Emergency system and method suitable for satellite equipment

Abstract

The invention relates to an emergency system and method suitable for satellite equipment. The emergency system comprises a solar panel, a pipeline device, an electromagnetic power generation device, an induction heating device, a heat dissipation device, an electromagnetic pump and an energy storage device. The pipeline device comprises a snakelike pipeline and a circulation pipeline which are communicated with each other; the snakelike pipeline is arranged on the back surface of the solar panel, and the pipeline device is used for connecting the solar panel, the electromagnetic power generation device, the induction heating device, the heat dissipation device and the electromagnetic pump, so that a flowing working medium can circularly flow in the pipeline device; the solar panel and the electromagnetic power generation device are both electrically connected with the energy storage device, and the energy storage device is electrically connected with the induction heating device and the electromagnetic pump. Therefore, the satellite equipment can still effectively deal with power failure and heat dissipation failure in an extreme environment, and stable operation of a satellite in various complex environments is ensured.

Description

Technical Field

[0001] The present application relates to the technical field of satellite equipment startup, and in particular to an emergency system and method applicable to satellite equipment. Background Art

[0002] The extremely harsh characteristics of the space environment pose a severe challenge to the stability and reliability of satellite equipment. The space environment has extreme characteristics such as high vacuum, ultra-low temperature, and no light. The temperature fluctuates greatly from -100°C to 150°C, which puts strict requirements on the thermal management system and material selection of satellite equipment. In such an environment, satellite equipment must maintain stable operation to ensure that it plays a vital role in communication, navigation, meteorological monitoring, earth observation, and emergency rescue.

[0003] When the communication system between the satellite and the ground station fails, it is crucial to quickly restore the communication link to ensure the transmission of critical information. To this end, the deployment of emergency communication satellites and ground stations can achieve rapid reconstruction of the communication network and ensure mission continuity and data security.

[0004] Sudden power outages and failure of cooling systems are two major risks in satellite operations. Traditional power supply methods may not be able to recover quickly, resulting in data loss or equipment damage; while failure of cooling systems may cause the temperature inside the satellite to rise sharply, endangering the safety of sensitive electronic components. Therefore, satellites must have the ability to respond quickly to protect themselves and maintain basic functions in the event of power outages or cooling failures.

[0005] Given that solar energy is the main energy source in space, advances in solar technology are crucial for emergency power supply for satellites. The design, manufacture, installation and maintenance of solar panels are key to ensuring that satellites can still operate in the event of a power outage. On the other hand, liquid metal has wide application potential in high-tech fields due to its excellent thermal conductivity, electrical conductivity and fluidity, but the high melting point of traditional liquid metal requires complex heating and insulation equipment to maintain its fluidity.

[0006] Faced with the above extreme situations, existing emergency measures are often not sufficient, especially when the power supply and cooling systems fail. There is a lack of a solution to ensure that satellites can reliably perform their missions under extreme conditions. Summary of the invention

[0007] In view of the above problems in the prior art, the present application provides an emergency system and method suitable for satellite equipment. The present application can effectively deal with the risks of power outages and heat dissipation failures, and ensure that satellite equipment can operate stably in extreme space environments.

[0008] To achieve the above-mentioned purpose, the first aspect of the present application provides an emergency system suitable for satellite equipment, including: a solar panel, a pipeline device, an electromagnetic power generation device, an induction heating device, a heat dissipation device, an electromagnetic pump, and an energy storage device;

[0009] The pipeline device includes a serpentine pipeline and a flow pipeline that are connected; wherein the serpentine pipeline is arranged on the back of the solar panel, and the pipeline device is used to connect the solar panel, the electromagnetic power generation device, the induction heating device, the heat dissipation device, and the electromagnetic pump, so that the flowing working medium can circulate in the pipeline device;

[0010] The solar panel and the electromagnetic power generation device are both electrically connected to the energy storage device, and the energy storage device is electrically connected to the induction heating device and the electromagnetic pump respectively;

[0011] The solar panel is used to convert the absorbed radiant heat into electrical energy and input it into the energy storage device, and heat the serpentine pipeline on the back side through heat conduction;

[0012] The energy storage device is used to store electrical energy and provide electrical energy to various devices;

[0013] The electromagnetic power generation device is used to generate electric current by utilizing the flowing working medium flowing in the circulation pipeline, and store the electric current in the energy storage device;

[0014] The electromagnetic pump is used to drive the flowing working medium to circulate in the pipeline device;

[0015] The induction heating device is used to heat the flowing working medium;

[0016] The heat dissipation device is used to use the flowing working medium to remove the heat in the satellite equipment.

[0017] In this way, the emergency system of this application integrates solar panels, pipeline devices, electromagnetic power generation devices, induction heating devices, heat dissipation devices, electromagnetic pumps and energy storage devices. Through the coordinated work between various devices, satellite equipment can still effectively respond to severe challenges such as power outages and heat dissipation failures in extreme environments, ensuring the stable operation of satellites in various complex environments. This emergency system not only improves the satellite's emergency response capabilities and self-protection mechanisms, but also provides a solid technical guarantee for the successful execution of satellite missions.

[0018] As a possible implementation manner of the first aspect, a plurality of pit structures are provided inside the serpentine pipeline.

[0019] In this way, the pit structure increases the contact area between the fluid and the solar panel, thereby improving the heat exchange efficiency, allowing the solar panel to transfer heat to the fluid more effectively. In addition, the pit structure can also resist the influence of excessive expansion rate of the fluid caused by drastic temperature changes to a certain extent, improving the stable operation of the emergency system.

[0020] As a possible implementation of the first aspect, an expansion joint is provided at the connection between the serpentine pipeline and the flow pipeline, so that the flowing working medium starts from the serpentine pipeline, passes through the electromagnetic power generation device, the induction heating device, the heat dissipation device, the electromagnetic pump, and finally returns to the serpentine pipeline on the back of the solar panel to form a circulation.

[0021] In this way, the use of expansion joints can compensate for the deformation of serpentine pipes and flow pipes due to thermal expansion and contraction at different temperatures, avoiding the risk of pipe rupture or leakage due to excessive stress, while ensuring the safety and reliability of the connection between pipes.

[0022] As a possible implementation of the first aspect, the electromagnetic power generation device includes:

[0023] A flow channel, used for guiding the flow of working fluid;

[0024] A plurality of magnetic poles are evenly arranged at the periphery of the flow channel for generating a magnetic field;

[0025] A plurality of coils are evenly arranged on the periphery of the flow channel and inside the magnetic poles, and are used to generate induced electromotive force in the coils according to Faraday's law of electromagnetic induction when the flowing working medium moves in the magnetic field;

[0026] an external circuit, arranged on one of the magnetic poles, for collecting the current generated by electromagnetic induction and transmitting the electric energy to the energy storage device; wherein the external circuit is electrically connected to the coil and the energy storage device respectively;

[0027] The movement of the flowing working fluid in the magnetic field causes the magnetic flux in the coil to change, thereby generating an induced electromotive force and driving the current to pass through the coil and the external circuit to achieve energy conversion.

[0028] In this way, the current is generated by the movement of the fluid in the magnetic field and stored in the energy storage device, achieving efficient energy conversion and storage. In addition, the electromagnetic power generation device does not require traditional mechanical parts (such as physical rotors), reducing the possibility of wear and failure, not only extending the service life, but also being particularly suitable for long-term unmanned space applications.

[0029] As a possible implementation of the first aspect, the induction heating device includes:

[0030] A liquid storage tank is used to store a flowing working medium and is provided with an inlet and an outlet so that the flowing working medium can enter and flow out of the liquid storage tank;

[0031] A heating element is wound around the outside of the liquid storage tank or arranged in the wall thickness of the liquid storage tank, and is used to heat the liquid storage tank to make the flowing working medium flow.

[0032] In this case, due to the low temperature of the space environment, the flowing medium in the liquid storage tank cannot maintain a flowing state. Therefore, the induction heating device must be powered by the energy storage device, and the flowing medium in the liquid storage tank must be heated by starting the heating element to ensure that the flowing medium can flow smoothly in the pipeline device.

[0033] As a possible implementation of the first aspect, the electromagnetic pump includes:

[0034] A transmission pipeline is used to guide the flow of working fluid through;

[0035] An inner iron core, located at the center of the electromagnetic pump and arranged in the transmission pipeline, is used to generate a magnetic field;

[0036] The primary iron core is arranged outside the transmission pipe and around the transmission pipe, and is used to generate a magnetic field.

[0037] In this way, the reasonable arrangement of the inner core and the primary core enables the electromagnetic pump to generate a stronger magnetic field, thereby improving the driving ability and efficiency of the pump.

[0038] As a possible implementation manner of the first aspect, the wall thickness of the transmission pipe is set to 8 to 16 mm.

[0039] Thus, the present application sets the wall thickness of the transmission pipeline to 8 to 16 mm. This thickness range can meet certain pressure requirements and ensure that the flowing medium flows safely and stably in the transmission pipeline. This thickness range also helps to optimize heat conduction efficiency and reduce energy loss.

[0040] As a possible implementation manner of the first aspect, the gap between the inner core and the transmission pipe is a pump groove gap, which is set to 5 to 8 mm.

[0041] In this way, the appropriate pump groove gap helps to reduce the resistance of the fluid during transmission and improve the flow efficiency. The gap width of 5 to 8 mm can reduce unnecessary energy loss while ensuring sufficient fluid channels, allowing the electromagnetic pump to more efficiently drive the flowing working fluid to circulate in the pipeline system.

[0042] As a possible implementation manner of the first aspect, the heat dissipation device includes:

[0043] A heat sink is arranged on the surface of the satellite device and is located on the side facing away from the sun;

[0044] A circulation pipeline is arranged around the heat dissipation device in the satellite device and is connected with the pipeline inside the heat dissipation plate;

[0045] The flowing working fluid is used to absorb and carry heat from the heat dissipation device, and is transported to the heat dissipation plate located on the side of the satellite surface facing away from the sun, so as to dissipate the heat into the outer space in the form of radiation.

[0046] In this way, the present application can efficiently transfer the heat generated by the heat dissipation device to the heat sink, which is arranged on the side of the satellite surface facing away from the sun, reducing the interference of additional radiant heat from the sun, so that the heat sink can more effectively dissipate heat to outer space in the form of radiation, thereby optimizing the heat dissipation performance and ensuring the stability of the internal temperature of the satellite equipment.

[0047] To achieve the above-mentioned purpose, the second aspect of the present application provides an emergency method applicable to satellite equipment, using the emergency system applicable to satellite equipment described in the first aspect above, including:

[0048] The radiant heat absorbed by the solar panel is converted into electrical energy and input into the energy storage device, and the serpentine pipe on the back is heated by heat conduction;

[0049] The flowing medium in the serpentine pipeline starts to flow after being heated, and each device is connected through the pipeline device to form a circulating flow path;

[0050] The flowing working fluid flows in the flow channel of the electromagnetic power generation device, and the generated electrical energy is stored in the energy storage device;

[0051] The energy storage device supplies power to the electromagnetic pump, and the electromagnetic pump serves as a power source to drive the flowing medium to circulate continuously in the entire pipeline device;

[0052] The energy storage device supplies power to the induction heating device, causing the heating element to heat the liquid storage tank, thereby causing the flowing working fluid to flow;

[0053] The heat dissipation device uses flowing working fluid to remove the heat generated by satellite equipment.

[0054] In summary, the present application includes at least one of the following beneficial technical effects:

[0055] (1) By integrating solar panels and pipe devices, dual efficient utilization of solar energy is achieved. On the one hand, solar energy is converted into electrical energy for storage; on the other hand, its radiant heat is used to heat the serpentine pipes, thereby significantly improving energy utilization efficiency. At the same time, the design of the pit structure and expansion joint effectively copes with the extreme temperature changes in space, significantly enhancing the reliability and stability of the entire system.

[0056] (2) The present application is equipped with an induction heating device and an electromagnetic pump, which work together to start quickly when the power fails. This design ensures that the flowing working fluid can be heated and driven in time in an emergency, thereby maintaining the critical operation of the satellite equipment. Therefore, the emergency system equipped in the present application significantly improves the emergency response capability and survivability of the satellite when encountering a power failure.

[0057] (3) A heat sink is used in satellite equipment. Through the effective heat conduction of the flowing working fluid, efficient heat transfer and heat dissipation are achieved, effectively protecting the satellite equipment from overheating damage. In addition, the integrated design of the electromagnetic pump and energy storage device enables the cooling of key components to be maintained in the event of a power outage, further enhancing the thermal management efficiency and self-protection capabilities of the satellite equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0058] Figure 1 It is a structural block diagram of an emergency system applicable to satellite equipment provided by the present application;

[0059] Figure 2 It is a schematic diagram of the relationship between an emergency system and satellite equipment provided by this application;

[0060] Figure 3 It is a structural schematic diagram of a solar panel provided by the present application;

[0061] Figure 4 It is a structural schematic diagram of an electromagnetic power generation device provided by the present application;

[0062] Figure 5 is a cross-sectional view of an electromagnetic power generation device provided by the present application;

[0063] Figure 6 It is a structural schematic diagram of an induction heating device provided by the present application;

[0064] Figure 7 It is a structural schematic diagram of an electromagnetic pump provided by the present application;

[0065] Figure 8 This is a flow chart of the main steps of an emergency method applicable to satellite equipment provided by this application.

[0066] It should be understood that the size and shape of each block diagram in the above structural diagram are for reference only and should not constitute an exclusive interpretation of the embodiment of the present invention. The relative position and inclusion relationship between the blocks presented in the structural diagram are only schematic representations of the structural association between the blocks, and do not limit the physical connection method of the embodiment of the present invention. DETAILED DESCRIPTION

[0067] The technical solution provided by the present application is further described below with reference to the accompanying drawings and examples. It should be understood that the system structure and business scenarios provided in the examples of the present application are mainly to illustrate the possible implementation methods of the technical solution of the present application and should not be interpreted as the only limitation on the technical solution of the present application. It is known to those of ordinary skill in the art that with the evolution of the system structure and the emergence of new business scenarios, the technical solution provided by the present application is also applicable to similar technical problems.

[0068] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art of the present application. In case of any inconsistency, the meaning described in this specification or the meaning derived from the contents recorded in this specification shall prevail. In addition, the terms used herein are only for the purpose of describing the embodiments of the present application and are not intended to limit the present application.

[0069] The present application embodiment provides an emergency system applicable to satellite equipment, such as Figure 1 As shown, it includes: a solar panel 1, a pipeline device 2, an electromagnetic power generation device 3, an induction heating device 4, a heat dissipation device 5, an electromagnetic pump 6, and an energy storage device 7;

[0070] The pipeline device 2 includes a serpentine pipeline 21 and a flow pipeline 22 which are connected to each other; wherein the serpentine pipeline 21 is arranged on the back of the solar panel 1, and the pipeline device 2 is used to connect the solar panel 1, the electromagnetic power generation device 3, the induction heating device 4, the heat dissipation device 5, and the electromagnetic pump 6, so that the flowing working medium can circulate in the pipeline device 2;

[0071] The solar panel 1 and the electromagnetic power generation device 3 are both electrically connected to the energy storage device 7, and the energy storage device 7 is electrically connected to the induction heating device 4 and the electromagnetic pump 6 respectively;

[0072] The solar panel 1 is used to convert the absorbed radiant heat into electrical energy and input it into the energy storage device 7, and heat the serpentine pipe 21 on the back side through heat conduction;

[0073] The energy storage device 7 is used to store electrical energy and provide electrical energy to various devices;

[0074] The electromagnetic power generation device 3 is used to generate electric current by utilizing the flowing working medium flowing in the circulation pipeline, and store the electric current in the energy storage device 7;

[0075] The electromagnetic pump 6 is used to drive the flowing medium to circulate in the pipeline device 2;

[0076] The induction heating device 4 is used to heat the flowing working medium;

[0077] The heat dissipation device 5 is used to use the flowing working medium to remove the heat in the satellite equipment.

[0078] Among them, the emergency system of the present application is installed on satellite equipment, such as Figure 2 As shown, the solar panel 1 of the emergency system is the solar panel on the satellite equipment, the pipeline device 2, the electromagnetic power generation device 3, the induction heating device 4, the electromagnetic pump 6 and the energy storage device 7 are arranged in the satellite equipment, and the heat dissipation device 5 is arranged on the surface of the satellite equipment and is located on the side facing away from the sun.

[0079] To clarify, the fluid is mainly gallium-indium-tin alloy, which has the characteristics of low melting point, melting point between 6 and 12 ° C. Other metals or alloys with low melting points can also be selected, such as sodium-potassium alloy with a melting point of -12.5 ° C, gallium with a melting point of 29.76 ° C, and other types of liquid metals such as lead-bismuth alloy (melting point 120-150 ° C). In order to significantly improve its electrical and thermal conductivity, the present application can also add iron powder, magnetic particles coated with aluminum oxide (Al2O3) or silicon dioxide (SiO2), and hard magnetic particles to the liquid metal to form a nanofluid.

[0080] For example, when the fluid is a liquid metal of gallium indium tin alloy, its melting point is usually between 6 and 12°C, and the specific melting point depends on the composition ratio of each element in the alloy. In general, since the ambient temperature of outer space is much lower than the melting point of gallium indium tin alloy, the fluid can be in a solid state in the outer space environment.

[0081] Thus, the emergency system of the present application integrates solar panels 1, pipeline devices 2, electromagnetic power generation devices 3, induction heating devices 4, heat dissipation devices 5, electromagnetic pumps 6 and energy storage devices 7. Through the coordinated work between the various devices, the satellite equipment can still effectively respond to severe challenges such as power outages and heat dissipation failures in extreme environments, ensuring the stable operation of the satellite in various complex environments. The emergency system not only improves the satellite's emergency response capabilities and self-protection mechanisms, but also provides a solid technical guarantee for the successful execution of satellite missions.

[0082] In some embodiments, a plurality of pit structures 11 are disposed inside the serpentine pipeline 21 .

[0083] Among them, Figure 3 As shown, the pit structure 11 is a rectangular pit.

[0084] Of course, in some other embodiments, spherical pits or conical pits are also used, which are not specifically limited here, so as to meet the needs of different scenarios and improve the flexibility of design.

[0085] In this way, the pit structure 11 increases the contact area between the fluid and the solar panel 1, thereby improving the heat exchange efficiency, so that the solar panel 1 can more effectively transfer heat to the fluid. In addition, the pit structure 11 can also resist the influence of excessive expansion rate of the fluid caused by drastic temperature changes to a certain extent, thereby improving the stable operation of the emergency system.

[0086] It should be noted that the present application can further improve the heat exchange efficiency by changing parameters such as the shape, size and distribution density of the pit structure 11.

[0087] In some embodiments, Figure 3 As shown, an expansion joint 12 is provided at the connection between the serpentine pipeline 21 and the flow pipeline 22, so that the flowing working medium starts from the serpentine pipeline 21, passes through the electromagnetic power generation device 3, the induction heating device 4, the heat dissipation device 5, the electromagnetic pump 6, and finally returns to the serpentine pipeline 21 on the back of the solar panel 1 to form a cycle.

[0088] In this way, the use of the expansion joint 12 can compensate for the deformation of the serpentine pipeline 21 and the flow pipeline 22 caused by thermal expansion and contraction at different temperatures, avoiding the risk of pipeline rupture or leakage due to excessive stress, while ensuring the safety and reliability of the connection between pipelines.

[0089] In some embodiments, Figure 4 and Figure 5 As shown, the electromagnetic power generation device 3 includes:

[0090] A flow channel 31, used for guiding the flow of working fluid;

[0091] A plurality of magnetic poles 32 are evenly arranged on the periphery of the flow channel 31 to generate a magnetic field;

[0092] A plurality of coils 33 are evenly arranged on the periphery of the flow channel 31 and inside the magnetic pole 32, and are used to generate an induced electromotive force in the coils 33 according to Faraday's law of electromagnetic induction when the flowing working medium moves in the magnetic field;

[0093] The external circuit 35 is arranged on one of the magnetic poles 32, and is used to collect the current generated by electromagnetic induction and transmit the electric energy to the energy storage device 7; wherein the external circuit 35 is electrically connected to the coil and the energy storage device 7 respectively;

[0094] The movement of the flowing working fluid in the magnetic field causes the magnetic flux in the coil 33 to change, thereby generating an induced electromotive force and driving the current to pass through the coil 33 and the external circuit 35 to achieve energy conversion.

[0095] In this way, the current is generated by the movement of the flowing working fluid in the magnetic field and stored in the energy storage device 7, thus achieving efficient energy conversion and storage. In addition, the electromagnetic power generation device 3 does not require traditional mechanical components (such as physical rotors), which reduces the possibility of wear and failure, not only prolongs the service life, but is also particularly suitable for long-term unmanned space applications.

[0096] Let me explain. Figure 5 Only one coil 33 is shown in FIG. 3 , and the other coils 33 are not shown.

[0097] In some embodiments, Figure 6 As shown, the induction heating device 4 comprises:

[0098] The liquid storage tank 41 is used to store the fluid, and is provided with an inlet 43 and an outlet 44, so that the fluid enters and flows out of the liquid storage tank 41;

[0099] The heating element 42 is wound around the outside of the liquid storage tank 41 or disposed in the wall thickness of the liquid storage tank 41, and is used to heat the liquid storage tank 41 to make the flowing working medium flow.

[0100] Example 1: The heating element 42 may be a resistance wire, which is wound around the outside of the liquid storage tank 41 .

[0101] Example 2: The heating element 42 may be an electric heating film, which is a thin heating element that can be directly attached to the inner wall or outer wall of the liquid storage tank 41. The electric heating film has the advantages of uniform heating, fast response, and easy installation, and is particularly suitable for occasions with limited space.

[0102] The present application provides a variety of heating methods. Different types of heating elements 42 have different heating efficiencies and characteristics. Appropriate heating elements 42 can be selected according to actual needs to achieve the best heating effect. In other words, in actual situations, selection can be made according to specific needs, which improves the flexibility and adaptability of the emergency system to meet the needs of different scenarios.

[0103] It is worth noting that Figure 6 Only the embodiment in which the heating element 42 can be a resistance wire is shown, and the embodiment in which the heating element 42 is arranged in the wall thickness of the liquid storage tank 41 is not shown.

[0104] In this way, due to the low temperature of the space environment, the flowing medium in the liquid storage tank 41 cannot maintain a flowing state. Therefore, the induction heating device 4 must be powered by the energy storage device 7, and the flowing medium in the liquid storage tank 41 is heated by starting the heating element 42 to ensure that the flowing medium can flow smoothly in the pipeline device 2.

[0105] In some embodiments, the emergency system further includes a temperature sensor. Specifically, the temperature sensor is embedded in the liquid storage tank 41 or is close to the wall thickness of the liquid storage tank 41 to directly monitor the temperature of the flowing medium in the liquid storage tank 41. When the flowing medium reaches the melting point, the emergency system stops heating the liquid storage tank 41.

[0106] In some embodiments, Figure 7 As shown, the electromagnetic pump 6 comprises:

[0107] The transmission pipeline 61 is used to guide the flow of working medium;

[0108] The inner iron core 62 is located at the center of the electromagnetic pump 6 and is arranged in the transmission pipeline 61 to generate a magnetic field;

[0109] The primary core 63 is disposed outside the transmission pipe 61 and around the transmission pipe 61 to generate a magnetic field.

[0110] Specifically, the electromagnetic pump 6 works on the principle of electromagnetic induction, that is, when a conductor moves in a magnetic field or a magnetic field passes through a conductor, an electromotive force is generated, thereby causing an electric current. In the present application, when the energy storage device 7 supplies power to the electromagnetic pump 6, the alternating magnetic field generated in the primary iron core 63 and the inner iron core 62 will cause an induced current in the transmission pipeline 61, and these currents interact with the magnetic field to generate a force, thereby driving the liquid metal in the pipeline to flow.

[0111] Thus, the reasonable arrangement of the inner core 62 and the primary core 63 enables the electromagnetic pump 6 to generate a stronger magnetic field, thereby improving the driving ability and efficiency of the pump.

[0112] In some embodiments, the wall thickness of the transmission pipe 61 is set to 8-16 mm.

[0113] Thus, the present application sets the wall thickness of the transmission pipe 61 to 8 to 16 mm. This thickness range can meet certain pressure requirements and ensure that the flowing medium flows safely and stably in the transmission pipe 61. This thickness range also helps to optimize heat conduction efficiency and reduce energy loss.

[0114] Of course, in practical applications, the wall thickness of the transmission pipe 61 can also be set to other values. For example, the wall thickness of the transmission pipe 61 is set to 7 mm. In other words, it can be set according to specific needs to meet the needs of different scenarios, thereby improving the flexibility of the emergency system.

[0115] In some embodiments, the gap between the inner core 62 and the transmission pipe 61 is a pump groove gap 64, which is set to 5 to 8 mm.

[0116] Thus, a proper pump groove gap 64 helps to reduce resistance of the fluid during transmission and improve flow efficiency.

[0117] The gap width of 5 to 8 mm can reduce unnecessary energy loss while ensuring sufficient fluid channels, so that the electromagnetic pump 6 can more efficiently drive the flowing working medium to circulate in the pipeline system.

[0118] Of course, in practical applications, the size of the pump groove gap 64 can also be set to other values. For example, the pump groove gap 64 is set to 10 mm. In other words, it can be set according to specific needs to meet the needs of different scenarios, thereby improving the flexibility of the emergency system.

[0119] In some embodiments, the heat dissipation device 5 includes:

[0120] A heat sink is arranged on the surface of the satellite device and is located on the side facing away from the sun;

[0121] The circulation pipeline 22 is arranged around the heat dissipation device in the satellite equipment and is connected with the pipeline inside the heat dissipation plate;

[0122] The fluid is used to absorb and carry heat from the heat dissipation device, and is transported to the heat dissipation plate on the satellite surface facing away from the sun, where the heat is radiated to outer space. On the other hand, the heat provided by the heat dissipation device can also be used to maintain the fluid in a liquid state.

[0123] In this way, the present application can efficiently transfer the heat generated by the heat dissipation device to the heat sink, which is arranged on the side of the satellite surface facing away from the sun, reducing the interference of additional radiant heat from the sun, so that the heat sink can more effectively dissipate heat to outer space in the form of radiation, thereby optimizing the heat dissipation performance and ensuring the stability of the internal temperature of the satellite equipment.

[0124] To clarify, the reason why the heat sink is located on the side facing away from the sun is that the position facing away from the sun can minimize the extra heat brought by direct sunlight and prevent such heat from offsetting the heat dissipation effect of the heat sink.

[0125] For example, the pipe inside the heat sink can be designed as a serpentine, similar to Figure 3 The serpentine pipe shown in the figure. The serpentine pipe significantly increases the flow path length of the fluid in the heat sink by making multiple turns in a limited space. The serpentine pipe can also be more evenly distributed inside the heat sink, ensuring that the fluid can efficiently absorb and dissipate heat, avoiding local overheating or uneven heat dissipation.

[0126] In some embodiments, an expansion joint may be used at the connection between the circulation pipeline 22 and the pipeline inside the heat sink to compensate for the deformation of the pipeline caused by thermal expansion and contraction at different temperatures and ensure the reliability of the connection.

[0127] The working principle of the emergency system of this application will be described in detail as follows:

[0128] Before the emergency system is activated, the flowing working fluid is a liquid metal of gallium indium tin alloy as an example. Its melting point is usually between 6 and 12°C. Due to the space environment, the temperature is relatively low, far lower than the melting point of gallium indium tin alloy. Therefore, the flowing working fluid is in a non-flowing state, that is, the flowing working fluid is stored in a solid form in the serpentine pipe 21, each flow pipe 22 and the liquid storage tank 41 arranged on the back of the solar panel 1.

[0129] It is worth noting that even if the flowing medium in each circulation pipeline 22 is solid at first, when the flowing medium in the serpentine pipeline 21 and the flowing medium in the liquid storage tank 41 reach the melting point and start to flow, they will gradually transfer heat to the solid flowing medium in the circulation pipeline 22, gradually making it reach the melting point and enter the flowing state. Ultimately, the flowing medium of the entire emergency system will be heated to the melting point and start to circulate.

[0130] After the emergency system is automatically started, the details are as follows:

[0131] First, the solar panel 1 faces the sun's radiation, absorbs light energy and converts it into electrical energy, and stores the electrical energy in the energy storage device 7. At the same time, the flowing medium is heated through the serpentine pipeline 21 arranged on the back. The purpose of heating is to make the flowing medium higher than the melting point, melt into a liquid state, and start to flow. At the same time, the energy storage device 7 supplies power to the induction heating device 4. Since the temperature of the space environment is too low, the flowing medium in the liquid storage tank 41 cannot maintain a flowing state. The energy storage device 7 supplies power to the induction heating device 4 and starts the heating element 42 until the flowing medium reaches the melting point and completely melts, and then stops heating to ensure that the flowing medium can flow smoothly in the pipeline;

[0132] Then, the flowing working fluid passes through the electromagnetic power generation device 3, and the movement of the flowing working fluid in the magnetic field causes the magnetic flux in the coil 33 to change, thereby generating an induced electromotive force and driving the current to pass through the coil 33 and the external circuit 35 to achieve energy conversion. In other words, the flowing working fluid is used to flow in the circulation pipe 31 to generate current and store it in the energy storage device 7.

[0133] The energy storage device 7 serves as a power supply device to supply power to the electromagnetic pump 6. The electromagnetic pump 6 serves as a power source to drive the circulating working medium in the entire pipeline device 2;

[0134] To clarify, the heat dissipation equipment in satellite equipment usually refers to high-power equipment that requires efficient heat dissipation to maintain normal operating temperature. These heat dissipation equipment will generate a lot of heat during operation, and its temperature may be as high as hundreds of degrees Celsius, which is much higher than the temperature of the flowing medium itself, so the heat of the heat dissipation equipment is carried away by the flowing medium. For example, the temperature of the semiconductor laser used for laser ranging may reach 150°C when it is output at high power. Therefore, the flowing medium (liquid metal of gallium indium tin alloy) can be used to flow through the flow pipe 22 around the heat dissipation equipment arranged in the satellite equipment to absorb the heat generated by these equipment. The flowing medium that absorbs the heat is transported to the heat sink located on the side of the satellite surface facing away from the sun. In the flow pipe 22 arranged inside the heat sink, the flowing medium continues to flow and dissipates the heat to outer space in the form of radiation through the large surface area of ​​the heat sink.

[0135] Finally, after the heat is dissipated by the heat sink, the cooled fluid returns to the serpentine pipe 21 on the back of the solar panel 1, completing a complete circulation path. Among them, the serpentine pipe 21 is arranged with a pit structure 11 inside, which enhances the heat exchange efficiency between the fluid and the solar panel 1, and can resist the influence of excessive expansion rate of the fluid caused by drastic temperature changes. An expansion joint 12 is provided at the connection between the serpentine pipe 21 and the circulation pipe 22 to compensate for the deformation of the pipe caused by thermal expansion and contraction at different temperatures, ensuring the reliability of the connection.

[0136] Among them, since the solar panels can always convert energy into electrical energy, the emergency system can always be in working condition after the first startup. On the one hand, the energy of the energy storage device 7 is full, and on the other hand, the flow state of the flowing working fluid can be maintained. When the satellite equipment encounters power outages and / or heat dissipation failures, the emergency system can achieve the above-mentioned heat dissipation and even supply power to the satellite through its energy storage device 7.

[0137] In some other embodiments, the emergency system can be activated only when the satellite equipment encounters power outage and / or heat dissipation failure, so that when the flowing working fluid is in liquid for a certain period of time, the above-mentioned heat dissipation can be achieved, and even power can be supplied to the satellite through its energy storage device 7.

[0138] The present application embodiment provides an emergency method applicable to satellite equipment, such as Figure 8 As shown, the above-mentioned emergency system applicable to satellite equipment includes:

[0139] S601: When the satellite equipment encounters power failure and / or heat dissipation failure, the emergency system is activated; or after the emergency system is activated for the first time, it is always in the on state;

[0140] S602, the radiant heat absorbed by the solar panel 1 is converted into electric energy and input into the energy storage device 7, and the serpentine pipe 21 on the back is heated by heat conduction;

[0141] S603, the fluid in the serpentine pipeline 21 starts to flow after being heated, and each device is connected through the pipeline device 2 to form a circulating flow path;

[0142] S604, the flowing working fluid flows in the flow channel 31 of the electromagnetic power generation device 3, and the generated electric energy is stored in the energy storage device 7;

[0143] S605, the energy storage device 7 supplies power to the electromagnetic pump 6, and the electromagnetic pump 6 acts as a power source to drive the flowing working medium to circulate continuously in the entire pipeline device 2;

[0144] S606, the energy storage device 7 supplies power to the induction heating device 4, so that the heating element 42 heats the liquid storage tank 41, so that the flowing working medium flows;

[0145] S607. The heat dissipation device 5 uses the flowing working fluid to remove the heat generated by the satellite equipment.

[0146] In this way, through the collaborative work between various devices, this application enables satellite equipment to effectively respond to severe challenges such as power outages and heat dissipation failures in extreme environments, ensuring the stable operation of satellites in various complex environments. This emergency system not only improves the satellite's emergency response capabilities and self-protection mechanisms, but also provides a solid technical guarantee for the successful execution of satellite missions.

[0147] It is worth noting that when the normal power supply and cooling needs of satellite equipment are met, the emergency system is usually in standby mode.

[0148] In addition, the words "first, second, third, etc." or module A, module B, module C and other similar terms in the specification and claims are only used to distinguish similar objects and do not represent a specific ordering of the objects. It can be understood that the specific order or sequence can be interchanged where permitted so that the embodiments of the present application described herein can be implemented in an order other than that illustrated or described herein.

[0149] In the above description, the numbers representing the steps, such as S110, S120, etc., do not necessarily mean that the steps will be executed in this manner. If permitted, the order of the steps can be interchanged or they can be executed simultaneously.

[0150] The term "comprising" as used in the description and claims should not be interpreted as being limited to what is listed thereafter; it does not exclude other elements or steps. Therefore, it should be interpreted as specifying the presence of the features, integers, steps or components mentioned, but does not exclude the presence or addition of one or more other features, integers, steps or components and groups thereof. Therefore, the expression "a device comprising means A and B" should not be limited to a device consisting of components A and B only.

[0151] References to "one embodiment" or "an embodiment" in this specification mean that a particular feature, structure, or characteristic described in conjunction with the embodiment is included in at least one embodiment of the present application. Therefore, the phrases "in one embodiment" or "in an embodiment" appearing in various places in this specification do not necessarily refer to the same embodiment, but may refer to the same embodiment. In addition, in one or more embodiments, the particular features, structures, or characteristics can be combined in any appropriate manner, as would be apparent to one of ordinary skill in the art from this disclosure.

[0152] Note that the above are only preferred embodiments of the present application and the technical principles used. Those skilled in the art will understand that the present application is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present application. Therefore, although the present application is described in more detail through the above embodiments, the present application is not limited to the above embodiments, and may also include more other equivalent embodiments without departing from the concept of the present application, all of which belong to the scope of protection of the present application.

Claims

1. An emergency system suitable for satellite equipment, characterized in that: include: Solar panel (1), pipeline device (2), electromagnetic power generation device (3), induction heating device (4), heat dissipation device (5), electromagnetic pump (6), and energy storage device (7); The pipeline device (2) comprises a serpentine pipeline (21) and a circulation pipeline (22) which are interconnected; wherein the serpentine pipeline (21) is arranged on the back of the solar panel (1), and the pipeline device (2) is used to connect the solar panel (1), the electromagnetic power generation device (3), the induction heating device (4), the heat dissipation device (5), and the electromagnetic pump (6), so that the flowing working medium can circulate in the pipeline device (2); The solar panel (1) and the electromagnetic power generation device (3) are both electrically connected to the energy storage device (7), and the energy storage device (7) is electrically connected to the induction heating device (4) and the electromagnetic pump (6) respectively; The solar panel (1) is used to convert the absorbed radiant heat into electrical energy which is input into the energy storage device (7), and to heat the serpentine pipeline (21) on the back side through heat conduction; The energy storage device (7) is used to store electrical energy and provide electrical energy to various devices; The electromagnetic power generation device (3) is used to generate electric current by utilizing the flowing working medium flowing in the circulation pipeline, and store the electric current in the energy storage device (7); The electromagnetic pump (6) is used to drive the flowing working medium to circulate in the pipeline device (2); The induction heating device (4) is used to heat the flowing working medium; The heat dissipation device (5) is used to use the flowing working fluid to remove the heat in the satellite equipment.

2. The emergency system according to claim 1, characterized in that: A plurality of pit structures (11) are provided inside the serpentine pipeline (21).

3. The emergency system according to claim 1, characterized in that: An expansion joint (12) is provided at the connection point between the serpentine pipeline (21) and the circulation pipeline (22), so that the flowing working medium starts from the serpentine pipeline (21), passes through the electromagnetic power generation device (3), the induction heating device (4), the heat dissipation device (5), and the electromagnetic pump (6), and finally returns to the serpentine pipeline (21) on the back side of the solar panel (1), thereby forming a circulation.

4. The emergency system according to claim 1, characterized in that: The electromagnetic power generation device (3) comprises: A flow channel (31) for guiding the flow of working fluid; A plurality of magnetic poles (32) are evenly arranged on the periphery of the flow channel (31) and are used to generate a magnetic field; A plurality of coils (33) are evenly arranged on the periphery of the flow channel (31) and inside the magnetic pole (32), and are used to generate an induced electromotive force in the coils (33) according to Faraday's law of electromagnetic induction when the flowing working fluid moves in the magnetic field; an external circuit (35) disposed on one of the magnetic poles (32) for collecting the current generated by electromagnetic induction and transmitting the electric energy to the energy storage device (7); wherein the external circuit (35) is electrically connected to the coil and the energy storage device (7) respectively; The movement of the flowing working fluid in the magnetic field causes the magnetic flux in the coil (33) to change, thereby generating an induced electromotive force and driving the current to pass through the coil (33) and the external circuit (35), thereby achieving energy conversion.

5. The emergency system according to claim 1, characterized in that: The induction heating device (4) comprises: A liquid storage tank (41) is used to store a flowing working medium and is provided with an inlet (43) and an outlet (44) so ​​that the flowing working medium can enter and flow out of the liquid storage tank (41); A heating element (42) is wound around the outside of the liquid storage tank (41) or arranged in the wall thickness of the liquid storage tank (41) and is used to heat the liquid storage tank (41) to enable the flowing working medium to flow.

6. The emergency system according to claim 1, characterized in that: The electromagnetic pump (6) comprises: A transmission pipeline (61) for guiding the flow of working fluid; An inner iron core (62) is located at the center of the electromagnetic pump (6) and is disposed in the transmission pipeline (61) for generating a magnetic field; The primary iron core (63) is arranged outside the transmission pipe (61) and around the transmission pipe (61) and is used to generate a magnetic field.

7. The emergency system according to claim 6, characterized in that: The wall thickness of the transmission pipe (61) is set to 8-16 mm.

8. The emergency system according to claim 6, characterized in that: The gap between the inner iron core (62) and the transmission pipe (61) is a pump groove gap (64), which is set to 5 to 8 mm.

9. The emergency system according to claim 1, characterized in that: The heat dissipation device (5) comprises: A heat sink is arranged on the surface of the satellite device and is located on the side facing away from the sun; A circulation pipeline (22) is arranged around the heat dissipation device in the satellite device and is connected to the pipeline inside the heat dissipation plate; The flowing working fluid is used to absorb and carry heat from the heat dissipation device, and is transported to the heat dissipation plate located on the side of the satellite surface facing away from the sun, so as to dissipate the heat into the outer space in the form of radiation.

10. An emergency method applicable to satellite equipment, using an emergency system applicable to satellite equipment as claimed in any one of claims 1 to 9, characterized in that: include: The radiant heat absorbed by the solar panel (1) is converted into electric energy and input into the energy storage device (7), and the serpentine pipe (21) on the back is heated by heat conduction; The flowing medium in the serpentine pipeline (21) starts to flow after being heated, and connects various devices through the pipeline device (2) to form a circulating flow path; The flowing working fluid flows in the flow channel (31) of the electromagnetic power generation device (3), and the generated electric energy is stored in the energy storage device (7); The energy storage device (7) supplies power to the electromagnetic pump (6), and the electromagnetic pump (6) serves as a power source to drive the flowing working fluid to continuously circulate in the entire pipeline device (2); The energy storage device (7) supplies power to the induction heating device (4), so that the heating element (42) heats the liquid storage tank (41) to make the flowing working fluid flow; The heat dissipation device (5) uses a flowing working fluid to remove the heat generated by the satellite equipment.

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