Aircraft cooling system

Abstract

This invention provides a cooling device for an aircraft, comprising: a radiator, which includes an inner cladding plate, an outer cladding plate, and heat dissipation fins, wherein the inner and outer cladding plates are fitted together, and the heat dissipation fins are distributed within a cooling cavity between the inner and outer cladding plates, and the inner cladding plate is fitted to the front end shell of the aircraft; a first collecting ring, which has an annular first liquid storage cavity; a second collecting ring, which has an annular second liquid storage cavity; a first distribution assembly, which is driven by coolant to move, opening a first annular opening and uniformly inputting coolant into the cooling cavity; and a second distribution assembly, which is driven by coolant to move, opening a second annular opening and uniformly outputting coolant from the cooling cavity. Using this solution, a coolant circulation is formed within the aircraft cooling device, and the coolant absorbs the heat generated by the friction between the outer cladding plate and the air, preventing heat from entering the aircraft and causing damage to internal components.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically, to an aircraft cooling device. Background Technology

[0002] During flight, the high speed of an aircraft generates heat through friction between its surface and the air. This heat can transfer into the aircraft's interior, causing overheating and damage to internal components. This limitation restricts the aircraft's speed. Since speed is a key performance factor for an aircraft, it is crucial to absorb and cool the aircraft by preventing heat transfer into its interior. Summary of the Invention

[0003] This invention provides a cooling device for aircraft to solve the problem in the prior art where heat generated by friction between the surface of an aircraft and the air is transferred into the interior of the aircraft, causing damage to internal components.

[0004] To address the aforementioned problems, this invention provides a flight vehicle cooling device, comprising: a radiator, the radiator including an inner covering plate, an outer covering plate, and heat dissipation fins, the inner and outer covering plates being sleeved together, the heat dissipation fins being distributed within a cooling cavity between the inner and outer covering plates, the inner covering plate being fitted to the front end shell of the flight vehicle; a first collecting ring, disposed at one end of the radiator, the first collecting ring having an annular first liquid storage cavity; a second collecting ring, disposed at the other end of the radiator, the second collecting ring having an annular second liquid storage cavity; a first distribution assembly, movably disposed at a first annular opening of the first liquid storage cavity, after the first liquid storage cavity is filled with coolant, the coolant pushes the first distribution assembly to move, the first annular opening opens and uniformly inputs coolant into the cooling cavity; and a second distribution assembly, movably disposed at a second annular opening of the second liquid storage cavity, after the second liquid storage cavity is filled with coolant, the coolant pushes the second distribution assembly to move, the second annular opening opens and uniformly outputs coolant from the cooling cavity.

[0005] Furthermore, when the first annular opening is closed, a portion of the first distribution assembly extends into the first liquid storage chamber and seals against the inner wall of the first liquid storage chamber. When the first annular opening is open, a first annular gap is formed between the inner side of the first distribution assembly and the inner wall of the first liquid storage chamber, and a second annular gap is formed between the outer side of the first distribution assembly and the inner wall of the first liquid storage chamber. The first and second annular gaps are used for the flow of coolant. When the second annular opening is closed, a portion of the second distribution assembly extends into the second liquid storage chamber and seals against the inner wall of the second liquid storage chamber. When the second annular opening is open, a third annular gap is formed between the inner side of the second distribution assembly and the inner wall of the second liquid storage chamber, and a fourth annular gap is formed between the outer side of the second distribution assembly and the inner wall of the second liquid storage chamber. The third and fourth annular gaps are used for the flow of coolant.

[0006] Furthermore, the heat sink has a wave-shaped plate structure, with the crests and troughs of the heat sink fixedly connected to the outer and inner covering plates, respectively. The heat sink divides the cooling chamber into multiple channels. When the first annular opening is open, the coolant in the first liquid storage chamber is diverted to multiple channels. When the second annular opening is open, the coolant in the multiple channels flows into the second liquid storage chamber.

[0007] Furthermore, the first distribution assembly includes a first distribution ring and a plurality of first elastic members. The first distribution ring is movably disposed at the first annular opening to open and close the first annular opening. The plurality of first elastic members are distributed on the side of the first distribution ring away from the first annular opening, and the first elastic members abut against the first distribution ring.

[0008] Furthermore, the second distribution assembly includes a second distribution ring and a plurality of second elastic members. The second distribution ring is movably disposed at the second annular opening to open and close the second annular opening. The plurality of second elastic members are distributed on the side of the second distribution ring away from the second annular opening, and the second elastic members abut against the second distribution ring.

[0009] Furthermore, the aircraft cooling device also includes multiple inlet guide columns, which are distributed circumferentially along the first collecting ring. One end of each inlet guide column is fixedly connected to the first collecting ring, and the inlet guide column inputs the coolant into the first liquid storage chamber.

[0010] Furthermore, the end of the inlet guide post away from the first collector ring has a first axial blind hole, and the side wall of the first axial blind hole has a first radial through hole, through which coolant enters the first liquid storage chamber.

[0011] Furthermore, the aircraft cooling device also includes multiple outlet guide columns, which are distributed circumferentially along the second collector ring. One end of each outlet guide column is fixedly connected to the second collector ring, and the outlet guide column outputs the coolant from the second liquid storage chamber.

[0012] Furthermore, the end of the outlet guide post away from the second collector ring has a second axial blind hole, and the side wall of the second axial blind hole has a second radial through hole, through which the coolant is output to the second reservoir.

[0013] Furthermore, the inner cladding plate, outer cladding plate, and heat sink are all made of aluminum alloy, and the heat sink is welded to both the inner and outer cladding plates; the first and second collector rings are also made of aluminum alloy, and both are welded to the heat sink.

[0014] The present invention provides a flight cooling device, comprising: a radiator, the radiator including an inner covering plate, an outer covering plate, and heat dissipation fins, the inner covering plate and the outer covering plate being sleeved together, the heat dissipation fins being distributed in a cooling cavity between the inner covering plate and the outer covering plate, the inner covering plate being attached to the front shell of the flight body; a first collecting ring disposed at one end of the radiator, the first collecting ring having an annular first liquid storage cavity; a second collecting ring disposed at the other end of the radiator, the second collecting ring having an annular second liquid storage cavity; a first distribution assembly movably disposed at the first annular opening of the first collecting ring, after the first liquid storage cavity is filled with coolant, the coolant pushes the first distribution assembly to move, the first annular opening opens and uniformly inputs coolant into the cooling cavity; and a second distribution assembly movably disposed at the second annular opening of the second collecting ring, after the second liquid storage cavity is filled with coolant, the coolant pushes the second distribution assembly to move, the second annular opening opens and uniformly outputs coolant from the cooling cavity. In this design, coolant flows into the first collector ring, filling the entire first reservoir. The coolant then pushes the first distribution assembly, allowing it to evenly enter the cooling chamber from the first annular opening. After the cooling chamber is evenly filled, the coolant flows into the second collector ring. When the second reservoir is full, the coolant pushes the second distribution assembly, allowing it to evenly exit the second collector ring from the second annular opening. This configuration creates a coolant circulation system within the aircraft's cooling device. The coolant absorbs the heat generated by friction between the outer casing and the air, preventing heat from entering the aircraft and damaging its internal components. Attached Figure Description

[0015] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0016] Figure 1 A schematic diagram of the structure of the aircraft cooling device provided in Embodiment 1 of the present invention is shown;

[0017] Figure 2 It shows Figure 1 A front view of the aircraft's cooling system;

[0018] Figure 3 It shows Figure 2 Cross-sectional view of section AA;

[0019] Figure 4 It shows Figure 2 Cross-sectional view of section BB in the middle;

[0020] Figure 5 It shows Figure 3 A magnified view of a section at point C;

[0021] Figure 6 It shows Figure 3 A magnified view of a section at point D.

[0022] The above figures include the following reference numerals:

[0023] 10. Radiator; 11. Inner cladding plate; 12. Outer cladding plate; 13. Heat sink fins;

[0024] 20. First flow ring; 21. First liquid storage chamber;

[0025] 30. Second flow ring; 31. Second liquid storage chamber;

[0026] 40. First distribution assembly; 41. First distribution ring; 42. First elastic element;

[0027] 50. Second distribution assembly; 51. Second distribution ring; 52. Second elastic element;

[0028] 60. Inlet guide post; 61. First axial blind hole; 62. First radial through hole;

[0029] 70. Outlet guide post; 71. Second axial blind hole; 72. Second radial through hole. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0031] like Figures 1 to 6As shown, Embodiment 1 of the present invention provides a flight vehicle cooling device, comprising: a radiator 10, the radiator 10 including an inner covering plate 11, an outer covering plate 12, and heat dissipation fins 13, the inner covering plate 11 and the outer covering plate 12 being sleeved together, the heat dissipation fins 13 being distributed in a cooling cavity between the inner covering plate 11 and the outer covering plate 12, the inner covering plate 11 being attached to the front end shell of the flight vehicle; a first collecting ring 20 disposed at one end of the radiator 10, the first collecting ring 20 having an annular first liquid storage cavity 21; and a second collecting ring 30 disposed at the other end of the radiator 10. The second collector ring 30 has an annular second liquid storage chamber 31; the first distribution assembly 40 is movably disposed at the first annular opening of the first liquid storage chamber 21. After the first liquid storage chamber 21 is filled with coolant, the coolant pushes the first distribution assembly 40 to move, the first annular opening opens and coolant is evenly input into the cooling chamber; the second distribution assembly 50 is movably disposed at the second annular opening of the second liquid storage chamber 31. After the second liquid storage chamber 31 is filled with coolant, the coolant pushes the second distribution assembly 50 to move, the second annular opening opens and coolant in the cooling chamber is evenly output.

[0032] In this design, coolant flows into the first collector ring 20, filling the entire first reservoir 21. The coolant then pushes the first distribution assembly 40, allowing it to uniformly enter the cooling chamber from the first annular opening. After uniformly filling the cooling chamber, the coolant flows into the second collector ring 30. When the second reservoir 31 is full, the coolant pushes the second distribution assembly 50, allowing it to uniformly exit the second collector ring 30 from the second annular opening. This configuration creates a coolant circulation system within the aircraft's cooling device. The coolant absorbs the heat generated by friction between the outer casing 12 and the air, preventing heat from entering the aircraft and damaging its internal components. The aircraft can be a missile, rocket, or similar device.

[0033] like Figure 5 and Figure 6 As shown, when the first annular opening is closed, a portion of the first distribution assembly 40 extends into the first liquid storage chamber 21 and seals with the inner wall of the first liquid storage chamber 21. When the first annular opening is open, a first annular gap is formed between the inner side of the first distribution assembly 40 and the inner wall of the first liquid storage chamber 21, and a second annular gap is formed between the outer side of the first distribution assembly 40 and the inner wall of the first liquid storage chamber 21. The first and second annular gaps are used for the flow of coolant. When the second annular opening is closed, a portion of the second distribution assembly 50 extends into the second liquid storage chamber 31 and seals with the inner wall of the second liquid storage chamber 31. When the second annular opening is open, a third annular gap is formed between the inner side of the second distribution assembly 50 and the inner wall of the second liquid storage chamber 31, and a fourth annular gap is formed between the outer side of the second distribution assembly 50 and the inner wall of the second liquid storage chamber 31. The third and fourth annular gaps are used for the flow of coolant.

[0034] With this configuration, a portion of the first distribution assembly 40 extends into the first liquid storage chamber 21 and seals against the inner wall of the first liquid storage chamber 21, ensuring that coolant will not leak from the first liquid storage chamber 21 when the first annular opening is closed. When the coolant pushes the first distribution assembly 40, the first annular opening opens, forming a gap. Due to the narrowness of the gap, the coolant in the first liquid storage chamber 21 flows evenly into the cooling chamber from the first annular gap and the second annular gap.

[0035] A portion of the second distribution assembly 50 extends into the second liquid storage chamber 31 and seals against the inner wall of the second liquid storage chamber 31, ensuring that coolant does not seep into the second liquid storage chamber 31 when the first annular opening is closed. When the coolant pushes the second distribution assembly 50, the second annular opening opens, forming a gap. Due to the narrowness of the gap, coolant in the cooling chamber flows into the second liquid storage chamber 31 from the third and fourth annular gaps.

[0036] like Figure 4 As shown, the heat sink 13 has a wave-shaped plate structure. The crests and troughs of the heat sink 13 are fixedly connected to the outer cover plate 12 and the inner cover plate 11, respectively. The heat sink 13 divides the cooling cavity into multiple channels. When the first annular opening is open, the coolant in the first liquid storage cavity 21 is diverted to multiple channels. When the second annular opening is open, the coolant in the multiple channels flows into the second liquid storage cavity 31.

[0037] With this configuration, the heat sink 13 increases the surface area of ​​contact between the aircraft's cooling device and the coolant, allowing for faster transfer of absorbed heat to the coolant. The heat sink 13 divides the cooling chamber into multiple channels, enabling the coolant to flow evenly into each channel after it enters the cooling chamber uniformly, ensuring that the coolant is evenly distributed within the cooling chamber regardless of the aircraft's flight status.

[0038] like Figure 5 As shown, the first distribution assembly 40 includes a first distribution ring 41 and a plurality of first elastic members 42. The first distribution ring 41 is movably disposed at the first annular opening to open and close the first annular opening. The plurality of first elastic members 42 are distributed on the side of the first distribution ring 41 away from the first annular opening, and the first elastic members 42 abut against the first distribution ring 41.

[0039] With this configuration, when the coolant pushes the first distribution ring 41, the first elastic element 42 is in a compressed state, and the first annular opening is open. When the first reservoir 21 is not filled with coolant, the coolant cannot push the first distribution ring 41, and the first elastic element 42 squeezes the first distribution ring 41 into the first annular opening. The first distribution ring 41 and the inner wall of the first reservoir 21 are sealed together, preventing the coolant from flowing out of the first reservoir 21.

[0040] like Figure 6As shown, the second distribution assembly 50 includes a second distribution ring 51 and a plurality of second elastic members 52. The second distribution ring 51 is movably disposed at the second annular opening to open and close the second annular opening. The plurality of second elastic members 52 are distributed on the side of the second distribution ring 51 away from the second annular opening, and the second elastic members 52 abut against the second distribution ring 51.

[0041] With this configuration, when the coolant pushes the second distribution ring 51, the second elastic element 52 is in a compressed state, and the second annular opening is open. When the cooling chamber is not filled with coolant, the coolant cannot push the second distribution ring 51, and the second elastic element 52 squeezes the second distribution ring 51 into the second annular opening. The second distribution ring 51 and the inner wall of the second liquid storage chamber 31 are sealed together, preventing coolant from flowing into the second liquid storage chamber 31.

[0042] like Figure 1 As shown, the aircraft cooling device also includes multiple inlet guide pillars 60, which are distributed circumferentially along the first collecting ring 20. One end of each inlet guide pillar 60 is fixedly connected to the first collecting ring 20, and the inlet guide pillars 60 input coolant into the first liquid storage chamber 21. This arrangement, with multiple inlet guide pillars 60 distributed circumferentially along the first collecting ring 20, ensures more uniform coolant injection into the first collecting ring 20.

[0043] Optionally, the end of the inlet guide post 60 that is fixedly connected to the first collector ring 20 has an external thread, and the first collector ring 20 and the inlet guide post 60 are screwed together. This connection method is more secure and facilitates disassembly. The first distribution ring 41 has multiple circular holes along the circumference of the first collector ring 20, and multiple inlet guide posts 60 pass through the circular holes on the first distribution ring 41 respectively. The first elastic element 42 is sleeved on the inlet guide post 60. The inlet guide post 60 guides the movement of the first distribution ring 41 and the first elastic element 42. A sealing gasket is provided between the inlet guide post 60 and the first distribution ring 41 to prevent coolant leakage. A flange is fixed to the end of the inlet guide post 60 away from the external thread, one end of the first elastic element 42 abuts against the first distribution ring 41, and the other end abuts against the flange.

[0044] like Figure 5 As shown, the inlet guide post 60 has a first axial blind hole 61 at the end away from the first collector ring 20. The side wall of the first axial blind hole 61 is provided with a first radial through hole 62. The coolant enters the first liquid storage chamber 21 from the first axial blind hole 61 and the first radial through hole 62.

[0045] With this configuration, the coolant enters the inlet guide post 60 through the first axial blind hole 61 and enters the first collector ring 20 through the first radial through hole 62. After being buffered and redirected by the first axial blind hole 61 and the first radial through hole 62, the coolant enters the first collector ring 20 without causing impact to the first collector ring 20, resulting in a more uniform coolant entry.

[0046] like Figure 6 As shown, the aircraft cooling device also includes multiple outlet guide pillars 70, which are distributed circumferentially along the second collector ring 30. One end of each outlet guide pillar 70 is fixedly connected to the second collector ring 30, and the outlet guide pillars 70 output the coolant from the second liquid storage chamber 31. This arrangement, with multiple outlet guide pillars 70 distributed circumferentially along the second collector ring 30, ensures more uniform coolant injection into the second collector ring 30.

[0047] The outlet guide post 70 has an external thread at one end that is fixedly connected to the second collector ring 30, and the second collector ring 30 and the outlet guide post 70 are screwed together. This connection method is more secure and facilitates disassembly. The second distribution ring 51 has multiple circular holes along the circumference of the second collector ring 30, and the outlet guide post 70 passes through the circular holes on the second distribution ring 51. The second elastic element 52 is sleeved on the outlet guide post 70. The outlet guide post 70 guides the movement of the second distribution ring 51 and the second elastic element 52. A sealing gasket is provided between the outlet guide post 70 and the second distribution ring 51 to prevent coolant leakage. A flange is fixed at the end of the outlet guide post 70 away from the external thread, one end of the second elastic element 52 abuts against the second distribution ring 51, and the other end abuts against the flange.

[0048] like Figure 6 As shown, the outlet guide post 70 has a second axial blind hole 71 at the end away from the second collector ring 30. A second radial through hole 72 is formed on the side wall of the second axial blind hole 71. Coolant exits from the second radial through hole 72 and the second axial blind hole 71 into the second reservoir 31. With this configuration, coolant enters the outlet guide post 70 through the second radial through hole 72 and exits the second collector ring 30 through the second axial blind hole 71.

[0049] The inner cladding plate 11, the outer cladding plate 12, and the heat sink 13 are all made of aluminum alloy, and the heat sink 13 is welded to the inner cladding plate 11 and the outer cladding plate 12; the first current collector ring 20 and the second current collector ring 30 are both made of aluminum alloy, and the first current collector ring 20 and the second current collector ring 30 are welded to the heat sink 10.

[0050] Optionally, in Embodiment 1 of the present invention, the inner cladding plate 11 and the outer cladding plate 12 are conical shells. The shape of the inner cladding plate 11 is the same as that of the front shell of the aircraft. The material is an aluminum alloy brazed composite plate with a thickness of 1 mm. The thickness of the cooling cavity between the inner cladding plate 11 and the outer cladding plate 12 is 2 mm. The heat sink 13 has a wavy cross-section and is made of 5182 aluminum alloy. It is disposed between the inner cladding plate 11 and the outer cladding plate 12. The heat sink 13 isolates the inner cladding plate 11 and the outer cladding plate 12 into 90 longitudinal channels. The crests and troughs of the heat sink 13 are brazed to the inner cladding plate 11 and the outer cladding plate 12, respectively. The first collector ring 20 and the second collector ring 30 are annular profiles with a semi-closed cross-section and are made of 6063 aluminum alloy.

[0051] The inlet guide post 60 is made of 6082 aluminum alloy and has a first axial blind hole 61 and a first radial through hole 62. One end is equipped with a flange. The inlet guide post 60 is screwed to the first collector ring 20. There are four inlet guide posts 60, evenly arranged circumferentially on the first collector ring 20. The first distribution ring 41 is made of 7136 aluminum alloy and is a rectangular ring. The first distribution ring 41 has four holes evenly arranged circumferentially, each hole slidingly engaging with one of the four inlet guide posts 60.

[0052] The outlet guide post 70 is made of 6082 aluminum alloy and has a second axial blind hole 71 and a second radial through hole 72. One end is equipped with a flange. The outlet guide post 70 is screwed to the second collector ring 30. There are four outlet guide posts 70, evenly arranged circumferentially on the second collector ring 30. The second distribution ring 51 is made of 7136 aluminum alloy and is a rectangular ring. Four holes are evenly arranged circumferentially on the second distribution ring 51, and each hole slides into one of the four outlet guide posts 70.

[0053] The first elastic element 42 and the second elastic element 52 are springs made of 65Mn. There are four first elastic elements 42, which are disposed between the flange of the inlet guide post 60 and the first distribution ring 41. There are four second elastic elements 52, which are disposed between the flange of the outlet guide post 70 and the second distribution ring 51.

[0054] The coolant is pure water, with an inlet flow rate of 0.4 L / min. The pipeline for delivering the coolant is made of structural adhesive and is connected to the inlet guide post 60 and the outlet guide post 70, respectively. The other end is connected to the pump or the coolant storage tank, thus forming a complete circulation loop for the aircraft cooling system.

[0055] Optionally, in Embodiment 2 of the present invention, the inner cladding plate 11 and the outer cladding plate 12 are conical shells. The shape of the inner cladding plate 11 is the same as that of the front shell of the aircraft. The material is an aluminum alloy brazed composite plate with a thickness of 1 mm. The thickness of the cooling cavity between the inner cladding plate 11 and the outer cladding plate 12 is 2 mm. The heat sink 13 has a corrugated cross-section and is made of 5754 aluminum alloy. It is disposed between the inner cladding plate 11 and the outer cladding plate 12. The heat sink 13 isolates the cooling cavity between the inner cladding plate 11 and the outer cladding plate 12 into 90 longitudinal channels. The inside and outside of the heat sink are brazed to the inner cladding plate and the outer cladding plate, respectively. The first collector ring 20 and the second collector ring 30 are annular profiles with a semi-closed cross-section and are made of 3003 aluminum alloy. The upper collector pipe and the lower collector pipe are installed at both ends of the device with structural adhesive.

[0056] The inlet guide post 60 is made of 6063 aluminum alloy and has a first axial blind hole 61 and a first radial through hole 62. One end is provided with a flange. The inlet guide post 60 is screwed to the first collector ring 20. There are 6 inlet guide posts 60, which are evenly arranged in the first collector ring 20 along the circumference.

[0057] The first distribution ring 41 is made of 6082 aluminum alloy. The first distribution ring 41 is a circular ring with a rectangular cross-section. The first distribution ring 41 has 6 holes evenly arranged along the circumference. The 6 holes are slidably engaged with the 6 inlet guide posts 60 respectively.

[0058] The outlet guide post 70 is made of 6063 aluminum alloy and has a second axial blind hole 71 and a second radial through hole 72. One end is provided with a flange. The outlet guide post 70 is screwed to the second collector ring 30. There are 6 outlet guide posts 70, which are evenly arranged in the second collector ring 30 along the circumference.

[0059] The material of the second distribution ring 51 is 6082 aluminum alloy. The second distribution ring 51 is a circular ring with a rectangular cross-section. The second distribution ring 51 has 6 holes evenly arranged along the circumference. The 6 holes are slidably engaged with the 6 outlet guide posts 70 respectively.

[0060] The first elastic element 42 and the second elastic element 52 are springs made of 65Mn. There are 6 first elastic elements 42, which are disposed between the flange of the inlet guide post 60 and the first distribution ring 41. There are 6 second elastic elements 52, which are disposed between the flange of the outlet guide post 70 and the second distribution ring 51.

[0061] The coolant is kerosene, with an inlet flow rate of 0.1 L / min. The pipeline for delivering the coolant is made of structural adhesive and is connected to the inlet guide post 60 and the outlet guide post 70, respectively. The other end is connected to the pump or the coolant storage tank, thus forming a complete circulation loop for the aircraft cooling system.

[0062] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A cooling device for an aircraft, characterized in that, include: The radiator (10) includes an inner cover plate (11), an outer cover plate (12), and heat sinks (13). The inner cover plate (11) and the outer cover plate (12) are fitted together. The heat sinks (13) are distributed in the cooling cavity between the inner cover plate (11) and the outer cover plate (12). The inner cover plate (11) is attached to the front shell of the aircraft. A first collector ring (20) is disposed at one end of the radiator (10), and the first collector ring (20) has an annular first liquid storage chamber (21). The second collector ring (30) is disposed at the other end of the radiator (10), and the second collector ring (30) has an annular second liquid storage chamber (31). The first distribution component (40) is movably disposed at the first annular opening of the first liquid storage chamber (21). After the first liquid storage chamber (21) is filled with coolant, the coolant pushes the first distribution component (40) to move, and the first annular opening opens and uniformly inputs coolant into the cooling chamber. The second distribution component (50) is movably disposed at the second annular opening of the second liquid storage chamber (31). The coolant pushes the second distribution component (50) to move, the second annular opening opens and the coolant in the cooling chamber is output evenly. The heat sink (13) has a wavy plate structure. The crests and troughs of the heat sink (13) are fixedly connected to the outer covering plate (12) and the inner covering plate (11), respectively. The heat sink (13) divides the cooling cavity into multiple channels. When the first annular opening is open, the coolant in the first liquid storage cavity (21) is diverted to multiple channels. When the second annular opening is open, the coolant in the multiple channels flows into the second liquid storage cavity (31). The first distribution component (40) includes a first distribution ring (41) and a plurality of first elastic members (42). The first distribution ring (41) is movably disposed at the first annular opening to open and close the first annular opening. The plurality of first elastic members (42) are distributed on the side of the first distribution ring (41) away from the first annular opening. The first elastic members (42) and the first distribution ring (41) abut against each other. The aircraft cooling device also includes an inlet guide post (60), there are multiple inlet guide posts (60), the multiple inlet guide posts (60) are distributed circumferentially along the first collecting ring (20), one end of the inlet guide post (60) is fixedly connected to the first collecting ring (20), the inlet guide post (60) inputs coolant into the first liquid storage chamber (21); the first elastic member (42) is sleeved on the inlet guide post (60), the inlet guide post (60) guides the movement of the first distribution ring (41) and the first elastic member (42); the end of the inlet guide post (60) away from the first collecting ring (20) has a first axial blind hole (61), the side wall of the first axial blind hole (61) is provided with a first radial through hole (62), the coolant enters the first liquid storage chamber (21) from the first axial blind hole (61) and the first radial through hole (62).

2. The aircraft cooling device according to claim 1, characterized in that, When the first annular opening is closed, a portion of the first distribution assembly (40) extends into the first liquid storage chamber (21) and seals against the inner wall of the first liquid storage chamber (21). When the first annular opening is open, a first annular gap is formed between the inner side of the first distribution assembly (40) and the inner wall of the first liquid storage chamber (21), and a second annular gap is formed between the outer side of the first distribution assembly (40) and the inner wall of the first liquid storage chamber (21). The first annular gap and the second annular gap are used for the flow of coolant. When the second annular opening is closed, a portion of the second distribution assembly (50) extends into the second liquid storage chamber (31) and seals against the inner wall of the second liquid storage chamber (31). When the second annular opening is open, a third annular gap is formed between the inner side of the second distribution assembly (50) and the inner wall of the second liquid storage chamber (31), and a fourth annular gap is formed between the outer side of the second distribution assembly (50) and the inner wall of the second liquid storage chamber (31). The third and fourth annular gaps are used for the flow of coolant.

3. The aircraft cooling device according to claim 1, characterized in that, The second distribution assembly (50) includes a second distribution ring (51) and a plurality of second elastic members (52). The second distribution ring (51) is movably disposed at the second annular opening to open and close the second annular opening. The plurality of second elastic members (52) are distributed on the side of the second distribution ring (51) away from the second annular opening. The second elastic members (52) and the second distribution ring (51) abut against each other.

4. The aircraft cooling device according to claim 1, characterized in that, The aircraft cooling device also includes an outlet guide post (70), there are multiple outlet guide posts (70), the multiple outlet guide posts (70) are distributed circumferentially along the second collecting ring (30), one end of the outlet guide post (70) is fixedly connected to the second collecting ring (30), and the outlet guide post (70) outputs the coolant in the second liquid storage chamber (31).

5. The aircraft cooling device according to claim 4, characterized in that, The outlet guide post (70) has a second axial blind hole (71) at one end away from the second collector ring (30). The side wall of the second axial blind hole (71) is provided with a second radial through hole (72). Coolant is output from the second radial through hole (72) and the second axial blind hole (71) to the second reservoir (31).

6. The aircraft cooling device according to claim 1, characterized in that, The inner cladding plate (11), the outer cladding plate (12), and the heat sink (13) are all made of aluminum alloy. The heat sink (13) is welded to the inner cladding plate (11) and the outer cladding plate (12). The first current collector ring (20) and the second current collector ring (30) are both made of aluminum alloy. The first current collector ring (20) and the second current collector ring (30) are welded to the heat sink (10).

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