CN115647671A - Spacecraft cabin circumferential weld welding cooling device and method - Google Patents
Spacecraft cabin circumferential weld welding cooling device and method Download PDFInfo
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- CN115647671A CN115647671A CN202211352266.3A CN202211352266A CN115647671A CN 115647671 A CN115647671 A CN 115647671A CN 202211352266 A CN202211352266 A CN 202211352266A CN 115647671 A CN115647671 A CN 115647671A
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Abstract
A spacecraft cabin circumferential weld welding cooling device and a spacecraft cabin circumferential weld welding cooling method comprise the following steps: a cooling shell (1) and a sealing ring (4); wherein, cooling shell (1) is the ring shape casing, and cooling shell (1) casing internal diameter is greater than spacecraft cabin column section (5) external diameter, and cooling shell (1) suit is in cabin column section (5) outside, and the coaxial fixed placement of the two, has the clearance between the two. A sealing ring (4) is arranged on the upper side and the lower side in a gap between the cooling shell (1) and the cabin column section (5); the inner wall of the cooling shell (1), the outer wall of the cabin column section (5) and the upper and lower side sealing rings (4) form a space for containing a cooling medium, and a liquid injection port (2) and a liquid outlet (3) are arranged on the cooling shell (1) corresponding to the space region. The method can effectively control the temperature of the wall plate area adjacent to the welding seam in the cabin body column section girth welding process, and greatly reduce or avoid the welding deformation of the wall plate area.
Description
Technical Field
The invention belongs to the technical field of spacecraft manufacturing, and particularly relates to a spacecraft cabin circumferential weld welding cooling device and method.
Background
At present, the diameter size of a large-scale spacecraft cabin structure can reach 5m level, a plurality of arc plates are adopted to be spliced and welded into a cylindrical section through longitudinal seams and then are metallurgically connected through girth welding, and finally, a whole cabin structure is formed. Because the spacecraft cabin body structure adopts a lightweight design to improve the bearing ratio, the cabin body wall plate has thin thickness and weak rigidity.
As shown in FIG. 1, the weld craters are all thickened due to the low joint coefficient of the weld. When the circular seam welding of the cylindrical section of the cabin body is carried out, the welding heat input is large, so that the wallboard area adjacent to the welding opening is easy to generate local deformation under the influence of welding heat, and the cabin body shape and position precision after the welding is finished can not meet the design requirement.
Disclosure of Invention
The invention provides a spacecraft cabin circumferential weld welding cooling device and method, which are used for solving the problem that when a cylindrical section circumferential weld of a large spacecraft cabin structure is welded, a wall plate area close to a welding opening is locally deformed under the influence of welding heat due to large welding heat input, and further the cabin shape and position accuracy cannot meet the design requirement after welding is finished.
The invention provides a spacecraft cabin circumferential weld welding cooling device, which comprises: the cooling shell, the sealing ring, wherein,
the cooling shell is a circular ring-shaped shell, the inner diameter of the shell of the cooling shell is larger than the outer diameter of the cylindrical section of the spacecraft cabin, the cooling shell is sleeved outside the cylindrical section of the spacecraft cabin and is coaxially and fixedly arranged, and a gap is formed between the cooling shell and the cylindrical section;
sealing rings are arranged on the upper side and the lower side in a gap between the cooling shell and the cabin column section;
the inner wall of the cooling shell, the outer wall of the column section of the cabin body and the upper and lower side sealing rings form a space for containing a cooling medium, and a liquid injection port and a liquid outlet are arranged on the cooling shell corresponding to the space region.
Further, the size of the gap is determined according to the required volume of the cooling medium.
Further, have refrigerator, flow valve and pipeline between the outside notes liquid mouth and the liquid outlet of cooling shell and constitute the sealed circulating device of coolant, the liquid outlet passes through the inlet liquid end of pipe connection refrigerator, and the play liquid end of refrigerator passes through the pipeline and connects via the flow valve notes liquid mouth.
Further, the refrigerator regulates and controls the temperature of the cooling medium to keep the temperature of the cooling medium within the set temperature range.
Further, the cooling medium is water.
Further, the flow valve regulates and controls the flow rate of the cooling medium, and the flow rate is maintained in the set flow rate interval.
Furthermore, valves are respectively installed on the liquid injection port and the liquid outlet, the valves are provided with temperature sensors, the temperature sensors sense the temperature of the cooling medium, and when the temperature of the cooling medium at the liquid injection port or the liquid outlet is higher than the upper limit of the set temperature interval, the valves are opened; and when the temperature of the cooling medium at the liquid injection port or the liquid outlet is lower than the lower limit of the set temperature interval, closing the valve.
Furthermore, the material of the sealing ring is a polymer material with compressibility, and the cross section of the sealing ring is circular, rectangular or trapezoidal.
A spacecraft cabin circumferential weld welding cooling method comprises the following steps: a refrigerating machine, a flow valve and a pipeline are arranged between a liquid injection port and a liquid outlet outside the cooling shell to form a cooling medium sealed circulation device, the liquid outlet is connected with a liquid inlet end of the refrigerating machine through the pipeline, and a liquid outlet end of the refrigerating machine is connected with the liquid injection port through the flow valve through the pipeline;
regulating and controlling the temperature of the cooling medium by using the refrigerating machine to keep the temperature of the cooling medium in a set temperature interval;
the flow valve is utilized to regulate and control the flow rate of the cooling medium, the flow rate is kept in the set flow rate interval,
valves are respectively arranged at the liquid injection port and the liquid outlet, the valves are provided with temperature sensors, the temperature sensors sense the temperature of the cooling medium, and when the temperature of the cooling medium at the liquid injection port or the liquid outlet is higher than the upper limit of the set temperature interval, the valves are opened; and when the temperature of the cooling medium at the liquid injection port or the liquid outlet is lower than the lower limit of the set temperature range, the valve is closed.
By the cooling device and the cooling method, the temperature of the wall plate area adjacent to the weld joint in the cabin column section circular seam welding process can be effectively controlled, and the welding deformation of the wall plate area is greatly reduced or avoided.
Drawings
FIG. 1 is a schematic structural diagram of a large spacecraft cabin column section;
FIG. 2 is a schematic structural view of a spacecraft cabin circumferential weld welding cooling device of the invention;
FIG. 3 is an external refrigeration system of the spacecraft cabin circumferential weld cooling device of the present invention;
fig. 4 is a schematic view of the structure and installation of the sealing ring of the present invention.
Detailed Description
The structure of the cooling device for circumferential seam welding of the large spacecraft cabin body provided by the invention is shown in figure 2 and comprises a cooling shell 1, a sealing ring 4 and a cabin body column section 5. Wherein cooling shell 1 is ring shape shell structure, and it has liquid filling mouth 2 and liquid outlet 3 to design on it, and liquid filling mouth 2 and liquid outlet 3 department are provided with valve 9, include temperature sensor in valve 9, and valve 9 can be opened or close according to the temperature that temperature sensor detected. The using method comprises the steps of firstly placing the cabin body column section 5 on a platform, sleeving the cooling shell 1 outside the cabin body column section 5, placing the liquid injection port 2 at the lower part and the liquid outlet port 3 at the upper part, adjusting the cooling shell 1 to a proper height, and supporting and positioning the cooling shell 1 at the lower part. The sealing ring 4 is inserted from the top into the gap between the top of the cabin column section 5 and the cooling shell 1. Subsequently, the assembly consisting of the cooling jacket 1, the cabin column section 5 and the sealing ring 4 is turned upside down and rotated on the platform. In the manner described above, a further sealing ring 4 is inserted into the lower gap of the component consisting of the cooling jacket 1, the cabin column section 5 and the sealing ring 4. To this end, the cooling jacket 1, the cabin column section 5 and the 2 sealing rings 4 form a complete cooling assembly. The material of the cooling shell 1 and the cabin column section 5 is metal, preferably light metal or alloy, such as aluminum or aluminum alloy.
And then, assembling the cooling assembly and another piece to be welded by girth welding, and after the assembly is completed, injecting a cooling medium, which can be water or other refrigerants, into the cavity between the cooling shell 1 and the cabin column section 5 of the assembly from the liquid injection port 2 until the cavity between the cooling shell 1 and the cabin column section 5 is completely filled with the water or other refrigerants.
At the moment, girth welding operation between cabin body column sections can be carried out, water or cooling medium in a cavity between the cooling shell 1 and the cabin body column section 5 absorbs a large amount of heat generated at a weld crater in the welding process, the temperature of the thin-wall plate area near the weld crater area in the welding process can be effectively ensured to be in a proper interval, and welding deformation is reduced or even avoided.
As shown in fig. 3, a refrigerating machine 10, a flow valve 11 and a pipeline are arranged between a liquid injection port 2 and a liquid outlet 3 outside a cooling housing 1 to form a sealed circulation device for cooling medium, the liquid outlet 3 is connected with a liquid inlet end of the refrigerating machine 10 through a pipeline, and a liquid outlet end of the refrigerating machine 10 is connected with the liquid injection port 2 through the flow valve 11 through a pipeline.
The cooling device provided by the invention can form a set of cooling device with a coolant real-time cooling function with an external refrigerator 10 and a flow valve 11 through the liquid injection port 2 and the liquid outlet 3 during welding, and the temperature of a welding process wallboard area can be further regulated and controlled by controlling the flow of the flow valve 11 and the temperature of the refrigerator 10, so that the temperature of a cooling medium is kept in a set temperature interval.
The clearance between the cabin column section 5 and the cooling shell 1 and the structural size of the sealing ring 4 have a certain constraint relation, the section of the sealing ring 4 can be any geometric shape, and fig. 4 is an example. Wherein the outer diameter of the cabin column section 5 is 2828mm, and the inner diameter of the cooling shell 1 is 2853mm. The clearance e between the cooling shell 1 and the cabin body column section 5 is 12.5mm, the section of the sealing ring 4 is in a right trapezoid shape, and the sizes of the lower bottom a, the height b and the upper bottom c are respectively 15.6mm, 10mm and 12.5mm. After the sealing ring 4 is arranged between the cooling shell 1 and the cabin body column section 5, the sealing ring 4 is compressed, the upper compression rate is 20%, and the width d of the sealing ring 4 is the same as the size of the gap e. In this state, the sealing ring 4 has sealing capability due to compression, and the self weight of the cooling device and the refrigerant added into the cooling device (at this time, the refrigerant) can be resisted through finite element calculation sealing stress, so that reliable sealing of the internal cooling medium can be realized when no auxiliary support is arranged outside.
The invention also provides a spacecraft cabin circumferential weld welding cooling method, which comprises the following steps: the temperature of the cooling medium is controlled by the refrigerator 10 so that the temperature of the cooling medium is maintained within the set temperature range. The flow valve 11 regulates and controls the flow rate of the cooling medium, and the flow rate needs to be maintained in a set flow rate interval.
The liquid injection port 2 and the liquid outlet 3 are respectively provided with a valve 9, the valve 9 is provided with a temperature sensor, the temperature sensor senses the temperature of the cooling medium, and when the temperature of the cooling medium at the liquid injection port 2 or the liquid outlet 3 is higher than the upper limit of the set temperature interval, the valve 9 is opened; when the temperature of the cooling medium at the liquid injection port 2 or the liquid outlet 3 is lower than the lower limit of the set temperature interval, the valve 9 is closed.
Examples
Considering a certain safety factor, the finite element method is adopted to calculate the sealing capacity when the compression ratio of the sealing ring is 15%, and the result shows that the sealable pressure when the compression ratio is 15% is 2.5MPa.
The pressure after water injection between the cooling enclosure and the cabin column sections was calculated. The height of the cabin column section is 1370mm, and the water injection height is higher than the cabin column section. When the height of water injection is 1500mm, the lower pressure is 0.015MPa, is far lower than the sealing capacity of the sealing ring, and the sealing of cooling water can be effectively realized.
The friction force generated by the seal ring was calculated in consideration of the deadweight of the water and the cooling case. In order to ensure the calculation margin, the compression rate is 15%, and the effective sealing height of the sealing ring is 5mm. The friction coefficient of the rubber and the aluminum is 0.1-0.6, and the lower limit value is 0.1. At this time, the generated frictional force was 11kN. The weight of the injected water is 360kg, the weight of the cooling shell is 72kg, the total weight is 432kg, the gravity is 4.3kN, and is less than the friction force. Therefore, the sealing force of the sealing ring in the water injection state can ensure the stability of the cooling shell in the water injection state.
Those matters not described in detail in the present specification are within the common general knowledge of those skilled in the art.
Claims (9)
1. The utility model provides a spacecraft cabin circumferential weld welds cooling device which characterized in that includes: the cooling shell (1) and the sealing ring (4); wherein the content of the first and second substances,
the cooling shell (1) is a circular ring-shaped shell, the inner diameter of the shell of the cooling shell (1) is larger than the outer diameter of the spacecraft cabin column section (5), the cooling shell (1) is sleeved on the outer side of the cabin column section (5) and is coaxially and fixedly arranged, and a gap is formed between the cooling shell and the cabin column section;
a sealing ring (4) is arranged on the upper side and the lower side in a gap between the cooling shell (1) and the cabin body column section (5);
the inner wall of the cooling shell (1), the outer wall of the cabin column section (5) and the upper and lower side sealing rings (4) form a space for containing a cooling medium, and a liquid injection port (2) and a liquid outlet (3) are arranged on the cooling shell (1) corresponding to the space region.
2. The spacecraft tank girth weld cooling device of claim 1, wherein the size of the gap is determined according to the volume of cooling medium required.
3. The spacecraft cabin circumferential weld cooling device of claim 1, characterized in that a refrigerating machine (10), a flow valve (11) and a pipeline are arranged between a liquid injection port (2) and a liquid outlet (3) outside the cooling shell (1) to form a cooling medium sealed circulation device, the liquid outlet (3) is connected with a liquid inlet end of the refrigerating machine (10) through a pipeline, and a liquid outlet end of the refrigerating machine (10) is connected with the liquid injection port (2) through the flow valve (11) through a pipeline.
4. The spacecraft cabin circumferential weld cooling arrangement of claim 1, characterized in that the refrigerator (10) regulates the temperature of the cooling medium such that the temperature of the cooling medium is maintained within a set temperature interval.
5. The spacecraft tank girth weld cooling device of claim 1, wherein the cooling medium is water.
6. Spacecraft cabin circumferential weld cooling arrangement according to claim 1, characterized in that the flow valves (11) regulate the cooling medium flow rate, which is maintained within the set flow rate interval.
7. The spacecraft cabin circumferential weld cooling device of claim 1, characterized in that the liquid injection port (2) and the liquid outlet (3) are respectively provided with a valve (9), the valve (9) is provided with a temperature sensor, the temperature sensor senses the temperature of a cooling medium, and when the temperature of the cooling medium at the liquid injection port (2) or the liquid outlet (3) is higher than the upper limit of a set temperature interval, the valve (9) is opened; and when the temperature of the cooling medium at the liquid injection port (2) or the liquid outlet (3) is lower than the lower limit of the set temperature interval, the valve (9) is closed.
8. The spacecraft cabin circumferential weld welding cooling device of claim 1, characterized in that the material of the sealing ring (4) is a compressible polymer material, and the cross-sectional shape of the sealing ring (4) is circular, rectangular or trapezoidal.
9. A spacecraft cabin circumferential weld welding cooling method is characterized by comprising the following steps: a refrigerating machine (10), a flow valve (11) and a pipeline are arranged between a liquid injection port (2) and a liquid outlet port (3) outside a cooling shell (1) of the device according to claim 1 to form a cooling medium sealed circulation device, the liquid outlet port (3) is connected with the liquid inlet end of the refrigerating machine (10) through a pipeline, and the liquid outlet end of the refrigerating machine (10) is connected with the liquid injection port (2) through a pipeline through the flow valve;
the temperature of the cooling medium is regulated and controlled by the refrigerating machine (10) so that the temperature of the cooling medium is kept in the set temperature interval;
the flow rate of the cooling medium is regulated and controlled by the flow valve (11), the flow rate is kept in a set flow rate interval,
valves (9) are respectively installed on the liquid injection port (2) and the liquid outlet (3), the valves (9) are provided with temperature sensors, the temperature sensors sense the temperature of the cooling medium, and when the temperature of the cooling medium at the liquid injection port (2) or the liquid outlet (3) is higher than the upper limit of the set temperature interval, the valves (9) are opened; and when the temperature of the cooling medium at the liquid injection port (2) or the liquid outlet (3) is lower than the lower limit of the set temperature interval, the valve (9) is closed.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211352266.3A CN115647671A (en) | 2022-10-31 | 2022-10-31 | Spacecraft cabin circumferential weld welding cooling device and method |
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| CN202211352266.3A CN115647671A (en) | 2022-10-31 | 2022-10-31 | Spacecraft cabin circumferential weld welding cooling device and method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117066812A (en) * | 2023-10-17 | 2023-11-17 | 南通日旭重工科技有限公司 | Metal member welding device and welding process |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117066812A (en) * | 2023-10-17 | 2023-11-17 | 南通日旭重工科技有限公司 | Metal member welding device and welding process |
| CN117066812B (en) * | 2023-10-17 | 2024-03-05 | 南通日旭重工科技有限公司 | Metal member welding device and welding process |
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