Aircraft liquid cooling system

Abstract

The invention relates to an aircraft liquid cooling system containing a vein-imitating liquid cooling plate runner, belongs to the technical field of electronic heat dissipation of aircrafts, and solves the problems of large occupied space and large flow resistance of the existing aircraft liquid cooling system. An aircraft liquid cooling system is characterized in that the aircraft liquid cooling system comprises cold source equipment, heat source equipment, an energy storage device and a circulating pump which are sequentially connected in series through flexible pipelines with the two ends connected with sealing joints to form a circulating loop; the cold source equipment is a part of an aircraft skin, and the skin contains a flow channel; the heat source equipment is a liquid cooling plate in the aircraft, the liquid cooling plate contains a flow channel, and the flow channel is one of a honeycomb-like liquid cooling plate flow channel, a vein-like liquid cooling plate flow channel or a cobweb-like liquid cooling plate flow channel. The aircraft liquid cooling system is small in occupied space and low in flow resistance, and the working time of electronic devices is not limited by an aircraft platform.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft electronic heat dissipation, and particularly to an aircraft liquid cooling system. Background Art

[0002] The current aircraft guidance system has gradually developed from traditional mechanical scanning technology to active phased array technology, which brings severe heat dissipation problems. At present, the volume and weight of the guidance system have been greatly reduced, and it is developing towards miniaturization, lightweight, and functional integration. However, the heat generation power of microwave and electronic devices has increased sharply, and the heat flux density has doubled. The heat flux density reaches 50W / m 2 , which poses a great challenge to the thermal management design.

[0003] The space of the existing aircraft platform is compact, resulting in the aircraft being unable to provide sufficient space and heat sink. The increase in the integration of electronic devices leads to a concentrated heat generation position and an increase in thermal resistance. The faster flight speed results in significant aerodynamic heat and a rapid increase in the cabin temperature. The long startup time and high power consumption of electronic equipment lead to a significant temperature accumulation effect, an increase in heat flux density, and an increase in total heat generation. This poses higher requirements for the heat dissipation of the aircraft platform.

[0004] The existing aircraft platform generally adopts a passive heat dissipation method, using phase change materials to control the temperature rise of electronic devices. The problem is that the heat capacity of the phase change materials directly determines the startup time of the aircraft. A large amount of phase change materials occupy the internal volume and weight of the aircraft, and it is only suitable for platforms with short-term operation and low initial temperature, and the applicable range is limited. Therefore, it is urgent to provide a system that adopts an active heat dissipation method, which can simultaneously meet the requirements of small space occupied by the aircraft heat dissipation system on the aircraft platform, long continuous working time, small flow resistance under high heat flux density, and large heat dissipation area under the conditions of high heat transfer and low flow resistance, which is of great significance. Summary of the Invention

[0005] In view of the above analysis, the embodiments of the present invention aim to provide an aircraft liquid cooling system to solve the problems that the existing aircraft liquid cooling system occupies a large space on the aircraft platform and has a large flow resistance when working under high power, long working hours, and high heat flux density.

[0006] The object of the present invention is mainly achieved by the following technical solutions:

[0007] An aircraft liquid cooling system includes a cold source device, a heat source device, an energy storage device, and a circulation pump. The cold source device, the heat source device, the energy storage device, and the circulation pump are sequentially connected in series through flexible pipelines with sealed joints at both ends to form a circulation loop;

[0008] The cold source device is a part of the aircraft skin, and the skin contains a flow channel;

[0009] The heat source device is an internal liquid cooling plate of an aircraft. The liquid cooling plate contains flow channels, and the flow channels are one of honeycomb-shaped liquid cooling plate flow channels, vein-shaped liquid cooling plate flow channels, or cobweb-shaped liquid cooling plate flow channels.

[0010] Further, the honeycomb-shaped liquid cooling plate flow channel is a rhombic honeycomb shape;

[0011] The honeycomb-shaped liquid cooling plate flow channel includes a honeycomb-shaped flow channel network, a first collecting flow channel, a second collecting flow channel, parallel straight flow channels, a flow channel inlet, and a flow channel outlet;

[0012] The first collecting flow channel and the second collecting flow channel are parallel and symmetrically arranged on opposite sides of the rhombus.

[0013] Further, the vein-shaped liquid cooling plate flow channel includes a vein-shaped flow channel network, a main flow channel, and a collecting flow channel;

[0014] The main flow channel is arranged at the middle position of the rectangular liquid cooling plate and is connected to the vein-shaped flow channel network. The vein-shaped flow channel network is composed of M micro-channel units arranged in a folded line shape and is symmetrically distributed above and below the main flow channel;

[0015] The main flow channel and the collecting flow channel are perpendicular to each other.

[0016] Further, the cobweb-shaped liquid cooling plate flow channel includes a first flow channel unit, a second flow channel unit, and a main flow channel;

[0017] The second flow channel unit has the same structure as the first flow channel unit and is symmetrically distributed on both sides of the main flow channel, jointly forming a cobweb-shaped flow channel network;

[0018] The main flow channel is arranged at the middle position of the rectangular liquid cooling plate and is respectively connected to the first flow channel unit and the second flow channel unit. Along the direction from the flow channel inlet to the flow channel outlet, the main flow channel has a constant diameter.

[0019] Further, the first collecting flow channel is connected to the honeycomb-shaped flow channel network through N parallel straight flow channels, and the second collecting flow channel is connected to the honeycomb-shaped flow channel network through N parallel straight flow channels.

[0020] Further, the folded line-shaped micro-channel unit includes an adjacent straight flow channel part and an inclined flow channel part. The straight flow channel parts are parallel to each other, the inclined flow channel parts are parallel to each other, the outlet ends of the straight flow channel parts are flush, and are connected to the collecting flow channel at the outlet end.

[0021] Further, the first flow channel unit is in the shape of an isosceles trapezoid and includes P isosceles trapezoid-shaped micro-channels distributed layer by layer, and the P isosceles trapezoid-shaped micro-channels distributed layer by layer are parallel to each other.

[0022] Further, the circulation pump is a centrifugal pump or a gear pump.

[0023] Further, the accumulator is a metal bellows type accumulator or a rubber bladder type accumulator.

[0024] Further, the flexible pipeline has a layered structure, with a polytetrafluoroethylene inner layer and a stainless steel braid outer layer. The two ends of the pipeline are connected to the sealing joint through a swaging process, and the sealing structure is a plunger type or an end face sealing type.

[0025] Compared with the prior art, the present invention can at least achieve one of the following beneficial effects:

[0026] 1. In the aircraft liquid cooling system of the present invention, when the occupied space in the aircraft platform cabin is relatively small, the working duration of the electronic devices is not restricted by the aircraft platform; it realizes the application requirements of the aircraft liquid cooling system with small occupied space in the aircraft platform, long continuous working time, small flow resistance, and large heat dissipation area when working under high heat flux density.

[0027] 2. When the aircraft liquid cooling system of the present invention is applied to a heating device with a heat flux density of 50 W / cm 2 in the aircraft platform, the flow resistance ≤ 1000 Pa, the heat dissipation area ≥ 25000 mm 2 , and the maximum temperature of the heat source ≤ 105 °C.

[0028] 3. The aircraft liquid cooling system of the present invention is applicable to the heat dissipation structures of all ground, vehicle-mounted, shipborne, missile-borne, satellite-borne, and airborne platforms using a single-phase liquid cooling circulation system; it is applicable to heat exchanger systems in various military and civilian application scenarios; it is applicable to various industries involving the flow of liquid working media, such as aerospace, construction, environmental control, petroleum, and chemical industries.

[0029] In the present invention, the above technical solutions can also be combined with each other to achieve more preferred combination schemes. Other features and advantages of the present invention will be described in the subsequent specification, and some advantages can be made obvious from the specification or understood by implementing the present invention. The objectives and other advantages of the present invention can be achieved and obtained from the content specifically pointed out in the specification and the drawings. Description of the Drawings

[0030] The drawings are only for the purpose of showing specific embodiments and are not considered to be a limitation of the present invention. Throughout the drawings, the same reference signs denote the same components.

[0031] Figure 1 It is a schematic diagram of the composition of the aircraft liquid cooling system of the present invention;

[0032] Figure 2 It is a schematic diagram of the flow channels of the honeycomb-like liquid cooling plate of the present invention;

[0033] Figure 3 Schematic diagram of the vein - like liquid - cooling plate flow channel of the present invention;

[0034] Figure 4 Schematic diagram of the cobweb - like liquid - cooling plate flow channel of the present invention;

[0035] Figure 5 Pressure contour map of the honeycomb - like liquid - cooling plate flow channel in Embodiment 1 of the present invention;

[0036] Figure 6 Temperature contour map of the honeycomb - like liquid - cooling plate flow channel in Embodiment 1 of the present invention;

[0037] Figure 7 Pressure contour map of the vein - like liquid - cooling plate flow channel in Embodiment 2 of the present invention;

[0038] Figure 8 Temperature contour map of the vein - like liquid - cooling plate flow channel in Embodiment 2 of the present invention;

[0039] Figure 9 Pressure contour map of the cobweb - like liquid - cooling plate flow channel in Embodiment 1 of the present invention;

[0040] Figure 10 Temperature contour map of the cobweb - like liquid - cooling plate flow channel in Embodiment 1 of the present invention;

[0041] Figure 11 Structural diagram of the ground verification system in Embodiment 4 of the present invention.

[0042] Reference numerals: 1 - cold source equipment; 2 - heat source equipment; 3 - energy storage device; 4 - circulation pump; 5 - flexible pipeline;

[0043] 6 - flow channel inlet of the honeycomb - like liquid - cooling plate flow channel; 7 - flow channel outlet of the honeycomb - like liquid - cooling plate flow channel; 8 - first converging flow channel of the honeycomb - like liquid - cooling plate flow channel; 9 - second converging flow channel of the honeycomb - like liquid - cooling plate flow channel; 10 - honeycomb - type flow channel network; 11 - parallel straight flow channels of the honeycomb - like liquid - cooling plate flow channel; A1 - A1 - cross - section direction of the honeycomb - type flow channel network; W1 - rectangular width of the cross - section of the honeycomb - like liquid - cooling plate flow channel in the A1 - A1 direction; H1 - rectangular height of the cross - section of the honeycomb - like liquid - cooling plate flow channel in the A1 - A1 direction; K1 - flow channel spacing of the honeycomb - like liquid - cooling plate flow channel;

[0044] 12 - Flow channel inlet of the vein - like liquid - cooled plate flow channel; 13 - Flow channel outlet of the vein - like liquid - cooled plate flow channel; 14 - Main flow channel of the vein - like liquid - cooled plate flow channel; 15 - Converging flow channel of the vein - like liquid - cooled plate flow channel; 16 - Vein - like flow channel network; 17 - Straight flow channel in the zigzag - shaped micro - flow channel unit of the vein - like liquid - cooled plate flow channel; 18 - Oblique flow channel in the zigzag - shaped micro - flow channel unit of the vein - like liquid - cooled plate flow channel; A2 - A2 - Section direction of the vein - like liquid - cooled plate flow channel; W3 - Rectangular width of the A - A direction section of the vein - like liquid - cooled plate flow channel; H2 - Rectangular height of the A - A direction section of the vein - like liquid - cooled plate flow channel; K2 - Flow channel spacing of the zigzag - shaped micro - flow channel unit of the vein - like liquid - cooled plate flow channel; W4 - Width of the main flow channel of the vein - like liquid - cooled plate flow channel; W5 - Width of the converging flow channel of the vein - like liquid - cooled plate flow channel; ɑ1 - Angle between the main flow channel of the vein - like liquid - cooled plate flow channel and the zigzag - shaped micro - flow channel unit on the same side of the main flow channel; β1 - Taper angle of the end wall of the main flow channel of the vein - like liquid - cooled plate flow channel;

[0045] 19 - Flow channel inlet of the spider - web - like liquid - cooled plate flow channel; 20 - Flow channel outlet of the spider - web - like liquid - cooled plate flow channel; 21 - Main flow channel at the inlet end of the spider - web - like liquid - cooled plate flow channel; 22 - Main flow channel at the outlet end of the spider - web - like liquid - cooled plate flow channel; 23 - Flow - around structure of the spider - web - like liquid - cooled plate flow channel; 24 - First flow channel unit of the spider - web - like liquid - cooled plate flow channel; 25 - Second flow channel unit of the spider - web - like liquid - cooled plate flow channel; A3 - A3 - Section direction of the spider - web - like liquid - cooled plate flow channel; W6 - Rectangular width of the A - A direction section of the spider - web - like liquid - cooled plate flow channel; H3 - Rectangular height of the A - A direction section of the spider - web - like liquid - cooled plate flow channel; K3 - Spacing of the spider - web - like liquid - cooled plate flow channel; W7 - Width of the main flow channel of the spider - web - like liquid - cooled plate flow channel; ɑ2 - Angle between the oblique - linear micro - flow channel and the main flow channel in the isosceles trapezoid - shaped first flow channel unit of the spider - web - like liquid - cooled plate flow channel; β2 - Taper angle of the end wall of the flow - around structure of the spider - web - like liquid - cooled plate flow channel. Detailed implementation manners

[0046] The following combines the accompanying drawings to specifically describe the preferred embodiments of the present invention. Among them, the accompanying drawings form a part of this application and are used together with the embodiments of the present invention to explain the principle of the present invention, and are not used to limit the scope of the present invention.

[0047] The present invention provides an aircraft liquid - cooling system, including a cold - source device, a heat - source device, an energy storage device, and a circulation pump. The cold - source device, the heat - source device, the energy storage device, and the circulation pump are all connected in series through flexible pipelines with sealed joints at both ends to form a circulation loop; as Figure 1 shown.

[0048] The cold source device is a part of the aircraft skin, and its specific position can be flexibly selected according to the actual spatial structure of the aircraft; the area of the skin is 0.1 - 1 m 2 , and a skin flow channel is arranged therein, which is the cold source device of the aircraft liquid cooling system.

[0049] Preferably, if the length of the skin to be selected is L, its position is set at: the distance from the device to be cooled ≤ 2L. The flow channel flows through the skin through the inlet and outlet on the inner side of the cabin, and exchanges heat with the outside through the skin, so as to achieve the refrigeration effect.

[0050] The material of the cold source device is one of stainless steel, superalloy, and titanium alloy.

[0051] The heat source device is in direct contact with the heat-generating electronic device for heat conduction, and is cooled by the low-temperature fluid coming from the cold source device to ensure the stable operation of the electronic device; the material is one of aluminum alloy, stainless steel, and red copper; the heat source device contains one of a honeycomb-like liquid cooling plate flow channel, a vein-like liquid cooling plate flow channel, or a spider-web-like liquid cooling plate flow channel.

[0052] The energy storage device is a metal bellows type energy storage device or a rubber airbag type energy storage device. The energy storage device mainly consists of a bellows assembly (including a liquid side head, a bellows, an end cover, and a guide ring), a cylinder body, a gas side head, an inflation valve, etc. The inner side of the bellows assembly is filled with an ethylene glycol aqueous solution working medium, and a certain amount of helium-nitrogen mixed gas is encapsulated on the gas side. When the liquid working medium in the fluid circuit contracts due to temperature reduction or decreases due to working medium leakage, under the action of the gas side pressure, the liquid side part of the energy storage device will be pressed into the fluid circuit to participate in the circulation of the fluid circuit; on the contrary, when the liquid working medium in the fluid circuit expands due to temperature increase, part of the liquid working medium is pressed back into the energy storage device, and the gas on the gas side is compressed. Thus, the purpose of effectively controlling the working pressure range of the fluid circuit is achieved, and the safe and stable operation of the fluid circuit is ensured.

[0053] As a pressure stabilizing element of the system, the energy storage device needs to provide the inlet pressure of the circulation pump on the one hand to ensure that the circulation pump works within the normal pressure range. Secondly, the energy storage device can absorb the pressure pulsation of the system, make the system operate smoothly, and avoid the system from generating vibration. On the other hand, when the system working conditions change, it compensates for the volume change of the system working medium caused by temperature change and maintains the pressure stability.

[0054] The circulation pump is a centrifugal pump or a gear pump, and is composed of a motor, an impeller, a compression nut, a volute, etc. The connection between the housing and the motor is statically sealed by two O-ring seals in the middle, removing the traditional shaft seal, reducing the number of seals, and improving the product life. The wet brushless DC motor is adopted. When working, the medium can enter the motor interior to cool the motor. The interior of the motor is sealed and isolated by a shielding cover, and the sealing performance can reach 1x10 -6 Pa·m2 / s.

[0055] The flexible pipeline is a layered structure, with a polytetrafluoroethylene inner layer and a stainless steel braid outer layer. Both ends of the pipeline are connected to the sealing joints through a swaging process, and the sealing structure is a plunger type or an end face sealing type.

[0056] Specifically, the honeycomb-like liquid cooling plate flow channel in the heat source device is as Figure 2 shown:

[0057] The honeycomb-like liquid cooling plate flow channel is arranged in a rectangular liquid cooling plate and includes a honeycomb-like flow channel network, a first collecting flow channel, a second collecting flow channel, parallel straight flow channels, a flow channel inlet, and a flow channel outlet;

[0058] The flow channel inlet and the flow channel outlet are symmetrically arranged at the centers of the left and right sides of the liquid cooling plate respectively. Among them, the flow channel inlet is arranged at the center of the right side of the liquid cooling plate and is connected to the first collecting flow channel; the flow channel outlet is arranged at the center of the left side of the liquid cooling plate and is connected to the second collecting flow channel;

[0059] The first collecting flow channel and the second collecting flow channel are respectively connected to N parallel straight flow channels, and the parallel straight flow channels are connected to the flow channel network forming the honeycomb;

[0060] Viewed from the overall structure, the liquid cooling plate flow channel is a rhombus-shaped honeycomb. The first collecting flow channel and the second collecting flow channel are respectively parallel and symmetrically arranged on the opposite sides of the rhombus. The first collecting flow channel is connected to the honeycomb-like flow channel network through N parallel straight flow channels, and the second collecting flow channel is connected to the honeycomb-like flow channel network through N parallel straight flow channels; the flow channel inlet is arranged at the middle position of the first collecting flow channel; the flow channel outlet is arranged at the middle position of the second collecting flow channel, and the axes of the flow channel inlet and the flow channel outlet are parallel and pass through the center of the rhombus.

[0061] The honeycomb-like flow channel network forms the main flow channel, which is axially symmetric as a whole and is composed of the arrangement of several regular hexagon-shaped micro flow channel units. Adjacent micro flow channel units share a common flow channel pipe, and each unit is interconnected through the common flow channel, forming a honeycomb-like shape as a whole.

[0062] Particularly, the lengths of the N parallel straight flow channels connecting the first collecting flow channel and the honeycomb-like flow channel network are equal to the side length of the regular hexagon of the honeycomb-like flow channel network. The lengths of the N parallel straight flow channels connecting the second collecting flow channel and the honeycomb-like flow channel network are also equal to the side length of the regular hexagon of the honeycomb-like flow channel network. And if the number of regular hexagons on a single side of the rhombus-shaped honeycomb-like liquid cooling plate flow channel is n, then the number N of the parallel straight flow channels connecting the first collecting flow channel or the second collecting flow channel and the honeycomb-like flow channel network is n + 1.

[0063] Regarding the setting of the length and quantity of the parallel straight channels, it can be understood that the first converging channel constitutes the set of adjacent two sides of multiple regular hexagons on a single side of the rhombus-shaped honeycomb liquid-cooling plate channel, and the channel width of the first converging channel is set to be much larger than the channel width of the regular hexagon in the honeycomb channel network; the second converging channel constitutes the set of adjacent two sides of multiple regular hexagons on a single side of the rhombus-shaped honeycomb liquid-cooling plate channel, and the channel width of the second converging channel is set to be much larger than the channel width of the regular hexagon in the honeycomb channel network. When the medium flows into the first converging channel from the channel inlet, it can uniformly and stably fill each channel of the honeycomb channel network and uniformly and stably converge into the second converging channel. When the liquid-cooling plate channel satisfies the above structure, when the medium flows into the liquid-cooling plate channel from the channel inlet, the medium can traverse the entire liquid-cooling plate with a relatively small flow resistance along with the honeycomb channel network, and at the same time, the temperature distribution of the liquid-cooling plate can be made uniform.

[0064] It should be noted that along the direction away from the channel inlet, the number of regular hexagons in the next vertical-level regular hexagon-shaped micro-channel unit connected to N parallel straight channels is N, and the number of regular hexagons in the next vertical-level regular hexagon-shaped micro-channel unit is N + 1. The number of regular hexagons in each vertical-level hexagonal micro-channel unit increases by one level by level until the distance between a certain vertical-level regular hexagon-shaped micro-channel unit and the upper and lower sides of the liquid-cooling plate ≤ 4 mm, then the increase in the number of regular hexagons in the vertical regular hexagon-shaped micro-channel unit stops, and then the number of regular hexagons in the next vertical-level regular hexagon-shaped micro-channel unit decreases level by level until the number of regular hexagons in the last vertical-level regular hexagon-shaped micro-channel unit is N, ensuring that the overall honeycomb channel network is axisymmetric and covers the entire liquid-cooling plate; preferably, N > 5. This honeycomb channel network structure ensures that when the medium flows into the first converging channel from the channel inlet, it will not flow away quickly in one channel. When the entire channel is filled with the medium after a period of time, the fluid inflow and outflow reach equilibrium, and the medium in the liquid-cooling plate fills the entire channel at any time and flows in each channel.

[0065] For the channels in the parallel straight channels and the regular hexagon-shaped micro-channel units in the honeycomb channel network, the channel width is W1, the channel height is H1, and the channel spacing is K1, satisfying 1.5 * W1 ≤ K1 ≤ 3 * W1. Meeting this condition for the channel spacing can improve the heat dissipation effect of the liquid-cooling plate and balance the convective heat transfer amount and heat conduction amount of the liquid-cooling plate.

[0066] The equivalent diameters of the channel inlet and the channel outlet are the same, satisfying D1 ≥ N * W1. Meeting this condition for the diameters of the channel inlet and the channel outlet can ensure sufficient flow supply of the medium at the channel inlet and outlet.

[0067] The first converging channel and the second converging channel are rectangular, with equal widths, both being W2, and W2 = 1.5N * W1. Meeting this condition can further ensure that the resistance of the medium flowing into the above-mentioned converging channel is smaller and the flow rate is larger compared to the flow channels of the honeycomb-shaped flow channel network, and the medium flows uniformly and stably in the flow channel network.

[0068] Specifically, the leaf vein-like liquid cooling plate flow channel in the heat source device is as Figure 3 shown:

[0069] The leaf vein-like liquid cooling plate flow channel is arranged in a rectangular liquid cooling plate, and includes a leaf vein-like flow channel network, a main flow channel, a converging channel, a flow channel inlet and a flow channel outlet;

[0070] The flow channel inlet and the flow channel outlet are symmetrically arranged at the centers of the left and right side edges of the liquid cooling plate respectively. Among them, the flow channel inlet is arranged at the center of the right side edge of the liquid cooling plate and is connected to the main flow channel; the flow channel outlet is arranged at the center of the left side plate of the liquid cooling plate and is connected to the converging channel;

[0071] The main flow channel is arranged at the middle position of the rectangular liquid cooling plate and is connected to the flow channel network forming the leaf veins. The main flow channel is indirectly connected to the converging channel through the leaf vein-like flow channel network; the whole leaf vein-like flow channel network is composed of M micro-channel units arranged in a zigzag shape and is symmetrically distributed up and down on both sides of the main flow channel; among them, the zigzag-shaped micro-channel units on the same side of the main flow channel are separated from each other by partitions, and the zigzag-shaped micro-channel units on the same side of the main flow channel are parallel to each other;

[0072] The zigzag-shaped micro-channel unit includes an adjacent straight flow channel part and an inclined flow channel part. The straight flow channel parts are parallel to each other, the inclined flow channel parts are parallel to each other, and the outlet ends of the straight flow channel parts are flush and are connected to the converging channel at the outlet end.

[0073] The included angle ɑ1 between the main flow channel and the inclined flow channel part of the zigzag-shaped micro-channel unit on the same side of the main flow channel satisfies 30° ≤ ɑ1 ≤ 60°;

[0074] The main flow channel and the converging channel are perpendicular to each other, and the axis of the main flow channel coincides with the axes of the flow channel inlet and the flow channel outlet; the longitudinal section of the main flow channel is rectangular, and the transverse section of the converging channel is rectangular.

[0075] It should be noted that the length of the main runner is half of the distance between the runner inlet and the runner outlet, that is, along the direction from the runner inlet to the runner outlet, the main runner extends from the runner inlet to the center of the entire cold plate runner. Along the direction from the runner inlet to the runner outlet, the inclined runners of the micro-channel units with a broken-line shape are arranged in parallel in sequence, extending along the direction away from the main runner. The extension ends of the inclined runners arranged in parallel on the same side are collinear, and the angle ɑ1 between the extension ends and the axis of the cold plate runner, that is, the angle between the main runner and the inclined runner part of the micro-channel unit with a broken-line shape on the same side of the main runner, satisfies 30°≤ɑ1≤60°; the straight-channel part of the micro-channel unit with a broken-line shape extends along the direction from the runner inlet to the runner outlet from the extension end of the inclined runner.

[0076] Among them, along the direction from the runner inlet to the runner outlet, the end wall surface of the main runner is conical, and the cone angle is β1 = 2ɑ1. Such a structural design is beneficial to the diversion of the main runner here, avoiding the generation of vortices and separated flows that cause an increase in flow resistance.

[0077] Preferably, M > 5; this vein-like flow channel network structure ensures that when the medium flows into the main runner from the runner inlet, it will not flow away quickly in one flow channel, but flow along the main runner to the left. During this period, the medium is successively distributed into the micro-channel units with a broken-line shape on both sides of the main runner. The medium entering the micro-channel units with a broken-line shape converges in the converging channels and then flows out from the runner outlet. When the entire flow channel is filled with the medium for a period of time, the fluid inflow and outflow reach equilibrium, and the medium in the liquid cooling plate fills the entire channel at any time and flows in each channel.

[0078] In the flow channels in the micro-channel units with a broken-line shape in the vein-like flow channel network, the cross-section facing the runner inlet direction is rectangular, the flow channel width is W3, the flow channel height is H2, and the flow channel spacing is K2, satisfying 1.5*W3≤K2≤3*W3, in mm. Meeting this condition for the flow channel spacing can improve the heat dissipation effect of the liquid cooling plate and make the convective heat transfer amount and heat conduction amount of the liquid cooling plate balanced.

[0079] The width of the main runner is W4, the length is L1, the width of the converging channel is W5, the length is L2, and the equivalent diameter of the runner inlet and the runner outlet is D2, satisfying W4 = W5 = D2≥M*W3, L2 = M*W3+(M - 1)*K2, and L1 is half of the distance between the runner inlet and the runner outlet; meeting this condition for the dimensions of the main runner and the converging channel and the equivalent diameter of the runner inlet and the runner outlet can ensure sufficient flow supply at the runner inlet and outlet and balanced flow distribution in the vein-like flow channel network.

[0080] Specifically, the spider-web-like liquid cooling plate runner in the heat source device is as Figure 4 shown:

[0081] The cobweb-like liquid cooling plate flow channel is arranged in a rectangular liquid cooling plate and includes a first flow channel unit, a second flow channel unit, a main flow channel, a flow channel inlet, and a flow channel outlet;

[0082] The flow channel inlet and the flow channel outlet are symmetrically arranged at the centers of the left and right side edges of the liquid cooling plate respectively. Among them, the flow channel inlet is arranged at the center of the right side edge of the liquid cooling plate and is connected to the main flow channel; the flow channel outlet is arranged at the center of the left side plate of the liquid cooling plate and is connected to the main flow channel;

[0083] The longitudinal section of the main flow channel is rectangular and is arranged at the middle position of the rectangular liquid cooling plate and is respectively connected to the first flow channel unit and the second flow channel unit;

[0084] The second flow channel unit and the first flow channel unit have the same structure and are symmetrically distributed on both sides of the main flow channel, jointly forming a cobweb-like flow channel network; along the direction from the flow channel inlet to the flow channel outlet, the main flow channel has a constant diameter.

[0085] The main flow channel includes: an inlet-end main flow channel and an outlet-end main flow channel. The inlet-end main flow channel is connected to the outlet-end main flow channel through isosceles trapezoid-shaped first flow channel units and second flow channel units;

[0086] The inlet-end main flow channel and the outlet-end main flow channel are coaxially arranged, and a flow-around structure is arranged at the axis center position from the flow channel inlet to the flow channel outlet. Part of the outer surface of the flow-around structure forms an innermost layer of isosceles trapezoid-shaped micro-channels with the innermost layer of the first flow channel unit and the second flow channel unit;

[0087] The first flow channel unit is isosceles trapezoid-shaped and includes P isosceles trapezoid-shaped micro-channels distributed layer by layer. The P isosceles trapezoid-shaped micro-channels distributed layer by layer are parallel to each other; along the direction of the main flow channel, the sizes of the isosceles trapezoid-shaped micro-channels distributed layer by layer decrease in an arithmetic progression step by step; each isosceles trapezoid-shaped micro-channel includes two oblique linear micro-channels and one horizontal linear micro-channel. The two oblique linear micro-channels are connected to the main flow channel, and the included angle ɑ2 between them and the main flow channel satisfies 30° ≤ ɑ2 ≤ 60°;

[0088] Along the axis direction, the end wall surface of the flow-around structure is conical, and the cone angle is β2 = 2ɑ2. Such a structural design is beneficial to the diversion of the inlet-end main flow channel and the outlet-end main flow channel, avoiding the generation of vortices and separated flows that cause an increase in flow resistance.

[0089] The cross-section of the isosceles trapezoid-shaped micro-channel facing the flow channel inlet direction is rectangular, the flow channel width is W6, the flow channel height is H3, and the flow channel spacing is K3, satisfying 1.5 * W6 ≤ K3 ≤ 3 * W6, in mm. Meeting this condition for the flow channel spacing can improve the heat dissipation effect of the liquid cooling plate and make the convective heat transfer amount and heat conduction amount of the liquid cooling plate achieve balance.

[0090] The width of the main runner is W7, and the equivalent diameters D3 of the runner inlet and the runner outlet satisfy W7 = D3 ≥ P * W6; the length of the main runner is the same as the length of the liquid cooling plate; the dimensions of the main runner and the equivalent diameters of the runner inlet and the runner outlet meet this condition, which can ensure sufficient flow supply at the runner inlet and outlet and balanced flow distribution in the spider-web-like runner network.

[0091] Preferably, P > 12; this spider-web-like runner network structure ensures that when the medium flows into the main runner from the runner inlet, it will not flow away quickly in one runner, but flow upward and downward along the main runner. During this period, the medium is successively distributed into the isosceles trapezoidal micro-runners on both sides of the main runner. The medium entering the isosceles trapezoidal micro-runners converges again in the main runner and then flows out from the runner outlet. When the entire runner is filled with the medium after a period of time, the fluid inflow and outflow reach equilibrium, and the medium in the liquid cooling plate fills the entire channel at any time and flows in each channel.

[0092] When the liquid cooling system of the present invention is used for heat dissipation of an aircraft, the circulation pump provides power to drive the working medium to circulate at a certain flow rate. At the heat source device (i.e., the internal liquid cooling plate of the aircraft containing the vein-like liquid cooling plate runner or the honeycomb-like liquid cooling plate runner), the heating device transfers heat to the liquid cooling plate through heat conduction. The working medium inside the liquid cooling plate takes away the heat and flows to the cold source device. The skin runner in the cold source device flows through the skin through the inlets and outlets on the inner side of the cabin, and exchanges heat with the outside through the skin, and the ram air outside the skin takes it away, thus achieving the refrigeration effect.

[0093] Under the condition of occupying a relatively small space in the aircraft platform cabin, the working duration of the electronic devices of the liquid cooling system of the present invention is not restricted by the aircraft platform; it realizes the application requirements of the aircraft liquid cooling system for small occupied space of the aircraft platform, long continuous working time, small flow resistance, and large heat dissipation area when working under high heat flux density; for the liquid cooling system of the aircraft of the present invention, when applied to the heating device with a heat flux density of 50 W / cm 2 the flow resistance ≤ 1000 Pa, the heat dissipation area ≥ 25000 mm 2 , and the maximum temperature of the heat source ≤ 105 °C.

[0094] The aircraft liquid cooling system of the present invention is applicable to the heat dissipation structures of all ground, vehicle-mounted, shipborne, missile-borne, satellite-borne, and airborne platforms using single-phase liquid cooling circulation systems; applicable to heat exchanger systems in various military and civilian application scenarios; applicable to various industries involving the flow of liquid working media such as aerospace, architecture, environmental control, petroleum, and chemical industries.

[0095] Embodiment 1

[0096] The aircraft liquid cooling system of this embodiment includes a cold source device, a heat source device, a storage device, and a circulation pump. The cold source device, the heat source device, the storage device, and the circulation pump are sequentially connected in series through flexible pipelines with sealed joints at both ends to form a circulation loop; as Figure 1 shown.

[0097] The cold source device is a part of the aircraft skin, and the area of the skin is 0.5 m 2 . A skin flow channel is arranged therein, which is the cold source device of the aircraft liquid cooling system. The length of the selected skin is 1 m, and its position is set at: the distance from the device to be cooled ≤ 2 m. The material is titanium alloy.

[0098] The heat source device is in direct contact with the heat-generating electronic device for heat conduction, and is cooled by the low-temperature fluid coming from the cold source device to ensure the stable operation of the electronic device; the material is aluminum alloy; the heat source device is an internal liquid cooling plate of the aircraft with a honeycomb-like liquid cooling plate flow channel. The honeycomb-like liquid cooling plate flow channel is arranged in a rectangular liquid cooling plate, as Figure 2 shown, and includes a honeycomb-like flow channel network, a first collecting flow channel, a second collecting flow channel, parallel straight flow channels, a flow channel inlet, and a flow channel outlet;

[0099] The flow channel inlet and the flow channel outlet are symmetrically arranged at the centers of the left and right sides of the liquid cooling plate respectively. Among them, the flow channel inlet is arranged at the center of the right side of the liquid cooling plate and is connected to the first collecting flow channel; the flow channel outlet is arranged at the center of the left side plate of the liquid cooling plate and is connected to the second collecting flow channel;

[0100] The first collecting flow channel and the second collecting flow channel are respectively connected to 6 parallel straight flow channels, and the parallel straight flow channels are connected to the flow channel network forming a honeycomb;

[0101] From the overall structure, the liquid cooling plate flow channel is a rhombus-shaped honeycomb. The first collecting flow channel and the second collecting flow channel are respectively parallel and symmetrically arranged on the opposite sides of the rhombus. The first collecting flow channel is connected to the honeycomb-like flow channel network through 6 parallel straight flow channels, and the second collecting flow channel is connected to the honeycomb-like flow channel network through 6 parallel straight flow channels; the flow channel inlet is arranged at the middle position of the first collecting flow channel; the flow channel outlet is arranged at the middle position of the second collecting flow channel, and the axes of the flow channel inlet and the flow channel outlet are parallel and pass through the center of the rhombus.

[0102] The honeycomb-like flow channel network constitutes the main flow channel, which is axially symmetric as a whole and is composed of 61 regular hexagonal micro-flow channel units arranged. Adjacent micro-flow channel units share a common flow channel pipe, and each unit is interconnected through the common flow channel, forming a honeycomb-like shape as a whole.

[0103] Specifically, the lengths of the six parallel straight channels connecting the first collecting channel and the honeycomb channel network are equal to the side length of the regular hexagon of the honeycomb channel network. The lengths of the six parallel straight channels connecting the second collecting channel and the honeycomb channel network are also equal to the side length of the regular hexagon of the honeycomb channel network. And if the number n of regular hexagons on a single side of the rhombic honeycomb liquid cooling plate channel is 5, then the number N of parallel straight channels connecting the first collecting channel or the second collecting channel and the honeycomb channel network is n + 1, that is, N is 6.

[0104] The overall honeycomb channel network is axisymmetric and is composed of 61 regular hexagon-shaped micro-channel units arranged. Adjacent micro-channel units share a common channel tube, and each unit is interconnected through the common channel, forming a honeycomb-like shape as a whole.

[0105] The first collecting channel constitutes the set of adjacent two sides of the 5 regular hexagons on a single side of the rhombic honeycomb liquid cooling plate channel, and the channel width of the first collecting channel is set to be much larger than the channel width of the regular hexagon of the honeycomb channel network; the second collecting channel constitutes the set of adjacent two sides of the 5 regular hexagons on a single side of the rhombic honeycomb liquid cooling plate channel, and the channel width of the second collecting channel is set to be much larger than the channel width of the regular hexagon of the honeycomb channel network

[0106] It should be noted that along the direction away from the channel inlet, the number of regular hexagons in the regular hexagon-shaped micro-channel unit of the next vertical layer connected to the six parallel straight channels is 6, and the number of regular hexagons in the regular hexagon-shaped micro-channel unit of the next vertical layer is 7. The number of regular hexagons in each vertical layer of the hexagonal micro-channel unit increases by one level by level until the distance between a certain vertical layer of the regular hexagon-shaped micro-channel unit and the upper and lower sides of the liquid cooling plate ≤ 4 mm, then the increase in the number of regular hexagons in the vertical regular hexagon-shaped micro-channel unit stops, and then the number of regular hexagons in the next vertical layer of the regular hexagon-shaped micro-channel unit decreases level by level until the number of regular hexagons in the regular hexagon-shaped micro-channel unit of the last vertical layer is 6, ensuring that the overall honeycomb channel network is axisymmetric and covers the entire liquid cooling plate;

[0107] For the channels in the parallel straight channels and the regular hexagon-shaped micro-channel units of the honeycomb channel network, the channel width is W1 = 1 mm, the channel height is H1 = 1 mm, and the channel spacing is K1 = 3 mm, satisfying 1.5 * W1 ≤ K1 ≤ 3 * W1.

[0108] The equivalent diameters of the channel inlet and the channel outlet are the same, D1 = 6 mm, satisfying D1 ≥ N * W1.

[0109] The first collecting channel and the second collecting channel are rectangular, and their width is W2 = 9 mm, and W2 satisfies W2 = 1.5N * W1.

[0110] The energy accumulator is a metal bellows type energy accumulator.

[0111] The circulation pump is a gear pump, which is composed of a motor, an impeller, a compression nut, a volute casing, etc.

[0112] The inner layer of the flexible pipeline is made of polytetrafluoroethylene, and the outer layer is stainless steel braiding. Special sealing joints are connected at both ends of the pipeline using a swaging process, and the sealing structure is an end face sealing type.

[0113] The pressure contour map of the honeycomb-like liquid cooling plate flow channel in this embodiment is as Figure 5 shown. It can be seen from the figure that the flow resistance obtained from the simulation calculation of the honeycomb-like liquid cooling plate flow channel in this embodiment is 844.92 Pa.

[0114] The temperature contour map of the honeycomb-like liquid cooling plate flow channel in this embodiment is as Figure 6 shown. It can be seen from the figure that the highest temperature of the heat source obtained from the simulation calculation of the honeycomb-like liquid cooling plate flow channel in this embodiment is 68.41 °C.

[0115] Embodiment 2

[0116] The liquid cooling system of the aircraft in this embodiment has a structure similar to that of Embodiment 1. The difference lies in that the liquid cooling plate flow channel inside the heat source device is different. The heat source device in this embodiment contains a vein-like liquid cooling plate flow channel.

[0117] The vein-like liquid cooling plate flow channel is arranged in a rectangular liquid cooling plate, as Figure 3 shown:

[0118] It includes a vein-like flow channel network, a main flow channel, a converging flow channel, a flow channel inlet, and a flow channel outlet;

[0119] The flow channel inlet and the flow channel outlet are symmetrically arranged at the centers of the left and right sides of the liquid cooling plate respectively. Among them, the flow channel inlet is arranged at the center of the right side of the liquid cooling plate and is connected to the main flow channel; the flow channel outlet is arranged at the center of the left side of the liquid cooling plate and is connected to the converging flow channel;

[0120] The main flow channel is arranged at the middle position of the rectangular liquid cooling plate and is connected to the vein-like flow channel network. The main flow channel is indirectly connected to the converging flow channel through the vein-like flow channel network; the vein-like flow channel network as a whole is composed of 12 micro-channel units in a zigzag shape, symmetrically distributed up and down on both sides of the main flow channel, with 6 zigzag-shaped micro-channel units on each side; among them, the zigzag-shaped micro-channel units on the same side of the main flow channel are separated from each other by partitions, and the zigzag-shaped micro-channel units on the same side of the main flow channel are parallel to each other;

[0121] The microchannel unit with a broken-line shape includes an adjacent straight-channel part and an inclined-channel part. The straight-channel parts are parallel to each other, and the inclined-channel parts are parallel to each other. The outlet ends of the straight-channel parts are flush and are connected to the converging channel at the outlet end.

[0122] The included angle ɑ1 between the main channel and the inclined-channel part of the microchannel unit with a broken-line shape on the same side of the main channel is 50°;

[0123] The main channel and the converging channel are perpendicular to each other, and the axis of the main channel coincides with the axes of the channel inlet and the channel outlet. The longitudinal section of the main channel is rectangular, and the transverse section of the converging channel is rectangular.

[0124] It should be noted that the length of the main channel is half of the distance between the channel inlet and the channel outlet. That is, along the direction from the channel inlet to the channel outlet, the main channel extends from the channel inlet to the center of the entire cold plate channel. Along the direction from the channel inlet to the channel outlet, the inclined channels of the microchannel units with a broken-line shape are arranged in parallel in sequence, extending in the direction away from the main channel. The extension endpoints of the inclined channels arranged in parallel on the same side are collinear, and the included angle with the axis of the cold plate channel, that is, the included angle ɑ1 between the main channel and the inclined-channel part of the microchannel unit with a broken-line shape on the same side of the main channel, is 50°; the straight-channel part of the microchannel unit with a broken-line shape extends along the direction from the channel inlet to the channel outlet from the extension endpoint of the inclined channel.

[0125] Among them, along the direction from the channel inlet to the channel outlet, the end wall surface of the main channel is tapered, and the cone angle is β1 = 2ɑ1 = 100°.

[0126] The cross-section of the channel in the microchannel unit with a broken-line shape in the leaf-vein-like channel network facing the channel inlet direction is rectangular, the channel width is W3 = 1mm, the channel height is H2 = 1mm, and the channel spacing is K2 = 3mm, satisfying 1.5 * W3 ≤ K2 ≤ 3 * W3, in units of mm.

[0127] The width of the main channel is W4 = 12mm, the length is L1 = 36mm, the width of the converging channel is W5 = 12mm, the length L2 = 45mm, and the equivalent diameter D2 of the channel inlet and the channel outlet is 12mm, satisfying W4 = W5 = D2 ≥ M * W3, L2 = M * W3 + (M - 1) * K2.

[0128] The pressure contour map of the leaf-vein-like liquid-cooled plate channel in this embodiment is as Figure 7 shown. It can be seen from the figure that the flow resistance obtained by the simulation calculation of the leaf-vein-like liquid-cooled plate channel in this embodiment is 495.97Pa.

[0129] The temperature contour map of the leaf-vein-like liquid-cooled plate channel in this embodiment is as Figure 8As shown, it can be seen from the figure that the highest temperature of the heat source obtained from the simulation calculation of the leaf vein-like liquid cooling plate flow channel in this embodiment is 101.67 °C.

[0130] Embodiment 3

[0131] The liquid cooling system of the aircraft in this embodiment is similar in structure to that of Embodiment 1, except that the liquid cooling plate flow channels in the heat source device are different. The heat source device in this embodiment contains a cobweb-like liquid cooling plate flow channel.

[0132] The cobweb-like liquid cooling plate flow channel is arranged in a rectangular liquid cooling plate, as Figure 4 shown:

[0133] It includes a first flow channel unit, a second flow channel unit, a main flow channel, a flow channel inlet and a flow channel outlet;

[0134] The flow channel inlet and the flow channel outlet are symmetrically arranged at the centers of the left and right side edges of the liquid cooling plate respectively. Among them, the flow channel inlet is arranged at the center of the right side edge of the liquid cooling plate and is connected to the main flow channel; the flow channel outlet is arranged at the center of the left side plate of the liquid cooling plate and is connected to the main flow channel;

[0135] The longitudinal section of the main flow channel is rectangular and is arranged at the middle position of the rectangular liquid cooling plate, and is respectively connected to the first flow channel unit and the second flow channel unit;

[0136] The second flow channel unit and the first flow channel unit have the same structure and are symmetrically distributed on both sides of the main flow channel, jointly forming a cobweb-like flow channel network; along the direction from the flow channel inlet to the flow channel outlet, the main flow channel has a constant diameter.

[0137] The main flow channel includes: an inlet end main flow channel and an outlet end main flow channel. The inlet end main flow channel is connected to the outlet end main flow channel through isosceles trapezoid-shaped first flow channel units and second flow channel units;

[0138] The inlet end main flow channel and the outlet end main flow channel are coaxially arranged, and a flow-around structure is arranged at the axis center position from the flow channel inlet to the flow channel outlet. Part of the outer surface of the flow-around structure forms the innermost layer of isosceles trapezoid-shaped micro-channels with the innermost layer of the first flow channel unit and the second flow channel unit;

[0139] The first flow channel unit is isosceles trapezoid-shaped and includes 12 isosceles trapezoid-shaped micro-channels distributed layer by layer. The 12 isosceles trapezoid-shaped micro-channels distributed layer by layer are parallel to each other; along the direction of the main flow channel, the sizes of the isosceles trapezoid-shaped micro-channels distributed layer by layer decrease in an arithmetic progression; each isosceles trapezoid-shaped micro-channel includes two oblique linear micro-channels and one horizontal linear micro-channel. The two oblique linear micro-channels are connected to the main flow channel, and the included angle ɑ2 with the main flow channel is 60°;

[0140] Along the axis direction, the end wall surface of the flow-around structure is conical, and the cone angle is β2 = 2ɑ2 = 120°.

[0141] The second flow channel unit has the same structure as the first flow channel unit and is symmetrically distributed on both sides of the main flow channel, jointly forming a cobweb-like flow channel network;

[0142] The cross-section of the isosceles trapezoidal micro-channel facing the flow channel inlet is rectangular, the flow channel width is W6 = 1 mm, the flow channel height is H3 = 1 mm, and the flow channel spacing is K3 = 3 mm, satisfying 1.5*W ≤ K3 ≤ 3*W6, in units of mm.

[0143] The width of the main flow channel is W7 = 12 mm, and the equivalent diameters of the flow channel inlet and the flow channel outlet are D3 = 12 mm, satisfying W7 = D3 ≥ P*W6.

[0144] The pressure contour map of the cobweb-like liquid cooling plate flow channel in this embodiment is as shown in Figure 9 It can be seen from the figure that the flow resistance obtained by the simulation calculation of the cobweb-like liquid cooling plate flow channel in this embodiment is 351.26 Pa.

[0145] The temperature contour map of the cobweb-like liquid cooling plate flow channel in this embodiment is as shown in Figure 10 It can be seen from the figure that the highest temperature of the heat source obtained by the simulation calculation of the cobweb-like liquid cooling plate flow channel in this embodiment is 100.91 °C.

[0146] Example 4

[0147] The aircraft liquid cooling system designed in Example 1 is actually verified by a ground verification system.

[0148] The structure of the ground verification system is as shown in Figure 11 It can be seen that the verification system consists of a liquid storage tank, a flow meter, a gear pump, a simulated heat load, a heat dissipation skin and sensors. The sensors are arranged at the flow channel inlet and the flow channel outlet positions of the heat dissipation skin (i.e., the cold source device);

[0149] After being actually verified by the ground verification system, the flow resistance of the aircraft liquid cooling system in Example 1 is 844.92 Pa, the highest temperature of the heat source is 68.41 °C, and the heat dissipation area is 25163 mm 2 , having a good cooling effect.

[0150] After being actually verified by the ground verification system, the flow resistance of the aircraft liquid cooling system in Example 2 is 495.97 Pa, the highest temperature of the heat source is 101.67 °C, and the heat dissipation area is 25127 mm 2 , having a good cooling effect.

[0151] After being actually verified by the ground verification system, the flow resistance of the aircraft liquid cooling system in Example 3 is 351.26 Pa, the highest temperature of the heat source is 100.91 °C, and the heat dissipation area is 25089 mm 2 , having a good cooling effect.

[0152] Comparative Example 1

[0153] The structure of the aircraft liquid cooling system in this comparative example is the same as that in Example 1, except that for some dimensions of the honeycomb-like liquid cooling plate flow channels in the heat source device:

[0154] For the flow channels in the parallel straight flow channels and the hexagonal micro-channel units in the honeycomb-like flow channel network, the flow channel width is W1 = 1 mm, the flow channel height is H1 = 1 mm, and the flow channel spacing is K1 = 1 mm, which does not satisfy 1.5 * W1 ≤ K1 ≤ 3 * W1.

[0155] The equivalent diameters of the flow channel inlet and the flow channel outlet are the same, D1 = 5 mm, which does not satisfy D1 ≥ N * W1.

[0156] The width W2 of the first collecting flow channel and the second collecting flow channel is 6 mm, which does not satisfy W2 = 1.5N * W1.

[0157] Verified by the actual ground verification system, the flow resistance of the aircraft liquid cooling system in Comparative Example 1 is 1238.76 Pa, the highest temperature of the heat source is 96.23 °C, and the heat dissipation area is 23102 mm 2 , and the heat dissipation effect is weaker than that of Example 1.

[0158] Comparative Example 2

[0159] The structure of the aircraft liquid cooling system in this comparative example is the same as that in Example 2, except that for some dimensions of the vein-like liquid cooling plate flow channels in the heat source device:

[0160] The included angle ɑ1 between the main flow channel and the micro-channel units in the shape of a broken line on the same side of the main flow channel is 80°;

[0161] For the flow channels in the micro-channel units in the shape of a broken line, the cross-section towards the flow channel inlet is rectangular, the flow channel width is W3 = 1 mm, the flow channel height is H2 = 1 mm, and the flow channel spacing is K2 = 1 mm, which does not satisfy 1.5 * W3 ≤ K2 ≤ 3 * W3, in units of mm;

[0162] The width of the main flow channel is W4 = 10 mm, the length is L1 = 30 mm, the width of the collecting flow channel is W5 = 10 mm, the length L2 = 23 mm, and the equivalent diameter D2 of the flow channel inlet and the flow channel outlet is 10 mm, which does not satisfy W4 = W5 = D2 ≥ M * W3.

[0163] Verified by the actual ground verification system, the flow resistance of the aircraft liquid cooling system in Comparative Example 2 is 895.78 Pa, the highest temperature of the heat source is 143.58 °C, and the heat dissipation area is 23832 mm 2 , and the heat dissipation effect is weaker than that of Example 2.

[0164] Comparative Example 3

[0165] The structure of the aircraft liquid cooling system in this comparative example is the same as that in Example 3, except for some dimensions of the spider-web-like liquid cooling plate flow channels in the heat source device:

[0166] The included angle ɑ2 between the main flow channel and the oblique linear micro-channel in the isosceles trapezoidal micro-channel on the same side of the main flow channel is 80°;

[0167] Along the axial direction, the end wall surface of the flow-around structure is conical, and the cone angle is β2 = 2ɑ2 = 160°.

[0168] The cross-section of the isosceles trapezoidal micro-channel facing the flow channel inlet direction is rectangular, the flow channel width is W6 = 1 mm, the flow channel height is H3 = 1 mm, and the flow channel spacing is K3 = 1 mm, not satisfying 1.5 * W6 ≤ K3 ≤ 3 * W6, unit mm;

[0169] The width of the main flow channel is W7 = 10 mm, and the equivalent diameters D3 of the flow channel inlet and the flow channel outlet are 10 mm, not satisfying W7 = D3 ≥ P * W6.

[0170] Verified by the actual ground verification system, the flow resistance of the aircraft liquid cooling system in Comparative Example 3 is 659.26 Pa, the highest temperature of the heat source is 126.87 °C, and the heat dissipation area is 24986 mm 2 , and the heat dissipation effect is weaker than that in Example 3.

[0171] In summary, verified by the actual ground verification system, the flow resistance of the aircraft liquid cooling system in Example 1 is 844.92 Pa, the highest temperature of the heat source is 68.41 °C, and the heat dissipation area is 25163 mm 2 ; the flow resistance of the aircraft liquid cooling system in Example 2 is 495.97 Pa, the highest temperature of the heat source is 101.67 °C, and the heat dissipation area is 25127 mm 2 ; the flow resistance of the aircraft liquid cooling system in Example 3 is 351.26 Pa, the highest temperature of the heat source is 100.91 °C, and the heat dissipation area is 25089 mm 2 , all having good cooling effects. The flow resistance of the aircraft liquid cooling system in Comparative Example 1 is 1238.76 Pa, the highest temperature of the heat source is 96.23 °C, and the heat dissipation area is 23102 mm 2 , and the heat dissipation effect is weaker than that in Example 1. The flow resistance of the aircraft liquid cooling system in Comparative Example 2 is 895.78 Pa, the highest temperature of the heat source is 143.58 °C, and the heat dissipation area is 23832 mm 2 , and the heat dissipation effect is weaker than that in Example 2. Verified by the actual ground verification system, the flow resistance of the aircraft liquid cooling system in Comparative Example 3 is 659.26 Pa, the highest temperature of the heat source is 126.87 °C, and the heat dissipation area is 24986 mm 2 , and the heat dissipation effect is weaker than that in Example 3.

[0172] As described above, it is only the preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. An aircraft liquid cooling system, characterized in that, it includes a cold source device, a heat source device, an energy storage device, and a circulation pump. The cold source device, the heat source device, the energy storage device, and the circulation pump are sequentially connected in series through flexible pipelines with sealed joints at both ends to form a circulation loop; the cold source device is a part of the aircraft skin, and the skin contains a flow channel; the heat source device is an internal liquid cooling plate of the aircraft, the liquid cooling plate contains a flow channel, and the flow channel is one of a honeycomb-like liquid cooling plate flow channel, a vein-like liquid cooling plate flow channel, or a spider web-like liquid cooling plate flow channel.

2. The aircraft liquid cooling system according to claim 1, characterized in that, the honeycomb-like liquid cooling plate flow channel is a rhombus-shaped honeycomb; the honeycomb-like liquid cooling plate flow channel includes a honeycomb flow channel network, a first collecting flow channel, a second collecting flow channel, parallel straight flow channels, a flow channel inlet, and a flow channel outlet; the first collecting flow channel and the second collecting flow channel are parallel and symmetrically arranged on opposite sides of the rhombus.

3. The aircraft liquid cooling system according to claim 1, characterized in that, the vein-like liquid cooling plate flow channel includes a vein-like flow channel network, a main flow channel, and a collecting flow channel; the main flow channel is arranged in the middle position of the rectangular liquid cooling plate and is connected to the vein-like flow channel network; the vein-like flow channel network is composed of M micro flow channels arranged in a broken line shape and is symmetrically distributed above and below the main flow channel; the main flow channel and the collecting flow channel are perpendicular to each other.

4. The aircraft liquid cooling system according to claim 1, characterized in that, the spider web-like liquid cooling plate flow channel includes a first flow channel unit, a second flow channel unit, and a main flow channel; the second flow channel unit has the same structure as the first flow channel unit and is symmetrically distributed on both sides of the main flow channel to jointly form a spider web-like flow channel network; the main flow channel is arranged in the middle position of the rectangular liquid cooling plate and is respectively connected to the first flow channel unit and the second flow channel unit. Along the direction from the flow channel inlet to the flow channel outlet, the main flow channel has a constant diameter.

5. The aircraft liquid cooling system according to claim 2, characterized in that, the first collecting flow channel is connected to the honeycomb flow channel network through N parallel straight flow channels, and the second collecting flow channel is connected to the honeycomb flow channel network through N parallel straight flow channels.

6. The aircraft liquid cooling system according to claim 3, characterized in that, the micro flow channel unit in the shape of a broken line includes an adjacent straight flow channel part and an inclined flow channel part. The straight flow channel parts are parallel to each other, the inclined flow channel parts are parallel to each other, the outlet ends of the straight flow channel parts are flush and are connected to the collecting flow channel at the outlet end.

7. The aircraft liquid cooling system according to claim 4, characterized in that, the first flow channel unit is in the shape of an isosceles trapezoid and includes P isosceles trapezoid-shaped micro flow channels arranged layer by layer, and the P isosceles trapezoid-shaped micro flow channels arranged layer by layer are parallel to each other.

8. The aircraft liquid cooling system according to any one of claims 1-7, characterized in that, the circulation pump is a centrifugal pump or a gear pump.

9. The aircraft liquid cooling system according to any one of claims 1-7, characterized in that, the energy storage device is a metal bellows type energy storage device or a rubber airbag type energy storage device.

10. The aircraft liquid cooling system according to any one of claims 1-7, characterized in that, the flexible pipeline is a layered structure, with a polytetrafluoroethylene inner layer and a stainless steel braid outer layer. Both ends of the pipeline are connected to the sealing joint through a swaging process, and the sealing structure is a plunger type or an end face sealing type.

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