Anti-reflux integrated preheating device and method for satellite-borne transient high power

Abstract

The invention provides an anti-reflux integrated preheating device and method for satellite-borne transient high power, and relates to the technical field of satellite thermal control, the preheating device comprises a power unit, a waste heat recovery heat exchange assembly, a preheater, a boiling heat exchange assembly, a focal plane, a heat dissipation terminal and a turbulent flow column, the heat transfer performance of the device is effectively improved, reverse flow resistance is multiplied through turbulent flow columns, reverse impact of a high-temperature vapor-liquid mixture is blocked, the flow stability, the working condition adaptation capacity and the flow control capacity of a two-phase loop driven by a lifting pump are enhanced, a snake-shaped flow channel can be flexibly arranged, and the space utilization rate is increased. The engineering reliability of a satellite thermal control system can be improved without a mechanical movable part, the instant hedging eddy current effect of the Tesla valve unit can effectively prevent reverse fluid channeling of steam, and the technical problems that an existing preheater lacks the anti-reflux function, and is low in heat transfer performance and low in system integration degree are solved.

Description

Technical Field

[0001] This invention relates to the field of satellite thermal control technology, specifically to an integrated anti-backflow preheating device and method for onboard transient high-power applications. Background Technology

[0002] With the development of aerospace technology, high-density integration and high-performance computing have become the norm for spaceborne electronic equipment. This has led to the development of numerous transient, high-power heat-generating components, such as high-resolution camera focal planes, high-power signal processors, high-efficiency power controllers, and laser communication units. These components often exhibit pulsed, high-peak heat load characteristics during operation, with extremely high instantaneous heat flux density and extreme sensitivity to temperature fluctuations. Unstable temperature fields can directly cause electrical performance drift, efficiency degradation, and even reliability decline, severely limiting the overall satellite performance and lifespan.

[0003] Pump-driven two-phase fluid loops have become the preferred solution for advanced thermal control systems that maintain constant temperature for high-power heating units due to their high heat transfer efficiency and precise temperature control characteristics. In this system, the liquid working fluid is pumped to an evaporator that is in close contact with the high-power heating unit. After absorbing heat, it boils and undergoes a phase change, thereby carrying away a large amount of heat. To ensure a stable and efficient evaporation process, a preheater is usually installed between the pump and the evaporator. Its core task is to precisely preheat the liquid working fluid to the target state (such as saturated liquid or slightly subcooled liquid) to avoid flashing or subcooling at the evaporator inlet, thus stabilizing the thermal state of the evaporation interface.

[0004] For existing two-phase fluid loop preheaters, the following problems exist in spacecraft applications, especially when dealing with transient and pulsed heat loads of high-power heat-generating single units. First, they lack backflow prevention capabilities, posing a challenge to system reliability: when a camera suddenly starts up or encounters a severe external heat flow impact, violent boiling may occur in the evaporator, and the resulting steam may backflow and impact the pipeline. In existing technologies, to prevent the backflow of the heat working fluid from damaging the preheater or causing cavitation in the pump, a mechanical one-way valve is usually added before the preheater; however, mechanical valves have moving parts, which are prone to jamming, wear, and sealing failure under long-term microgravity and high vibration environments, constituting a single point of failure in the system and making it difficult to meet the stringent requirements of long life and high reliability for space missions. Second, traditional preheater flow channel designs are simple, with limited heat transfer and flow performance: microgravity causes the gas and liquid phases to lose buoyancy drive, easily leading to bubble stagnation, blockage flow, and even local overheating. Traditional serpentine or straight-channel preheaters, while extending the flow path, have limited internal flow field disturbance and a thicker boundary layer, leaving room for further improvement in heat transfer efficiency. Third, their low system integration hinders the lightweight and compact design of spacecraft: the preheater and one-way valve, as two independent functional components, require series connection via additional piping, joints, and mounting structures. This not only increases the system's mass, size, and potential leakage points but also contradicts the spacecraft's requirements for extreme lightweighting and high integration. Summary of the Invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the defects in the prior art, thereby providing an integrated anti-backflow preheating device and method for spaceborne transient high power.

[0006] An integrated anti-backflow preheating device for spaceborne transient high-power applications includes a power unit and a coke surface. The preheating device further includes a waste heat recovery heat exchange component, a preheater, a boiling heat exchange component, and a heat dissipation terminal. The preheater has a preheater inlet and a preheater outlet. The waste heat recovery heat exchange component is connected to the outlet of the power unit and the preheater inlet. The waste heat recovery heat exchange component is also connected to the outlet of the boiling heat exchange component. The preheater outlet is connected to the inlet of the boiling heat exchange component. The coke surface is connected to the boiling heat exchange component. The outlet of the waste heat recovery heat exchange component is also connected to the heat dissipation terminal. The outlet of the heat dissipation terminal is connected to the inlet of the power unit. The preheater is equipped with a serpentine flow channel and a Tesla valve unit. The Tesla valve unit is located on the serpentine flow channel, and the Tesla valve unit is also equipped with a turbulence column.

[0007] Furthermore, the waste heat recovery heat exchange component is a heat exchanger, which is provided with a cold fluid flow channel and a hot fluid flow channel. The cold fluid flow channel is connected to the outlet of the power unit and the inlet of the preheater, and the hot fluid flow channel is connected to the outlet of the boiling heat exchange component and the inlet of the heat dissipation terminal.

[0008] Furthermore, the preheater is also equipped with a connecting elbow, which is connected to the Tesla valve unit, and the serpentine flow channel has a serpentine layout with bends.

[0009] Furthermore, the Tesla valve unit has a Y-shaped layout, and the included angle M between adjacent Tesla valve units is 115 degrees.

[0010] Furthermore, the power unit is a mechanical pump, the boiling heat exchange component is an evaporator, the heat dissipation terminal is a radiant condenser, the outlet of the radiant condenser is connected to the inlet of the mechanical pump, and the coke surface is connected to the evaporator.

[0011] Furthermore, the preheating device also includes a liquid phase pipeline and a gas-liquid two-phase pipeline. The radiant condenser is connected to the mechanical pump, the mechanical pump to the heat exchanger, the heat exchanger to the preheater, and the preheater to the evaporator through the liquid phase pipeline. The radiant condenser is connected to the heat exchanger and the heat exchanger to the evaporator through the gas-liquid two-phase pipeline.

[0012] Furthermore, the preheating device also includes a liquid reservoir connected to the outlet of the radiant condenser and the inlet of the mechanical pump.

[0013] Furthermore, the liquid reservoir is connected to the radiant condenser and the mechanical pump via liquid phase pipelines.

[0014] Furthermore, a heating layer and a heat insulation layer are sequentially arranged on the outside of the preheater.

[0015] The present invention also includes an integrated anti-backflow preheating method for spaceborne transient high-power applications. This method is based on an integrated anti-backflow preheating device for spaceborne transient high-power applications described in any of the above claims. The power unit drives the subcooled liquid working fluid to flow through a waste heat recovery heat exchange component and a preheater. The preheater heats the liquid working fluid to a specified temperature. Then, the liquid working fluid enters a boiling heat exchange component. In the boiling heat exchange component, the liquid working fluid absorbs the transient high-power heat released from the coke surface and undergoes a boiling phase change, transforming the liquid working fluid into a gas-liquid two-phase mixture. The gas-liquid two-phase mixture then flows to a heat dissipation terminal via the waste heat recovery heat exchange component. After being radiated and cooled to the space environment by the heat dissipation terminal, the gas-liquid two-phase mixture re-condenses into a liquid working fluid, which returns to the power unit, thus completing the cycle.

[0016] The technical solution of this invention has the following advantages: The technical solution provided by this invention, by setting a serpentine flow channel and a Tesla valve unit, and by setting a turbulence column on the Tesla valve unit, makes the inner surface area of ​​the Tesla valve unit exceed that of a simple flow channel of the same length. Under the continuous disturbance of the serpentine bend and the Tesla valve unit, the fluid is always in a turbulent state, resulting in a high heat transfer coefficient and uniform working fluid outlet temperature. The turbulence column and Tesla valve unit significantly increase the reverse flow resistance, effectively blocking the reverse impact of the high-temperature vapor-liquid mixture. The rectifying characteristics of the serpentine flow channel and the Tesla valve unit transform the flow pulsation generated by the power unit into a stable flow field, providing stable inlet conditions for the boiling heat exchange component. This significantly improves the flow stability and operating condition adaptability of the pump-driven two-phase circuit, effectively suppressing flow fluctuations from upstream or downstream, and providing more stable flow. The serpentine flow channel can run along the side wall of the satellite cabin. The flexible corner arrangement improves space utilization and meets the requirements of satellite lightweighting and compactness compared with traditional preheater and one-way valve combinations. The whole unit is made of aluminum alloy 3D printing and has no mechanical moving parts. It can withstand the impact of extreme temperature difference and microgravity environment and improve the on-orbit fault-free working life. By replacing independent components with functional integration, potential sources of failure are reduced and the engineering reliability of satellite thermal control system is greatly improved. When the camera is suddenly started or the heat load changes suddenly, the large amount of steam generated rapidly in the boiling heat exchange component is prone to pulse impact. Through the instantaneous counter-current effect of the Tesla valve unit, a high-resistance barrier can be quickly formed to prevent the steam from flowing backward. This effectively protects upstream core components such as power unit from impact damage and avoids overshoot of focal surface temperature due to loop fluctuations, ensuring imaging stability during camera startup. Attached Figure Description

[0017] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a diagram of the overall architecture of the present invention; Figure 2 This is an exploded view of the preheater structure of the present invention; Figure 3 This is a diagram showing the forward and reverse flow states of the preheater of the present invention.

[0019] Explanation of reference numerals in the attached figures: 1-Mechanical pump; 2-Heat exchanger; 201-Cold fluid flow channel; 202-Hot fluid flow channel; 3-Preheater; 4-Evaporator; 5-Coke surface; 6-Radiation condenser; 7-Liquid reservoir; 8-Liquid phase pipeline; 9-Gas-liquid two-phase pipeline; 10-Insulation layer; 11-Heating layer; 12-Preheater inlet; 13-Preheater outlet; 14-Serpentine flow channel; 15-Temperature measuring point; 16-Connecting elbow; 17-Forward flow field; 18-Reverse flow field; 19-Turbulence column. Detailed Implementation

[0020] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0022] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0023] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0024] like Figures 1-3The diagram shows an integrated anti-backflow preheating device for spaceborne transient high-power applications, comprising: a power unit and a coke surface 5. The preheating device further includes a waste heat recovery heat exchange component, a preheater 3, a boiling heat exchange component, and a heat dissipation terminal. The preheater 3 is provided with a preheater inlet 12 and a preheater outlet 13. The waste heat recovery heat exchange component is connected to the outlet of the power unit and the preheater inlet 12. The waste heat recovery heat exchange component is also connected to the outlet of the boiling heat exchange component. The preheater outlet 13 is connected to the inlet of the boiling heat exchange component. The coke surface 5 is connected to the boiling heat exchange component. The outlet of the waste heat recovery heat exchange component is also connected to the heat dissipation terminal. The outlet of the heat dissipation terminal is connected to the inlet of the power unit. The preheater 3 is provided with a serpentine flow channel 14 and a Tesla valve unit. The Tesla valve unit is provided on the serpentine flow channel 14, and the Tesla valve unit is also provided with a turbulence column 19.

[0025] The aforementioned integrated anti-backflow preheating device for high-power transient satellite applications utilizes a serpentine flow channel 14 and a Tesla valve unit. A turbulence column 19 is installed on the Tesla valve unit, increasing its internal surface area to exceed that of a simple flow channel of equal length. Under the continuous disturbance of the serpentine bend and Tesla valve unit, the fluid remains in a turbulent state, resulting in a high heat transfer coefficient and uniform working fluid outlet temperature. The turbulence column 19 and Tesla valve unit significantly increase the reverse flow resistance, effectively blocking the reverse impact of the high-temperature vapor-liquid mixture. The rectifying characteristics of the serpentine flow channel 14 and Tesla valve unit transform the flow pulsations generated by the power unit into a stable flow field, providing stable inlet conditions for the boiling heat exchange components. This significantly improves the flow stability and operational adaptability of the pump-driven two-phase circuit, effectively suppressing flow fluctuations from upstream or downstream and providing more stable flow. The serpentine flow channel 14 can be flexibly arranged along the satellite cabin sidewalls and corners, improving space utilization. Compared with traditional preheaters and single-phase preheaters... Compared to valve assemblies, this invention meets the requirements for satellite lightweighting and compactness. The entire assembly is manufactured using 3D printing of aluminum alloy, with no moving mechanical parts, allowing it to withstand extreme temperature differences and microgravity environments, thus improving its on-orbit fault-free operating life. By integrating functions to replace independent components, it reduces potential sources of failure, significantly improving the engineering reliability of the satellite thermal control system. Furthermore, when the camera suddenly starts or experiences a sudden change in heat load, the large amount of steam rapidly generated within the boiling heat exchange component can easily form pulse impacts. Through the instantaneous counter-current effect of the Tesla valve unit, a high-resistance barrier can be quickly formed to prevent backflow of steam, effectively protecting upstream core components such as the power unit from impact damage. This also prevents overshoot of the focal plane 5 temperature due to loop fluctuations, ensuring imaging stability during camera startup. This invention is primarily adapted to high-power single-unit temperature control scenarios in satellites and can be extended to aerospace, aviation, and ground-based high-precision electronic equipment systems requiring efficient preheating, backflow prevention, and strong space adaptability in pump-driven two-phase fluid loop systems.

[0026] like Figures 1-3As shown, in this embodiment, the waste heat recovery heat exchange component is a heat exchanger 2. The heat exchanger 2 is provided with a cold fluid channel 201 and a hot fluid channel 202. The cold fluid channel 201 is connected to the outlet of the power unit and the inlet 12 of the preheater, and the hot fluid channel 202 is connected to the outlet of the boiling heat exchange component and the inlet of the heat dissipation terminal. The heat exchanger 2 is a waste heat recovery type heat exchange component, connected in series on the liquid phase pipeline 8 between the outlet of the power unit and the inlet 12 of the preheater. At the same time, it is connected to the gas-liquid two-phase pipeline of the outlet of the boiling heat exchange component through a branch pipeline. It adopts a shell-and-tube or microchannel plate structure. The cold fluid channel 201 and the hot fluid channel 202 are built into the heat exchanger 2 and are isolated from each other. The cold fluid channel 201 is used to pump the subcooled working fluid. The cold fluid channel 201 and the hot fluid channel 202 exchange heat through the channel wall, reducing the heating power consumption of the subsequent preheater 3.

[0027] like Figures 1-3 As shown, in this embodiment, the preheater 3 is also equipped with a connecting elbow 16, which is connected to the Tesla valve unit. The serpentine flow channel 14 has a 180-degree bend serpentine layout. The Tesla valve unit has a Y-shaped layout, and the included angle M between adjacent Tesla valve units is 115 degrees. Heating elements are laid on the outer wall of the preheater 3, which can further and accurately preheat the working fluid after it has been preheated by the heat exchanger 2 to a near-saturated state. The connecting elbow 16 has a U-shaped cross-section, and the serpentine flow channel 14 is the working fluid flow channel inside the preheater 3. The length of the flow channel is formed by connecting a straight pipe and the U-shaped connecting elbow 16 with a 180° bend in sequence, which is used to extend the heat exchange of the working fluid. The path, in conjunction with the Tesla valve unit, forms a vortex mixing flow field. The connecting elbow 16 is directly and seamlessly connected to the head or tail of two adjacent Tesla valve units, that is, the inlet or outlet of two adjacent Tesla valve units, so that the connecting elbow 16 itself constitutes an integrated part of the Tesla valve unit. The height of the serpentine flow channel 14 is 3mm, the width of the serpentine flow channel 14 is 2mm, and it consists of 4 serpentine structures connected end to end at 180 degrees, with a total length of about 360mm. Each serpentine structure consists of 5 Tesla valve units, the spacing between each Tesla valve unit is 18mm, and the width of the Tesla valve unit is 12.7mm.

[0028] like Figures 1-3As shown, in this embodiment, the power unit is a mechanical pump 1, the boiling heat exchange component is an evaporator 4, and the heat dissipation terminal is a radiative condenser 6. The outlet of the radiative condenser 6 is connected to the inlet of the mechanical pump 1, and the coke surface 5 is connected to the evaporator 4. The mechanical pump 1 provides power for the working fluid in the pump-driven two-phase fluid loop system, pumping the working fluid flowing in the system. The mechanical pump 1 is located at the beginning of the liquid phase pipeline 8 and adopts a satellite-adapted micro-frequency variable centrifugal pump structure. The voltage is adapted to the spacecraft power supply, and the flow rate is adapted to the CCD or CMOS heat dissipation requirements. The speed can be dynamically adjusted to match the changes in the loop heat load, providing a stable driving force for the working fluid circulation. The evaporator 4 is the core component of the boiling heat exchange, which is attached to the outside of the coke surface 5 and connected in series with the outlet of the preheater 3. Evaporator 4 adopts a plate structure with capillary fins on the inner wall to enhance boiling heat transfer. It can absorb the heat load of the focal plane 5 to cause the preheated working fluid to flow and boil, transforming it into a high-temperature gas-liquid two-phase fluid and transporting it to the hot fluid channel 202 in heat exchanger 2. The focal plane 5 is the core component for imaging in remote sensing satellite cameras. It adopts a CMOS or CCD chip integrated structure and needs to maintain high temperature stability to ensure imaging resolution and noise control. The heat load generated by it is conducted to the working fluid through evaporator 4. Radiation condenser 6 is the loop heat dissipation terminal, located on the outlet pipe of hot fluid channel 202 in heat exchanger 2. It can further condense the gas-liquid two-phase working fluid after the waste heat is released by heat exchanger 2 into a subcooled liquid phase through spatial radiation.

[0029] like Figures 1-3 As shown, in this embodiment, the preheating device also includes a liquid phase pipeline 8 and a gas-liquid two-phase pipeline 9. The radiant condenser 6 is connected to the mechanical pump 1, the mechanical pump 1 is connected to the heat exchanger 2, the heat exchanger 2 is connected to the preheater 3, and the preheater 3 is connected to the evaporator 4 through the liquid phase pipeline 8. The radiant condenser 6 is connected to the heat exchanger 2 and the heat exchanger 2 is connected to the evaporator 4 through the gas-liquid two-phase pipeline 9. The liquid phase pipeline 8 is the liquid phase working fluid transport channel to ensure low-resistance transport. The gas-liquid two-phase pipeline 9 is the working fluid transport channel after phase change. The heat loss during the transport process is reduced by adding a heat insulation layer to the pipeline.

[0030] like Figures 1-3 As shown, in this embodiment, the preheating device further includes a liquid receiver 7, which is connected to the outlet of the radiant condenser 6 and the inlet of the mechanical pump 1. The liquid receiver 7 is connected in series between the outlet of the radiant condenser 6 and the inlet of the mechanical pump 1 to buffer the pressure fluctuations in the circuit, compensate for the loss of the working fluid, and stabilize the subcooled working fluid state at the inlet of the mechanical pump 1. The liquid receiver 7 is connected to the radiant condenser 6 and to the mechanical pump 1 through a liquid phase pipeline 8.

[0031] like Figures 1-3As shown, in this embodiment, a heating layer 11 and a heat insulation layer 10 are sequentially arranged on the outside of the preheater 3. The preheater 3 is an integrated component combining a serpentine flow channel 14 and a Tesla valve unit, connected in series between the outlet of the cold fluid flow channel 201 in the heat exchanger 2 and the inlet of the evaporator 4. The preheater 3 is manufactured by 3D printing of aluminum alloy, with a length of 120mm, a width of 90mm, and a height of 7mm. The serpentine flow channel 14 and the Tesla valve unit are used to carry the working fluid flow, realize eddy mixing and unidirectional anti-backflow functions, and the heat insulation layer 10 is... A multilayer polyimide assembly, wrapped around the outer side of the heating layer 11, possesses characteristics of resistance to extreme temperature differences and low thermal conductivity. It is used to prevent heat loss from the preheater 3 to the satellite cabin, while also reducing the interference of external ambient temperature fluctuations on the preheating process. The heating layer 11 is a polyimide thin-film heating element, i.e., a thin-film heater, attached to the outer wall of the preheater 3, providing the preheater 3 with the required heating power. The preheater inlet 12 is the inflow channel for the working fluid, with an interface compatible with the liquid phase pipeline 8. Combined with a PTFE sealing gasket, it can be used for heat exchange. The liquid phase pipeline 8 of the cold fluid flow channel 201 in the preheater 2 is sealed to ensure a stable inflow of subcooled working fluid. The preheater outlet 13 is the working fluid outflow channel, and its interface is adapted to the liquid phase pipeline 8. With the help of a polytetrafluoroethylene sealing gasket, it is sealed to the liquid phase pipeline 8 at the inlet of the evaporator 4 for transporting the nearly saturated working fluid to the evaporator 4. The preheater 3 is also equipped with multiple temperature measuring points 15, which are temperature monitoring nodes. A total of 3 temperature measuring points 15 are set, which are respectively located on the outer wall of the flow channel at the preheater inlet 12 and the preheater outlet 13, as well as the Tesla valve in the middle. In the unit area, temperature measurement point 15 uses a PT100 platinum resistance sensor, also known as a temperature sensor, with a temperature measurement accuracy of ±0.1℃. It can collect temperature data in real time during the preheating process of the working fluid, providing feedback signals for heating power regulation. The thin film heater and the temperature sensor are connected to an external PID controller. The PID controller dynamically adjusts the heating power of the thin film heater based on the temperature signal fed back by the temperature sensor, thereby achieving precise closed-loop control of the thermodynamic state of the working fluid at the preheater outlet 13, stabilizing it at the target subcooling or saturated liquid state.

[0032] like Figure 3 As shown in this embodiment, Figure 3The diagram illustrates the forward and reverse flow states of the preheater 3 of this invention, including a forward flow field 17 and a reverse flow field 18. The forward flow field 17 is a low-resistance heat transfer flow field formed when the working fluid flows from the preheater inlet 12 to the preheater outlet 13. The working fluid enters the main channel of the serpentine flow channel 14 in a subcooled liquid phase state. Due to the angle between the branch and the main channel, i.e., the angle M between adjacent Tesla valve units, and the guiding effect of the serpentine bend, a vortex is formed at the junction of the branch outlet and the main channel. The vortex entrains the high-temperature fluid conducted from the heating layer 11 to the flow channel wall and draws it to the center of the flow channel, eliminating radial temperature stratification. The reverse flow field 18 is a high-resistance flow field formed when the working fluid flows back from the preheater outlet 13 to the preheater inlet 12. The working fluid enters the serpentine flow channel 14 in a high-temperature gas-liquid two-phase state and flows through the branch Tesla valve unit. The opposing fluids in the two branch channels form opposing vortices due to the branch angle limitation. The branch angle is the supplementary angle of the included angle M, which is 65 degrees. After the vortex collision, turbulent dissipation is generated. At the same time, the turbulence column 19 on the inner wall of the flow channel further breaks up the vortex and increases the resistance, which increases the pressure along the flow field and the flow resistance ratio (reverse flow resistance / forward flow resistance), thus achieving the effect of preventing backflow. The turbulence column 19, also known as the Tesla valve island structure, is a key component in the Tesla valve unit that enhances heat transfer and flow resistance. It is integrally formed with the serpentine flow channel 14 and has a height of 3mm. When the flow is forward, it plays a role in turbulence enhancement and can further break up the vortex boundary layer with almost no increase in resistance. When the flow is reverse, it enhances the flow resistance. The turbulence column 19 structure is arranged in the core area of ​​the high-temperature vapor-liquid opposing vortex, which destroys the stability of the vortex and generates local turbulent dissipation.

[0033] like Figures 1-3 As shown, the present invention also includes an integrated anti-backflow preheating method for spaceborne transient high power. This method is based on an integrated anti-backflow preheating device for spaceborne transient high power as described in any of the above claims. The power unit drives the subcooled liquid working fluid to flow through the waste heat recovery heat exchange component and the preheater 3. The preheater 3 heats the liquid working fluid to a specified temperature. Then, the liquid working fluid enters the boiling heat exchange component. In the boiling heat exchange component, the liquid working fluid absorbs the transient high power heat released by the coke surface 5 and undergoes a boiling phase change, transforming the liquid working fluid into a gas-liquid two-phase mixture. The gas-liquid two-phase mixture then flows to the heat dissipation terminal via the waste heat recovery heat exchange component. After being radiated and cooled to the space environment by the heat dissipation terminal, the gas-liquid two-phase mixture re-condenses into a liquid working fluid. The liquid working fluid returns to the power unit, and this cycle continues. Specifically, in actual operation, mechanical pump 1 drives the subcooled liquid working fluid through the cold fluid channel 201 in heat exchanger 2 and preheater 3. The specially designed serpentine channel 14 and Tesla valve unit in preheater 3 cause strong turbulence and mixing of the fluid, thereby achieving full and efficient heat exchange with the heated wall surface. The liquid working fluid is uniformly heated to the set temperature. Then, the liquid working fluid enters evaporator 4, which is thermally coupled with a transient high-power heating element. In evaporator 4, the liquid working fluid absorbs the transient high-power heat released by the element and undergoes a boiling phase change. Here, the element specifically refers to the coke surface 5, or it could be other high-power elements. After the boiling phase change, the liquid working fluid transforms into a gas-liquid two-phase mixture. The gas-liquid two-phase mixture flows through the hot fluid channel 202 to the radiation condenser 6 under the pressure difference. After being radiated and cooled by the radiation condenser 6 to the space environment, the gas-liquid two-phase mixture re-condenses into a liquid working fluid. After the condensate flows through the liquid reservoir 7 to complete the volume adjustment, the liquid working fluid returns to the mechanical pump 1, thus forming a continuous and closed passive heat transfer cycle. When the system encounters a pulse heat load that causes gas-liquid backflow at the evaporator 4 end, the reverse-flowing working fluid enters the high-resistance direction of the Tesla valve unit, generating a large number of vortex structures, resulting in a large amount of kinetic energy dissipation and forming a high local pressure drop, effectively suppressing backflow, protecting upstream components, and ensuring the flow stability and operational reliability of the system under extreme heat loads. A practical implementation case was carried out based on the above method. In the specific implementation case, liquid ammonia was used as the working fluid with a flow rate of 5 g / s. The liquid ammonia temperature was preheated from 5℃ to 15℃. In the actual results, compared with the traditional serpentine preheater, the temperature difference between the fluid boundary layer and the central area was reduced by more than 85%. At the same time, the reverse flow pressure drop of the preheater 3 composed of the serpentine flow channel 14 and the Tesla valve unit was more than 270% of the forward flow pressure drop. It is suitable for two-phase fluid loops of spaceborne transient high-power single units.

[0034] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. An integrated anti-backflow preheating device for spaceborne transient high-power applications, comprising: The power unit and the coke surface (5) are characterized in that the preheating device further includes a waste heat recovery heat exchange component, a preheater (3), a boiling heat exchange component and a heat dissipation terminal. The preheater (3) is provided with a preheater inlet (12) and a preheater outlet (13). The waste heat recovery heat exchange component is connected to the outlet of the power unit and the preheater inlet (12). The waste heat recovery heat exchange component is also connected to the outlet of the boiling heat exchange component. The preheater outlet (13) is connected to the inlet of the boiling heat exchange component. The coke surface (5) is connected to the boiling heat exchange component. The outlet of the waste heat recovery heat exchange component is also connected to the heat dissipation terminal. The outlet of the heat dissipation terminal is connected to the inlet of the power unit. The preheater (3) is provided with a serpentine flow channel (14) and a Tesla valve unit. The Tesla valve unit is provided on the serpentine flow channel (14). The Tesla valve unit is also provided with a turbulence column (19).

2. The integrated anti-backflow preheating device for spaceborne transient high-power applications according to claim 1, characterized in that, The waste heat recovery heat exchange component is a heat exchanger (2). The heat exchanger (2) is provided with a cold fluid flow channel (201) and a hot fluid flow channel (202). The cold fluid flow channel (201) is connected to the outlet of the power unit and the inlet (12) of the preheater, and the hot fluid flow channel (202) is connected to the outlet of the boiling heat exchange component and the inlet of the heat dissipation terminal.

3. The integrated anti-backflow preheating device for spaceborne transient high-power applications according to claim 1, characterized in that, The preheater (3) is also provided with a connecting elbow (16), which is connected to the Tesla valve unit. The serpentine flow channel (14) has a 180-degree zigzag layout.

4. The integrated anti-backflow preheating device for spaceborne transient high-power applications according to claim 1, characterized in that, The Tesla valve unit has a Y-shaped layout, and the included angle M between adjacent Tesla valve units is 115 degrees.

5. The integrated anti-backflow preheating device for spaceborne transient high-power applications according to claim 2, characterized in that, The power unit is a mechanical pump (1), the boiling heat exchange component is an evaporator (4), the heat dissipation terminal is a radiant condenser (6), the outlet of the radiant condenser (6) is connected to the inlet of the mechanical pump (1), and the coke surface (5) is connected to the evaporator (4).

6. The integrated anti-backflow preheating device for spaceborne transient high-power applications according to claim 5, characterized in that, The preheating device also includes a liquid phase pipeline (8) and a gas-liquid two-phase pipeline (9). The radiant condenser (6) is connected to the mechanical pump (1), the mechanical pump (1) is connected to the heat exchanger (2), the heat exchanger (2) is connected to the preheater (3), and the preheater (3) is connected to the evaporator (4) through the liquid phase pipeline (8). The radiant condenser (6) is connected to the heat exchanger (2), and the heat exchanger (2) is connected to the evaporator (4) through the gas-liquid two-phase pipeline (9).

7. The integrated anti-backflow preheating device for spaceborne transient high-power applications according to claim 6, characterized in that, The preheating device also includes a liquid storage tank (7), which is connected to the outlet of the radiant condenser (6) and the inlet of the mechanical pump (1).

8. The integrated anti-backflow preheating device for spaceborne transient high-power applications according to claim 7, characterized in that, The liquid storage tank (7) is connected to the radiant condenser (6) and the liquid storage tank (7) is connected to the mechanical pump (1) via liquid phase pipelines (8).

9. The integrated anti-backflow preheating device for spaceborne transient high-power applications according to claim 1, characterized in that, The preheater (3) is provided with a heating layer (11) and a heat insulation layer (10) in sequence on the outside.

10. A preheating method for preventing backflow during transient high-power spaceborne applications, the method being implemented based on the integrated preheating device for preventing backflow during transient high-power spaceborne applications as described in any one of claims 1 to 9, characterized in that... The power unit drives the subcooled liquid working fluid to flow through the waste heat recovery heat exchange component and the preheater (3). The preheater (3) heats the liquid working fluid to a specified temperature. Then the liquid working fluid enters the boiling heat exchange component. In the boiling heat exchange component, the liquid working fluid absorbs the transient high-power heat released by the coke surface (5) and undergoes a boiling phase change. The liquid working fluid is transformed into a gas-liquid two-phase mixture. The gas-liquid two-phase mixture then flows to the heat dissipation terminal through the waste heat recovery heat exchange component. After the gas-liquid two-phase mixture is radiated to the space environment by the heat dissipation terminal, it re-condenses into a liquid working fluid. The liquid working fluid returns to the power unit, and the cycle continues.

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