cover Download PDFInfo
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- CN111496365A CN111496365A CN202010255347.6A CN202010255347A CN111496365A CN 111496365 A CN111496365 A CN 111496365A CN 202010255347 A CN202010255347 A CN 202010255347A CN 111496365 A CN111496365 A CN 111496365A
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- end cover
- embedded
- special
- rear end
- rocket engine
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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
- B23K15/00—Electron-beam welding or cutting
- B23K15/06—Electron-beam welding or cutting within a vacuum chamber
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Abstract
The invention discloses a solid rocket engine shell assembly welding tool with an embedded end cover, which comprises: the special-shaped nut comprises a nut, a gasket I, a front end cover, a gasket II, an embedded rear end cover, a special-shaped nut and a splicing mandrel component; the front end cover is fixed at one end of the splicing mandrel component through a nut and a gasket I; the embedded rear end cover is fixed at the other end of the splicing mandrel component through a special-shaped nut and a washer II; the front end cover and the embedded rear end cover are used for clamping and fixing a shell assembly of a workpiece, and the splicing mandrel assembly penetrates through the middle of the workpiece. The invention solves the problems that the shell with large length-diameter ratio is limited by the space of the electron beam welding vacuum chamber during assembly welding, the limit distance from an electron gun to a single side of the vacuum chamber conflicts with the position of a welding seam, clamping interference and the like, improves the interchangeability of the tool, effectively utilizes the space on the length of the electron beam welding vacuum chamber and successfully completes the assembly welding of the shell with large length-diameter ratio.
Description
Technical Field
The invention belongs to the technical field of butt welding of solid rocket engine shells, and particularly relates to a solid rocket engine shell assembling and welding tool with embedded end covers.
Background
The solid rocket engine shell is formed by assembling and welding a plurality of spinning shells and machined parts, so that welding is one of essential key processes in the production process of the solid rocket engine.
At present, the butt-joint circumferential weld of the shell is formed by welding through a vacuum electron beam, and the integral price of a vacuum electron beam welding machine is influenced by the size of a vacuum chamber of the vacuum electron beam welding machine, so that the specification of a workpiece which can be processed by the vacuum electron beam welding machine is limited to a certain extent. In the commonly-used shell assembling and welding tool, one end of a core rod is fixed on a three-jaw chuck, the other end of the core rod is fixed by adopting a tail top, and a shell assembly of a workpiece rotates along with the chuck during welding. The housing assembly, the extension of the mandrel, and the length of the tail cap cause the weldable length of the vacuum chamber to be often less than the length of the actual workpiece, so that the space utilization of the vacuum chamber is low. When the welding length of the shell reaches the critical value of the weldable length in the vacuum chamber, the welding of the welding seam at the extreme position cannot be completed.
Disclosure of Invention
The technical problem of the invention is solved: the defects of the prior art are overcome, the solid rocket engine shell assembling and welding tool with the embedded end cover is provided, and the problem that the length of the tool and the shell exceeds the limit of the weldable length of an electronic gun in a vacuum chamber when the existing shell assembling and welding tool is used for assembling and welding the shell is solved.
In order to solve the technical problem, the invention discloses a solid rocket engine shell assembly welding tool of an embedded end cover, which comprises: the special-shaped nut comprises a nut, a gasket I, a front end cover, a gasket II, an embedded rear end cover, a special-shaped nut and a splicing mandrel component;
the front end cover is fixed at one end of the splicing mandrel component through a nut and a gasket I;
the embedded rear end cover is fixed at the other end of the splicing mandrel component through a special-shaped nut and a washer II;
the front end cover and the embedded rear end cover are used for clamping and fixing a shell assembly of a workpiece, and the splicing mandrel assembly penetrates through the middle of the workpiece.
In the solid rocket engine shell assembling and welding tool with the embedded end cover, the embedded rear end cover can be embedded into a workpiece, so that the distance between the assembled workpiece and the tool in the axial length is shortened.
In the solid rocket engine shell assembling and welding tool of the embedded end cover,
the upper end of the special-shaped nut is of a hexagonal structure, and the lower end of the special-shaped nut is of a threaded structure;
a round hole I is formed in the center of the embedded rear end cover;
the thread structure at the lower end of the special-shaped nut is positioned in the round hole I and connected with the embedded rear end cover; the hexagonal structure of the upper end of the special-shaped nut is positioned outside the embedded rear end cover.
In the solid rocket engine shell assembling and welding tool of the embedded end cover,
the center of the embedded rear end cover is also provided with a round hole II; wherein the inner diameter of the round hole II is smaller than that of the round hole I;
the other end of the splicing mandrel component penetrates through the round hole II and is in threaded connection with a threaded structure at the lower end of the special-shaped nut.
In the solid rocket engine shell assembling and welding tool of the embedded end cover,
a round hole III is formed in the center of the hexagonal structure at the upper end of the special-shaped nut;
the size of round hole III and the size phase-match of tail top to guarantee that the tail top can go deep into in the special-shaped nut and push up the other end of concatenation mandrel subassembly.
In the solid rocket engine shell assembling and welding tool of the embedded end cover,
the outer diameter of the thread structure is matched with the inner diameter of the round hole I;
the external thread at the other end of the splicing mandrel component is matched with the screw hole of the threaded structure.
In the solid rocket engine shell assembling and welding tool of the embedded end cover,
the sizes of the front end cover and the embedded rear end cover are matched with the sizes of openings at two ends of a shell component of the workpiece;
the strength of the front end cover and the embedded rear end cover meets the following requirements: the strength of the 2A12 aluminum alloy is not lower than 390MPa-420 MPa.
In the solid rocket engine shell assembly welding frock of above-mentioned embedded end cover, the concatenation mandrel subassembly includes: the large shaft head, the cylindrical pin, the connecting pipe and the small shaft head;
the big shaft head, the connecting pipe and the small shaft head are sequentially connected through a cylindrical pin; wherein, the front end cover is fixed at one end of the big shaft head; the embedded rear end cover is fixed at one end of the small shaft head.
In the solid rocket engine shell assembling and welding tool of the embedded end cover,
the coaxiality of the big shaft head, the connecting pipe and the small shaft head meets the following requirements: the coaxiality is not more than 0.05 mm;
the spliced mandrel assembly can be adjusted according to the change of the length size of the workpiece, and the adjustable length range is as follows: 1-4 m.
In the solid rocket engine shell assembling and welding tool for the embedded end cover, the small shaft head is provided with a central hole for guiding when the tail top extends into the embedded rear end cover.
The invention has the following advantages:
the invention discloses a solid rocket engine shell assembly welding tool with an embedded end cover, which shortens the length of an assembled shell assembly as much as possible, has a compact space structure, does not influence the assembly precision and the assembly difficulty of the shell assembly welding, and further improves the utilization rate of an electron beam vacuum chamber.
Drawings
FIG. 1 is a schematic structural diagram of a solid rocket engine casing assembly welding tool with an embedded end cover in an embodiment of the invention;
FIG. 2 is a schematic structural diagram of an embedded rear end cap according to an embodiment of the invention;
FIG. 3 is a schematic structural diagram of a special-shaped nut according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a thin-wall shell to be welded according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the embodiments of the present invention will be described in detail with reference to the accompanying drawings.
Referring to fig. 1, in this embodiment, the solid rocket engine casing assembling and welding tooling for the embedded end cover includes: nut 2, packing ring I3, front end housing 4, packing ring II 8, embedded rear end cap 9, special-shaped nut 10 and concatenation mandrel subassembly. The front end cover 4 is fixed at one end of the splicing mandrel component through a nut 2 and a gasket I3; the embedded rear end cover 9 is fixed at the other end of the splicing mandrel component through a special-shaped nut 10 and a washer II 8; the front end cover 4 and the embedded rear end cover 9 are used for clamping and fixing a shell assembly of a workpiece, and the spliced core rod assembly penetrates through the middle of the workpiece.
Preferably, the embedded rear end cover 9 can be embedded into the workpiece, so that the distance between the assembled workpiece and the tool in the axial length direction is shortened.
In the present embodiment, as shown in fig. 2 and 3, the upper end of the special-shaped nut 10 is a hexagonal structure 1001, and the lower end is a threaded structure 1002; the center of the embedded rear end cover 9 is provided with a round hole I901. The threaded structure 1002 at the lower end of the special-shaped nut 10 is positioned in the circular hole I901 and is connected with the embedded rear end cover 9; the hexagonal structure 1001 at the upper end of the shaped nut 10 is located outside the embedded rear end cap 9.
Further, a round hole II 902 is also arranged in the center of the embedded rear end cover 9; the other end of the splicing mandrel component penetrates through the round hole II 902 and is in threaded connection with a threaded structure 1002 at the lower end of the special-shaped nut 10. Wherein, the internal diameter of round hole II 902 is less than the internal diameter of round hole I901.
Further, a round hole III 1003 is arranged in the center of the hexagonal structure 1001 at the upper end of the special-shaped nut 10. Wherein, the size of round hole III 1003 and the size phase-match of tail top to guarantee that the tail top can go deep into special-shaped nut 10 and push up the other end of concatenation mandrel subassembly.
It should be noted that the outer diameter of the threaded structure 1002 is matched with the inner diameter of the circular hole i 901; the external threads at the other end of the splice mandrel assembly mate with the threaded holes 1004 of the threaded structure 1002; the sizes of the front end cover 4 and the embedded rear end cover 9 are matched with the sizes of openings at two ends of a shell component of the workpiece; the specific dimensional parameters are not limiting in this embodiment.
The strength of the front end cover 4 and the embedded rear end cover 9 should meet the following requirements: the strength of the 2A12 aluminum alloy is not lower than 390MPa-420 MPa. The advantages are that: the end cover is ensured not to deform after being subjected to larger tightening force of the nut, can be repeatedly used, and still can ensure good precision.
In this embodiment, as shown in fig. 1, the splicing mandrel assembly may specifically include: the large shaft head 1, the cylindrical pin 5, the connecting pipe 6 and the small shaft head 7. Wherein, the big shaft head 1, the connecting pipe 6 and the small shaft head 7 are connected in sequence through the cylindrical pin 5; wherein, the front end cover 4 is fixed at one end of the big shaft head 1; the embedded rear end cover 9 is fixed at one end of the small shaft head 7.
Preferably, the stub shaft 7 is provided with a central hole for guiding the tail end when the tail end penetrates into the embedded rear end cover 9.
Preferably, the coaxiality of the big shaft head 1, the connecting pipe 6 and the small shaft head 7 should satisfy: the axiality is not more than 0.05mm, can effectively guarantee housing assembly's assembly precision, reduces the unfitness of butt joint.
Preferably, the adjustable length range of the splicing mandrel assembly is as follows: 1-4 m, and can be suitable for assembly welding of shells of workpieces with different length requirements.
In conclusion, the vacuum electron beam welding vacuum chamber platform adopts a clamping mode of clamping one top, the three-jaw chuck clamps one end of the spliced mandrel component, and the other end of the spliced mandrel component adopts a tail top to be tightly propped. The three-jaw chuck is a rotary motion mechanism, a workpiece is driven to rotate during welding, and the three-jaw chuck can only be clamped on the splicing mandrel component and cannot be changed; the tail top is propped against the other end of the splicing mandrel component, the splicing mandrel component can extend out of the workpiece for a certain distance to be used as a space for the end cover and the nut, therefore, a distance reserved for the tool exists between the tail top and the workpiece, in order to enable the space structure of the tool to be more compact, the embedded rear end cover and the special-shaped nut are adopted for connection and fixation, the embedded rear end cover is placed at one end of the workpiece, the other end of the splicing mandrel component penetrates through the round hole II, the length of the splicing mandrel component is shorter than that of the original splicing mandrel component, and therefore the splicing mandrel component is reserved between the inside of the workpiece and the embedded rear end cover, according to the opening range of the workpiece, no space for screwing the nut exists in the embedded rear end cover, the splicing mandrel component with the nut section is positioned in the embedded rear end cover, therefore, the threaded part and the tightening part of the nut must be dislocated, and the design of the special-shaped nut meets the requirement. One end of the special-shaped nut with a thread part (a thread structure 1002) extends into the workpiece and the interior of the embedded rear end cover to be connected with the splicing mandrel component, and the other end of the special-shaped nut with a tightening part (a hexagon structure 1001) is left outside the embedded rear end cover. A round hole III is formed in the center of a hexagonal structure at the upper end of the special-shaped nut, and the size of the round hole III is matched with that of the tail top, so that the tail top can be guaranteed to penetrate into the special-shaped nut and be jacked to the other end of the splicing mandrel component; in addition, a center hole for guiding is formed in the small shaft head of the splicing mandrel component, so that the tail top can be aligned with the small shaft head of the splicing mandrel component in the special-shaped nut, the space is effectively utilized, and the conflict between the shell assembly welding tool and the space of the vacuum chamber for vacuum electron beam welding is successfully solved.
As shown in figure 4, the extreme position from the electron gun to the other end in a vacuum chamber for vacuum electron beam welding of a certain type is 3400mm, the final assembly welding state of a workpiece of a certain type is 3129.5mm in the length of a shell, the distance from the first welding seam to the boundary of the shell at one end of the three-jaw chuck is 106mm, namely, the distance from the first welding seam to the other end is 3023.5mm, and the distance from the boundary of a tail top base to the apex is 380 mm. Thus. When the tail top is in the extreme position, the total length from the tail top end to the first welding seam position is 3403.5mm, even if no tool is arranged, the total length exceeds the extreme position of the electronic gun for welding, the embedded rear end cover and the special-shaped nut are adopted, the tail top tip can stretch into a workpiece, therefore, the technical problem that the workpiece cannot be machined due to the limitation of the space distance is successfully solved, and the space utilization rate of a vacuum chamber is effectively improved.
Further, as shown in fig. 4, during assembly, the front-section shell assembly, the spinning cylinder and the rear end enclosure are butted on an assembly table, a hoop is adopted to fix the butted position in advance, the spliced mandrel assembly penetrates through the inside of the shell, two ends of the spliced mandrel assembly are sleeved with end covers (a front end cover 4 and an embedded rear end cover 9), the spliced mandrel assembly is clamped and fixed through a nut 2 and a special-shaped nut 10 respectively after being sleeved, the hoop to be welded is dismounted, and the assembly of the shell assembly is completed. The assembled shell assembly is hoisted to a vacuum electron beam welding working platform, one end of the large shaft head is fixed by a three-jaw chuck, one end with an embedded rear end cover is fixed by pushing the tail against the central hole of the core rod, and the tail top tip penetrates through the special-shaped nut and extends into a workpiece, so that the space structure is more compact, and the space occupied by the tool is greatly reduced.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Those skilled in the art will appreciate that the details of the invention not described in detail in this specification are well within the skill of those in the art.
Claims (10)
1. The utility model provides a solid rocket engine casing assembly welding frock of embedded end cover which characterized in that includes: the special-shaped nut comprises a nut (2), a gasket I (3), a front end cover (4), a gasket II (8), an embedded rear end cover (9), a special-shaped nut (10) and a splicing mandrel component;
the front end cover (4) is fixed at one end of the splicing mandrel component through a nut (2) and a gasket I (3);
the embedded rear end cover (9) is fixed at the other end of the splicing mandrel component through a special-shaped nut (10) and a gasket II (8);
the front end cover (4) and the embedded rear end cover (9) are used for clamping and fixing a shell assembly of a workpiece, and the spliced core rod assembly penetrates through the middle of the workpiece.
2. The solid rocket engine shell assembling and welding tool with embedded end covers according to claim 1, wherein the embedded rear end cover (9) can be embedded into a workpiece, so that the distance between the assembled workpiece and the tool in the axial length is shortened.
3. The solid rocket engine casing assembly welding tooling of embedded end covers of claim 1,
the upper end of the special-shaped nut (10) is of a hexagonal structure (1001), and the lower end of the special-shaped nut is of a threaded structure (1002);
a round hole I (901) is formed in the center of the embedded rear end cover (9);
the thread structure (1002) at the lower end of the special-shaped nut (10) is positioned in the round hole I (901) and is connected with the embedded rear end cover (9); the hexagonal structure (1001) at the upper end of the special-shaped nut (10) is positioned outside the embedded rear end cover (9).
4. The solid rocket engine casing assembly welding tooling of embedded end covers of claim 3,
the center of the embedded rear end cover (9) is also provided with a round hole II (902); the inner diameter of the round hole II (902) is smaller than that of the round hole I (901);
the other end of the splicing mandrel component penetrates through the round hole II (902) and is in threaded connection with a threaded structure (1002) at the lower end of the special-shaped nut (10).
5. The solid rocket engine casing assembly welding tooling of embedded end covers of claim 4,
a round hole III (1003) is formed in the center of a hexagonal structure (1001) at the upper end of the special-shaped nut (10);
the size of round hole III (1003) and the size phase-match of tail top to guarantee that the tail top can go deep into special-shaped nut (10) and push up the other end of concatenation mandrel subassembly.
6. The solid rocket engine casing assembly welding tooling of embedded end covers of claim 4,
the outer diameter of the threaded structure (1002) is matched with the inner diameter of the round hole I (901);
the external thread at the other end of the splicing mandrel component is matched with the screw hole (1004) of the thread structure (1002).
7. The solid rocket engine shell assembling and welding tool for the embedded end covers according to any one of claims 1 to 6,
the sizes of the front end cover (4) and the embedded rear end cover (9) are matched with the sizes of openings at two ends of a shell component of the workpiece;
the strength of the front end cover (4) and the embedded rear end cover (9) meets the following requirements: the strength of the 2A12 aluminum alloy is not lower than 390MPa-420 MPa.
8. The solid rocket engine casing assembly welding tooling of embedded end covers of claim 1, wherein the spliced mandrel assembly comprises: the device comprises a big shaft head (1), a cylindrical pin (5), a connecting pipe (6) and a small shaft head (7);
the big shaft head (1), the connecting pipe (6) and the small shaft head (7) are sequentially connected through a cylindrical pin (5); wherein, the front end cover (4) is fixed at one end of the big shaft head (1); an embedded rear end cover (9) is fixed at one end of the small shaft head (7).
9. The solid rocket engine casing assembly welding tooling of embedded end covers of claim 8,
the coaxiality of the big shaft head (1), the connecting pipe (6) and the small shaft head (7) meets the following requirements: the coaxiality is not more than 0.05 mm;
the spliced mandrel assembly can be adjusted according to the change of the length size of the workpiece, and the adjustable length range is as follows: 1-4 m.
10. The solid rocket engine casing assembly welding tool of embedded end cover according to claim 8, characterized in that the small shaft head (7) is provided with a central hole for guiding when the tail top penetrates into the embedded rear end cover (9).
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| CN202010255347.6A CN111496365B (en) | 2020-04-02 | 2020-04-02 | Solid rocket engine shell assembly welding tool with embedded end cover |
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| CN202010255347.6A CN111496365B (en) | 2020-04-02 | 2020-04-02 | Solid rocket engine shell assembly welding tool with embedded end cover |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112355426A (en) * | 2020-10-28 | 2021-02-12 | 中国航发贵州黎阳航空动力有限公司 | Protective device for nuts with anodized layers in flame brazing process |
| CN114871557A (en) * | 2022-06-21 | 2022-08-09 | 南京晨光集团有限责任公司 | Vacuum electron beam manufacturing method for spacecraft thin-wall cylindrical storage tank |
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| CN114871557A (en) * | 2022-06-21 | 2022-08-09 | 南京晨光集团有限责任公司 | Vacuum electron beam manufacturing method for spacecraft thin-wall cylindrical storage tank |
| CN114871557B (en) * | 2022-06-21 | 2024-05-07 | 南京晨光集团有限责任公司 | Vacuum electron beam manufacturing method for spacecraft thin-wall cylindrical storage tank |
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| CN111496365B (en) | 2022-03-04 |
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