CN212169470U - Spot welding tool for pressure reducing valve diaphragm assembly of rocket engine - Google Patents
Spot welding tool for pressure reducing valve diaphragm assembly of rocket engine Download PDFInfo
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- CN212169470U CN212169470U CN202020874351.6U CN202020874351U CN212169470U CN 212169470 U CN212169470 U CN 212169470U CN 202020874351 U CN202020874351 U CN 202020874351U CN 212169470 U CN212169470 U CN 212169470U
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- upper cover
- insulating base
- spot welding
- hole
- pressure reducing
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Abstract
The utility model discloses a spot welding tool for a rocket engine pressure reducing valve diaphragm assembly, which comprises an upper cover, an insulating base and an annular copper pad, wherein the annular copper pad is embedded into a through hole on the insulating base, the insulating base is provided with a groove, the bottom surface of the groove is higher than the annular copper pad, a plate frame is arranged on the annular copper pad and is fixed in the through hole, the upper part of the disk is provided with a first bulge part which is used for welding with the membrane, the first bulge part is positioned in the groove, the membrane is placed on the first bulge part and limited by the side wall of the groove, the upper cover is buckled on the insulating base, the upper cover is provided with an insertion hole for inserting the electrode, the inner part of the upper cover is provided with a second bulge part, when the upper cover is buckled on the insulation base, the second bulge compresses the diaphragm on the first bulge, a plurality of scribed lines which are uniformly distributed are arranged on the circumferential side wall of the insulation base, and one scribed line is arranged on the circumferential side wall of the upper cover and is matched with the plurality of scribed lines of the insulation base for use. The method can avoid poor coaxiality of the membrane and the disc, scratch on the surface of the membrane and overburning of welding spots.
Description
Technical Field
The utility model relates to a rocket engine relief pressure valve diaphragm subassembly spot welding technical field especially relates to a rocket engine relief pressure valve diaphragm subassembly's spot welding frock.
Background
The diaphragm assembly is a pressure sensitive element in the gas pressure reducer of the liquid rocket engine, and the pressure of the decompressed gas acts on the diaphragm and is balanced with the acting force of the reference spring, so that the pressure at the outlet of the pressure reducer is stabilized at an adjusting value. When the inlet pressure of the pressure reducer is reduced or the downstream flow fluctuation causes the outlet pressure of the pressure reducer to change, the diaphragm assembly can perform adaptive adjustment on the opening of the valve core after sensing the change, and the outlet pressure is kept stable at an adjusted value.
The diaphragm assembly is formed by spot welding of diaphragm and disk assembly. The coaxiality of the spot-welded diaphragm and the disc is not more than 0.2, welding points are uniformly distributed on the diaphragm along the circumference, overburning and splashing are not allowed, and the diaphragm is not allowed to be scratched. However, at present, the problems of poor coaxiality of the diaphragm and the disc, scratch on the surface of the diaphragm, over-burning of welding points and the like exist after spot welding of common diaphragm assembly products.
Therefore, how to provide a spot welding tool for a rocket engine pressure reducing valve diaphragm assembly to avoid poor coaxiality of the diaphragm and the disc, avoid surface scratching of the diaphragm and avoid overburning of welding spots is a technical problem to be solved by technical personnel in the field at present.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model aims at providing a spot welding frock of rocket engine relief valve diaphragm subassembly to avoid diaphragm and the dish axiality not good, avoid diaphragm surface fish tail and avoid the solder joint to burn excessively.
In order to achieve the above object, the utility model provides a following technical scheme:
a spot welding tool for a pressure reducing valve diaphragm assembly of a rocket engine comprises an upper cover, an insulating base and an annular copper pad, wherein,
the insulating base is provided with a through hole, the annular copper pad is embedded into the through hole,
the insulating base is provided with a groove which is coaxial with the through hole and the inner diameter hole of the annular copper pad, the bottom surface of the groove is higher than the annular copper pad,
the disk frame of the pressure reducing valve diaphragm assembly is arranged on the annular copper pad and fixed in the through hole, the upper part of the disk is provided with a first bulge part used for being welded with the diaphragm, the first bulge part is positioned in the groove,
the diaphragm is placed on the first bulge and limited by the side wall of the groove,
the upper cover is buckled on the insulating base, an inserting hole for inserting an electrode is formed in the upper cover, the axial direction of the inserting hole is parallel to the axial direction of the through hole,
the inner part of the upper cover is provided with a second bulge, when the upper cover is buckled on the insulating base, the second bulge presses the diaphragm on the first bulge,
the insulation base is characterized in that a plurality of scribed lines are uniformly distributed on the circumferential side wall of the insulation base, one scribed line is arranged on the circumferential side wall of the upper cover, and after one point is welded each time, the upper cover is rotated to enable the scribed lines on the upper cover to leave the scribed lines on the insulation base which are closed at present and to be closed with other scribed lines on the insulation base, so that the spot welding of a plurality of uniformly distributed welding spots on the diaphragm is completed.
Preferably, the upper cover, the insulating base and the annular copper pad are coaxially arranged.
Preferably, the insulating base is a teflon base.
Preferably, the bottom of the annular copper pad exceeds the bottom of the insulating base, and the bottom of the annular copper pad is used for being in contact butt joint with a table top of a spot welding machine.
Preferably, a threaded hole is formed in a circumferential side wall of the upper cover, and a bolt for fixing the upper cover and the insulating base is inserted into the threaded hole.
Preferably, the number of the scribed lines on the insulation base is even.
Preferably, the annular copper pad is in interference fit with the through hole.
Preferably, the diameter size of the through hole and the inner diameter size of the annular copper pad are in transition fit with the outer diameter size of the disc.
Preferably, the number of the scribed lines on the insulation base is the same as the number of the welding spots on the pressure reducing valve diaphragm assembly.
Preferably, the plurality of scribed lines on the insulation base and the scribed lines on the upper cover are axial scribed lines.
The utility model provides a spot welding tool for a rocket engine pressure reducing valve diaphragm assembly, which comprises an upper cover, an insulating base and an annular copper pad, wherein,
the insulating base is provided with a through hole, the annular copper pad is embedded into the through hole,
the insulating base is provided with a groove which is coaxial with the through hole and the inner diameter hole of the annular copper pad, the bottom surface of the groove is higher than the annular copper pad,
the disk frame of the pressure reducing valve diaphragm assembly is arranged on the annular copper pad and fixed in the through hole, the upper part of the disk is provided with a first bulge part used for being welded with the diaphragm, the first bulge part is positioned in the groove,
the diaphragm is placed on the first bulge and limited by the side wall of the groove,
the upper cover is buckled on the insulating base, an inserting hole for inserting an electrode is formed in the upper cover, the axial direction of the inserting hole is parallel to the axial direction of the through hole,
the inner part of the upper cover is provided with a second bulge, when the upper cover is buckled on the insulating base, the second bulge presses the diaphragm on the first bulge,
the insulation base is characterized in that a plurality of scribed lines are uniformly distributed on the circumferential side wall of the insulation base, one scribed line is arranged on the circumferential side wall of the upper cover, and after one point is welded each time, the upper cover is rotated to enable the scribed lines on the upper cover to leave the scribed lines on the insulation base which are closed at present and to be closed with other scribed lines on the insulation base, so that the spot welding of a plurality of uniformly distributed welding spots on the diaphragm is completed.
The utility model provides a spot welding frock of rocket engine relief pressure valve diaphragm subassembly, assemble spacing to diaphragm and dish through the frock, solve the not good problem of axiality after the two spot welding; the problem that welding spots are not uniformly distributed on the diaphragm is solved through the scribed lines on the tool; through the good copper base of electric conductivity on the frock, annular copper pad promptly, solve the dish and beat the problem that hinders easily in the spot welding process. Meanwhile, the assembly welding efficiency is improved, and the operation difficulty is reduced. Thereby realizing avoiding diaphragm and the dish axiality not good, avoiding diaphragm surface fish tail and avoiding the solder joint to burn excessively.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a spot welding tool for a rocket engine pressure reducing valve diaphragm assembly provided by an embodiment of the present invention;
fig. 2 is a schematic cross-sectional structural view of an upper cover according to an embodiment of the present invention;
fig. 3 is a schematic cross-sectional structural view of an annular copper pad according to an embodiment of the present invention;
fig. 4 is a schematic cross-sectional structural view of an insulation base according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a bolt provided in an embodiment of the present invention;
fig. 6 is a schematic structural view illustrating a disc being limited by an annular copper pad and an insulating base according to an embodiment of the present invention;
fig. 7 is a schematic structural view illustrating the upper cover pressing the membrane onto the disc according to the embodiment of the present invention;
fig. 8 is a schematic structural view of the bolt screwed in threaded hole provided by the embodiment of the present invention fixing the upper cover and the insulating base.
In the above FIGS. 1-8:
the diaphragm-type air-conditioner comprises an upper cover 1, a diaphragm 2, an insulating base 3, a disc 4, a bolt 5, an annular copper pad 6, an insertion hole 7, a second boss 8, a threaded hole 9, a groove 10, a through hole 11 and a first boss 12.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Please refer to fig. 1 to 8:
fig. 1 is a schematic structural diagram of a spot welding tool for a rocket engine pressure reducing valve diaphragm assembly provided by an embodiment of the present invention;
fig. 2 is a schematic cross-sectional structural view of an upper cover according to an embodiment of the present invention;
fig. 3 is a schematic cross-sectional structural view of an annular copper pad according to an embodiment of the present invention;
fig. 4 is a schematic cross-sectional structural view of an insulation base according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a bolt provided in an embodiment of the present invention;
fig. 6 is a schematic structural view illustrating a disc being limited by an annular copper pad and an insulating base according to an embodiment of the present invention;
fig. 7 is a schematic structural view illustrating the upper cover pressing the membrane onto the disc according to the embodiment of the present invention;
fig. 8 is a schematic structural view of the bolt screwed in threaded hole provided by the embodiment of the present invention fixing the upper cover and the insulating base.
The spot welding tool for the pressure reducing valve diaphragm assembly of the rocket engine provided by the embodiment of the utility model comprises an upper cover 1, an insulating base 3 and an annular copper pad 6, wherein,
the insulating base 3 is provided with a through hole 11, the annular copper pad 6 is embedded into the through hole 11,
the insulating base 3 is provided with a groove 10, the groove 10 is coaxially arranged with the through hole 11 and the inner diameter hole of the annular copper pad 6, the bottom surface of the groove 10 is higher than the annular copper pad 6,
the disk 4 of the pressure reducing valve diaphragm assembly is erected on the annular copper pad 6 and fixed in the through hole 11, the upper part of the disk 4 is provided with a first bulge 12 for welding with the diaphragm 2, the first bulge 12 is positioned in the groove 10, the diaphragm 2 is placed on the first bulge 12 and limited by the side wall of the groove 10,
the upper cover 1 is buckled on the insulating base 3, the upper cover 1 is provided with an inserting hole 7 for inserting an electrode, the axial direction of the inserting hole 7 is parallel to the axial direction of the through hole 11,
the inner part of the upper cover 1 is provided with a second bulge 8, when the upper cover 1 is buckled on the insulating base 3, the second bulge 8 presses the membrane 2 on the first bulge 12,
a plurality of scribed lines which are uniformly distributed are arranged on the circumferential side wall of the insulating base 3, one scribed line is arranged on the circumferential side wall of the upper cover 1, and after one point is welded each time, the upper cover 1 is rotated to enable the scribed lines on the upper cover 1 to leave the scribed lines on the insulating base 3 which are closed at present and to be closed with other scribed lines on the insulating base 3, so that spot welding of a plurality of uniformly distributed welding spots on the diaphragm 2 is completed.
The spot welding tool for the rocket engine pressure reducing valve diaphragm assembly provided by the embodiment of the utility model can be used for assembling and limiting the diaphragm 2 and the disc 4 through the tool, thereby solving the problem of poor coaxiality after spot welding of the diaphragm and the disc; the problem that welding spots are not uniformly distributed on the diaphragm 2 is solved through the scribed lines on the tool; through the good copper base of electric conductivity on the frock, annular copper pad 6 promptly, solve the problem that dish 4 was damaged easily in the spot welding process. Meanwhile, the assembly welding efficiency is improved, and the operation difficulty is reduced. Thereby realize avoiding diaphragm 2 and 4 not good axiality of dish, avoid diaphragm 2 surface fish tail and avoid the solder joint to burn excessively.
Specifically, the upper cover 1, the insulating base 3 and the annular copper pad 6 are coaxially arranged, so that the diaphragm 2 and the disc 4 can be assembled more conveniently and can be limited.
Specifically, the insulating base 3 is a teflon base, but the insulating base 3 may be made of other insulating materials.
In order to further optimize the above solution, the bottom of the annular copper pad 6 extends beyond the bottom of the insulating base 3, and the bottom of the annular copper pad 6 is used for contact butt joint with the table top of the spot welding machine. Specifically, the bottom surface of the annular copper pad 6 slightly protrudes out of the insulating base 3 and is in contact with the table top of the spot welding machine to conduct good electric conduction.
In order to further optimize the scheme, a threaded hole 9 is formed in the circumferential side wall of the upper cover 1, and a bolt 5 for fixing the upper cover 1 and the insulating base 3 is inserted into the threaded hole 9.
In order to further optimize the above solution, the number of the scribed lines on the insulating base 3 is even, so that the requirements of a plurality of different numbers of welding points can be met simultaneously.
In order to further optimize the scheme, the annular copper pad 6 and the through hole 11 are in interference fit and are inlaid into a whole.
In order to further optimize the solution, the diameter of the through hole 11 and the inner diameter of the annular copper pad 6 are in transition fit with the outer diameter of the disc 4. As will be apparent from the description of fig. 1, the outer wall of the prior art disc 4 is stepped, having a larger diameter disc retained in the through hole 11 and a smaller diameter disc retained in the inner diameter of the annular copper pad 6.
In order to further optimize the scheme, the number of the plurality of scribed lines on the insulating base 3 is the same as the number of the welding spots on the pressure reducing valve diaphragm assembly, so that the operation is more convenient, and the operation can be directly performed, or certainly, the number of the scribed lines can be different, for example, the number of the scribed lines in the insulating base and the number of the welding spots in the pressure reducing valve diaphragm assembly can be 40, and the number of the welding spots in the insulating base and the number of the welding spots in the pressure reducing valve diaphragm assembly are 20, i.e., after the scribed.
In order to further optimize the scheme, the plurality of scribed lines on the insulating base 3 and the scribed lines on the upper cover 1 are axial scribed lines, so that the use is more convenient.
The embodiment of the utility model provides a spot welding frock of rocket engine relief valve diaphragm subassembly, during the concrete implementation, including upper cover 1, insulating base 3, bolt 5, annular copper pad 6 etc..
The insulating base 3 and the annular copper pad 6 of polytetrafluoroethylene material are inlayed as an organic wholely, and annular copper pad 6 is used for spacing and fixed disk 4, and insulating base 3 is used for spacing diaphragm 2. The bottom surface of the annular copper pad 6 slightly protrudes out of the base 3 and is connected with the table top of the spot welding machine for good electric conduction.
The upper cover 1 serves to press the membrane 2 into close contact with the disc 4. The upper cover 1 is provided with an insertion hole 7 for inserting an electrode, the specific position is on the upper end surface of the upper cover 1, and the electrode of the spot welding machine penetrates through the hole and then contacts with the diaphragm 2 for spot welding.
The hole on the excircle lateral wall of upper cover 1 is screw hole 9, and bolt 5 is screwed into tightly with insulating base 3 top after this hole, ensures the state that upper cover 1 compresses tightly diaphragm 2.
There is a groove on the excircle lateral wall of upper cover 1, has a plurality of grooves of equipartition on the excircle lateral wall of insulator foot 3, loosens bolt 5 after every spot welding is a little, and rotatory upper cover 1 aligns the next groove on insulator foot 3, then spot welding is carried out again to fixing bolt 5, can accomplish the spot welding of a plurality of equipartition solder joint on diaphragm 2 in proper order.
The spot welding tool for the pressure reducing valve diaphragm assembly of the rocket engine provided by the embodiment of the utility model has the advantages that the diaphragm 1, the diaphragm 2 and the disc 4 are strictly limited, thereby being beneficial to ensuring the coaxiality of the two; 2. the uniformity of the distribution of the spot welding points is ensured by a method of rotating the upper cover 1 to align the scribed lines in sequence; 3. the annular copper pad 6 is in close contact with the disc 4, so that good electric conduction is ensured in the spot welding process, and damage is not easy to occur; 4. the assembly operation is simplified, the product processing consistency is good, and the production efficiency is high.
The embodiment of the utility model provides a spot welding frock of rocket engine relief valve diaphragm subassembly, during concrete implementation, the insulating base 3 and the annular copper pad 6 of polytetrafluoroethylene material compress tightly through interference fit and inlay as an organic wholely, and the diameter size of the through-hole on the insulating base 3 and the internal diameter size of annular copper pad 6 cooperate with the relevant external diameter size of dish 4 to the realization is to the spacing fixed of dish 4. A plurality of axial scribed lines which are uniformly distributed in the circumferential direction are carved on the outer circle side wall of the insulating base 3, and the number of the scribed lines can be consistent with the number of welding spots on the diaphragm assembly.
Wherein, the upper cover 1 is made of polytetrafluoroethylene, the aperture of an electrode insertion hole punched on the end surface of the upper cover is matched with the diameter of an electrode, and the position of the hole is matched with the position of a spot welding point on the diaphragm 2.
The upper cover 1 is buckled on the insulating base 3, namely the inner diameter of the upper cover 1 is matched with the outer diameter of the insulating base 3, and an axial scribed line is carved on the outer circular side wall of the upper cover 1 and is used for aligning with the scribed line on the insulating base 3. And a threaded hole is formed in the outer circle side wall of the upper cover 1 and used for screwing the bolt 5 in to fix the upper cover 1 and the insulating base 3.
When spot welding the membrane module, the disc 4 is fitted into the combination of the insulating base 3 and the annular copper pad 5, and the disc 4 is fitted to the end. The diaphragm 2 is then fitted onto the disk 4, being retained by the recess 10 of the insulating base 3. Then the upper cover 1 is assembled, the scribed lines of the upper cover are aligned with any scribed line on the excircle of the insulating base 3 and tightly press the disc 4, and the bolt 5 is screwed into the threaded hole 9 on the excircle side surface of the upper cover 1 until the upper cover is screwed and fixed with the insulating base 3.
Will the embodiment of the utility model provides a spot welding frock of rocket engine relief valve diaphragm subassembly is placed on the spot welder mesa, makes the electrode insert from the patchhole 7 of upper cover 1, spot welding diaphragm 2 in dish 4. After each spot welding point, the bolt 5 is loosened, the upper cover 1 is rotated to align with the next scribed line on the insulating base 3, the bolt 5 is fixed to perform spot welding after the diaphragm 2 is compressed, and spot welding of a plurality of uniformly distributed welding spots on the diaphragm 2 can be completed in sequence.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A spot welding tool for a pressure reducing valve diaphragm assembly of a rocket engine is characterized by comprising an upper cover, an insulating base and an annular copper pad, wherein,
the insulating base is provided with a through hole, the annular copper pad is embedded into the through hole,
the insulating base is provided with a groove which is coaxial with the through hole and the inner diameter hole of the annular copper pad, the bottom surface of the groove is higher than the annular copper pad,
the disk frame of the pressure reducing valve diaphragm assembly is arranged on the annular copper pad and fixed in the through hole, the upper part of the disk is provided with a first bulge part used for being welded with the diaphragm, the first bulge part is positioned in the groove,
the diaphragm is placed on the first bulge and limited by the side wall of the groove,
the upper cover is buckled on the insulating base, an inserting hole for inserting an electrode is formed in the upper cover, the axial direction of the inserting hole is parallel to the axial direction of the through hole,
the inner part of the upper cover is provided with a second bulge, when the upper cover is buckled on the insulating base, the second bulge presses the diaphragm on the first bulge,
the insulation base is characterized in that a plurality of scribed lines are uniformly distributed on the circumferential side wall of the insulation base, one scribed line is arranged on the circumferential side wall of the upper cover, and after one point is welded each time, the upper cover is rotated to enable the scribed lines on the upper cover to leave the scribed lines on the insulation base which are closed at present and to be closed with other scribed lines on the insulation base, so that the spot welding of a plurality of uniformly distributed welding spots on the diaphragm is completed.
2. A spot welding fixture for a rocket engine pressure reducing valve diaphragm assembly according to claim 1, wherein said upper cover, said insulating base and said annular copper gasket are coaxially disposed.
3. A spot welding fixture for a rocket engine pressure reducing valve diaphragm assembly according to claim 1, wherein said insulating base is a teflon base.
4. A spot welding tool for a rocket engine pressure reducing valve diaphragm assembly according to claim 1, wherein the bottom of the annular copper pad exceeds the bottom of the insulating base, and the bottom of the annular copper pad is used for being in contact butt joint with a table top of a spot welding machine.
5. A spot welding tool for a rocket engine pressure reducing valve diaphragm assembly according to claim 1, wherein a threaded hole is opened on a circumferential side wall of the upper cover, and a bolt for fixing the upper cover and the insulating base is inserted into the threaded hole.
6. A spot welding fixture for a rocket engine pressure reducing valve diaphragm assembly as recited in claim 1, wherein said insulating base has an even number of score lines.
7. A spot welding fixture for a rocket engine pressure reducing valve diaphragm assembly as recited in claim 1, wherein said annular copper pad is an interference fit with said through hole.
8. A spot welding fixture for a rocket engine pressure reducing valve diaphragm assembly according to claim 1, wherein the diameter size of said through hole and the inner diameter size of said annular copper pad are in transition fit with the outer diameter size of said disk.
9. A spot welding fixture for a rocket engine pressure reducing valve diaphragm assembly according to claim 1, wherein the number of the plurality of scribed lines on said insulating base is the same as the number of the welding spots on the pressure reducing valve diaphragm assembly.
10. A rocket engine pressure reducing valve diaphragm assembly spot welding fixture as recited in claim 1, wherein said insulation base has a plurality of score lines and said upper cover has score lines that are axial.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020874351.6U CN212169470U (en) | 2020-05-22 | 2020-05-22 | Spot welding tool for pressure reducing valve diaphragm assembly of rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020874351.6U CN212169470U (en) | 2020-05-22 | 2020-05-22 | Spot welding tool for pressure reducing valve diaphragm assembly of rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212169470U true CN212169470U (en) | 2020-12-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020874351.6U Active CN212169470U (en) | 2020-05-22 | 2020-05-22 | Spot welding tool for pressure reducing valve diaphragm assembly of rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212169470U (en) |
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2020
- 2020-05-22 CN CN202020874351.6U patent/CN212169470U/en active Active
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