High-speed aircraft heat dissipation-power generation integrated device

Abstract

This invention discloses an integrated heat dissipation and power generation device for high-speed aircraft, comprising: a heat dissipation pulsating heat pipe arranged in the nose cone of the high-speed aircraft; the heat dissipation pulsating heat pipe includes an annular pulsating heat pipe condensation section, several U-shaped pulsating heat pipe evaporation sections, and two intermediate sections connecting each U-shaped pulsating heat pipe evaporation section to the annular pulsating heat pipe condensation section; at least one branch pipe communicating with the intermediate section is arranged at intervals between the two intermediate sections; a heat extraction pipe for heat exchange with the annular pulsating heat pipe condensation section of the heat dissipation pulsating heat pipe; and a power generation module for converting the heat energy acquired by the heat extraction pipe into electrical energy. This integrated device provides thermal protection for the aircraft while converting high-temperature aerodynamic heat into electricity, alleviating the aircraft's demand for onboard battery power, reducing the need for carrying cooling fluid, and improving energy utilization efficiency. It is of great significance for aircraft operating in harsh thermal environments for extended periods.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aerospace vehicle thermal protection and thermal utilization, in particular to a high-speed vehicle heat dissipation-power generation integrated device. BACKGROUND

[0002] During the flight of a high-speed vehicle in the atmosphere, the aerodynamic heating generated by the friction with the incoming atmosphere can rapidly increase the temperature of the outer surface of the vehicle, resulting in a decrease in the strength and stiffness of the vehicle structure, threatening the normal operation of the vehicle. For long-time operation, higher requirements are put forward for the thermal protection means of the vehicle.

[0003] If the high-speed vehicle in a long-time operation state removes heat by ablation or uses the properties of the material itself to resist heat, it does not meet the demand of long-time operation of the vehicle, and at the same time, the vehicle in a long-time operation state necessarily has a greater demand for battery power supply. The active thermal protection technologies such as gas film cooling and sweating cooling are more effective, in addition, the high-temperature thermal energy generated by aerodynamic heating is a kind of high-grade energy, the existing thermal protection technology mainly removes heat from the surface of the vehicle for thermal protection, and cannot effectively utilize the aerodynamic heating thermal energy. In the traditional active cooling mode, only the convection cooling can effectively utilize this part of energy, through the circulating working medium to convert the thermal energy into mechanical energy, and link the generator to form a thermoelectric conversion system, utilize the aerodynamic thermal energy for power generation, realize the thermal protection of the high-speed vehicle, and replace the power supply carried by the vehicle.

[0004] The above-mentioned thermoelectric conversion system can meet the cooling demand of most of the area of the vehicle cabin end, but it is difficult to effectively cool the super-high-temperature components of the vehicle nose cone part subjected to severe aerodynamic heating. The extreme high temperature of the leading edge of the vehicle nose cone is transferred through the dissipation structure, and is averaged to the trailing edge of the vehicle nose cone and the cabin section, which can effectively alleviate the high temperature danger of the leading edge of the nose cone. At present, there are few heat dissipation schemes applied to the leading edge of the vehicle nose cone, and the main thermal protection technologies are sweating cooling and gas film cooling, which need to carry more additional cooling working medium.

[0005] In summary, there is still room for development in the application of thermal protection means and the recovery of aerodynamic thermal energy during the flight of a high-speed vehicle. Taking targeted thermal protection measures for different key parts of a high-speed vehicle and flexibly and efficiently utilizing the advantages of different thermal protection technologies are effective ways to solve the problem of thermal protection of a high-speed vehicle under high heat load, and have a promoting effect on the development of a high-speed vehicle. SUMMARY

[0006] The technical problem this invention addresses is the development of an integrated heat dissipation and power generation device for high-speed aircraft. This device couples convection cooling, thermoelectric conversion, and heat pipe heat dissipation technology. Extreme heat flow at the leading edge of the aircraft's nose cone is transferred through heat pipes, progressively dissipating heat to the trailing edge of the nose cone and the aircraft's cabin end. A circulating working fluid, through heat extraction pipes on the cabin wall, absorbs the high temperature from the cabin wall and the heat dissipated through the heat pipes via convection cooling, and uses this heat for thermoelectric conversion. This achieves thermal protection for the aircraft while simultaneously powering internal instruments, replacing some of the aircraft's onboard power supply. This invention ensures the safe operation of high-speed aircraft while utilizing aerodynamic heating heat for power generation, improving energy utilization and providing a feasible approach for the development of thermal protection technologies for high-speed aircraft.

[0007] To address the aforementioned technical problems, the specific technical solution of the present invention is as follows:

[0008] A high-speed aircraft heat dissipation-power generation integrated device, comprising:

[0009] A heat-conducting pulsating heat pipe is arranged in the nose cone of a high-speed aircraft. The heat-conducting pulsating heat pipe includes an annular pulsating heat pipe condensation section, several U-shaped pulsating heat pipe evaporation sections, and two intermediate sections connecting each U-shaped pulsating heat pipe evaporation section to the annular pulsating heat pipe condensation section. At least one branch pipe communicating with the intermediate section is provided at intervals between the two intermediate sections. Liquid plugs and gas plugs are randomly distributed in the heat-conducting pulsating heat pipe.

[0010] The heat extraction pipes are arranged at the trailing edge of the nose cone and the wall of the cabin section of the high-speed aircraft; and exchange heat with the annular pulsating heat pipe condensation section of the heat-conducting pulsating heat pipe.

[0011] The power generation module is connected to the heat extraction pipeline and converts the heat energy obtained by the heat extraction pipeline into electrical energy.

[0012] The diversion pipe has two nodes in the two intermediate sections, one a diversion node and the other a merging node; the diversion pipe consists of two arc-shaped segments and one straight segment; the bifurcation angle of the node is α, the distance between the two ends of the diversion pipe is x1, the inner diameter of the arc-shaped segment is r1, and the outer diameter of the arc-shaped segment is r2; and it should satisfy: 1 / 4*x1 <r2<1 / 3*x1,x2 / 2+r2*sinα<r2。

[0013] Fins are installed in the condensation section of the annular pulsating heat pipe and the evaporation section of the U-shaped pulsating heat pipe, respectively.

[0014] The heat exchange pipeline employs a heat exchange channel with an array of hook-shaped ribs. The working fluid flows through this channel, absorbing heat from the surface of the spacecraft compartment and the cold end of the diverting pulsating heat pipe. The hook-shaped rib array pipeline optimizes the number and arrangement of ribs by adding smooth hook-shaped rib structures within the channel, forming a staggered array. As the fluid flows through this array, the heat exchange area increases, and the circulating working fluid, flowing through the hook-shaped ribs, forms vortices under the influence of the hook structure, generating strong disturbances and significantly improving heat exchange performance.

[0015] In the hook-shaped rib array, the length of the hook-shaped rib is L1, the maximum width of the top and bottom edges is L2, the hook radius is r1, and the height of the hook-shaped rib structure is equal to the channel height H1. Taking the end positioning center of the hook-shaped rib structure as a reference, the length distance between the hook-shaped ribs is L3, and the width distance is L4. Furthermore, L1 / 3 3 / 2 * L2, L3 > 3 / 2 * L2, and 3 / 4 * L2 <r1<5 / 4*L2。 <h1>

[0016] The power generation module includes a generator, a drive pump, a coolant tank, a sealed cooling chamber, and connecting pipes. The drive pump is located at the inlet of the heat extraction pipe. The circulating working fluid flows into the heat extraction pipe under the action of the drive pump, absorbing heat from the cold end of the heat pipe and the heat from the aircraft cabin wall. The heat-absorbing working fluid is then fed into the generator. The cooling medium in the coolant tank is fed into the sealed cooling chamber, cooling the circulating working fluid in the generator before being transported to the nose cone of the aircraft for discharge, carrying away the heat at the nose cone stagnation point and forming an air film on the outer surface of the nose cone tip.

[0017] The generator is a Stirling generator.

[0018] The Stirling generator includes an expansion chamber and a compression chamber, with indirect high and low temperature heat exchangers and regenerators installed on both sides; the inlet and outlet of the circulating working fluid are located on both sides of the expansion chamber, with the inlet end connected to the outlet of the heat extraction pipeline and the outlet end connected to the working fluid pump and connected to the inlet end of the heat extraction pipeline; the compression chamber is placed inside the closed cooling chamber.

[0019] The cooling media used include, but are not limited to, liquid hydrogen, liquid helium, and liquid nitrogen.

[0020] The phase change working fluid used in the heat-conducting pulsating heat pipe includes, but is not limited to, water, methanol, ethanol, Freon, dichlorofluoroethane, etc., with a filling rate of 60% to 70%.

[0021] This invention provides an integrated heat dissipation and power generation device for high-speed aircraft, combining heat pipes, convection cooling, and thermoelectric conversion technologies. Through the heat dissipation effect of pulsating heat pipes, the extreme heat flow at the leading edge of the aircraft's nose cone is transferred along the pulsating heat pipe pipeline to the trailing edge of the nose cone and the cabin section, reducing the high-temperature load on the nose cone section and ensuring operational safety. The circulating working fluid absorbs the high-temperature heat from the aircraft cabin wall through the laid heat extraction pipelines via convection cooling, and is used for thermoelectric conversion. This achieves thermal protection while replacing part of the aircraft's onboard power supply, improving energy utilization.

[0022] This invention employs a Stirling cycle power configuration. The Stirling cycle boasts excellent energy recovery efficiency; under ideal conditions of extreme regeneration, its cycle thermal efficiency can equal that of a Carnot cycle within the same temperature limit. Furthermore, the Stirling cycle power generation system is compact, capable of using any fuel or utilizing any heat source, exhibiting strong adaptability. Based on a free-piston Stirling generator, high- and low-temperature heat exchangers and a regenerator are added. A heat exchanger is also installed outside the Stirling generator, connecting the expansion chamber and compression chamber via pipes to exchange heat between the circulating working fluid before and after expansion. The circulating working fluid flows through heat extraction channels arranged in the cabin section, absorbing heat and expanding. This expansion is then fed into the free-piston Stirling generator, driving the piston to perform work, which in turn powers the engine to generate electricity. This achieves the collection and utilization of aerodynamic thermal energy, ensuring the normal operation of the aircraft cabin section.

[0023] To improve the heat transfer efficiency of the heat pipe for extreme heat flow at the leading edge of the aircraft's nose cone and ensure safe operation, this integrated device employs a convective pulsating heat pipe. On one hand, fins are added to the hot and cold ends of the pulsating heat pipe to improve heat exchange efficiency. On the other hand, convection channels are provided between adjacent sections of the pulsating heat pipe to reduce problems such as local stagnation and backflow, further enhancing the heat exchange effect.

[0024] By employing the above technical solutions, the present invention has the following beneficial effects compared to the prior art:

[0025] This invention relates to a high-speed aircraft heat conduction-power generation integrated device that couples three technologies: heat pipe, convection cooling, and thermoelectric conversion. Through the heat conduction effect of the pulsating heat pipe, the extreme heat flow at the leading edge of the aircraft's nose cone is transferred along the pulsating heat pipe pipeline to the trailing edge of the nose cone and the cabin section, reducing the high-temperature load on the nose cone section and ensuring operational safety. The circulating working fluid absorbs the high-temperature heat from the aircraft cabin wall through the laid hook-shaped rib array heat extraction pipeline via convection cooling, and uses this heat for thermoelectric conversion. This achieves thermal protection while replacing part of the aircraft's onboard power supply, improving energy utilization.

[0026] This invention relates to a Stirling cycle power configuration. The Stirling cycle has excellent energy recovery efficiency; under ideal conditions of extreme regeneration, its cycle thermal efficiency can be equal to that of a Carnot cycle within the same temperature limit. The working fluid in the Stirling power generation system applied to aircraft has high compatibility and adaptability. High-density power working fluids can be used to improve heat absorption efficiency (improving cooling efficiency and ensuring timely heat transfer from the aircraft surface) while ensuring a compact system structure, reusability, and reduced costs associated with cooling and heat utilization. Simultaneously, the high-temperature, high-pressure working fluid, after heat absorption, expands and performs work, further converting into electrical energy, thus realizing the collection and utilization of aerodynamic thermal energy.

[0027] This invention relates to a convective pulsating heat pipe structure for heat conduction of extreme heat flow at the leading edge of the nose cone. Heat from the leading edge of the aircraft nose cone is transported from the hot end to the cold end along the pulsating heat pipe. During this transport, heat is simultaneously released to the trailing edge of the aircraft nose cone and the aircraft cabin wall outside the heat pipe, dispersing the heat from the leading edge of the nose cone to areas less threatened by aerodynamic heat. This integrated device uses a convective pulsating heat pipe, improving the heat conduction efficiency of the heat pipe for extreme heat flow at the leading edge of the aircraft nose cone, ensuring safe aircraft operation. On one hand, fins are added to the hot and cold ends of the pulsating heat pipe to improve heat exchange efficiency; on the other hand, diversion pipes are installed between adjacent sections of the pulsating heat pipe to reduce problems such as local stagnation and backflow, further improving the heat exchange effect.

[0028] This invention relates to a hook-shaped rib array structure for heat exchange microchannels with strong disturbance effect. Utilizing micro-surface processing design, a hook-shaped rib array is set in the heat exchange channel. The circulating working fluid flows through the heat exchange channel and undergoes convective heat exchange with the high-temperature wall surface of the aircraft compartment. Due to the presence of the hook-shaped rib array in the microchannel, more heat exchange surface area is provided. When the circulating working fluid flows in the channel, vortices are formed under the action of the hook-shaped structure, generating strong disturbance, thereby improving heat exchange performance. More heat is absorbed by the circulating working fluid, ensuring that the temperature of the aircraft wall surface is within a safe range while improving the device's power generation capacity.

[0029] This invention relates to a thermal protection method that combines heat conduction and convection cooling. After the cooling medium in the coolant tank and the enclosed cooling chamber cools the working fluid in the compression chamber of the free piston Stirling generator, it evaporates upon heating and is transported along the connecting pipeline to the stagnation point of the aircraft nose cone. It is then discharged to the outside of the aircraft through a porous permeable material, carrying away the heat at the stagnation point of the nose cone, preventing heat accumulation inside the aircraft, improving the power generation efficiency of the power generation module, and forming an air film on the outer surface of the tip of the aircraft nose cone, thus enhancing the thermal protection effect at the stagnation point of the aircraft nose cone.

[0030] Other features and advantages of the present invention will be described in detail in the following detailed description section. Attached Figure Description

[0031] Figure 1 : Schematic diagram of the high-speed aircraft heat dissipation-power generation integrated device of the present invention;

[0032] Figure 2 : Schematic diagram of the heat conduction and diversion pulsating heat pipe structure of the present invention;

[0033] Figure 3 : Figure 2 A plan view of a heat pipe with pulsating heat conduction and diversion.

[0034] Figure 4 : Schematic diagram of the free piston Stirling generator of this invention;

[0035] Figure 5 Schematic diagram of the Stirling cycle thermodynamic process of this invention: a) PV diagram; b) Ts diagram;

[0036] Figure 6 : Schematic diagram of the hook-shaped wing rib array heat extraction channel structure of the present invention;

[0037] Figure 7 : Figure 6 AA section view;

[0038] Figure 8 Schematic diagram comparing the heat transfer performance of the edge measuring points of the hook-shaped rib array heat exchange channel of the present invention: a) the highest temperature at the bottom of the heat exchange channel; b) the pressure drop at the inlet and outlet of the heat exchange channel;

[0039] Figure 9 Schematic diagram comparing the heat exchange performance of the center measuring point of the hook-shaped wing rib array heat exchange channel of the present invention: a) the highest temperature at the bottom of the heat exchange channel; b) the pressure drop at the inlet and outlet of the heat exchange channel.

[0040] In the diagram: 1. Heat-conducting pulsating heat pipe; 101. Evaporation section of pulsating heat pipe; 102. Liquid plug; 103. Gas plug; 104. Diversion pipe; 105. Condensation section of pulsating heat pipe; 2. Hook-shaped rib array channel; 201. Flow channel inlet; 202. Flow channel outlet; 203. Hook-shaped rib structure; 3. Cabin wall; 4. Free piston Stirling generator; 401. Expansion chamber; 402. High-temperature heat exchanger; 403. Regenerator; 404. Low-temperature heat exchanger; 405. Compression chamber; 406. Magnetic coil motor; 407. Leaf spring; 408. Power piston; 409. Piston rod; 410. Phase adjuster; 5. Drive pump; 6. Enclosed cooling chamber; 7. Coolant tank; 8. Connecting pipe; 9. Porous medium permeable material. Detailed Implementation

[0041] To enhance understanding of the present invention, the invention will be further described in detail below with reference to the accompanying drawings. These embodiments are only used to explain the invention and do not constitute a limitation on the scope of protection of the invention.

[0042] like Figure 1 As shown, this invention is an integrated heat dissipation and power generation device for high-speed aircraft, comprising a heat dissipation pulsating heat pipe 1, a hook-shaped wing rib array heat extraction channel 2, a cabin wall 3, a free piston Stirling generator 4, a drive pump 5, a sealed cooling chamber 6, a coolant tank 7, and connecting pipes 8. The specific working process of this integrated device is as follows: the extreme heat flow at the leading edge of the high-speed aircraft's nose cone is diverted by the heat dissipation pulsating heat pipe 1, dissipating the heat along the heat pipe to the trailing edge of the nose cone and the cabin wall 3, alleviating the high-temperature threat in the nose cone area; under the action of the drive pump 5, circulating working fluid is introduced into the cooling chamber 6 located on the cabin wall 3. The hook-shaped rib array heat extraction channel 2 absorbs heat from the condensation section 105 of the pulsating heat pipe and the cabin wall 3, and passes it into the free piston Stirling generator 4 to convert thermal energy into mechanical energy. The circulating working fluid after heat exchange re-enters the hook-shaped rib array heat extraction channel 2 to absorb heat and start a new cycle. The coolant is passed from the coolant 7 through the connecting pipe 8 into the closed cooling chamber 6, which serves as the cold source for the free piston Stirling generator 4. The heat-absorbing and evaporating cooling medium is passed into the stagnation point at the tip of the aircraft's nose cone and discharged outward through the porous medium breathable material 9, carrying away the extreme heat at the stagnation point and forming a heat-blocking gas film.

[0043] like Figure 2 and Figure 3 As shown, the heat-dissipating pulsating heat pipe 1 of this invention includes a pulsating heat pipe evaporation section 101, a liquid plug 102, a gas plug 103, a diversion pipe 104, and a pulsating heat pipe condensation section 105. To address the extreme heat flow at the leading edge of the nose cone of a high-speed aircraft, fins are added to the pulsating heat pipe evaporation section 101 to improve heat exchange capacity and promptly absorb heat from the leading edge of the nose cone. The working fluid inside the pulsating heat pipe evaporation section 101 absorbs heat and evaporates, flowing towards the pulsating heat pipe condensation section 105. Randomly distributed liquid plugs 102 and gas plugs 103 exist within the pipe section. In the gas plug 103, there is a pressure difference between adjacent pipes. The working fluid oscillates between the evaporation end and the condensation end to achieve heat transfer. If only the heat transfer path or heat transfer area of ​​the pulsating heat pipe is increased, the pulsation path of the working fluid will become longer and the pulsation will be weakened, and the effective thermal conductivity will decrease accordingly. Although multiple pulsating heat pipes connected in parallel will not have a weakened pulsation effect due to the path, if the working fluid in one group is blocked, it will affect the flow of the working fluid in other pulsating heat pipes connected in parallel, resulting in a decrease in the overall heat transfer coefficient of the pulsating heat pipe. After passing through the diversion pipe 104, the main part of the working fluid continues to flow to the condensation section 105 of the pulsating heat pipe. Some liquid plugs 102 or gas plugs 103 that may cause obstruction and backflow temporarily enter the diversion pipe 104, which reduces the disorder of the distribution of liquid plugs 102 and gas plugs 103 when the working fluid flows in the pipe, reduces the possible backflow and obstruction of the working fluid, improves the circulation flow of the working fluid from the evaporation section 101 to the condensation section 105, and improves the heat transfer capacity and stability of the pulsating heat pipe.

[0044] The size characteristics of the diversion pulsating heat pipe are as follows: the bifurcation angle of the diversion pipe is α, the distance between the two ends of the diversion pipe is x1, the inner bending diameter is r1, and the outer diameter is r2; and it should satisfy: 1 / 4*x1 < r2 < 1 / 3*x1, x2 / 2 + r2*sinα < r2, ensuring that the working medium is divided into two relatively uniform working media of liquid plug 102 and gas plug 103, flowing to the diversion pipe and the condensation end of the pulsating heat pipe respectively.

[0045] As Figure 2 shown, the free piston Stirling generator in the present invention includes an expansion chamber 401, a high-temperature heat exchanger 402, a regenerator 403, a low-temperature heat exchanger 404, a compression chamber 405, a magnetic coil motor 406, a leaf spring 407, a power piston 408, a piston rod 409, and a phase shifter 410; the power piston 408 is connected to the leaf spring 407 through the piston rod 409, the magnetic coil motor is arranged around the power piston 408, the compression chamber 405 is arranged between the power piston 408 and the piston rod 409, and the high-temperature regenerator 402, the regenerator 403, and the low-temperature regenerator 404 are arranged in sequence; under the action of the driving pump 5, the high-temperature and high-pressure circulating working medium enters the expansion chamber 401, pushes the gas piston,带动 the piston rod 409 and the power piston 408 to move, converts thermal energy into mechanical energy, the power piston 408带动 the magnetic coil motor 406 to generate electricity, and the high-temperature heat exchanger 402, the regenerator 403, and the low-temperature heat exchanger 404 exchange heat between the gases on both sides of the expansion chamber 401 and the compression chamber 405 to improve the efficiency of the Stirling generator.

[0046] As Figure 6 、 7 shown, the heat extraction channel of the hook-shaped wing rib array in the present invention includes a flow channel inlet 201, a flow channel outlet 202, and a hook-shaped wing rib structure 203; the hook-shaped wing rib structure 203 is arranged in an array on the lower surface (outer surface) of the heat extraction channel, and the top of the hook-shaped wing rib structure 203 is pressed and coincided with the upper surface (inner surface) of the heat exchange channel; the presence of the wing-shaped side wall surface of the hook-shaped wing rib structure 203 significantly increases the heat exchange area, the circulating working medium flows into the heat exchange channel through the flow channel inlet 201, generates strong disturbance when flowing through the hook-shaped wing rib structure 203, and forms a vortex in the hook, strengthening the heat exchange effect between the working medium and the wall surface of the high-temperature cabin section, and enhancing the work capacity of the circulating working medium; finally, the circulating working medium flows out through the flow channel outlet 202.

[0047] The dimensional characteristics of the hook-shaped fin structure are as follows: the length is L1, and the maximum width of the upper and lower edges is L2; taking the positioning center of the end of the hook-shaped fin structure as the reference, the length distance between the hook-shaped fin structures is L3, the width distance is L4, the hook radius is r1, the height H1 of the single-layer heat exchange channel is considered according to the actual wall thickness of the aircraft, and the height of the hook-shaped fin structure should be equal to the channel height H1. And there should be: L1 / 3 < H1 < L1 / 2, to avoid an overly thick flow boundary layer around the hook-shaped fin structure 203 due to excessive height, insufficient bottom flow, and affecting the heat exchange effect; L4 > 3 / 2 * L2, L3 > 3 / 2 * L2, to ensure enough space for the flow to fully develop and at the same time reduce the pressure loss through the hook-shaped fin array; 3 / 4 * L2 < r1 < 5 / 4 * L2, to ensure a suitable hook size, which can help form vortices, enhance the secondary disturbance in the flow, and improve the heat exchange effect.

[0048] The present invention aims to propose an integrated device for efficiently utilizing aerodynamic heat to achieve thermal protection and power generation. By coupling a pulsating heat pipe with a Stirling generator and arranging them in the nose cone and cabin sections respectively, the extreme heat flux at the leading edge of the nose cone is diverted to the trailing edge of the nose cone and the cabin section. The circulating working fluid absorbs heat and does work, which is converted into electrical energy to supply the internal equipment of the aircraft, realizing the recycling of aerodynamic heat and reducing the consumption of battery power. Since the heat in the nose cone part is diverted through the pulsating heat pipe, the required cooling working fluid is saved, and the aircraft has more potential when there is a demand for long-duration operation and the cost required for repeated operation is lower. With the participation of the optimized heat exchange channels, the performance of this integrated device is improved.

[0049] The above specific embodiments are only for illustrating the technical concept and structural characteristics of the present invention, aiming to enable those skilled in the art to implement it accordingly. However, the above content does not limit the protection scope of the present invention. Any equivalent changes or modifications made according to the spirit and essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A high-speed aircraft heat dissipation-power generation integrated device, characterized in that, The application relates to a heat dissipation pulsating heat pipe arranged in the head cone of a high-speed aircraft. The heat dissipation pulsating heat pipe comprises a ring-shaped pulsating heat pipe condensing section, a plurality of U-shaped pulsating heat pipe evaporating sections and two intermediate sections connecting each U-shaped pulsating heat pipe evaporating section with the ring-shaped pulsating heat pipe condensing section; at least one shunt pipeline is arranged between the two intermediate sections and communicates with the intermediate sections; liquid plugs and gas plugs are randomly distributed in the heat dissipation pulsating heat pipe; the plurality of U-shaped pulsating heat pipe evaporating sections are located at the leading edge of the head cone of the high-speed aircraft, and the ring-shaped pulsating heat pipe condensing section is located at the trailing edge of the head cone of the high-speed aircraft. A heat extraction pipeline is arranged at the trailing edge of the head cone of the high-speed aircraft and the wall surface of a cabin section; the heat extraction pipeline exchanges heat with the ring-shaped pulsating heat pipe condensing section of the heat dissipation pulsating heat pipe. A power generation module is connected with the heat extraction pipeline and converts the heat energy obtained by the heat extraction pipeline into electric energy. Fins are arranged on the ring-shaped pulsating heat pipe condensing section and the U-shaped pulsating heat pipe evaporating section.

2. The heat dissipation-power generation integrated device for high-speed aircraft according to claim 1, wherein The shunt pipeline is connected with two nodes of two intermediate sections, one is a shunt node and the other is a confluence node; the shunt pipeline is composed of two arc sections and one straight section; the bifurcation angle of the node is a , the distance between the two ends of the shunt pipeline is x 1, the inner diameter of the arc section is r 1, the outer diameter of the arc section is r 2; and the following conditions should be met: 1 / 4 * x 1 < r 2 < 1 / 3 * x 1, x 2 / 2 + r 2 * sin a < r 2.

3. The heat dissipation-power generation integrated device for high-speed aircraft according to claim 1, wherein The heat extraction pipeline adopts a heat exchange channel provided with a hook-shaped rib array; working medium flows through the hook-shaped rib array heat exchange channel, absorbs the heat of the surface layer of the cabin section of the aircraft and the cold end of the heat dissipation shunt pulsating heat pipe.

4. The heat dissipation-power generation integrated device for high-speed aircraft according to claim 1, wherein The power generation module comprises a generator, a driving pump, a cooling liquid tank, a closed cooling cabin and connecting pipelines; the driving pump is arranged at the inlet of the heat extraction pipeline; under the action of the driving pump, the circulating working medium flows into the heat extraction pipeline, absorbs the heat of the cold end of the heat pipe and the heat of the wall surface of the cabin section of the aircraft; the working medium after absorbing heat is input into the generator; the cooling medium in the cooling liquid tank is input into the closed cooling cabin, cools the circulating working medium in the generator and is then transported to the head cone of the aircraft and discharged.

5. The heat dissipation-power generation integrated device for high-speed aircraft according to claim 4, wherein The length of the hook-shaped ribs in the array of hook-shaped ribs is L 1. The maximum width of the upper and lower edges is L 2. The hook-shaped radius is r 1. The height of the hook-shaped rib structure is equal to the channel height H 1. The length distance between the hook-shaped ribs is measured from the center of the end of the hook-shaped rib structure L 3. The width distance is L 4. And there should be: L 1 / 3 H 1 L 1 / 2, L 4 > 3 / 2 L 2, L 3 > 3 / 2 L 2, and 3 / 4 L 2 r 1 <5 / 4 L 2.

6. The heat dissipation-power generation integrated device for high-speed aircraft according to any one of claims 1-5, characterized in that, The generator is a Stirling generator.

7. The heat dissipation-power generation integrated device for high-speed aircraft according to claim 6, wherein The Stirling generator comprises an expansion cavity and a compression cavity, both sides of which are provided with an interwall type high-temperature heat exchanger and a low-temperature heat exchanger and a regenerator; the inlet and outlet of the circulating working medium are arranged at both sides of the expansion cavity, the inlet end is connected with the outlet of the heat extraction pipeline, the outlet end is connected with the working medium pump and is connected with the inlet end of the heat extraction pipeline; the compression cavity is arranged in the closed cooling cabin.

8. The heat dissipation-power generation integrated device for high-speed aircraft according to claim 7, wherein The cooling medium comprises liquid hydrogen, liquid helium and liquid nitrogen.

9. The heat dissipation-power generation integrated device for high-speed aircraft according to claim 6, wherein The phase change working medium used in the heat dissipation pulsating heat pipe comprises water, methanol, ethanol, freon and difluoro-chloroethane, and the filling rate is 60%-70%.

10. The heat dissipation-power generation integrated device for high-speed aircraft according to any one of claims 1-5, wherein ​

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