Spacecraft cabin circumferential seam welding cooling device and method

Abstract

A spacecraft cabin girth welding cooling device and method, comprising: a cooling shell (1) and a sealing ring (4); wherein the cooling shell (1) is a circular ring shell, the inner diameter of the cooling shell (1) shell is larger than the outer diameter of the spacecraft cabin column section (5), the cooling shell (1) is sleeved on the outside of the cabin column section (5), and the two are coaxially fixed and placed, with a gap between them. In the gap between the cooling shell (1) and the cabin column section (5), sealing rings (4) are provided on the upper and lower sides; the inner wall of the cooling shell (1), the outer wall of the cabin column section (5), and the upper and lower sealing rings (4) constitute a space for accommodating a cooling medium, and a liquid injection port (2) and a liquid outlet (3) are provided on the cooling shell (1) corresponding to the space area. The present invention can effectively control the temperature of the wall panel area adjacent to the weld during the cabin column section girth welding process, and greatly reduce or avoid welding deformation of the wall panel area.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft manufacturing, and in particular relates to a spacecraft cabin annular seam welding cooling device and method. Background Art

[0002] Currently, large spacecraft cabin structures can reach diameters of up to 5 meters. They are constructed by welding multiple curved plates longitudinally to form cylindrical segments, which are then metallurgically connected by circumferential welding to form the entire cabin structure. Because spacecraft cabin structures utilize a lightweight design to improve load-bearing efficiency, the cabin wall panels are thin and weak in rigidity.

[0003] like Figure 1 As shown in the figure, due to the low weld joint coefficient, the weld joints are all thickened. When welding the circumferential seam of the hull cylindrical section, the welding heat input is large, causing the wall panel area adjacent to the weld joint to easily deform under the influence of welding heat. As a result, the shape and position accuracy of the hull after welding does not meet the design requirements. Summary of the Invention

[0004] The present invention proposes a spacecraft cabin circumferential seam welding cooling device and method to solve the problem that when welding the circumferential seams of the cylindrical section of a large spacecraft cabin structure, the wall panel area adjacent to the weld joint undergoes local deformation due to the influence of the welding heat due to the large welding heat input, and the cabin shape and position accuracy after welding is completed cannot meet the design requirements.

[0005] The present invention proposes a spacecraft cabin annular seam welding cooling device, comprising: a cooling shell, a sealing ring, wherein:

[0006] The cooling shell is a circular shell, the inner diameter of which is larger than the outer diameter of the spacecraft cabin column. The cooling shell is sleeved on the outside of the cabin column, and the two are coaxially fixed with a gap between them.

[0007] There are sealing rings on the upper and lower sides of the gap between the cooling shell and the cabin column section;

[0008] The inner wall of the cooling shell, the outer wall of the cabin column section and the upper and lower side sealing rings form a space for accommodating the cooling medium. The cooling shell corresponding to the space area is provided with a liquid injection port and a liquid outlet.

[0009] Furthermore, the size of the gap is determined according to the required volume of the cooling medium.

[0010] Furthermore, a refrigerator, a flow valve and a pipeline are provided between the liquid injection port and the liquid outlet outside the cooling shell to form a cooling medium sealed circulation device. The liquid outlet is connected to the liquid inlet end of the refrigerator through a pipeline, and the liquid outlet end of the refrigerator is connected to the liquid injection port through a pipeline via the flow valve.

[0011] Furthermore, the refrigerator regulates the temperature of the cooling medium so that the temperature of the cooling medium is maintained within a set temperature range.

[0012] Furthermore, the cooling medium is water.

[0013] Furthermore, the flow valve regulates the flow rate of the cooling medium, and the flow rate is maintained within a set flow rate range.

[0014] Furthermore, valves are respectively installed at the liquid injection port and the liquid outlet, and the valves have temperature sensors, which sense the temperature of the cooling medium. 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 range, the valve opens; 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 closes.

[0015] Furthermore, the sealing ring is made of a compressible polymer material, and the cross-sectional shape of the sealing ring is circular, rectangular, or trapezoidal.

[0016] A method for cooling a spacecraft cabin annular seam weld, comprising: providing a refrigerator, a flow valve, and a pipeline between a liquid injection port and a liquid outlet on the outside of a cooling shell to form a cooling medium sealed circulation device, wherein the liquid outlet is connected to a liquid inlet of the refrigerator via a pipeline, and the liquid outlet of the refrigerator is connected to the liquid injection port via a pipeline via the flow valve;

[0017] The refrigerator is used to control the temperature of the cooling medium so that the temperature of the cooling medium is maintained within a set temperature range;

[0018] The flow valve is used to regulate the flow rate of the cooling medium to keep the flow rate within the set flow rate range.

[0019] Valves are installed at the liquid injection port and the liquid outlet respectively. The valves have temperature sensors. The temperature sensors sense the temperature of the cooling medium. 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 range, the valve opens; 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 closes.

[0020] The cooling device and method proposed in the present invention can effectively control the temperature of the wall panel area adjacent to the weld during the circumferential seam welding of the cabin column section, thereby greatly reducing or avoiding welding deformation of the wall panel area. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the column structure of a large spacecraft cabin;

[0022] Figure 2 This is a schematic structural diagram of a spacecraft cabin annular seam welding cooling device according to the present invention;

[0023] Figure 3 The external refrigeration system of the spacecraft cabin annular seam welding cooling device of the present invention;

[0024] Figure 4 This is a schematic diagram of the sealing ring structure and installation of the present invention. DETAILED DESCRIPTION

[0025] The structure of the large spacecraft cabin annular seam welding cooling device proposed by the present invention is as follows Figure 2 As shown, the cooling system comprises a cooling shell 1, a sealing ring 4, and a cabin column 5. The cooling shell 1 is a circular shell structure with a liquid inlet 2 and a liquid outlet 3. Valves 9 are installed at the liquid inlet 2 and liquid outlet 3. These valves contain temperature sensors that open or close based on the temperature detected by the temperature sensors. To use the system, first place the cabin column 5 on a platform. Slide the cooling shell 1 over the cabin column 5, with the liquid inlet 2 at the bottom and the liquid outlet 3 at the top. Adjust the cooling shell 1 to an appropriate height and support it from below. Insert the sealing ring 4 from the top into the gap between the upper side of the cabin column 5 and the cooling shell 1. Then, flip the cooling shell 1, cabin column 5, and sealing ring 4 assembly upside down and rotate it on the platform. Similarly, install another sealing ring 4 into the gap below the cooling shell 1, cabin column 5, and sealing ring 4 assembly. At this point, the cooling shell 1, cabin column 5, and two sealing rings 4 form a complete cooling assembly. The cooling shell 1 and the cabin column section 5 are made of metal, preferably a lightweight metal or alloy, such as aluminum or aluminum alloy.

[0026] Subsequently, the above-mentioned cooling component and another part to be welded are assembled by circumferential seam welding. After the assembly is complete, the cooling medium, which can be water or other refrigerant, is injected into the cavity between the cooling shell 1 and the cabin column section 5 of the above-mentioned component from the liquid injection port 2 until the water or other refrigerant completely fills the cavity between the cooling shell 1 and the cabin column section 5.

[0027] At this time, the circumferential seam welding operation between the cabin column sections can be carried out. The water or cooling medium in the cavity between the cooling shell 1 and the cabin column section 5 will absorb a large amount of heat generated at the weld during the welding process, which can effectively ensure that the welding process temperature of the thin-walled plate area near the weld area is in a suitable range, reducing or even avoiding welding deformation.

[0028] like Figure 3 As shown, a refrigerator 10, a flow valve 11 and a pipeline are provided between the liquid injection port 2 and the liquid outlet 3 outside the cooling shell 1 to form a cooling medium sealed circulation device. The liquid outlet 3 is connected to the liquid inlet end of the refrigerator 10 through a pipeline, and the liquid outlet end of the refrigerator 10 is connected to the liquid injection port 2 through a pipeline via the flow valve 11.

[0029] The cooling device proposed in the present invention can form a cooling device with real-time cooling function of the coolant through the liquid injection port 2 and the liquid outlet 3 with the external refrigerator 10 and the flow valve 11 during welding. By controlling the flow of the flow valve 11 and the temperature of the refrigerator 10, the temperature of the wall panel area during the welding process can be further regulated to keep the temperature of the cooling medium within the set temperature range.

[0030] There is a certain constraint relationship between the gap between the cabin column section 5 and the cooling shell 1 and the structural dimensions of the sealing ring 4. The cross section of the sealing ring 4 can be of any geometric shape. Figure 4 For example. The outer diameter of the cabin column section 5 is 2828 mm, and the inner diameter of the cooling shell 1 is 2853 mm. The gap e between the cooling shell 1 and the cabin column section 5 is 12.5 mm, and the cross-sectional shape of the sealing ring 4 is a right-angled trapezoid, with the lower base a, height b, and upper base c being 15.6 mm, 10 mm, and 12.5 mm, respectively. After the sealing ring 4 is installed between the cooling shell 1 and the cabin column section 5, the sealing ring 4 will be compressed, and the upper compression rate is 20%. At this time, 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 a sealing ability due to compression. According to finite element calculation, the sealing stress can withstand the weight of the cooling device described in the present invention and the refrigerant added inside (the refrigerant at this time is water), and can achieve reliable sealing of the internal cooling medium when there is no external auxiliary support.

[0031] The present invention also provides a spacecraft cabin circumferential seam welding cooling method, comprising: utilizing a refrigerator 10 to regulate the temperature of a cooling medium so that the temperature of the cooling medium is maintained within a set temperature range; and utilizing a flow valve 11 to regulate the flow rate of the cooling medium so that the flow rate is maintained within the set flow rate range.

[0032] Valves 9 are respectively installed at the liquid injection port 2 and the liquid outlet 3. The valves 9 have temperature sensors. The temperature sensors sense the temperature of the cooling medium. 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 range, the valves 9 open; 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 range, the valves 9 close.

[0033] Example

[0034] Considering a certain safety factor, the finite element method was used to calculate the sealing ability of the sealing ring when the compression rate was 15%. The results showed that the sealing pressure when the compression rate was 15% was 2.5MPa.

[0035] The pressure after water injection between the cooling shell and the hull column was calculated. The hull column is 1370 mm high, and the water injection height is higher than the hull column. When the water injection height reaches 1500 mm, the lower pressure is 0.015 MPa, far below the sealing capacity of the sealing ring, effectively achieving a cooling water seal.

[0036] The friction generated by the sealing ring was calculated, taking into account the weight of the water and cooling housing. To ensure a calculation margin, a compression ratio of 15% and an effective sealing height of 5mm were used. The friction coefficient between rubber and aluminum ranges from 0.1 to 0.6, with a lower limit of 0.1. The friction generated is 11kN. The weight of the filled water is 360kg, the weight of the cooling housing is 72kg, and the total weight is 432kg. The gravity is 4.3kN, which is less than the friction force. Therefore, the sealing force of the sealing ring in the water-filled state ensures the stability of the cooling housing.

[0037] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A spacecraft cabin annular seam welding cooling device, characterized in that: include: Cooling housing (1), sealing ring (4); wherein, The cooling shell (1) is a circular shell, the inner diameter 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 the two are coaxially fixed and placed with a gap between them; A sealing ring (4) is provided on the upper and lower sides of the gap between the cooling shell (1) and the cabin column section (5); the sealing ring (4) is made of a compressible polymer material, and the cross-sectional shape of the sealing ring (4) is circular, rectangular, or trapezoidal; after the predetermined compression amount is achieved by setting the size of the sealing ring (4), reliable sealing of the internal cooling medium is achieved when there is no external auxiliary support; 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 accommodating the cooling medium, and the cooling shell (1) corresponding to the space area has a liquid injection port (2) and a liquid outlet (3); The method of use is as follows: first, the cabin column section (5) is placed on the platform, and the cooling shell (1) is placed outside the cabin column section (5), with the liquid injection port (2) at the bottom and the liquid outlet (3) at the top. The cooling shell (1) is adjusted to an appropriate height and the cooling shell (1) is supported and positioned at the bottom. The sealing ring (4) is inserted from the upper side into the gap between the upper side of the cabin column section (5) and the cooling shell (1); then, the component consisting of the cooling shell (1), the cabin column section (5) and the sealing ring (4) is turned upside down and rotated on the platform. In the same way, another sealing ring (4) is inserted into the lower side gap of the component consisting of the cooling shell (1), the cabin column section (5) and the sealing ring (4). At this point, the cooling shell (1), the cabin column section (5) and the two sealing rings (4) form a complete cooling assembly; Assemble the cooling assembly and another part to be welded by circumferential welding. After the assembly is complete, inject cooling medium into the cavity between the cooling shell (1) of the cooling assembly and the cabin column section (5) from the liquid injection port (2) until the cooling medium completely fills the cavity between the cooling shell (1) and the cabin column section (5); During the circumferential welding operation between the cabin column sections, the cooling medium in the cavity between the cooling shell (1) and the cabin column section (5) absorbs the heat generated at the weld joint during the welding process, ensuring that the temperature of the thin-walled plate area near the weld joint area is within a suitable range during the welding process, thereby avoiding welding deformation.

2. The spacecraft cabin circumferential seam welding cooling device according to claim 1, characterized in that: The size of the gap is determined according to the required cooling medium volume.

3. The spacecraft cabin circumferential seam welding cooling device according to claim 1, characterized in that: A cooling medium sealed circulation device is formed between a liquid injection port (2) and a liquid outlet (3) outside the cooling shell (1), and a refrigerator (10), a flow valve (11), and a pipeline. The liquid outlet (3) is connected to the liquid inlet of the refrigerator (10) through a pipeline, and the liquid outlet of the refrigerator (10) is connected to the liquid injection port (2) through a pipeline via the flow valve (11).

4. The spacecraft cabin circumferential seam welding cooling device according to claim 3, characterized in that: The refrigerator (10) regulates the temperature of the cooling medium so that the temperature of the cooling medium is maintained within a set temperature range.

5. The spacecraft cabin circumferential seam welding cooling device according to claim 1, characterized in that: The cooling medium is water.

6. The spacecraft cabin circumferential seam welding cooling device according to claim 3, characterized in that: The flow valve (11) regulates the flow rate of the cooling medium, and the flow rate is maintained within a set flow rate range.

7. The spacecraft cabin circumferential seam welding cooling device according to claim 1, characterized in that: The liquid injection port (2) and the liquid outlet (3) are respectively provided with valves (9), and the valves (9) have temperature sensors, and the temperature sensors sense the temperature of the cooling medium. 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 range, the valves (9) are 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 range, the valves (9) are closed.

8. A method for cooling a spacecraft cabin annular seam welding based on the device according to any one of claims 1 to 7, characterized in that: The following steps are involved: A refrigerator (10), a flow valve (11) and a pipeline are provided between the liquid injection port (2) and the liquid outlet (3) outside the cooling shell (1) of the cooling device to form a cooling medium sealing circulation device, the liquid outlet (3) is connected to the liquid inlet end of the refrigerator (10) through a pipeline, and the liquid outlet end of the refrigerator (10) is connected to the liquid injection port (2) through a pipeline via the flow valve; Utilizing the refrigerator (10) to regulate the temperature of the cooling medium so that the temperature of the cooling medium is maintained within a set temperature range; The flow valve (11) is used to regulate the flow rate of the cooling medium to keep the flow rate within the set flow rate range. Valves (9) are respectively installed at the liquid injection port (2) and the liquid outlet (3). The valves (9) have temperature sensors. The temperature sensors sense the temperature of the cooling medium. 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 range, the valves (9) are 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 range, the valves (9) are closed.

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