Spacecraft cooling pond
The spacecraft cooling pool addresses uneven heating during launch by using differential pumps and structured inflow/outflow pipes to enhance mixing and uniform cooling, ensuring efficient resource utilization.
Patent Information
- Application Number
- CN202521164175.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-06-09
- Publication Date
- 2025-07-15
- Estimated Expiration
- 2035-06-09
AI Technical Summary
The existing spacecraft cooling pools have uneven cooling effects during the spacecraft launch, resulting in waste of cooling resources.
The differential circulation pump and support frame design are adopted, combined with the heat absorption coating, and the temperature differential flow and underwater vortex are formed through the differential circulation pump to ensure uniform mixing of the coolant, and the water inlet is set at the bottom of the pool to enhance the cooling effect.
The uniform distribution and efficient cooling of the coolant are achieved, the waste of cooling resources is avoided, and the overall cooling effect of the cooling pool is improved.
Smart Images
Figure CN223101025U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of cooling pools, in particular to a spacecraft cooling pool. Background Art
[0002] In order to complete space missions, a space system must cooperate with each other through spacecraft and space launch vehicles, spacecraft launch sites and recovery facilities, space TT&C and data acquisition networks and user stations (networks), etc., coordinate work, and jointly form a system. A spacecraft is the main body of executing space missions and is the main component of a space system. A cooling pool is a kind of water cooling facility. Ponds, reservoirs, lakes, and special water pools used to cool circulating water are collectively called cooling pools. When a spacecraft is launched, the tail flame temperature is relatively high, reaching thousands of degrees Celsius. The intense high temperature will cause damage to the surroundings. Therefore, the hot gas needs to be input into the cooling pool through a diversion groove to achieve the effect of absorbing heat by evaporating water.
[0003] Patent CN212172581U discloses a spacecraft cooling pool for aerospace applications, including a cooling pool body, a support rod, and a water inlet pipe. An anti-fire inner liner layer is provided inside the cooling pool body. An insulation layer is fixedly installed between the anti-fire inner liner layer and the cooling pool body. Cooling water is provided inside the anti-fire inner liner layer. A support rod is fixedly installed at the bottom inside the anti-fire inner liner layer. A support frame is fixedly installed at the top of the support rod. A launch hole is provided inside the support frame. A number of ventilation holes are provided around the launch hole. The water inlet pipe is fixedly installed at the bottom of the right side wall of the cooling pool body. Fixing seats are fixedly installed at the top and bottom inside the water inlet pipe. A one-way valve is fixedly installed between the fixing seats. The device has a simple structure, high practicability, and good safety.
[0004] It can be seen that existing spacecraft cooling pools often achieve continuous cooling based on one-way water supply and drainage at the input and output ends. However, in fact, the water in the cooling pool is often unevenly heated during the spacecraft launch process, which results in limited cooling effect of the cooling pool and waste of cooling resources.
[0005] There is a need for a spacecraft cooling pool to solve the above problems. Summary of the Utility Model
[0006] The utility model aims to solve the problem that existing spacecraft cooling pools often achieve continuous cooling based on one-way water supply and drainage at the input and output ends. However, in fact, the water in the cooling pool is often unevenly heated during the spacecraft launch process, which results in limited cooling effect of the cooling pool and waste of cooling resources. A spacecraft cooling pool is provided to solve the above problems.
[0007] The utility model provides a spacecraft cooling pool, which includes a cooling pool, a support frame, a coolant, an inlet pipe, at least three outlet pipes and several circulation pumps. The cooling pool is a tank body with an open top. The hollow structure inside the cooling pool is a stretched body. The stretching cross-section of the cooling pool is perpendicular to the stretching direction. The coolant is arranged inside the cooling pool. The outlet pipes are uniformly arranged at the same height on the side wall of the circulation pumps. One-way valves are arranged on both the inlet pipe and the outlet pipes. The one-way valve of the inlet pipe is one-way from outside the cooling pool to inside the cooling pool, and the one-way valve of the outlet pipe is one-way from inside the cooling pool to outside the cooling pool. The inlet pipe is connected to the bottom of the spacecraft cooling pool, and the water inlet direction of the inlet pipe is vertically upward. The circulation pumps are arranged at the inlets of the outlet pipes. The power of the circulation pumps decreases sequentially from high to low in the same direction along the circumferential direction of the side wall of the cooling pool based on one of the circulation pumps. The circulation pump with the lowest power is adjacent to the circulation pump with the highest power. The support frame is arranged inside the cooling pool. The lower half of the support frame is arranged inside the coolant, and the upper half of the support frame protrudes out of the coolant.
[0008] In a preferred embodiment of the spacecraft cooling pool described in the utility model, the support frame includes several support columns and a support plate. The support plate is a ring-shaped plate structure. Several through holes are uniformly arranged on the circumferential surface of the support plate. The support columns are vertically connected to the lower surface of the support plate, and the connection points of the support columns and the support plate are alternately arranged at the inner ring position and the outer ring position of the support plate.
[0009] In a preferred embodiment of the spacecraft cooling pool described in the utility model, a heat-absorbing coating is arranged on the inner wall of the cooling pool.
[0010] In a preferred embodiment of the spacecraft cooling pool described in the utility model, the one-way valves of the inlet pipe and the outlet pipe are both arranged in the water outlet direction of the circulation pumps.
[0011] The beneficial effects of the utility model are as follows:
[0012] Through the differential circulation pumps of the utility model, the water discharge speed on the outer periphery of the cooling pool is made different. Also, based on the use environment of this device where the surface of the pool radiates high temperature downward, a temperature difference will be generated in the pool, causing the water to flow through the temperature gradient. Coupled with the speed difference, a slow underwater vortex is formed, avoiding the generation of high-intensity vortices that cause a large amount of the central liquid to move outward to the periphery and resulting in cooling failure. At the same time, it ensures that the water in the pool is fully mixed, reducing the concentration of the water in the pool in a certain part of the whole and weakening the cooling effect. The water inlet is arranged at the bottom of the pool to ensure the relative flow of the cooling water and the flame of the aircraft, obtaining the maximum cooling effect. Description of the Drawings
[0013] Figure 1 It is a schematic diagram of a spacecraft cooling pool;
[0014] Figure 2 It is a front view and a top view schematic diagram of the support frame of a spacecraft cooling pool.
[0015] Reference numerals:
[0016] 1. Cooling pool; 2. Support frame; 21. Support column; 22. Support plate; 3. Cooling liquid; 4. Inlet pipe; 5. Outlet pipe; 6. Circulation pump. Detailed implementation mode
[0017] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Embodiment 1
[0018] As Figure 1 shown, a spacecraft cooling pool includes a cooling pool 1, a support frame 2, a cooling liquid 3, an inlet pipe 4, at least three outlet pipes 5 and several circulation pumps 6. The cooling pool 1 is a tank body with an open top. The hollow structure inside the cooling pool 1 is a stretched body. The stretching cross-section of the cooling pool 1 is perpendicular to the stretching direction. The cooling liquid 3 is arranged inside the cooling pool 1. The outlet pipes 5 are uniformly arranged at the same height on the side wall of the circulation pump 6. One-way valves are arranged on both the inlet pipe 4 and the outlet pipe 5. The one-way valve of the inlet pipe 4 is one-way from outside the cooling pool 1 to inside the cooling pool 1, and the one-way valve of the outlet pipe 5 is one-way from inside the cooling pool 1 to outside the cooling pool 1. The inlet pipe 4 is connected to the bottom of the spacecraft cooling pool, and the water inlet direction of the inlet pipe 4 is vertically upward. The circulation pump 6 is arranged at the inlet of the outlet pipe 5. The power of the circulation pump 6 is sequentially decreased from high to low in the same direction along the circumferential direction of the side wall of the cooling pool 1 based on one of the circulation pumps 6, and the circulation pump 6 with the lowest power is adjacent to the circulation pump 6 with the highest power. The support frame 2 is arranged inside the cooling pool 1. The lower half of the support frame 2 is arranged inside the cooling liquid 3, and the upper half of the support frame 2 extends out of the cooling liquid 3.
[0019] As Figure 2 shown, the support frame 2 includes several support columns 21 and a support plate 22. The support plate 22 is a ring-shaped plate structure. Several through holes are uniformly arranged on the circumferential surface of the support plate 22. The support columns 21 are vertically connected to the lower surface of the support plate 22, and the connection points of the support columns and the support plate 22 are alternately arranged at the inner ring position and the outer ring position of the support plate 22.
[0020] An endothermic coating is provided on the inner wall of the cooling pool 1.
[0021] The one-way valves of the inlet pipe 4 and the outlet pipe 5 are both arranged in the water outlet direction of the circulation pump 6.
[0022] On the basis of this embodiment, heat insulation materials can also be arranged inside the inner wall of the cooling pool to ensure the integrity of the inner wall of the cooling pool.
[0023] The above are only the preferred specific embodiments of the present utility model, but the protection scope of the present utility model is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present utility model, according to the technical solution of the present utility model and its inventive concept, making equivalent substitutions or changes, shall be covered by the protection scope of the present utility model.
Claims
1. A spacecraft cooling pool, characterized in that: It includes a cooling pool (1), a support frame (2), a coolant (3), an inlet pipe (4), at least three outlet pipes (5) and a number of circulation pumps (6). The cooling pool (1) is an open-top trough. The hollow structure inside the cooling pool (1) is a stretched body. The stretching cross-section of the cooling pool (1) is perpendicular to the stretching direction. The coolant (3) is arranged inside the cooling pool (1). The outlet pipes (5) are evenly arranged at the same height on the side wall of the circulation pump (6). One-way valves are provided on both the inlet pipe (4) and the outlet pipe (5). The one-way valve of the inlet pipe (4) is one-way from outside the cooling pool (1) to inside the cooling pool (1), and the one-way valve of the outlet pipe (5) is one-way from inside the cooling pool (1) to outside the cooling pool (1). The inlet pipe (4) is connected to the bottom of the spacecraft cooling pool, and the water inlet direction of the inlet pipe (4) is vertically upward. The circulation pump (6) is arranged at the inlet of the outlet pipe (5). The power of the circulation pump (6) decreases sequentially from high to low in the same direction along the circumferential direction of the side wall of the cooling pool (1) based on one of the circulation pumps (6). The circulation pump (6) with the lowest power is adjacent to the circulation pump (6) with the highest power. The support frame (2) is arranged inside the cooling pool (1). The lower half of the support frame (2) is arranged inside the coolant (3), and the upper half of the support frame (2) protrudes out of the coolant (3).
2. The spacecraft cooling pool according to claim 1, wherein: The support frame (2) includes a number of support columns (21) and a support plate (22). The support plate (22) is a ring-shaped plate structure. A number of through holes are evenly arranged on the circumferential surface of the support plate (22). The support columns (21) are vertically connected to the lower surface of the support plate (22). The connection points of the support columns (21) and the support plate (22) are alternately arranged at the inner ring position and the outer ring position of the support plate (22).
3. A spacecraft cooling pool according to claim 1, characterized in that: An endothermic coating is provided on the inner wall of the cooling pool (1).
4. A spacecraft cooling pool according to claim 1, characterized in that: The one-way valves of the inlet pipe (4) and the outlet pipe (5) are both arranged in the water outlet direction of the circulation pump (6).