Loop heat pipe temperature control method and device for on-orbit refueling gas tank

Abstract

The present disclosure provides a loop heat pipe temperature control method and device for in-orbit refueling gas tank. The present disclosure is connected with the controlled gas tank in heat conduction, and the loop heat pipe is provided with a liquid accumulator. The outer wall of the liquid accumulator is provided with a refrigeration fin. The temperature control method comprises the following steps: in the case that the measured temperature of the controlled gas tank is greater than the preset target temperature of the controlled gas tank, the effective over-temperature amount of the controlled gas tank is determined based on the measured temperature, the preset target temperature and the preset upper limit of temperature dead zone; in the case that the effective over-temperature amount is greater than zero, the two-phase region temperature adjustment amount of the liquid accumulator is determined based on the effective over-temperature amount and the preset proportional compensation coefficient, and the two-phase region temperature adjustment amount is converted into the target net refrigeration power of the refrigeration fin; the refrigeration fin is started and controlled to operate at the target net refrigeration power until the measured temperature of the controlled gas tank falls below the sum of the preset target temperature and the preset upper limit of temperature dead zone. The temperature control method of the present disclosure can improve the temperature control stability and accuracy of the in-orbit refueling gas tank.

Description

Technical Field

[0001] This disclosure relates to the field of thermal control technology for on-orbit refueling of spacecraft, specifically to a loop heat pipe temperature control method and device for on-orbit refueling gas containers. Background Technology

[0002] In-orbit refueling is a core on-orbit service technology for extending the service life of spacecraft and reducing the cost of space launches. In-orbit refueling systems include gas tanks for storing high-pressure booster gases. The gas pressure inside these tanks directly depends on their temperature; temperature fluctuations can cause unstable gas supply pressure, affecting propellant flow and operational safety. Therefore, high-precision temperature control of the gas tanks is necessary.

[0003] Currently, thermal control methods for gas containers used in on-orbit refueling mainly rely on loop heat pipes in conjunction with refrigeration components to achieve refrigeration regulation. However, existing temperature control methods are mostly simple on / off temperature control, that is, directly starting and stopping the refrigeration components based solely on the gas container temperature. This control method has the following drawbacks: on the one hand, micro-disturbances in orbit can easily cause frequent starting and stopping of the refrigeration components, resulting in repeated fluctuations in the gas container temperature and poor temperature control stability; on the other hand, the refrigeration output cannot match the real-time temperature control requirements, resulting in a low degree of matching between the refrigeration capacity and the actual temperature control requirements, and insufficient temperature control accuracy.

[0004] In summary, existing temperature control methods suffer from poor temperature control stability and insufficient temperature control accuracy. Summary of the Invention

[0005] This disclosure addresses the problems existing in the prior art by providing a loop heat pipe temperature control method and device for on-orbit refueling gas capacity, which can effectively solve the problems of poor temperature control stability and insufficient temperature control accuracy in existing temperature control methods.

[0006] To achieve the above objectives, the technical solution adopted in this disclosure is as follows: A first aspect of this disclosure provides a loop heat pipe temperature control method for an on-orbit refueling gas container. The controlled gas container is thermally connected to the loop heat pipe, the loop heat pipe is equipped with a liquid receiver, and a cooling fin is disposed on the outer wall of the liquid receiver. The method includes: when the measured temperature of the controlled gas container is greater than the preset target temperature of the controlled gas container, determining the effective over-temperature of the controlled gas container based on the measured temperature, the preset target temperature, and the upper limit of the preset temperature dead zone; when the effective over-temperature is greater than zero, determining the two-phase zone temperature adjustment of the liquid receiver based on the effective over-temperature and a preset proportional compensation coefficient, and converting the two-phase zone temperature adjustment into the target net cooling power of the cooling fin; starting and controlling the cooling fin to operate at the target net cooling power until the measured temperature of the controlled gas container falls below the sum of the preset target temperature and the upper limit of the preset temperature dead zone.

[0007] In some embodiments of this disclosure, the temperature adjustment amount of the two-phase region of the liquid receiver is determined based on the effective overheat amount and a preset proportional compensation coefficient, and the temperature adjustment amount of the two-phase region is converted into the target net cooling power of the cooling chip. This includes: determining the temperature adjustment amount of the two-phase region of the liquid receiver based on the effective overheat amount and the preset proportional compensation coefficient; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the preset proportional compensation coefficient; and using an equivalent heat capacity model of the liquid receiver, the temperature adjustment amount of the two-phase region is converted into the target net cooling power of the cooling chip.

[0008] In some embodiments of this disclosure, the preset proportional compensation coefficient includes a first proportional compensation coefficient, a second proportional compensation coefficient, and a third proportional compensation coefficient. Determining the temperature adjustment amount of the two-phase region of the liquid receiver based on the effective overheat amount and the preset proportional compensation coefficient includes: determining the temperature adjustment amount of the two-phase region of the liquid receiver based on the effective overheat amount and the first proportional compensation coefficient, the second proportional compensation coefficient, or the third proportional compensation coefficient; wherein the first proportional compensation coefficient is greater than the second proportional compensation coefficient, and the second proportional compensation coefficient is greater than the third proportional compensation coefficient; the first proportional compensation coefficient is any value within the range of 1.10 to 1.30, the second proportional compensation coefficient is any value within the range of 0.90 to 1.09, and the third proportional compensation coefficient is any value within the range of 0.70 to 0.89.

[0009] In some embodiments of this disclosure, the temperature adjustment amount of the two-phase region of the liquid reservoir is determined based on the effective overheat amount and a first proportional compensation coefficient, a second proportional compensation coefficient, or a third proportional compensation coefficient. This includes: determining the temperature adjustment amount of the two-phase region based on the effective overheat amount and the first proportional compensation coefficient; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the first proportional compensation coefficient; wherein, the first proportional compensation coefficient is preferably 1.20.

[0010] In some embodiments of this disclosure, the temperature adjustment amount of the two-phase region of the liquid reservoir is determined based on the effective overheat amount and a first proportional compensation coefficient, a second proportional compensation coefficient, or a third proportional compensation coefficient. This includes: determining the temperature adjustment amount of the two-phase region based on the effective overheat amount and the second proportional compensation coefficient; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the second proportional compensation coefficient; wherein, the second proportional compensation coefficient is preferably 1.00.

[0011] In some embodiments of this disclosure, the temperature adjustment amount of the two-phase region of the liquid reservoir is determined based on the effective overheat amount and a first proportional compensation coefficient, a second proportional compensation coefficient, or a third proportional compensation coefficient. This includes: determining the temperature adjustment amount of the two-phase region based on the effective overheat amount and the third proportional compensation coefficient; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the third proportional compensation coefficient; wherein, the third proportional compensation coefficient is preferably 0.80.

[0012] In some embodiments of this disclosure, the equivalent heat capacity model of the liquid reservoir includes: In the formula, The target net cooling power of the thermoelectric cooler. The equivalent heat capacity of the reservoir and its internal working fluid. This is the temperature adjustment amount for the two-phase region of the liquid receiver. τ For the expected response time, Heat is transferred from the reservoir to the environment and adjacent structures.

[0013] In some embodiments of this disclosure, the effective overtemperature amount of the controlled gas capacity is determined based on the measured temperature, the preset target temperature, and the upper limit of the preset temperature dead zone. This includes: determining the overtemperature amount of the controlled gas capacity based on the measured temperature and the preset target temperature; the overtemperature amount is the difference between the measured temperature and the preset target temperature; determining the effective overtemperature amount of the controlled gas capacity based on the overtemperature amount and the upper limit of the preset temperature dead zone; the effective overtemperature amount is the difference between the overtemperature amount and the upper limit of the preset temperature dead zone; wherein, the preset target temperature is any temperature value within the range of -20℃ to 50℃, and the upper limit of the preset temperature dead zone is any temperature value within the range of 0.05℃ to 0.2℃.

[0014] In some embodiments of this disclosure, the method further includes: when the measured temperature of the controlled gas container falls below the sum of the preset target temperature and the upper limit of the preset temperature dead zone, gradually reducing the net cooling power of the cooling chip to zero; and keeping the net cooling power of the cooling chip at zero until the next effective over-temperature is greater than zero.

[0015] A second aspect of this disclosure provides a loop heat pipe temperature control device for an on-orbit refueling gas container, comprising a controlled gas container, a loop heat pipe, a temperature sensor for acquiring the measured temperature of the controlled gas container, and a controller; wherein the controlled gas container is thermally connected to the loop heat pipe, the loop heat pipe is equipped with a liquid reservoir, a cooling fin is disposed on the outer wall of the liquid reservoir, and the controller is connected to the cooling fin and the temperature sensor respectively; the controller is configured to execute the loop heat pipe temperature control method for an on-orbit refueling gas container according to the first aspect or any embodiment of the first aspect.

[0016] Compared with the prior art, this disclosure has the following beneficial effects: The loop heat pipe temperature control method for on-orbit refueling gas tanks disclosed herein quantifies and determines the temperature adjustment amount in the two-phase region of the reservoir by means of effective overheating and a preset proportional compensation coefficient. This is then used to dynamically calculate and match the target net cooling power of the cooling elements. This method can adapt to the differentiated heat transfer characteristics of different types of loop heat pipes, achieving refined and adaptive cooling control. This overall control method abandons the traditional on / off coarse temperature control mode, effectively suppressing frequent equipment start-ups and shutdowns and temperature oscillations caused by on-orbit temperature disturbances and environmental thermal fluctuations, thus improving the temperature control stability and accuracy of the on-orbit refueling gas tanks. Attached Figure Description

[0017] Figure 1 This is a schematic flowchart of a loop heat pipe temperature control method for an on-orbit refueling gas container provided according to an embodiment of this disclosure; Figure 2 This is a partial structural block diagram of a loop heat pipe temperature control device for an on-orbit refueling gas container provided according to an embodiment of this disclosure; Figure 3 This is a partial structural block diagram of a loop heat pipe temperature control device for another on-orbit refueling gas container provided according to an embodiment of this disclosure. Detailed Implementation

[0018] The present disclosure will now be further described with reference to the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solutions of the present disclosure and should not be construed as limiting the scope of protection of the present disclosure. It should be noted that the following detailed descriptions are exemplary and intended to provide further explanation of this application.

[0019] The acquisition, transmission, storage, use, and processing of data in this disclosed technical solution comply with relevant national laws and regulations. In the embodiments of this disclosure, certain existing industry solutions such as software, components, and models may be mentioned. These should be considered exemplary, intended only to illustrate the feasibility of implementing the technical solution of this disclosure, and do not imply that the applicant has already used or necessarily used such solutions.

[0020] All terms used in this disclosure have the same meaning as understood by one of ordinary skill in the art to which this disclosure pertains, unless otherwise specifically defined. It should also be understood that terms defined in general dictionaries should be interpreted as having meanings consistent with their meanings in the context of the relevant art, and not as idealized or highly formalized, unless expressly defined herein.

[0021] This disclosure provides a loop heat pipe temperature control device for an on-orbit refueling gas capacity, such as... Figure 1 and Figure 2 As shown, it includes a controlled gas container 1, a loop heat pipe 2, a temperature sensor 6 for acquiring the measured temperature of the controlled gas container 1, and a controller 7; wherein, the controlled gas container 1 is thermally connected to the loop heat pipe 2, specifically through the evaporator 5 of the loop heat pipe 2; the loop heat pipe 2 is equipped with a liquid reservoir 3, and a cooling chip 4 is provided on the outer wall of the liquid reservoir 3; the controller 7 is connected to the cooling chip 4 and the temperature sensor 6 respectively; the controller 7 is configured to execute the loop heat pipe temperature control method for on-orbit refueling gas container described in any embodiment of this disclosure.

[0022] In this embodiment, the cooling control principle of the loop heat pipe is as follows: When the effective overheat of the controlled gas container 1 (measured temperature of the controlled gas container - preset target temperature - upper limit of preset temperature dead zone) is greater than zero, the controller 7 lowers the temperature of the two-phase region of the liquid receiver 3, starts the cooling chip 4, and causes some of the vapor in the two-phase region of the liquid receiver 3 to condense. The pressure of the liquid receiver 3 decreases along the working fluid saturation temperature-pressure curve. The controller 7 calculates the cooling chip power through the equivalent heat capacity model of the liquid receiver.

[0023] In some embodiments, heating regulation is also included. Heating elements may be provided on the outer wall of the controlled gas container 1. The specific heating regulation principle is similar to the cooling regulation principle described above: when the effective undertemperature of the controlled gas container 1 (measured temperature of the controlled gas container - preset target temperature - preset temperature dead zone lower limit) is less than zero, the controller 7 increases the temperature of the two-phase region of the liquid receiver 3, and the saturated pressure of the working fluid increases accordingly, thereby improving the heat exchange capacity of the loop heat pipe and realizing the temperature regulation of the controlled gas container 1; under this condition, the heating power can also be calculated based on the equivalent heat capacity model of the liquid receiver.

[0024] This disclosure provides a loop heat pipe temperature control method for an on-orbit refueling gas container, and the following is a detailed description of the loop heat pipe temperature control method.

[0025] like Figure 3 As shown, the loop heat pipe temperature control method specifically includes the following steps S11 to S13.

[0026] Step S11: When the measured temperature of the controlled gas container is greater than the preset target temperature of the controlled gas container, determine the effective overtemperature amount of the controlled gas container based on the measured temperature, the preset target temperature and the upper limit of the preset temperature dead zone.

[0027] It should be noted that, in this embodiment, the controlled gas container refers to the sealed, pressure-resistant cavity structure used for storing and buffering the working fluid during on-orbit refueling in the on-orbit refueling system, and is the controlled object of the temperature control method of this disclosure. The measured temperature refers to the surface temperature or internal medium temperature of the controlled gas container obtained in real time through a temperature sensor, which can accurately reflect the real-time thermal state of the controlled gas container. The preset target temperature includes the pre-set optimal operating temperature under on-orbit cryogenic vacuum conditions, suitable for normal on-orbit refueling operation, structural stability, and working fluid property stability of the controlled gas container. The preset temperature dead zone upper limit refers to the pre-calibrated upper limit threshold of the allowable temperature deviation to avoid frequent start-stop of the temperature control system and the occurrence of temperature oscillation overshoot problems. The effective over-temperature amount refers to the quantitative control parameter used to characterize the real-time over-temperature degree of the controlled gas container, and is the core calculation basis for the temperature control system to carry out refrigeration control.

[0028] Additionally, it should be noted that in this embodiment, the overall execution entity for this step is the controller of the temperature control system. The core purpose of this step is to accurately determine the over-temperature condition of the controlled gas capacity, eliminate invalid control signals caused by small temperature fluctuations, and avoid the problems of frequent start-stop of the cooling element and system temperature oscillation. The implementation idea of ​​this step is as follows: the temperature control system continuously compares the real-time temperature status of the controlled gas capacity with the standard operating temperature range. When the measured temperature exceeds the preset target temperature, it combines the preset temperature dead zone threshold to quantitatively calculate the accurate over-temperature offset, providing accurate input parameters for subsequent cooling power adjustment and temperature closed-loop control, ensuring the stability and accuracy of temperature control. Through the setting of this step, it is possible to effectively filter out erroneous control commands caused by micro-disturbances and slight measurement errors of sensors in the on-orbit space environment, and improve the stability of long-term on-orbit temperature control.

[0029] In one possible implementation, the preset upper limit of the temperature dead zone can be dynamically calibrated according to the on-orbit operating conditions. Different upper limit values ​​of the temperature dead zone are configured for two different working modes: the on-orbit refueling operation stage and the on-orbit standby static stage. A small upper limit of the dead zone is used in the operation stage to ensure temperature control accuracy, while a large upper limit of the dead zone is used in the standby stage to reduce system power consumption.

[0030] In another possible implementation, the calculation of the effective overtemperature quantity can be combined with historical temperature data for filtering and correction to eliminate instantaneous temperature spikes and ensure that the calculated effective overtemperature quantity can truly reflect the steady-state overtemperature state of the controlled gas capacity.

[0031] In some embodiments of this disclosure, the effective overtemperature amount of the controlled gas capacity is determined based on the measured temperature, the preset target temperature, and the upper limit of the preset temperature dead zone. This includes: determining the overtemperature amount of the controlled gas capacity based on the measured temperature and the preset target temperature; the overtemperature amount is the difference between the measured temperature and the preset target temperature; determining the effective overtemperature amount of the controlled gas capacity based on the overtemperature amount and the upper limit of the preset temperature dead zone; the effective overtemperature amount is the difference between the overtemperature amount and the upper limit of the preset temperature dead zone; wherein, the preset target temperature is any temperature value within the range of -20℃ to 50℃, which can be determined according to the working conditions of the actual application scenario, and the upper limit of the preset temperature dead zone is any temperature value within the range of 0.05℃ to 0.2℃, which can be set according to the temperature control accuracy requirements.

[0032] For example, in one specific embodiment, a preset target temperature is set. 21℃, temperature dead zone e_dead The temperature dead zone is -0.2℃ to 0.2℃ (i.e., the upper limit of the preset temperature dead zone). (0.2℃), initial temperature of the two-phase region of the reservoir At 20°C, the initial pressure in the two-phase region of the reservoir... The pressure is 0.85784 MPa (saturation pressure of ammonia at 20℃), when the measured temperature of the controlled gas volume is... Calculate the overheat amount at 22℃. Further calculation of effective overtemperature ,because A value greater than 0 indicates that the gas temperature has exceeded the allowable dead zone, and the controller should enter cooling control. At this time, the liquid receiver cooling chip should be turned on to lower the temperature of the liquid receiver's two-phase region.

[0033] It should be noted that in actual engineering, temperature sensors are subject to measurement errors, sampling noise, and the influence of installation thermal resistance. Without a dead zone, if the measured temperature exceeds the target temperature by even 0.001℃, the integral term will begin to accumulate, causing the receiver's cooling coils to frequently start and stop, resulting in oscillations in the gas-capacity temperature.

[0034] Step S12: When the effective over-temperature is greater than zero, determine the two-phase temperature adjustment amount of the liquid receiver based on the effective over-temperature and the preset proportional compensation coefficient, and convert the two-phase temperature adjustment amount into the target net cooling power of the cooling chip.

[0035] It should be noted that, in this embodiment, the preset proportional compensation coefficient refers to a control coefficient pre-calibrated by the temperature control system, used to characterize the linear correspondence between the effective overheat amount and the temperature adjustment amount in the two-phase region of the liquid receiver, and is used to achieve proportional closed-loop compensation for temperature deviation. The liquid receiver includes the core cavity structure in the loop heat pipe system used to store the liquid working fluid, achieve phase change buffering and pressure regulation, and is the core component for controlling the heat exchange capacity of the loop heat pipe. The two-phase region refers to the gas-liquid coexistence phase change region inside the liquid receiver where both liquid and gaseous working fluids coexist. The temperature and pressure of this region directly determine the overall heat exchange performance of the loop heat pipe. The two-phase region temperature adjustment amount refers to the temperature change amplitude required to adjust the temperature of the two-phase region of the liquid receiver to offset the overheat deviation of the controlled gas capacity. The cooling element refers to a temperature control actuator based on the semiconductor thermoelectric cooling principle used for active cooling control of the liquid receiver. The target net cooling power refers to the precise operating power of the cooling element required to accurately offset the overheat heat of the controlled gas capacity and achieve temperature drop.

[0036] Furthermore, it should be noted that in this embodiment, the execution entity of this step is the controller of the temperature control system. The core purpose of this step is to convert the quantified temperature over-temperature deviation into corresponding device control parameters, thereby achieving a precise mapping from temperature deviation to cooling power. The implementation approach is as follows: Given that the controlled gas capacity exhibits effective over-temperature, a proportional compensation coefficient is used to calculate the proportional compensation of the temperature deviation, determining the required temperature adjustment for the two-phase region of the liquid receiver. Then, combined with the equivalent heat capacity model of the liquid receiver, parameter conversion is performed, transforming the temperature adjustment into the target net cooling power that the cooling element can execute, thus achieving precise conversion of temperature control parameters. Through this step, the over-temperature amount and cooling power can be matched and controlled, avoiding the problems of excessive cooling power causing overcooling or insufficient cooling power preventing temperature reduction, thereby improving the accuracy of temperature control.

[0037] In some embodiments of this disclosure, the temperature adjustment amount of the two-phase region of the liquid receiver is determined based on the effective overheat amount and a preset proportional compensation coefficient, and the temperature adjustment amount of the two-phase region is converted into the target net cooling power of the cooling chip. This includes: determining the temperature adjustment amount of the two-phase region of the liquid receiver based on the effective overheat amount and the preset proportional compensation coefficient; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the preset proportional compensation coefficient; and using an equivalent heat capacity model of the liquid receiver, the temperature adjustment amount of the two-phase region is converted into the target net cooling power of the cooling chip.

[0038] In some embodiments of this disclosure, the equivalent heat capacity model of the liquid reservoir includes: In the formula, The target net cooling power of the thermoelectric cooler. The equivalent heat capacity of the reservoir and its internal working fluid. τ represents the temperature adjustment of the two-phase region of the liquid reservoir, and τ represents the desired response time. Heat is transferred from the reservoir to the environment and adjacent structures.

[0039] For example, in one specific embodiment, a preset proportional compensation coefficient is set for a certain type of loop heat pipe under this operating condition. That is, for every 1°C increase in effective overtemperature, the target temperature of the two-phase region of the liquid reservoir is reduced by 1°C, based on the result obtained in step S12. For example, the temperature adjustment amount in the two-phase region Given the initial temperature of the two-phase region of the liquid reservoir. The target temperature for the two-phase region of the liquid reservoir is 20℃. It is understandable that the target temperature of the liquid receiver two-phase zone given in this control cycle is 19.2℃. The physical meaning is: the actual temperature of the gas container is 1℃ higher than the preset target temperature. After deducting the 0.2℃ dead zone, the operating temperature of the liquid receiver will be lowered by 0.8℃ first, so that the gas container temperature is expected to fall back to near the upper dead zone of the preset target temperature. It is not a one-time large-scale cooling.

[0040] When ammonia is in two-phase equilibrium within the reservoir, the reservoir pressure is uniquely determined by the ammonia saturation temperature. Since the target temperature of 19.2℃ may not exactly appear in the property table, it can be directly read from the REFPROP (Reference Fluid Thermodynamics and Transport Properties) database, or linear interpolation can be performed between adjacent table points. To facilitate explanation of the interpolation process, the saturation pressure of the previous temperature point can be used for adjacent temperature points in the ammonia saturation table. The saturation pressure at the next temperature point is 0.83080 MPa. If the pressure is 0.85784 MPa, then the saturation pressure at the target temperature of 19.2℃ in the two-phase region is: ; Right now ; The initial pressure in the two-phase region of the reservoir is known. The saturation pressure adjustment is 0.85784 MPa (saturation pressure of ammonia at 20℃). =-21.63 kPa; Calculations show that after the temperature of the reservoir drops from 20°C to 19.2°C, its saturation pressure decreases from 0.85784 MPa to approximately 0.83621 MPa, a decrease of about 21.63 kPa. This result is consistent with the physical law that "as temperature decreases, saturation pressure decreases" in ammonia saturation curves.

[0041] Due to the target temperature of the two-phase region of the reservoir Less than the initial temperature of the two-phase region of the reservoir The controller output should be a cooling command. The goal of the receiver cooling element is not to directly remove the circuit pressure, but to remove heat from the two-phase region of the receiver, causing some of the ammonia vapor to condense, thus lowering the two-phase temperature of the receiver and consequently reducing the saturation pressure along the ammonia saturation curve.

[0042] If it is necessary to convert the target temperature of the two-phase region into the net cooling power of the cooling chip, the equivalent heat capacity model of the liquid receiver can be used: ; In the formula, The target net cooling power of the thermoelectric cooler. The equivalent heat capacity of the reservoir and its internal working fluid. The initial temperature of the two-phase region of the liquid reservoir. The target temperature for the two-phase region of the liquid reservoir. This is the temperature adjustment amount for the two-phase region of the liquid receiver. τ For the expected response time, Heat is transferred from the reservoir to the environment and adjacent structures.

[0043] In some embodiments of this disclosure, the preset proportional compensation coefficient includes a first proportional compensation coefficient, a second proportional compensation coefficient, and a third proportional compensation coefficient. Determining the temperature adjustment amount of the two-phase region of the liquid receiver based on the effective overheat amount and the preset proportional compensation coefficient includes: determining the temperature adjustment amount of the two-phase region of the liquid receiver based on the effective overheat amount and the first proportional compensation coefficient, the second proportional compensation coefficient, or the third proportional compensation coefficient; wherein the first proportional compensation coefficient is greater than the second proportional compensation coefficient, and the second proportional compensation coefficient is greater than the third proportional compensation coefficient; the first proportional compensation coefficient is any value within the range of 1.10 to 1.30, the second proportional compensation coefficient is any value within the range of 0.90 to 1.09, and the third proportional compensation coefficient is any value within the range of 0.70 to 0.89.

[0044] It should be noted that different proportional compensation coefficients can be adapted to the heat transfer performance scenarios of different types of loop heat pipes, achieving differentiated and precise control. Specifically, the first proportional compensation coefficient is suitable for low-power loop heat pipes, such as the C13 type loop heat pipe with a heat transfer capacity of 150W. This type of loop heat pipe has limited heat transfer capacity and low temperature response sensitivity under slight over-temperature conditions. By using a larger first proportional compensation coefficient, the temperature adjustment can be appropriately amplified to compensate for the heat transfer lag characteristic of low-power heat pipes, ensuring temperature control response speed and control accuracy. The second proportional compensation coefficient is suitable for medium-power loop heat pipes, such as the C18 type loop heat pipe with a heat transfer capacity of 300W. This type of loop heat pipe has balanced heat transfer performance and moderate response speed, with no significant heat transfer lag or heat transfer overload problems under normal over-temperature conditions. A coefficient around 1.00 is used to compensate for this. The second proportional compensation coefficient achieves a proportional match between the temperature adjustment amount and the effective over-temperature amount, enabling stable adaptation to conventional on-orbit over-temperature conditions while balancing temperature control accuracy and stability. The third proportional compensation coefficient is suitable for high-power loop heat pipes, such as the C25 type loop heat pipe with a heat transfer capacity of 800W. This type of loop heat pipe has a large heat transfer power and fast heat exchange response speed, resulting in high heat dissipation redundancy under significant over-temperature conditions. It is prone to overheating, leading to temperature overshoot and localized overcooling. By using a smaller third proportional compensation coefficient, the temperature adjustment amount is appropriately reduced, buffering the strong heat transfer characteristics of the high-power heat pipe, effectively suppressing temperature control oscillations and over-control phenomena, and ensuring a smooth temperature drop under significant cooling conditions. Each proportional compensation coefficient can be obtained through ground thermal vacuum tests combined with corresponding heat pipe type parameters. The optimal value is then fitted using full-condition on-orbit thermal load test data to ensure the linearity and accuracy of temperature control under all conditions.

[0045] In some embodiments of this disclosure, the temperature adjustment amount of the two-phase region of the liquid reservoir is determined based on the effective overheat amount and a first proportional compensation coefficient, a second proportional compensation coefficient, or a third proportional compensation coefficient. This includes: determining the temperature adjustment amount of the two-phase region based on the effective overheat amount and the first proportional compensation coefficient; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the first proportional compensation coefficient; wherein, the first proportional compensation coefficient is preferably 1.20.

[0046] In some embodiments of this disclosure, the temperature adjustment amount of the two-phase region of the liquid reservoir is determined based on the effective overheat amount and a first proportional compensation coefficient, a second proportional compensation coefficient, or a third proportional compensation coefficient. This includes: determining the temperature adjustment amount of the two-phase region based on the effective overheat amount and the second proportional compensation coefficient; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the second proportional compensation coefficient; wherein, the second proportional compensation coefficient is preferably 1.00.

[0047] In some embodiments of this disclosure, the temperature adjustment amount of the two-phase region of the liquid reservoir is determined based on the effective overheat amount and a first proportional compensation coefficient, a second proportional compensation coefficient, or a third proportional compensation coefficient. This includes: determining the temperature adjustment amount of the two-phase region based on the effective overheat amount and the third proportional compensation coefficient; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the third proportional compensation coefficient; wherein, the second proportional compensation coefficient is preferably 0.80.

[0048] Step S13: Start and control the cooling chip to operate at the target net cooling power until the measured temperature of the controlled gas volume falls below the sum of the preset target temperature and the upper limit of the preset temperature dead zone.

[0049] It should be noted that, in this embodiment, the target net cooling power refers to the rated operating power of the cooling element that can accurately achieve temperature drop when matching the controlled gas capacity over-temperature condition. The sum of the preset target temperature and the preset upper limit of the temperature dead zone refers to the highest safe operating temperature threshold allowed by the controlled gas capacity, which is the core criterion for determining the end of over-temperature control.

[0050] Additionally, it should be noted that in this embodiment, the execution entities for this step are the controller and cooling element of the temperature control system. The core purpose of this step is to perform closed-loop cooling regulation, eliminate the over-temperature deviation of the controlled gas container, and bring the temperature of the controlled gas container back to the standard operating range. The implementation idea of ​​this step is as follows: the temperature control system drives the cooling element to operate stably according to the calculated target net cooling power. The cooling element cools the two-phase region of the liquid receiver, reducing the saturation pressure of the working fluid inside the liquid receiver, improving the heat exchange and dissipation capacity of the loop heat pipe, continuously removing excess heat from the controlled gas container, and monitoring the measured temperature change of the controlled gas container in real time until the measured temperature falls back to the safe temperature threshold range, completing a single over-temperature cooling regulation process. Through this step, closed-loop precise temperature regulation can be achieved, effectively solving the problem of excessive temperature rise in the controlled gas container under on-orbit conditions and ensuring the long-term stable operation of the on-orbit refueling equipment.

[0051] In this embodiment of the disclosure, after the saturation pressure of the liquid receiver decreases, the loop pressure level will decrease in the same direction. The saturation pressure at the evaporator should be written as the liquid receiver pressure plus the corresponding loop pressure drop term.

[0052] Right now In the formula, The saturation pressure at the evaporator. The saturation pressure of the reservoir. This is the loop voltage drop term.

[0053] Within a small adjustment step of this embodiment, if the loop flow and voltage drop do not change significantly, then After a reduction of approximately 21.63 kPa, It also decreases by approximately the same order of magnitude. Since the saturation pressure of ammonia corresponds one-to-one with its saturation temperature, the saturation temperature of the working fluid in the evaporator also decreases accordingly, approximately from 20℃ to 19.2℃.

[0054] The gas volume temperature can be approximately expressed as the evaporator saturation temperature plus the temperature difference caused by the heat transfer resistance: Right now In the formula, For gas volume temperature, This is the saturation temperature of the working fluid inside the evaporator. For the gas-capacity side heat load, For equivalent thermal resistance, This is the interface contact temperature difference (i.e., the temperature drop corresponding to the contact thermal resistance).

[0055] If in a short period of time , If the change in contact thermal resistance is not significant, then after the evaporator saturation temperature decreases by approximately 0.8℃, the gas volume temperature will also decrease by approximately 0.8℃ later, meaning the updated gas volume temperature... The temperature of 21.2℃ is exactly equal to the preset target temperature of 21℃ plus the upper limit of the dead zone of 0.2℃, indicating that the gas volume temperature has been pulled back from the obviously overheated state to the allowable dead zone boundary.

[0056] In some embodiments of this disclosure, the method further includes: when the measured temperature of the controlled gas container falls below the sum of the preset target temperature and the upper limit of the preset temperature dead zone, gradually reducing the net cooling power of the cooling chip to zero; and keeping the net cooling power of the cooling chip at zero until the next effective over-temperature is greater than zero.

[0057] For ease of understanding, the following example uses ammonia as the working fluid, setting a preset target temperature. 21℃, temperature dead zone e_dead The temperature dead zone is -0.2℃ to 0.2℃ (i.e., the upper limit of the preset temperature dead zone). (0.2℃), initial temperature of the two-phase region of the reservoir At 20°C, the initial pressure in the two-phase region of the reservoir... The refrigeration control logic of the embodiments of this disclosure is described in general as 0.85784 MPa (saturation pressure of ammonia at 20°C).

[0058] The cooling control logic of this embodiment can be described as follows: When the measured temperature of the controlled gas container (22°C) is higher than the preset target temperature (21°C) and exceeds the 0.2°C dead zone, the controller determines that the heat source has an effective over-temperature of 0.8°C. Therefore, it activates the receiver cooling coil, lowering the target temperature of the receiver's two-phase region from 20°C to 19.2°C. According to the ammonia saturated property table interpolation, the receiver saturation pressure drops from 0.85784 MPa to approximately 0.83621 MPa, a decrease of approximately 21.63 kPa. After the receiver pressure decreases, the loop pressure level and the evaporator saturation pressure decrease in the same direction, and the evaporator saturation temperature decreases accordingly. With the load power and interface thermal resistance remaining approximately constant for a short period, the heat source temperature is expected to drop from 22°C to approximately 21.2°C, i.e., return to the dead zone boundary of the preset target temperature. If the over-temperature continues, the cooling compensation is further increased through the temperature rise rate term and the over-temperature integral term. If the temperature returns to the dead zone, the cooling capacity is gradually reduced to zero to prevent temperature overshoot.

[0059] In some embodiments of this disclosure, a heating control step is also included. The specific heating control step is similar to the specific cooling control step described above, and will not be repeated here.

[0060] It should be noted that the terms "first," "second," and similar terms used in this disclosure do not indicate any order, quantity, or importance, but are merely used to distinguish different parts. Terms such as "including" or "contains" mean that the element preceding the word covers the element listed after the word, and do not exclude the possibility of covering other elements as well.

[0061] Although operations are described in a specific order in the accompanying drawings in this disclosure, it should not be construed as requiring these operations to be performed in the specific order or serial order shown, or requiring all of the shown operations to obtain the desired result. In certain environments, multitasking and parallel processing may be advantageous.

[0062] Finally, it should be noted that the above content is only used to illustrate the technical solution of this disclosure, and is not intended to limit the scope of protection of this disclosure. Simple modifications or equivalent substitutions made by those skilled in the art to the technical solution of this disclosure do not depart from the substance and scope of the technical solution of this disclosure.

Claims

1. A method for controlling the temperature of a loop heat pipe in an on-orbit refueling gas container, characterized in that, A controlled gas container is thermally connected to a loop heat pipe, the loop heat pipe is equipped with a liquid receiver, and a cooling fin is disposed on the outer wall of the liquid receiver. The method includes: When the measured temperature of the controlled gas container is greater than the preset target temperature of the controlled gas container, the effective overtemperature amount of the controlled gas container is determined based on the measured temperature, the preset target temperature and the upper limit of the preset temperature dead zone. When the effective overheating amount is greater than zero, the two-phase temperature adjustment amount of the liquid storage tank is determined based on the effective overheating amount and the preset proportional compensation coefficient, and the two-phase temperature adjustment amount is converted into the target net cooling power of the cooling chip. Start and control the cooling chip to operate at the target net cooling power until the measured temperature of the controlled gas volume falls below the sum of the preset target temperature and the upper limit of the preset temperature dead zone.

2. The loop heat pipe temperature control method for on-orbit refueling gas capacity according to claim 1, characterized in that, The step of determining the two-phase temperature adjustment amount of the liquid receiver based on the effective overheat amount and the preset proportional compensation coefficient, and converting the two-phase temperature adjustment amount into the target net cooling power of the cooling chip, includes: Based on the effective overheat amount and the preset proportional compensation coefficient, the two-phase region temperature adjustment amount of the liquid reservoir is determined; the two-phase region temperature adjustment amount is the product of the effective overheat amount and the preset proportional compensation coefficient. Using the equivalent heat capacity model of the liquid receiver, the temperature adjustment of the two-phase region is converted into the target net cooling power of the refrigeration element.

3. The loop heat pipe temperature control method for on-orbit refueling gas capacity according to claim 2, characterized in that, The preset proportional compensation coefficient includes a first proportional compensation coefficient, a second proportional compensation coefficient, and a third proportional compensation coefficient; determining the two-phase temperature adjustment amount of the liquid reservoir based on the effective overheat amount and the preset proportional compensation coefficient includes: Based on the effective over-temperature amount and the first proportional compensation coefficient, the second proportional compensation coefficient, or the third proportional compensation coefficient, the two-phase region temperature adjustment amount of the liquid reservoir is determined; Wherein, the first proportional compensation coefficient is greater than the second proportional compensation coefficient, and the second proportional compensation coefficient is greater than the third proportional compensation coefficient; the first proportional compensation coefficient is any value in the range of 1.10 to 1.30, the second proportional compensation coefficient is any value in the range of 0.90 to 1.09, and the third proportional compensation coefficient is any value in the range of 0.70 to 0.

89.

4. The loop heat pipe temperature control method for on-orbit refueling gas capacity according to claim 3, characterized in that, The step of determining the two-phase temperature adjustment amount of the liquid reservoir based on the effective over-temperature amount and the first proportional compensation coefficient, the second proportional compensation coefficient, or the third proportional compensation coefficient includes: Based on the effective overheat amount and the first proportional compensation coefficient, the temperature adjustment amount of the two-phase region is determined; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the first proportional compensation coefficient. The first proportional compensation coefficient is 1.

20.

5. The loop heat pipe temperature control method for on-orbit refueling gas capacity according to claim 3, characterized in that, The step of determining the two-phase temperature adjustment amount of the liquid reservoir based on the effective over-temperature amount and the first proportional compensation coefficient, the second proportional compensation coefficient, or the third proportional compensation coefficient includes: Based on the effective overheat amount and the second proportional compensation coefficient, the temperature adjustment amount of the two-phase region is determined; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the second proportional compensation coefficient. The second proportional compensation coefficient is 1.

00.

6. The loop heat pipe temperature control method for on-orbit refueling gas capacity according to claim 3, characterized in that, The step of determining the two-phase temperature adjustment amount of the liquid reservoir based on the effective over-temperature amount and the first proportional compensation coefficient, the second proportional compensation coefficient, or the third proportional compensation coefficient includes: Based on the effective overheat amount and the third proportional compensation coefficient, the temperature adjustment amount of the two-phase region is determined; the temperature adjustment amount of the two-phase region is the product of the effective overheat amount and the third proportional compensation coefficient. The third proportional compensation coefficient is 0.

80.

7. The loop heat pipe temperature control method for on-orbit refueling gas capacity according to any one of claims 2-6, characterized in that, The equivalent heat capacity model of the liquid reservoir includes: ； In the formula, The target net cooling power of the thermoelectric cooler. The equivalent heat capacity of the reservoir and its internal working fluid. This is the temperature adjustment amount for the two-phase region of the liquid receiver. For the expected response time, Heat is transferred from the reservoir to the environment and adjacent structures.

8. The loop heat pipe temperature control method for on-orbit refueling gas capacity according to claim 1, characterized in that, The determination of the effective overtemperature amount of the controlled gas volume based on the measured temperature, the preset target temperature, and the preset upper limit of the temperature dead zone includes: Based on the measured temperature and the preset target temperature, the overtemperature amount of the controlled gas volume is determined; the overtemperature amount is the difference between the measured temperature and the preset target temperature. Based on the overtemperature amount and the upper limit of the preset temperature dead zone, the effective overtemperature amount of the controlled gas capacity is determined; the effective overtemperature amount is the difference between the overtemperature amount and the upper limit of the preset temperature dead zone. The preset target temperature is any temperature value within the range of -20℃ to 50℃, and the upper limit of the preset temperature dead zone is any temperature value within the range of 0.05℃ to 0.2℃.

9. The loop heat pipe temperature control method for on-orbit refueling gas capacity according to claim 1, characterized in that, Also includes: When the measured temperature of the controlled gas volume falls below the sum of the preset target temperature and the upper limit of the preset temperature dead zone, the net cooling power of the cooling chip is gradually reduced to zero; the net cooling power of the cooling chip is kept at zero until the next effective overtemperature is greater than zero.

10. A loop heat pipe temperature control device for on-orbit refueling gas capacity, characterized in that, The system includes a controlled gas container, a loop heat pipe, a temperature sensor for acquiring the measured temperature of the controlled gas container, and a controller; wherein the controlled gas container is thermally connected to the loop heat pipe, the loop heat pipe is equipped with a liquid reservoir, the outer wall of the liquid reservoir is provided with a cooling chip, and the controller is connected to the cooling chip and the temperature sensor respectively; the controller is configured to: perform the loop heat pipe temperature control method for the on-orbit refueling gas container according to any one of claims 1-9.

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