Spacecraft loop heat pipe switch control system and method based on multi-source information fusion

Abstract

The invention discloses a spacecraft loop heat pipe switch control system and method based on multi-source information fusion, and belongs to the technical field of spacecraft thermal control. The loop heat pipe on the cabin plate on one side is fixed on the pre-buried orthogonal heat pipe, and the condenser is pre-buried on the cabin plate on the other side; the loop heat pipe comprises a loop heat pipe body, an evaporator auxiliary heater, a semiconductor refrigerator and auxiliary parts of the semiconductor refrigerator. A saddle monitoring point and a liquid storage device monitoring point are arranged in the loop heat pipe, and the temperature of the saddle and the temperature of the liquid storage device are collected by the pipe counting subsystem; and the digital pipe subsystem is used for controlling loop heat pipes on the cabin plates on the two sides to be powered up according to the obtained solar azimuth angle and the average temperature of the two cabin plates and a preset strategy. According to the system, spacecraft attitude information and different cabin plate temperature data are collected in real time and efficiently fused through the data management subsystem, a multi-loop heat pipe refrigerator and a heater switch are autonomously regulated and controlled, and meanwhile safety monitoring and fault judgment are conducted on expected conformity of a control instruction.

Description

Technical Field

[0001] The invention relates to a spacecraft loop heat pipe switch control system and method based on multi-source information fusion, belonging to the technical field of spacecraft thermal control. Background Art

[0002] The spacecraft loop heat pipe is a highly efficient heat transfer device that uses capillary force to drive the working fluid to circulate in a closed loop to achieve efficient heat transfer and distribution. In the complex thermal environment of space, the spacecraft cabin is often faced with extreme temperature differences due to attitude adjustment. The loop heat pipe has become a key device to ensure the stability of the cabin temperature with its excellent heat transfer performance and long-distance transmission capability. As the intelligent control center of the spacecraft, the digital control subsystem accurately controls the switch of the loop heat pipe, and achieves the important goal of cabin isothermalization by increasing or decreasing the amount of heat transferred. Its basic working principle is to monitor the temperature changes of different temperature measurement points in the cabin in real time through the temperature acquisition equipment, and autonomously adjust the working state of the loop heat pipe. When the cabin temperature deviates from the set range, the digital control subsystem adjusts the start or shut down of the loop heat pipe, thereby controlling the flow of heat and ensuring that the cabin temperature is maintained at a stable level. This autonomous temperature control strategy not only improves the thermal management efficiency of the spacecraft, but also significantly enhances its ability to adapt to extreme environments, thereby providing a solid guarantee for the stable operation of the spacecraft in space. The existing technical methods mainly have the following problems:

[0003] (1) The above method mainly relies on the heat transfer characteristics of the loop heat pipe itself to achieve temperature control, which lacks flexibility. An autonomous control algorithm should be designed to monitor and adjust the working status of the heat pipe in real time through the spacecraft digital control subsystem software to achieve more precise temperature control and improve the thermal management efficiency of the spacecraft.

[0004] (2) Current methods for controlling loop heat pipes in spacecraft often only focus on the switch status of the product, while ignoring factors such as solar radiation caused by changes in the spacecraft's attitude and temperature differences in the cabin. Therefore, these strategies are not incorporated into the control strategy to achieve comprehensive and multi-dimensional thermal environment monitoring and management.

[0005] (3) The current design of spacecraft loop heat pipes is often specially designed for specific missions or special environments. It lacks versatility and is difficult to meet the needs of different space missions, and it is also difficult to achieve large-scale promotion and application. Summary of the invention

[0006] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide a spacecraft loop heat pipe switch control system and method based on multi-source information fusion, wherein the thermal control subsystem uses multi-loop heat pipes to realize the coupling design of heat dissipation surfaces between different cabin panels, and through the digital control subsystem, the spacecraft attitude information and the real-time collection and efficient fusion processing of the temperature data of different cabin panels are collected, the multi-loop heat pipe coolers and heater switches are autonomously regulated, and at the same time, the expected compliance of the control instructions is monitored for safety and fault judgment is made, thereby realizing high-efficiency and high-reliability control of the spacecraft temperature in a complex space thermal environment.

[0007] The technical solution of the present invention is: a spacecraft loop heat pipe switch control system based on multi-source information fusion, comprising:

[0008] The spacecraft cabin section adopting loop heat control temperature control is provided with cabin panels distributed on both sides, and the spacecraft heating equipment is dispersedly arranged on the cabin panels on both sides; the cabin panels are pre-buried with orthogonal heat pipes to ensure that the heat pipes pass through the concentrated heating area of ​​the heating equipment; the loop heat pipe on the cabin panel on one side is fixed on the pre-buried orthogonal heat pipe, and the cabin panel on the other side is pre-buried with a condenser, and contacts with the pre-buried orthogonal heat pipe in the cabin panel on the side, so as to realize the transfer of heat from the cabin panel on one side to the cabin panel on the other side; the loop heat pipe includes a loop heat pipe body, an evaporator auxiliary heater and a semiconductor refrigerator and its attached parts; a saddle monitoring point and a liquid reservoir monitoring point are provided in the loop heat pipe, and the saddle temperature and the liquid reservoir temperature are collected by a digital control subsystem;

[0009] The digital tube subsystem obtains the average temperature of the two decks according to the collected saddle temperature and liquid storage temperature, and controls the power supply of the loop heat pipes of the decks on both sides according to the preset strategy based on the obtained solar azimuth and the average temperature of the two decks.

[0010] Furthermore, the solar azimuth angle includes a cosine value of an angle between a solar vector and a deck panel on one side of the orbital coordinate system, and a cosine value of an angle between a solar vector and a deck panel axis on one side of the body.

[0011] Furthermore, the preset strategy includes a first strategy, and the first strategy includes:

[0012] 1) When A≥M≥B, it is considered that the sun is shining on the +Y plane of the star, and the loop heat pipe on the +Y side is turned on; A is 1, B is 0.259, M is Soy or Sby, the default is Soy, and it is switched according to the command; Soy is the cosine value of the angle between the sun vector and the +Y deck of the orbital coordinate system, and Sby is the cosine value of the angle between the sun vector and the +Y axis of the body; +Y is the direction perpendicular to the deck plane, and -Y is opposite to the +Y direction;

[0013] 2) When C≤M≤D, it is assumed that the sunlight is shining on the -Y side of the star, and the loop heat pipe on the -Y side is turned on; C is -1, D is -0.259, and M is Soy;

[0014] 3) When the value of M does not meet 1) and 2), keep the previous state unchanged;

[0015] 4) From the state where 1) and 2) are not met to the state where 1) and 2) are met, only execute the judgment control strategy of state 1) and 2) once; in other cases, keep the state unchanged;

[0016] If M < -1 or M > 1, the data management subsystem issues an alarm signal; when M cannot be obtained, the loop heat pipe maintains the current state, and at the same time the data management subsystem issues an alarm signal.

[0017] Further, the loop heat pipe on the +Y side is turned on, including:

[0018] First, turn off the loop heat pipe, the thermoelectric cooler, and the evaporator auxiliary heater circuit on the -Y side, and then turn on the thermoelectric cooler and the evaporator auxiliary heater circuit in the enabled state of the loop heat pipe on the +Y side; when the loop heat pipe and the thermoelectric cooler on the +Y side are turned on, the evaporator auxiliary heater is turned on at the same time, and the thermoelectric cooler is turned on sequentially at a preset interval time; the evaporator auxiliary heater is turned off after a preset duration;

[0019] If the partial circuit shutdown fails when turning off the thermoelectric cooler and the evaporator auxiliary heater circuit of the loop heat pipe on the -Y side, the subsequent operation of turning on the thermoelectric cooler and the evaporator auxiliary heater circuit in the enabled state of the loop heat pipe on the +Y side will not be executed, and at the same time the data management subsystem transmits this alarm state through telemetry.

[0020] The operation of turning on the loop heat pipe on the -Y side is the same as that of turning on the loop heat pipe on the +Y side.

[0021] Further, the preset strategy includes a second strategy, and the second strategy includes:

[0022] 1) When TH1 - TH2 > E, turn on the loop heat pipe on the +Y side, turn on the loop heat pipe on the +Y side;

[0023] 2) When TH1 - TH2 < F, turn on the loop heat pipe on the -Y side, turn on the loop heat pipe on the -Y side; E is 10, F is -10; TH1 is the average temperature of the +Y cabin board, and TH2 is the average temperature of the -Y cabin board;

[0024] 3) When F ≤ TH1 - TH2 ≤ E, keep the previous state unchanged;

[0025] 4) From the state where 1) and 2) are not met to the state where 1) and 2) are met, only execute the judgment control strategy of state 1) and 2) once; in other cases, keep the state unchanged.

[0026] Furthermore, when 1) and 2) of the first strategy and the second strategy are satisfied, the condition judgment of the first strategy and the second strategy is suspended for a preset time during the execution of the instruction sending, and the judgment is made again after the instruction sending is completed; after the judgment is made again, the corresponding loop heat pipe circuit is turned on, and the loop heat pipe power-on instruction is no longer sent;

[0027] After the loop heat pipe power-on command is sent, the digital control subsystem determines whether the switch status of the enable status loop meets expectations. If not, a telemetry alarm message is issued. At the same time, when the saddle temperature exceeds 50°C, the corresponding loop heat pipe loop is closed. The loop heat pipe is only judged when the action is switched on the track. If no switching is performed, the saddle temperature is not judged.

[0028] Furthermore, when the loop heat pipe temperature control is enabled, when the liquid reservoir temperature is higher than 40°C, the loop heat pipe circuit will alarm; when the liquid reservoir temperature is higher than 50°C, the corresponding loop heat pipe semiconductor refrigerator circuit will be closed and an alarm signal will be issued.

[0029] A spacecraft loop heat pipe switch control method implemented by using the spacecraft loop heat pipe switch control system based on multi-source information fusion comprises:

[0030] According to the solar azimuth and the average temperature of the two decks, the heat pipes of the deck loops on both sides are controlled to be powered according to the preset strategy; the solar azimuth includes the cosine value of the angle between the solar vector and the deck on one side of the orbital coordinate system, and the cosine value of the angle between the solar vector and the deck axis on one side of the body;

[0031] The preset strategy includes a first strategy and a second strategy; the first strategy includes:

[0032] 1) When A≥M≥B, it is considered that the sun is shining on the +Y plane of the star, and the loop heat pipe on the +Y side is turned on; A is 1, B is 0.259, M is Soy or Sby, the default is Soy, and it is switched according to the command; Soy is the cosine value of the angle between the sun vector and the +Y deck of the orbital coordinate system, and Sby is the cosine value of the angle between the sun vector and the +Y axis of the body; +Y is the direction perpendicular to the deck plane, and -Y is opposite to the +Y direction;

[0033] 2) When C≤M≤D, it is assumed that the sunlight is shining on the -Y side of the star, and the loop heat pipe on the -Y side is turned on; C is -1, D is -0.259, and M is Soy;

[0034] 3) When the value of M does not meet the ranges described in 1) and 2), the previous state remains unchanged;

[0035] 4) From the state that does not satisfy 1) and 2) to the state that satisfies 1) and 2), the judgment and control strategies of states 1) and 2) are only executed once; in other cases, the state remains unchanged;

[0036] If M < -1 or M > 1, the data management subsystem issues an alarm signal; when M cannot be obtained, the loop heat pipe maintains its current state, and at the same time, the data management subsystem issues an alarm signal;

[0037] The second strategy includes:

[0038] 1) When TH1 - TH2 > E, turn on the loop heat pipe on the +Y side, turn on the loop heat pipe on the +Y side;

[0039] 2) When TH1 - TH2 < F, turn on the loop heat pipe on the -Y side, turn on the loop heat pipe on the -Y side; E is 10 and F is -10;

[0040] 3) When F ≤ TH1 - TH2 ≤ E, keep the previous state unchanged;

[0041] 4) From the state that does not satisfy 1) and 2), to the state that satisfies 1) and 2), only execute the judgment control strategy of state 1) and 2) once; in other cases, keep the state unchanged.

[0042] Further, the turning on of the loop heat pipe on the +Y side includes:

[0043] First, turn off the loop heat pipe on the -Y side, the thermoelectric cooler, and the evaporator auxiliary heater circuit, and then turn on the thermoelectric cooler and the evaporator auxiliary heater circuit in the enabled state of the loop heat pipe on the +Y side; when the loop heat pipe on the +Y side and the thermoelectric cooler are turned on, the evaporator auxiliary heater is turned on simultaneously, and the thermoelectric cooler is turned on at preset intervals in sequence; the evaporator auxiliary heater is turned off after a preset duration;

[0044] If the turning off of the thermoelectric cooler and the evaporator auxiliary heater circuit of the loop heat pipe on the -Y side fails for some circuits, the subsequent operation of turning on the thermoelectric cooler and the evaporator auxiliary heater circuit in the enabled state of the loop heat pipe on the +Y side will not be executed, and at the same time, the data management subsystem transmits this alarm state through telemetry;

[0045] The operation of turning on the loop heat pipe on the -Y side is the same as that of turning on the loop heat pipe on the +Y side.

[0046] Further, when the first strategy and 1) and 2) of the second strategy are satisfied, during the preset duration of the instruction sending, the condition judgment of the first strategy and the second strategy is suspended. After the instruction sending is completed, re - judge; after re - judging, the corresponding loop heat pipe circuit is turned on, and no loop heat pipe power - on instruction is sent again;

[0047] After the loop heat pipe power-on command is sent, the digital control subsystem determines whether the switch status of the enable state loop meets expectations. If not, a telemetry alarm message is issued. At the same time, when the saddle temperature exceeds 50°C, the corresponding loop heat pipe loop is closed. The loop heat pipe is only judged when the action is switched on the track; if it is not switched, the saddle temperature is not judged.

[0048] When the loop heat pipe temperature control is enabled, when the liquid reservoir temperature is higher than 40°C, the loop heat pipe circuit will alarm; when the liquid reservoir temperature is higher than 50°C, the corresponding loop heat pipe semiconductor cooler circuit will be closed and an alarm signal will be issued.

[0049] The advantages of the present invention compared with the prior art are:

[0050] (1) The present invention introduces a multi-source information fusion control algorithm for temperature control through the digital control subsystem software, which significantly improves the thermal control effect of the spacecraft loop heat pipe. The algorithm can monitor and adjust the working status of the heat pipe, realize flexible, efficient and scalable thermal control management, and improve the thermal control efficiency of the spacecraft.

[0051] (2) The method of the present invention comprehensively considers various information such as temperature differences and solar radiation caused by attitude changes, and realizes comprehensive monitoring and management of the spacecraft thermal environment. Multi-dimensional thermal environment monitoring is achieved through the digital control subsystem to ensure the stable operation of the spacecraft in a complex thermal environment.

[0052] (3) The method described in the present invention is based on universal loop heat pipes, which improves its adaptability and scalability and breaks the limitations of specially designed heat pipes. Different spacecraft can select different numbers of universal specification loop heat pipes to meet mission requirements, which is convenient for promotion and application. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0054] Figure 1 It is a schematic diagram of the ±Y cabin plate loop heat pipe coupling system of the present invention. DETAILED DESCRIPTION

[0055] In order to better understand the above technical scheme, the technical scheme of the present invention is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present invention and the specific features in the embodiments are detailed descriptions of the technical scheme of the present invention, rather than limitations on the technical scheme of the present invention. In the absence of conflict, the embodiments of the present invention and the technical features in the embodiments can be combined with each other.

[0056] The following is a further detailed description of the spacecraft loop heat pipe switch control system and method based on multi-source information fusion provided by the embodiments of the present invention in conjunction with the accompanying drawings of the specification. The specific implementation method may include:

[0057] High-power equipment is dispersed on the +Y and -Y decks of the spacecraft. Orthogonal heat pipes are embedded in the decks. The heat pipes pass through the high-power heating equipment to level the temperature difference between the equipment and realize the isothermal design of the deck. Temperature measuring points are arranged on the deck to monitor the temperature changes of the deck.

[0058] The digital control subsystem controls the switch of the heat pipe's cooler or auxiliary heater through the remote control command channel. Two control strategies for the loop heat pipe are pre-set in the computer software, namely strategy 1 (sun azimuth) and strategy 2 (average temperature difference of the cabin). Strategy 1 is used by default on orbit, and the control strategy can be switched by issuing commands from the ground. Both strategies can set relevant parameters. A set of default control parameters for the two strategies is preset in the digital control software. The parameters can be set by injection commands during ground testing or on-orbit operation.

[0059] After the computer of the digital control subsystem is powered on, it periodically collects various telemetry parameters required for control of strategy 1 and strategy 2. When the function is enabled, it automatically determines whether the corresponding telemetry parameters meet the judgment conditions according to the selected control strategy. If the judgment conditions are met, the semiconductor cooler and evaporator auxiliary heater circuit switch operations are executed according to the timing.

[0060] After executing the switching operation of the semiconductor refrigerator and the evaporator auxiliary heater circuit, the digital tube subsystem software monitors whether the circuit opening status is as expected, and monitors the saddle temperature and the reservoir temperature on the capillary pump corresponding to the enabling circuit, and performs alarm or over-temperature processing.

[0061] In the solution provided by the embodiment of the present invention, the high-power equipment of the spacecraft is dispersedly arranged on the +Y and -Y decks of the payload cabin, and orthogonal heat pipes are pre-embedded in the decks, and the orthogonal heat pipes are bonded. The heat pipes are pre-embedded in the honeycomb panels to ensure that the heat pipes pass through the concentrated heating area of ​​the high-power heating equipment. The entire deck is a pre-embedded orthogonal heat pipe network to level the temperature difference between the equipment and realize the isothermal design of the deck. In this way, the thermal coupling system design is realized through the loop heat pipe in a limited space, and the strong coupling between the +Y and -Y decks of the payload cabin is realized, such as Figure 1 shown.

[0062] The loop heat pipe on the +Y deck of the load compartment is brazed to the pre-buried heat pipe in the +Y deck by a capillary pump, while the condenser is pre-buried in the -Y deck and brazed in contact with the pre-buried heat pipe in the -Y deck, thereby realizing the transfer of heat from the +Y position to the -Y position. Similarly, the loop heat pipe on the -Y deck of the load compartment is brazed to the pre-buried heat pipe in the -Y deck by a capillary pump, while the condenser is pre-buried in the +Y deck and brazed in contact with the pre-buried heat pipe in the +Y deck, thereby realizing the transfer of heat from the -Y position to the +Y position. Taking the C18 model as an example, each set of loop heat pipes has 2 semiconductor cooler loops and 1 auxiliary heater loop.

[0063] In the present invention, the computer of the digital control subsystem collects the temperature of the cabin compensation heater for cabin average temperature calculation; collects the temperature of the saddle monitoring point and the liquid storage tank corresponding to each loop heat pipe loop for temperature early warning monitoring and control. The computer of the digital control subsystem obtains the solar azimuth angle data (including the cosine value Soy of the angle between the solar vector and the orbital coordinate system +Y cabin, and the cosine value Sby of the angle between the solar vector and the body +Y axis, both in 16-bit binary complement) from the computer of the control subsystem through the internal bus of the spacecraft (such as 1553B or CAN bus).

[0064] The specific implementation process is as follows:

[0065] The digital control subsystem software controls the corresponding ON / OFF status (i.e., whether it is powered on) of the ±Y N loop heat pipes according to different preset strategies. The software can enable and disable the loop heat pipe control function; when the loop heat pipe control function is disabled, the ON / OFF status remains unchanged, and the ON / OFF status is changed through ground instructions. The format of the loop heat pipe control function enable and disable setting instructions is shown in Table 1. Each loop executes the loop heat pipe control strategy only when it is enabled, and it is not executed in the disabled state. The format of the loop heat pipe loop enable and disable setting instructions is shown in Table 2.

[0066] Table 1 Loop heat pipe control function enable / disable setting instruction format

[0067]

[0068] Table 2 Loop heat pipe loop enable and disable setting instruction format

[0069]

[0070] The loop heat pipe adopts two control strategies, namely strategy 1 and strategy 2. Strategy 1 is adopted by default in orbit, and the control strategy can be switched by issuing commands from the ground. The command format for selecting the loop heat pipe automatic control strategy is shown in Table 3.

[0071] Table 3 Loop heat pipe automatic control strategy selection instruction format

[0072]

[0073] Strategy 1: Determine the timing of opening the loop heat pipe through attitude and orbit parameters. The specific judgment method of Strategy 1 is as follows:

[0074] 1) When A≥M≥B (the default state is A is 1, B is 0.259, M is Soy or Sby, the default is Soy), it is considered that the sunlight is shining on the +Y side of the star, and the loop heat pipe on the +Y side is turned on.

[0075] First, turn off the -Y side loop heat pipe, semiconductor cooler and evaporator auxiliary heater loop, and then turn on the +Y side loop heat pipe in the enabled state of the semiconductor cooler and evaporator auxiliary heater loop. When the +Y side loop heat pipe and semiconductor cooler are turned on, the evaporator auxiliary heater can be turned on at the same time, and the semiconductor cooler needs to be turned on in sequence. The opening interval of each semiconductor cooler is G (the default state is 1) minutes. The evaporator auxiliary heater is automatically disconnected after being turned on for H (the default state is 30) minutes.

[0076] If the semiconductor cooler and evaporator auxiliary heater circuits of the -Y side loop heat pipe are closed and some circuits fail to close, the subsequent operation of opening the semiconductor cooler and evaporator auxiliary heater circuits in the enabled state of the +Y side loop heat pipe will no longer be executed. At the same time, the digital control software transmits the alarm status through telemetry.

[0077] 2) When C≤M≤D (the default state C is -1, D is -0.259, and the default value of M is Soy), it is considered that the sunlight is shining on the -Y side of the star, and the loop heat pipe on the -Y side is turned on.

[0078] First, turn off the semiconductor cooler and evaporator auxiliary heater circuit of the +Y side loop heat pipe, and then turn on the semiconductor cooler and evaporator auxiliary heater circuit in the enabled state of the -Y side loop heat pipe. When the -Y side loop heat pipe is turned on, the evaporator auxiliary heater can be turned on at the same time, and the semiconductor cooler needs to be turned on in sequence. The opening interval of each semiconductor cooler is G (the default state value is 1) minutes. The evaporator auxiliary heater is automatically disconnected after being turned on for H (the default state value is 30) minutes.

[0079] If the semiconductor cooler and evaporator auxiliary heater circuits of the +Y side loop heat pipe are closed and some circuits fail to close, the subsequent operation of opening the semiconductor cooler and evaporator auxiliary heater circuits in the enabled state of the -Y side loop heat pipe will no longer be executed, and the software will transmit the alarm status through telemetry.

[0080] 3) When the value of M does not meet the ranges described in 1) and 2), the previous state remains unchanged and no adjustment is made.

[0081] 4) Only when changing from a state that does not meet 1) and 2) to a state that meets 1) and 2), the judgment and control strategies of states 1) and 2) are executed only once; in other cases, the state remains unchanged.

[0082] The above control parameter M is extracted by the digital management subsystem from the bus data of the control subsystem. If M < -1 or M > 1 is returned, the digital management subsystem software issues an alarm signal; when the control parameter M cannot be sent from the control bus, the loop heat pipe maintains the current state without control, and at the same time the digital management subsystem software issues an alarm signal.

[0083] The ground can upload instructions to adjust the values of parameters A, B, C, and D, and the instruction format for parameter setting is shown in Table 4.

[0084] Table 4 Instruction Format for Parameter Setting

[0085]

[0086] Strategy 2: Determine the timing to turn on the loop heat pipe through the average temperature of the +Y panel (TH1) and the average temperature of the -Y panel (TH2). The method to calculate TH1 is that the digital management subsystem collects the measured values of the temperature measuring resistors on the +Y panel, removes the measured values of the resistors that exceed the reasonable temperature range, and then takes the average value of the remaining temperature measuring points. The method to calculate TH2 is the same. The ground can set the numbers and quantities of the temperature measuring resistors in Strategy 2 of the loop heat pipe through upload instructions, and the instruction format is shown in Table 5.

[0087] Table 5 Instruction Format for Setting

[0088]

[0089] The specific judgment method of Strategy 2 is as follows:

[0090] 1) When TH1 - TH2 > E, turn on the loop heat pipe on the +Y side, and the instruction operation to turn on the loop heat pipe on the +Y side is the same as that of Strategy 1;

[0091] 2) When TH1 - TH2 < F, turn on the loop heat pipe on the -Y side, and the instruction operation to turn on the loop heat pipe on the -Y side is the same as that of Strategy 1;

[0092] 3) When F ≤ TH1 - TH2 ≤ E, keep the previous state unchanged without adjustment.

[0093] 4) Only when changing from a state that does not meet 1) and 2) to a state that meets 1) and 2), the judgment and control strategies of states 1) and 2) are executed only once; in other cases, the state remains unchanged.

[0094] 5) By default, E takes the value of 10 and F takes the value of -10; at the same time, the ground can upload instructions to adjust the values of parameters E, F, G, and H. The instruction format for setting parameters E and F is shown in Table 6, and the instruction format for setting parameters G and H is shown in Table 7.

[0095] Table 6E, F parameter setting instruction format

[0096]

[0097] Table 7G, H parameter setting instruction format

[0098]

[0099] When conditions 1) and 2) in Strategy 1 and Strategy 2 are met, the software will suspend the condition judgment of Strategy 1 and Strategy 2 within H (default value 30) minutes during the execution of the instruction, and re-judge after the instruction is sent. After the re-judgment, the circuit needs to be opened, but the circuit is already opened at this time, and no more instructions need to be sent.

[0100] After the command is sent (including on and off), the digital control subsystem software determines whether the switch status of the enable state loop meets the expectations. If not, the software issues a telemetry alarm message prompt; at the same time, the software monitors the saddle temperature on the capillary pump corresponding to the enable loop: when the temperature exceeds 50°C, the corresponding loop heat pipe loop is closed; the loop heat pipe is only on track when the action is switched, the saddle temperature is judged; when not switched, the saddle temperature is not judged. This judgment is judged three times in 1s, and the judgment stops after the evaporator auxiliary start loop shutdown command is sent.

[0101] When the loop heat pipe temperature control is enabled, the digital control subsystem software also monitors the temperature of the liquid reservoir: when the temperature of the liquid reservoir is higher than 40°C (3 times in a row at 1s intervals), the loop heat pipe circuit alarms; when the liquid reservoir temperature is higher than 50°C (3 times in a row at 1s intervals), the corresponding loop heat pipe semiconductor cooler circuit is closed and an alarm signal is issued.

[0102] When using strategy 1 and strategy 2 to determine whether the loop heat pipe is on or off, determine whether the conditions for opening or closing are met three times at an interval of 1 second. If the results of three consecutive condition judgments are consistent, it can be used to control the on or off of the loop heat pipe.

[0103] The two cabin panels ±Y used to control the temperature difference in the implementation steps of the present invention are example cabin panel names, but the invention is not limited to these two cabin panels. Any two spacecraft cabin panels designed with a thermal coupling system based on a loop heat pipe can perform loop heat pipe switch control with multi-source information fusion based on the ideas in the present invention.

[0104] The C18 loop heat pipe in the implementation steps of the present invention is an example loop heat pipe model, but the invention is not limited to this model. Any loop heat pipe with a semiconductor refrigerator circuit and an auxiliary heater circuit can perform over-temperature detection and protection processing after sending instructions based on the ideas in the present invention.

[0105] The instruction format and encoding codewords used for setting the control parameters of the loop heat pipe switch in the steps of the present invention are an example format, but the invention is not limited to this format. Any instruction format that contains the setting information described in this patent can be based on the ideas in the present invention and can be received by the on-board software for control parameter setting.

[0106] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0107] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

[0108] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. Spacecraft loop heat pipe switch control system based on multi-source information fusion, characterized in that: include: The spacecraft cabin section adopting loop heat control temperature control is provided with cabin panels distributed on both sides, and the spacecraft heating equipment is dispersedly arranged on the cabin panels on both sides; the cabin panels are pre-buried with orthogonal heat pipes to ensure that the heat pipes pass through the concentrated heating area of ​​the heating equipment; the loop heat pipe on the cabin panel on one side is fixed on the pre-buried orthogonal heat pipe, and the cabin panel on the other side is pre-buried with a condenser, and contacts with the pre-buried orthogonal heat pipe in the cabin panel on the side, so as to realize the transfer of heat from the cabin panel on one side to the cabin panel on the other side; the loop heat pipe includes a loop heat pipe body, an evaporator auxiliary heater and a semiconductor refrigerator and its attached parts; a saddle monitoring point and a liquid reservoir monitoring point are provided in the loop heat pipe, and the saddle temperature and the liquid reservoir temperature are collected by a digital control subsystem; The digital tube subsystem obtains the average temperature of the two decks according to the collected saddle temperature and liquid storage temperature, and controls the power supply of the loop heat pipes of the decks on both sides according to the preset strategy based on the obtained solar azimuth and the average temperature of the two decks.

2. The spacecraft loop heat pipe switch control system based on multi-source information fusion according to claim 1 is characterized in that: The solar azimuth angle includes the cosine value of the angle between the solar vector and the deck on one side of the orbital coordinate system, and the cosine value of the angle between the solar vector and the deck axis on one side of the body.

3. The spacecraft loop heat pipe switch control system based on multi-source information fusion according to claim 1, characterized in that: The preset strategy includes a first strategy, and the first strategy includes: 1) When A≥M≥B, it is considered that the sun is shining on the +Y plane of the star, and the loop heat pipe on the +Y side is turned on; A is 1, B is 0.259, M is Soy or Sby, the default is Soy, and it is switched according to the command; Soy is the cosine value of the angle between the sun vector and the +Y deck of the orbital coordinate system, and Sby is the cosine value of the angle between the sun vector and the +Y axis of the body; +Y is the direction perpendicular to the deck plane, and -Y is opposite to the +Y direction; 2) When C≤M≤D, it is assumed that the sunlight is shining on the -Y side of the star, and the loop heat pipe on the -Y side is turned on; C is -1, D is -0.259, and M is Soy; 3) When the value of M does not satisfy 1) and 2), keep the previous state unchanged; 4) From not satisfying 1) and 2) to satisfying 1) and 2), the judgment and control strategies of states 1) and 2) are only executed once; in other cases, the states remain unchanged; If M<-1 or M>1, the digital control subsystem sends an alarm signal; when M cannot be obtained, the loop heat pipe maintains the current state and the digital control subsystem sends an alarm signal.

4. The spacecraft loop heat pipe switch control system based on multi-source information fusion according to claim 3 is characterized in that: The loop heat pipe on the open +Y side includes: First, the -Y side loop heat pipe, semiconductor refrigerator and evaporator auxiliary heater circuit are closed, and then the semiconductor refrigerator and evaporator auxiliary heater circuit in the enabled state of the +Y side loop heat pipe are opened; when the +Y side loop heat pipe and semiconductor refrigerator are opened, the evaporator auxiliary heater is opened at the same time, and the semiconductor refrigerator is opened in sequence according to the preset interval time; the evaporator auxiliary heater is disconnected after being opened for a preset time; If the semiconductor cooler and evaporator auxiliary heater circuits of the -Y side loop heat pipe are closed and some circuits fail to close, the subsequent operation of opening the semiconductor cooler and evaporator auxiliary heater circuits in the enabled state of the +Y side loop heat pipe will no longer be executed, and the digital control subsystem will transmit the alarm status through telemetry; The operation of opening the loop heat pipe on the -Y side is the same as the operation of opening the loop heat pipe on the +Y side.

5. The spacecraft loop heat pipe switch control system based on multi-source information fusion according to claim 3, characterized in that: The preset strategy includes a second strategy, and the second strategy includes: 1) When TH1 - TH2 > E, turn on the loop heat pipe on the +Y side, and turn on the loop heat pipe on the +Y side; 2) When TH1 - TH2 < F, turn on the loop heat pipe on the -Y side, and turn on the loop heat pipe on the -Y side; E is 10, F is -10; TH1 is the average temperature of the +Y cabin panel, and TH2 is the average temperature of the -Y cabin panel; 3) When F ≤ TH1 - TH2 ≤ E, keep the previous state unchanged; 4) From the state where 1) and 2) are not satisfied to the state where 1) and 2) are satisfied, only execute the judgment control strategy of state 1) and 2) once; in other cases, keep the state unchanged.

6. The spacecraft loop heat pipe switch control system based on multi-source information fusion according to claim 5, characterized in that: When 1) and 2) in the first strategy and the second strategy are satisfied, during the preset duration of the instruction sending, pause the condition judgment of the first strategy and the second strategy. After the instruction sending is completed, re-judge; after re-judging, the corresponding loop heat pipe circuit is turned on, and the loop heat pipe power-on instruction is no longer sent; After the loop heat pipe power-on instruction is sent, the telemetry sub-system judges whether the switch state of the enable state circuit meets the expectation. If not, it issues a telemetry alarm message for prompt; at the same time, when the saddle temperature exceeds 50 °C, turn off the corresponding loop heat pipe circuit; the saddle temperature is judged only when the loop heat pipe makes an action switch during orbit operation; when there is no switch, the saddle temperature is not judged.

7. The spacecraft loop heat pipe switch control system based on multi-source information fusion according to claim 6, characterized in that: In the case of loop heat pipe temperature control enabled, when the accumulator temperature is higher than 40 °C, the loop heat pipe circuit gives an alarm; when the accumulator temperature is higher than 50 °C, turn off the corresponding loop heat pipe semiconductor refrigeration circuit and issue an alarm signal.

8. A spacecraft loop heat pipe switch control method implemented by using the spacecraft loop heat pipe switch control system based on multi-source information fusion as claimed in claim 1, characterized in that: It includes: According to the solar azimuth angle and the average temperature of the two cabin panels, control the power supply of the loop heat pipes on both sides of the cabin panels according to a preset strategy; the solar azimuth angle includes the cosine value of the included angle between the solar vector and one side of the cabin panel in the orbital coordinate system, and the cosine value of the included angle between the solar vector and the axis of one side of the body; The preset strategy includes a first strategy and a second strategy; the first strategy includes: 1) When A ≥ M ≥ B, it is considered that the sunlight shines on the +Y surface of the star body, and turn on the loop heat pipe on the +Y side; A is 1, B is 0.259, M is Soy or Sby, default is Soy, and it is switched according to the instruction; Soy is the cosine value of the included angle between the solar vector and the +Y cabin panel in the orbital coordinate system, and Sby is the cosine value of the included angle between the solar vector and the +Y axis of the body; +Y is the direction perpendicular to the cabin panel plane, and -Y is opposite to the +Y direction; 2) When C ≤ M ≤ D, it is considered that the sunlight shines on the -Y surface of the star body, and turn on the loop heat pipe on the -Y side; C is -1, D is -0.259, M is Soy; 3) When the value of M does not satisfy the ranges described in 1) and 2), keep the previous state unchanged; 4) From the state where 1) and 2) are not satisfied to the state where 1) and 2) are satisfied, only execute the judgment control strategy of state 1) and 2) once; in other cases, keep the state unchanged; If M < -1 or M > 1, the telemetry sub-system issues an alarm signal; when M cannot be obtained, the loop heat pipe maintains the current state, and at the same time the telemetry sub-system issues an alarm signal; The second strategy includes: 1) When TH1 - TH2 > E, turn on the loop heat pipe on the +Y side, and turn on the loop heat pipe on the +Y side; 2) When TH1 - TH2 < F, turn on the loop heat pipe on the -Y side; turn on the loop heat pipe on the -Y side; E is 10 and F is -10; 3) When F ≤ TH1 - TH2 ≤ E, keep the previous state unchanged; 4) When changing from a state that does not satisfy 1) and 2) to a state that satisfies 1) and 2), only execute the judgment control strategy of state 1) and 2) once; in other cases, keep the state unchanged.

9. The spacecraft loop heat pipe switch control method based on multi-source information fusion according to claim 8, characterized in that: The operation of turning on the loop heat pipe on the +Y side includes: First, turn off the loop heat pipe on the -Y side, the thermoelectric cooler, and the evaporator auxiliary heater circuit, and then turn on the thermoelectric cooler and the evaporator auxiliary heater circuit in the enabled state of the loop heat pipe on the +Y side; when the loop heat pipe on the +Y side and the thermoelectric cooler are turned on, the evaporator auxiliary heater is turned on simultaneously, and the thermoelectric cooler is turned on sequentially at a preset interval; the evaporator auxiliary heater is turned off after a preset duration; If the partial circuit shutdown fails when turning off the thermoelectric cooler and the evaporator auxiliary heater circuit of the loop heat pipe on the -Y side, the subsequent operation of turning on the thermoelectric cooler and the evaporator auxiliary heater circuit in the enabled state of the loop heat pipe on the +Y side will not be executed, and at the same time, the telemetry sub-system transmits this alarm state; The operation of turning on the loop heat pipe on the -Y side is the same as that of turning on the loop heat pipe on the +Y side.

10. The spacecraft loop heat pipe switch control method based on multi-source information fusion according to claim 8, characterized in that: After 1) and 2) in the first strategy and the second strategy are satisfied, during the preset duration of the instruction sending, suspend the condition judgment of the first strategy and the second strategy, and after the instruction sending is completed, re-judge; after re-judging, the corresponding loop heat pipe circuit is turned on, and no loop heat pipe power-on instruction is sent again; After the loop heat pipe power-on instruction is sent, the telemetry sub-system judges whether the switch state of the enabled state circuit meets the expectation. If not, it issues a telemetry alarm message prompt; at the same time, when the saddle temperature exceeds 50°C, turn off the corresponding loop heat pipe circuit; the saddle temperature is judged only when the loop heat pipe makes an action switch in orbit; when there is no switch, the saddle temperature is not judged; Under the condition of enabling loop heat pipe temperature control, when the accumulator temperature is higher than 40°C, the loop heat pipe circuit gives an alarm; when the accumulator temperature is higher than 50°C, turn off the corresponding loop heat pipe thermoelectric cooler circuit and issue an alarm signal.

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