Inter-cabin energy switching method and system based on spacecraft approaching and exiting Earth's shadow

Abstract

This invention provides a method and system for inter-module energy switching based on spacecraft entering and exiting Earth's shadow, comprising: acquiring the position information of the spacecraft and the sun; calculating the spacecraft's shadow angle and the angle subtended by the sun, Earth, and spacecraft based on the position information and the Earth's radius; determining whether the spacecraft is currently in Earth's shadow based on the shadow angle and the angle subtended; if so, cutting off the power transmission between the two modules of the spacecraft according to the entry-in-shadow flag calculated in real time on orbit, thus disconnecting the power transmission path between the two modules; if not, restoring the power transmission path between the two modules to its state before disconnection based on the exit-in-shadow flag calculated in real time on orbit and the identifiers of the three power distribution states before entering Earth's shadow. This invention switches the power transmission state of the two modules of the spacecraft according to the entry-in-shadow flag and a programmed control strategy, ensuring the spacecraft's on-orbit energy safety and effectively improving its on-orbit reliability.

Description

Technical Field

[0001] This invention relates to the field of spacecraft space energy transmission technology, specifically to a method and system for inter-cabin energy switching based on the judgment of spacecraft entering and leaving the Earth's shadow. Background Technology

[0002] Traditional satellites employ a fixed structure between the payload module and the platform module, and energy transfer between the modules does not involve the satellite's entry and exit from the Earth's shadow. The dual-supersatellite platform, however, uses a configuration where the payload module and platform module are separable, with the solar array mounted in the platform module. Therefore, when the spacecraft enters or exits the Earth's shadow, the energy transfer control strategy between the platform module and the payload module has unique requirements that differ from those of traditional satellites.

[0003] Patent document CN106314827A discloses a master-slave non-contact dual-super satellite platform inter-module energy transmission system, including a platform module power system, a payload module power system, and an inter-module energy transmission switching mechanism; the platform module power system and the payload module power system transmit electrical energy to each other through the inter-module energy transmission switching mechanism; when the inter-module energy transmission switching mechanism is turned on, the platform module power system provides electrical energy to the payload module power system.

[0004] Patent document CN103594749A discloses a method for charging a spacecraft based on wireless energy transmission, including the following steps: (1) The spacecraft that needs to be charged sends a charging request command to the command and control center. The ground command and control center calculates the wireless energy transmission time based on the required charging amount and energy transmission efficiency; (2) The rendezvous trajectory is calculated with the orbits of the charging and charged spacecraft and the charging time as constraints, and the charging spacecraft is guided to rendezvous with the charged spacecraft according to the orbit calculation results using a CW guidance strategy; (3) An energy transmission channel is established, and the charging spacecraft and the charged spacecraft confirm their relative positions and attitudes; (4) Energy is transmitted to the charged spacecraft via laser or microwave.

[0005] Patent document CN204539137U discloses an underwater non-contact data and energy transmission connector. This utility model includes a transmitting main control module and a data signal generation module with signal connections at their input terminals. The output terminal of the data signal generation module is connected to one input terminal of a signal coupling module. The output terminal of the power carrier generation module is connected to the other input terminal of the signal coupling module. The output terminal of the signal coupling module is connected to the transmitting coil with a signal connection. The receiving coil is connected to the input terminals of a low-pass filter module and a power processing module, respectively. The output terminal of the low-pass filter module is connected to the input terminal of a receiving processing module with a signal connection. The transmitting coil and the receiving coil are inductively coupled.

[0006] Patent document CN204119037U discloses a multi-channel continuously adjustable voltage power supply module and a continuously adjustable power supply system. The multi-channel continuously adjustable voltage power supply module includes: a continuously adjustable voltage section, a high-precision multi-level current detection section, and a combinable multi-channel usage section. The adjustable voltage generation section is connected to an output load, and the current detection section detects the current output by the output load.

[0007] Patent document CN102385105A discloses a method for energy-level linear light transmission, comprising: an optically dense medium, an optically rarer medium, and a non-optical medium. Its characteristic is that: the unit element for energy-level linear light transmission is composed of a linear portion of the optical medium, a light transmission condensation portion, and an optical medium interface portion; the linear portion of the optical medium is composed of an optically dense medium and an optically rarer medium, and the light is transmitted via total internal reflection; the optically dense medium of the linear portion is a cylindrical optically dense medium, and the optically rarer medium of the linear portion is of two types: the first is vacuum, and the second is air; the light transmission... The light transmission and focusing section functions to focus and adjust the direction of light rays. The light transmission and focusing section is an integrated focusing functional unit with a focusing mirror as the main body. The optical medium interface section is divided into two types: the first type is the two ends of a cylindrical optically dense medium, and the second type is the upper and lower surfaces of the integrated focusing functional unit with a focusing mirror as the main body. The connection method between the optical medium interfaces is as follows: a cylindrical optically dense medium and an integrated focusing functional unit with a focusing mirror as the main body are connected to form the most basic unit of energy-level light linear transmission. The unit of energy-level light linear transmission is connected to form an optical medium channel for energy-level light linear transmission.

[0008] However, none of the above patent documents involve a method for switching energy transmission. Therefore, there is a market need for a simple and efficient switching method that has engineering value in ensuring the on-orbit energy safety of spacecraft, based on the judgment of spacecraft entering and leaving the Earth's shadow, for inter-cabin energy switching programmable control. Summary of the Invention

[0009] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method and system for inter-cabin energy switching based on the judgment of spacecraft entering and leaving the Earth's shadow.

[0010] A method for inter-cabin energy switching based on spacecraft entering and leaving Earth's shadow, provided by the present invention, includes:

[0011] Step S1: Obtain the position information of the spacecraft and the sun;

[0012] Step S2: Calculate the spacecraft's shadow angle and the angle formed by the Sun, Earth, and spacecraft based on the location information and Earth's radius;

[0013] Step S3: Based on the shadow angle and the subtended angle, determine whether the spacecraft is currently in the shadow. If so, based on the shadow entry flag given by the spacecraft's real-time on-orbit calculation, cut off the power transmission status of the two modules of the spacecraft and disconnect the power transmission path between the two modules. If not, trigger step S4.

[0014] Step S4: Based on the Earth Shadow exit marker given by the spacecraft's real-time on-orbit calculation, and according to the identifiers of the three power distribution states before entering the Earth Shadow, restore the energy transmission path between the two modules of the spacecraft to the state before it was disconnected.

[0015] Preferably, step S2 includes:

[0016] Step S2.1: When the spacecraft is in orbit, calculate the Earth's shadow angle as it enters the Earth's shadow region, using the following formula:

[0017]

[0018] In the formula, α Shadow_0 R represents the angle of the Earth's shadow as the spacecraft enters the Earth's shadow region. e The radius r of the Earth is represented by the radius r of the Earth. x r y and r z These represent the distances along the x, y, and z axes of the spacecraft, respectively.

[0019] Step S2.2: While the spacecraft is in orbit, calculate the angle subtended by the Sun, Earth, and spacecraft as currently captured in the image. The formula is as follows:

[0020]

[0021] In the formula, α Shadow_t The angle r represents the subtended angle between the Sun, Earth, and the spacecraft. sunix r suniy and r suniz These represent the distances to the sun along the x, y, and z axes, respectively.

[0022] Preferably, determining whether the current spacecraft is in the Earth's shadow includes:

[0023] Continuous judgment over multiple periods, when α Shadow_t ≥α Shadow_0 At that time, it was determined that the satellite was in the Earth's shadow, and the Earth's shadow marker DYBZ was set to AA;

[0024] Continuous judgment across multiple frames, α Shadow_t <α Shadow_0 At that time, it was determined that the satellite was under illumination, and the ground shadow marker DYBZ was set to 55;

[0025] Where, α Shadow_t α represents the angle subtended by the Sun, Earth, and spacecraft. Shadow_0This indicates the angle of the Earth's shadow when a spacecraft enters the Earth's shadow region.

[0026] Preferably, the two modules of the spacecraft include a platform module and a payload module; the energy transmission status of the two modules includes a wired disconnect device, a wireless power device, and a reusable device.

[0027] The wired disconnection device is a low-frequency cable wired device responsible for transmitting power between the two compartments. After disconnection, the wired disconnection device is stored between the two compartments, and the internal low-frequency cable cannot be reconnected.

[0028] The wireless power device is an electromagnetic conversion wireless device that transmits energy between the two cabins via electromagnetic induction in space.

[0029] The reusable pluggable device is a reusable low-frequency cable wired device that transmits power between the two compartments, enabling the internal low-frequency cable to be repeatedly switched on and off.

[0030] Preferably, the three power transmission paths between the platform compartment and the payload compartment—the wired disconnection device, the wireless power device, and the reusable pluggable device—are mutually exclusive, with only one of the three paths being powered on at any given time.

[0031] An inter-cabin energy switching system based on spacecraft entering and leaving Earth's shadow, provided by the present invention, includes:

[0032] Module M1: Acquires the position information of the spacecraft and the sun;

[0033] Module M2: Calculates the spacecraft's shadow angle and the angle formed by the Sun, Earth, and spacecraft based on the location information and Earth's radius;

[0034] Module M3: Based on the shadow angle and the subtended angle, determine whether the spacecraft is currently in the shadow. If so, based on the shadow entry flag given by the spacecraft in real time calculation on orbit, cut off the power transmission status of the two modules of the spacecraft and disconnect the power transmission path between the two modules. If not, trigger module M4.

[0035] Module M4: Based on the Earth Shadow exit marker given by the spacecraft in real time calculation on orbit, and according to the identifiers of the three power distribution states before entering the Earth Shadow, restores the energy transmission path between the two modules of the spacecraft to the state before it was disconnected.

[0036] Preferably, module M2 includes:

[0037] Module M2.1: When a spacecraft is in orbit, the Earth's shadow angle is calculated when it enters the Earth's shadow region. The formula is as follows:

[0038]

[0039] In the formula, α Shadow_0R represents the angle of the Earth's shadow as the spacecraft enters the Earth's shadow region. e The radius r of the Earth is represented by the radius r of the Earth. x r y and r z These represent the distances along the x, y, and z axes of the spacecraft, respectively.

[0040] Module M2.2: Calculates the angle subtended by the Sun, Earth, and spacecraft in a current photograph while the spacecraft is in orbit, using the following formula:

[0041]

[0042] In the formula, α Shadow_t The angle r represents the subtended angle between the Sun, Earth, and the spacecraft. sunix r suniy and r suniz These represent the distances to the sun along the x, y, and z axes, respectively.

[0043] Preferably, determining whether the current spacecraft is in the Earth's shadow includes:

[0044] Continuous judgment over multiple periods, when α Shadow_t ≥α Shadow_0 At that time, it was determined that the satellite was in the Earth's shadow, and the Earth's shadow marker DYBZ was set to AA;

[0045] Continuous judgment across multiple frames, α Shadow_t <α Shadow_0 At that time, it was determined that the satellite was under illumination, and the ground shadow marker DYBZ was set to 55;

[0046] Where, α Shadow_t α represents the angle subtended by the Sun, Earth, and spacecraft. Shadow_0 This indicates the angle of the Earth's shadow when a spacecraft enters the Earth's shadow region.

[0047] Preferably, the two modules of the spacecraft include a platform module and a payload module; the energy transmission status of the two modules includes a wired disconnect device, a wireless power device, and a reusable device.

[0048] The wired disconnection device is a low-frequency cable wired device responsible for transmitting power between the two compartments. After disconnection, the wired disconnection device is stored between the two compartments, and the internal low-frequency cable cannot be reconnected.

[0049] The wireless power device is an electromagnetic conversion wireless device that transmits energy between the two cabins via electromagnetic induction in space.

[0050] The reusable pluggable device is a reusable low-frequency cable wired device that transmits power between the two compartments, enabling the internal low-frequency cable to be repeatedly switched on and off.

[0051] Preferably, the three power transmission paths between the platform compartment and the payload compartment—the wired disconnection device, the wireless power device, and the reusable pluggable device—are mutually exclusive, with only one of the three paths being powered on at any given time.

[0052] Compared with the prior art, the present invention has the following beneficial effects:

[0053] 1. Based on the entry and exit shadow judgment mark, the present invention switches the energy transmission status of the two modules of the spacecraft through a programmable strategy to ensure the energy safety of the spacecraft in orbit and effectively improve the reliability of the spacecraft in orbit.

[0054] 2. Through the inter-module energy switching strategy of the present invention, the energy of the two-module separated spacecraft can be switched autonomously between wired connection and wireless transmission, avoiding interference caused by energy transmission between the two modules, which is conducive to independent attitude control of the two modules of the spacecraft.

[0055] 3. The method provided by this invention is simple yet efficient and has strong engineering value. Attached Figure Description

[0056] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0057] Figure 1 This is a schematic diagram of the process for determining the ground shadow upon entry and exit and the control flow for switching energy between cabins, as described in this invention.

[0058] Figure 2 This is a schematic diagram of the inter-cabin energy transmission status according to the present invention. Detailed Implementation

[0059] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0060] This invention uses the entry and exit shadow judgment mark to switch the energy transmission status of the two modules of the spacecraft through a programmable strategy.

[0061] Example 1

[0062] According to the present invention, a method for inter-cabin energy switching based on spacecraft entering and exiting Earth's shadow is provided, such as... Figure 1 As shown, it includes:

[0063] Step S1: Obtain the position information of the spacecraft and the sun. This can be achieved through methods including storing and recursively calculating the spacecraft and sun's position information on the spacecraft's onboard computer.

[0064] Step S2: Calculate the spacecraft's shadow angle and the angle formed by the Sun, Earth, and spacecraft based on the location information and Earth's radius. Step S2 includes:

[0065] Step S2.1: When the spacecraft is in orbit, calculate the Earth's shadow angle as it enters the Earth's shadow region, using the following formula:

[0066]

[0067] In the formula, α Shadow_0 R represents the angle of the Earth's shadow as the spacecraft enters the Earth's shadow region. e The radius r of the Earth is represented by the radius r of the Earth. x r y and r z These represent the distances along the x, y, and z axes of the spacecraft, respectively.

[0068] Step S2.2: While the spacecraft is in orbit, calculate the angle subtended by the Sun, Earth, and spacecraft as currently captured in the image. The formula is as follows:

[0069]

[0070] In the formula, α Shadow_t The angle r represents the subtended angle between the Sun, Earth, and the spacecraft. sunix r suniy and r suniz These represent the distances to the sun along the x, y, and z axes, respectively.

[0071] Step S3: Based on the shadow angle and the subtended angle, determine whether the spacecraft is currently in the shadow. If so, based on the shadow entry flag given by the spacecraft's real-time on-orbit calculation, cut off the power transmission status of the two modules of the spacecraft, and disconnect the power transmission path between the two modules. If not, based on the shadow exit flag given by the spacecraft's real-time on-orbit calculation, and according to the identifiers of the three power distribution states before entering the shadow, restore the power transmission path between the two modules of the spacecraft to the state before it was disconnected.

[0072] Specifically, the two modules of a spacecraft include a platform module and a payload module. For example... Figure 2As shown, the energy transmission status between the two modules includes a wired disconnect device, a wireless power supply device, and a reusable device. The wired disconnect device is a low-frequency cable wired device responsible for power transmission between the two modules. After disconnection, the wired disconnect device is stored between the two modules, and the internal low-frequency cable cannot be reconnected. The wireless power supply device is an electromagnetic conversion wireless device that transmits energy between the two modules through electromagnetic induction in space. The reusable device is a reusable low-frequency cable wired device responsible for power transmission between the two modules, allowing the internal low-frequency cable to be repeatedly switched on and off. The connection states of the three energy transmission paths between the platform module and the payload module—the wired disconnect device, the wireless power supply device, and the reusable device—are mutually exclusive; only one of the three paths can be energized at any given time.

[0073] The process of determining whether the spacecraft is currently in the Earth's shadow includes: continuously judging multiple frames, when α Shadow_t ≥α Shadow_0 At that time, the satellite is determined to be in the Earth's shadow, and the shadow marker DYBZ is set to AA. During the shadow period, all three energy transmission paths between spacecraft modules are set to a completely off state, and the battery packs in the platform module and payload module discharge respectively. Continuous judgment is performed over multiple frames, α Shadow_t <α Shadow_0 At that time, the satellite is determined to be under illumination, and the ground shadow marker DYBZ is set to 55. During illumination periods, the spacecraft's payload module PCDU draws power from the platform module busbar through the power transmission path. When the payload module experiences a short-term high-current load, power is supplied jointly by the platform module busbar and the platform module battery, and the payload module battery does not discharge. Among them, α Shadow_t α represents the angle subtended by the Sun, Earth, and spacecraft. Shadow_0 This indicates the angle of the Earth's shadow when a spacecraft enters the Earth's shadow region.

[0074] Furthermore, the invention will be further illustrated by an example of its implementation in orbit:

[0075] When a spacecraft is flying normally in orbit, the computer on the spacecraft uses the stored spacecraft position and sun position information to calculate the spacecraft's shadow angle and the angle formed by the sun, the earth, and the spacecraft every 0.5 seconds according to the programmed control strategy.

[0076] If the angle formed by the Sun, Earth, and spacecraft is greater than the Earth's shadow angle for three consecutive frames, then the spacecraft is in the Earth's shadow. At this time, the spacecraft computer will set the Earth's shadow marker DYBZ to AA, and at the same time, the three energy transmission paths between the spacecraft modules will be set to a completely disconnected state, and the battery packs of the platform module and the payload module will discharge respectively.

[0077] If the angle formed by the Sun, Earth, and spacecraft is less than the Earth's shadow angle for three consecutive frames, then the spacecraft is under illumination. At this time, the spacecraft computer will set the Earth's shadow marker DYBZ to 55, and the three energy transmission paths between the spacecraft modules will be restored to their state before entering the Earth's shadow. At this time, the spacecraft's payload module PCDU will draw power from the platform module bus through the energy transmission path. When the payload module experiences a short-term high current load, it will be powered by the platform module bus and the platform module battery together, and the payload module battery will not discharge.

[0078] The spacecraft's computer program uses the above strategies to determine when the spacecraft enters or leaves the Earth's shadow and to switch the corresponding inter-cabin energy.

[0079] Example 2

[0080] The present invention also provides an inter-cabin energy switching system based on spacecraft entering and exiting Earth's shadow. Those skilled in the art can implement the inter-cabin energy switching system based on spacecraft entering and exiting Earth's shadow by executing the steps of the method. That is, the method based on spacecraft entering and exiting Earth's shadow can be understood as a preferred embodiment of the inter-cabin energy switching system based on spacecraft entering and exiting Earth's shadow.

[0081] An inter-cabin energy switching system based on spacecraft entering and leaving Earth's shadow, provided by the present invention, includes:

[0082] Module M1: Acquires the position information of the spacecraft and the sun.

[0083] Module M2: Calculates the spacecraft's shadow angle and the subtended angle formed by the Sun, Earth, and spacecraft based on the location information and Earth's radius. Module M2 includes:

[0084] Module M2.1: When a spacecraft is in orbit, the Earth's shadow angle is calculated when it enters the Earth's shadow region. The formula is as follows:

[0085]

[0086] In the formula, α Shadow_0 R represents the angle of the Earth's shadow as the spacecraft enters the Earth's shadow region. e The radius r of the Earth is represented by the radius r of the Earth. x r y and r z These represent the distances along the x, y, and z axes of the spacecraft, respectively.

[0087] Module M2.2: Calculates the angle subtended by the Sun, Earth, and spacecraft in a current photograph while the spacecraft is in orbit, using the following formula:

[0088]

[0089] In the formula, α Shadow_tThe angle r represents the subtended angle between the Sun, Earth, and the spacecraft. sunix r suniy and r suniz These represent the distances to the sun along the x, y, and z axes, respectively.

[0090] Module M3: Based on the shadow angle and the subtended angle, determine whether the spacecraft is currently in the shadow. If so, based on the shadow entry flag calculated in real-time on-orbit, cut off the power transmission status of the two modules of the spacecraft, disconnecting the power transmission path between the two modules. If not, trigger module M4. Specifically, determining whether the spacecraft is currently in the shadow includes: continuously judging multiple times, when α... Shadow_t ≥α Shadow_0 When the satellite is in the Earth's shadow, the shadow marker DYBZ is set to AA. This is repeated for multiple shots. Shadow_t <α Shadow_0 At that time, it was determined that the satellite was under illumination, and the ground shadow marker DYBZ was set to 55. Among them, α Shadow_t α represents the angle subtended by the Sun, Earth, and spacecraft. Shadow_0 This indicates the angle of the Earth's shadow when a spacecraft enters the Earth's shadow region.

[0091] Module M4: Based on the Earth's shadow marker calculated in real-time on-orbit by the spacecraft, and according to the identifiers of the three power distribution states before entering the Earth's shadow, restores the energy transmission path between the two modules of the spacecraft to its state before disconnection. The two modules of the spacecraft include the platform module and the payload module. The energy transmission status of the two modules includes a wired disconnection device, a wireless power device, and a reusable device.

[0092] Specifically, the wired disconnect device is a low-frequency cable wired device responsible for power transmission between the two compartments. After disconnection, the wired disconnect device is stored between the two compartments, and the internal low-frequency cable cannot be reconnected. The wireless power device is an electromagnetic conversion wireless device that transmits energy between the two compartments through spatial electromagnetic induction. The reusable device is a reusable low-frequency cable wired device responsible for power transmission between the two compartments, enabling repeated switching of the internal low-frequency cable. The three power transmission paths between the platform compartment and the payload compartment—the wired disconnect device, the wireless power device, and the reusable device—are mutually exclusive; only one of the three paths can be energized at any given time.

[0093] Those skilled in the art will understand that, in addition to implementing the system, apparatus, and their modules provided by this invention in purely computer-readable program code, the same program can be implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system, apparatus, and their modules provided by this invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; alternatively, modules for implementing various functions can be considered both software programs implementing the method and structures within the hardware component.

[0094] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for inter-cabin energy switching based on spacecraft entering and leaving Earth's shadow, characterized in that, include: Step S1: Obtain the position information of the spacecraft and the sun; Step S2: Calculate the spacecraft's shadow angle and the angle formed by the Sun, Earth, and spacecraft based on the location information and Earth's radius; Step S3: Based on the shadow angle and the subtended angle, determine whether the spacecraft is currently in the shadow. If so, based on the shadow entry flag given by the spacecraft's real-time on-orbit calculation, cut off the power transmission status of the two modules of the spacecraft and disconnect the power transmission path between the two modules. If not, trigger step S4. Step S4: Based on the Earth Shadow exit marker given by the spacecraft's real-time on-orbit calculation, and according to the identifiers of the three power distribution states before entering the Earth Shadow, restore the energy transmission path between the two modules of the spacecraft to the state before it was disconnected.

2. The inter-cabin energy switching method based on spacecraft entering and leaving Earth's shadow as described in claim 1, characterized in that, Step S2 includes: Step S2.1: When the spacecraft is in orbit, calculate the Earth's shadow angle as it enters the Earth's shadow region, using the following formula: In the formula, α Shadow_0 R represents the angle of the Earth's shadow as the spacecraft enters the Earth's shadow region. e The radius of the Earth, r x r y and r z These represent the distances along the x, y, and z axes of the spacecraft, respectively. Step S2.2: While the spacecraft is in orbit, calculate the angle subtended by the Sun, Earth, and spacecraft as currently captured in the image. The formula is as follows: In the formula, α Shadow_t The angle r represents the subtended angle between the Sun, Earth, and the spacecraft. sunix r suniy and r suniz These represent the distances to the sun along the x, y, and z axes, respectively.

3. The inter-cabin energy switching method based on spacecraft entering and leaving Earth's shadow as described in claim 1, characterized in that, The determination of whether the current spacecraft is in the Earth's shadow includes: Continuous judgment over multiple periods, when α Shadow_t ≥α Shadow_0 At that time, it was determined that the satellite was in the Earth's shadow, and the Earth's shadow marker DYBZ was set to AA; Continuous judgment across multiple frames, α Shadow_t <α Shadow_0 At that time, it was determined that the satellite was under illumination, and the ground shadow marker DYBZ was set to 55; Where, α Shadow_t α represents the angle subtended by the Sun, Earth, and spacecraft. Shadow_0 This indicates the angle of the Earth's shadow when a spacecraft enters the Earth's shadow region.

4. The inter-cabin energy switching method based on spacecraft entering and leaving Earth's shadow as described in claim 1, characterized in that, The spacecraft has two modules, including a platform module and a payload module; the energy transmission status of the two modules includes a wired disconnect device, a wireless power device, and a re-pluggable device. The wired disconnection device is a low-frequency cable wired device responsible for transmitting power between the two compartments. After disconnection, the wired disconnection device is stored between the two compartments, and the internal low-frequency cable cannot be reconnected. The wireless power device is an electromagnetic conversion wireless device that transmits energy between the two cabins via electromagnetic induction in space. The reusable pluggable device is a reusable low-frequency cable wired device that transmits power between the two compartments, enabling the internal low-frequency cable to be repeatedly switched on and off.

5. The inter-cabin energy switching method based on spacecraft entering and leaving Earth's shadow as described in claim 4, characterized in that, The three power transmission paths between the platform compartment and the payload compartment—the wired disconnection device, the wireless power device, and the reusable plug-in device—are mutually exclusive, with only one of the three paths being powered at any given time.

6. A cabin energy switching system based on spacecraft entering and exiting Earth's shadow, characterized in that, include: Module M1: Acquires the position information of the spacecraft and the sun; Module M2: Calculates the spacecraft's shadow angle and the angle formed by the Sun, Earth, and spacecraft based on the location information and Earth's radius; Module M3: Based on the shadow angle and the subtended angle, determine whether the spacecraft is currently in the shadow. If so, based on the shadow entry flag given by the spacecraft in real time calculation on orbit, cut off the power transmission status of the two modules of the spacecraft and disconnect the power transmission path between the two modules. If not, trigger module M4. Module M4: Based on the Earth Shadow exit marker given by the spacecraft in real time calculation on orbit, and according to the identifiers of the three power distribution states before entering the Earth Shadow, restores the energy transmission path between the two modules of the spacecraft to the state before it was disconnected.

7. The inter-cabin energy switching system based on spacecraft entry / exit from Earth's shadow as described in claim 6, characterized in that, Module M2 includes: Module M2.1: When a spacecraft is in orbit, the Earth's shadow angle is calculated when it enters the Earth's shadow region. The formula is as follows: In the formula, α Shadow_0 R represents the angle of the Earth's shadow as the spacecraft enters the Earth's shadow region. e The radius of the Earth, r x r y and r z These represent the distances along the x, y, and z axes of the spacecraft, respectively. Module M2.2: Calculate the angle subtended by the Sun, Earth, and spacecraft in a current photograph while the spacecraft is in orbit. The formula is as follows: In the formula, α Shadow_t The angle r represents the subtended angle between the Sun, Earth, and the spacecraft. sunix r suniy and r suniz These represent the distances to the sun along the x, y, and z axes, respectively.

8. The inter-cabin energy switching system based on spacecraft entry / exit from Earth's shadow as described in claim 6, characterized in that, The determination of whether the current spacecraft is in the Earth's shadow includes: Continuous judgment over multiple periods, when α Shadow_t ≥α Shadow_0 At that time, it was determined that the satellite was in the Earth's shadow, and the Earth's shadow marker DYBZ was set to AA; Continuous judgment across multiple frames, α Shadow_t <α Shadow_0 At that time, it was determined that the satellite was under illumination, and the ground shadow marker DYBZ was set to 55; Where, α Shadow_t α represents the angle subtended by the Sun, Earth, and spacecraft. Shadow_0 This indicates the angle of the Earth's shadow when a spacecraft enters the Earth's shadow region.

9. The inter-cabin energy switching system based on spacecraft entry / exit from Earth's shadow as described in claim 6, characterized in that, The spacecraft has two modules, including a platform module and a payload module; the energy transmission status of the two modules includes a wired disconnect device, a wireless power device, and a re-pluggable device. The wired disconnection device is a low-frequency cable wired device responsible for transmitting power between the two compartments. After disconnection, the wired disconnection device is stored between the two compartments, and the internal low-frequency cable cannot be reconnected. The wireless power device is an electromagnetic conversion wireless device that transmits energy between the two cabins via electromagnetic induction in space. The reusable pluggable device is a reusable low-frequency cable wired device that transmits power between the two compartments, enabling the internal low-frequency cable to be repeatedly switched on and off.

10. The inter-cabin energy switching system based on spacecraft entry / exit from Earth's shadow as described in claim 9, characterized in that, The three power transmission paths between the platform compartment and the payload compartment—the wired disconnection device, the wireless power device, and the reusable plug-in device—are mutually exclusive, with only one of the three paths being powered at any given time.

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