Satellite detonating device unlocking circuit and spacecraft

Abstract

The utility model discloses a satellite initiation device unlocking circuit and a spacecraft. The unlocking circuit comprises a storage battery pack; the positive line switching circuit is connected with the positive end of the storage battery pack; one end of the detonating switch circuit is connected with the main line switch circuit, and the other end of the detonating switch circuit is connected with M satellite detonating assemblies arranged in parallel; wherein M is an integer, and M is greater than or equal to 1; the satellite detonating assembly comprises N detonating switch units which are arranged in series, and each detonating switch unit is connected with a satellite detonating device; wherein N is an integer, and N is greater than or equal to 1. According to the satellite detonating device, the plurality of detonating switch units are connected in series, so that the resistance value of the unlocking circuit is increased, the detonating time can be better controlled, and the safety and the reliability of the satellite detonating device are improved.

Description

Technical Field

[0001] This utility model relates to the field of spacecraft control system technology, and in particular to a satellite detonation device unlocking circuit and spacecraft. Background Technology

[0002] During missions, spacecraft's auxiliary equipment (such as solar panels, antennas, or instrument payloads) typically needs to be unlocked and deployed in orbit to perform functions such as power generation, communication, or scientific observation. During launch, these auxiliary devices must be locked to ensure they can withstand high-intensity vibrations, shocks, and other external factors. To ensure reliable unlocking of the locking mechanism and deployment of the equipment, unlocking circuits are usually designed to drive the actuators to complete the unlocking action.

[0003] In existing technologies, unlocking devices mostly employ heat-driven methods. Shape memory alloys (MMAs) are widely used in unlocking circuits due to their excellent deformation capabilities and high reliability. When an EMAs are applied, they deform through resistance heating, driving the unlocking mechanism to release the locking device. However, the performance of MMAs is easily affected by ambient temperature. For example, at low temperatures, the heating efficiency of MMAs decreases, and the unlocking time increases; while at high temperatures, the unlocking time may be shortened. Ensuring the stable and reliable operation of unlocking circuits in the complex space environment is a key technical challenge in current spacecraft design.

[0004] Due to the significant temperature difference between the ambient temperature and the outer space environment, the unlocking circuit needs to be adapted to various test conditions to verify its reliability during on-orbit operation. However, how to accurately control the energizing time of the shape memory alloy during ground testing, so as to meet the unlocking time requirements while avoiding overheating damage, is a problem that urgently needs to be solved by those skilled in the art. Utility Model Content

[0005] The purpose of this application is to provide a satellite detonation device unlocking circuit and spacecraft, which can solve the problems of the existing spacecraft unlocking circuits during ground testing and on-orbit operation, such as the difficulty in accurately controlling the unlocking time, the instability of shape memory alloy performance due to the influence of ambient temperature, and the lack of protection mechanisms.

[0006] To achieve the above objectives:

[0007] In a first aspect, embodiments of this application provide an unlocking circuit for a satellite detonation device, comprising:

[0008] Battery pack;

[0009] A positive line switch circuit is connected to the positive terminal of the battery pack.

[0010] The detonation switch circuit has one end connected to the positive line switch circuit and the other end connected to M satellite detonation assemblies arranged in parallel; where M is an integer and M≥1.

[0011] The satellite detonation assembly includes N detonation switch units connected in series, each of which is connected to a satellite detonation device; where N is an integer and N≥1.

[0012] Furthermore, the unlocking circuit also includes:

[0013] A resistance control module, wherein the resistance module is connected in series with the detonation switch circuit or the satellite detonation assembly;

[0014] The resistance control module includes variable resistors and / or fixed resistors.

[0015] Furthermore, the unlocking circuit also includes,

[0016] Each detonation switch unit is made of shape memory alloy material, and the detonation switch unit unlocks the satellite detonation device by thermal deformation.

[0017] Furthermore, the unlocking circuit includes,

[0018] A temperature detection unit is used to detect the temperature of the environment in which the satellite detonation assembly is located.

[0019] Furthermore, the unlocking circuit also includes,

[0020] A current detection unit, connected to the satellite detonation assembly, is used to detect the current magnitude of the unlocking circuit in real time.

[0021] Furthermore, the unlocking circuit also includes,

[0022] A control module is provided to control the power supply module's connection and disconnection of the unlocking circuit.

[0023] Secondly, embodiments of this application provide a spacecraft that utilizes the unlocking circuit of the aforementioned satellite detonation device. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the unlocking circuit for the satellite detonation device provided in an embodiment of the present invention;

[0025] Figure 2 This is an electrical schematic diagram of the electric lock circuit of the satellite detonation device provided in an embodiment of the present invention;

[0026] Figure 3 A flowchart of a satellite detonation device unlocking method provided in an embodiment of the present invention;

[0027] Figure 4 A detailed flowchart of the satellite detonation device unlocking method provided in this embodiment of the invention.

[0028] In the picture:

[0029] 1. Battery pack; 2. Positive line switch circuit; 3. Detonation switch circuit; 31. Detonation switch unit; 4. Resistance control module; 5. Temperature detection unit; 6. Current detection unit. Detailed Implementation

[0030] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.

[0031] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element. Furthermore, components, features, and elements with the same names in different embodiments of this application may have the same meaning or different meanings, the specific meaning of which must be determined by its interpretation in that specific embodiment or further in conjunction with the context of that specific embodiment.

[0032] It should be understood that although the terms first, second, third, etc., may be used herein to describe various information, such information should not be limited to these terms. These terms are used only to distinguish information of the same type from one another. For example, without departing from the scope of this document, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Depending on the context, the word "if," as used herein, can be interpreted as "when," "when," or "in response to determination." Furthermore, as used herein, the singular forms "a," "an," and "the" are intended to also include the plural forms unless the context indicates otherwise. It should be further understood that the terms "comprising," "including," indicate the presence of the stated feature, step, operation, element, component, item, kind, and / or group, but do not exclude the presence, occurrence, or addition of one or more other features, steps, operations, elements, components, items, kinds, and / or groups. The terms "or" and "and / or" as used herein are to be interpreted as inclusive, or mean any one or any combination thereof. Therefore, "A, B, or C" or "A, B, and / or C" means "any one of the following: A; B; C; A and B; A and C; B and C; A, B, and C". Exceptions to this definition will only occur if the combination of elements, functions, steps, or operations is inherently mutually exclusive in some way.

[0033] It should be understood that although the steps in the flowcharts of this application's embodiments are shown sequentially according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some of the steps in the figures may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily completed at the same time, but can be executed at different times, and their execution order is not necessarily sequential, but can be performed alternately or in turn with other steps or at least a portion of the sub-steps or stages of other steps.

[0034] It should be noted that step designations such as S101 and S102 are used in this document for the purpose of more clearly and concisely describing the corresponding content, and do not constitute a substantial limitation on the order. In specific implementation, those skilled in the art may execute S102 first and then S101, etc., but these should all be within the protection scope of this application.

[0035] It should be understood that the specific embodiments described herein are merely illustrative of this application and are not intended to limit this application.

[0036] In the following description, the use of suffixes such as "module," "part," or "unit" to denote elements is solely for the purpose of illustrative purposes and has no specific meaning in itself. Therefore, "module," "part," or "unit" may be used interchangeably.

[0037] See Figure 1 and Figure 2 This application provides an unlocking circuit for a satellite detonation device, comprising a battery pack 1, a positive line switch circuit 2, a detonation switch circuit 3, and several satellite detonation components. The battery pack 1 provides power to the unlocking circuit, and the positive line switch circuit 2 controls the on / off state of the unlocking circuit. One end of the detonation switch circuit 3 is connected to the positive line switch circuit 2, and the other end is connected to multiple satellite detonation components connected in parallel.

[0038] Specifically, each satellite detonation assembly includes multiple detonation switch units 31 connected in series, with each detonation switch unit 31 connected to a satellite detonation device. This series design increases the total resistance of the circuit, thereby reducing the total current flowing through the circuit and extending the heating time. This meets the precise control requirements for the heating time during ground testing and prevents the detonation switch unit 31 from overheating and burning out due to excessive heating time.

[0039] During operation, when the main line switch circuit 2 is closed, the battery pack 1 supplies power to each satellite detonation assembly through the detonation switch circuit 3. The detonation current passes sequentially through the series-connected detonation switch unit 31 in each satellite detonation assembly, providing energizing heating energy to the connected satellite detonation device, triggering the detonation device to complete the unlocking operation. The series-connected detonation switch unit 31 design ensures the stability of the circuit current and the controllability of the energizing time, thereby guaranteeing the safety and reliability of the unlocking operation.

[0040] In this embodiment, the detonation switch unit 31 is designed in series, which not only extends the heating time to meet the precise control requirements of the heating process during ground testing, but also avoids the problem of overheating and burning of the detonation switch unit 31 due to excessive power-on time. It is suitable for satellite ground testing and orbit unlocking operation scenarios.

[0041] Furthermore, the unlocking circuit of the satellite detonation device includes a resistance control module 4, which is connected in series with the detonation switch circuit 3 or the satellite detonation assembly to adjust the total resistance value of the unlocking circuit, thereby controlling the energizing current and heating time.

[0042] Specifically, the resistor control module 4 consists of at least one fixed resistor and / or an adjustable resistor. The fixed resistor provides the basic resistance value of the circuit to ensure the stability of the circuit operation; the adjustable resistor is used to flexibly adjust the resistance value according to actual working requirements to adapt to different environmental conditions or testing needs.

[0043] During ground testing, the power-on time of the unlocking circuit can be controlled by adjusting the value of the adjustable resistor according to different ambient temperatures.

[0044] In low-temperature environments, shape memory alloys heat up slowly, requiring a longer heating time for unlocking. To ensure that the unlocking operation can be completed within a reasonable time, the resistance of the resistance control module 4 can be reduced to increase the current, thereby accelerating the heating process of the shape memory alloy and ensuring that the detonation device can complete the unlocking operation within a reasonable time.

[0045] In high-temperature environments, shape memory alloys heat up quickly and require shorter heating times. To prevent the shape memory alloy from burning out due to excessive power-on time, the resistance value of the resistance control module 4 can be increased to reduce the current and thus extend the power-on time.

[0046] The resistance control module 4 is connected in series in the unlocking circuit to adjust the total resistance of the circuit. When the circuit is energized, the resistance control module 4 operates in series with the detonation switch circuit 3, and its resistance directly affects the total resistance of the circuit, thereby adjusting the current flowing through the circuit. After the satellite detonation assembly receives a suitable energizing current, it heats the shape memory alloy in the unlocking device to complete the unlocking operation.

[0047] Through the resistor control module 4 in this embodiment, the unlocking circuit can adapt to the power-on requirements under different environmental conditions, achieve precise control of the power-on time, ensure the safety and reliability of the unlocking operation, and effectively avoid damage to the detonation device due to overcurrent or overheating.

[0048] Furthermore, in the satellite detonation device unlocking circuit, each detonation switch unit 31 is made of shape memory alloy material. Shape memory alloy has good thermal response characteristics; when heated, it can undergo shape memory effect, thereby achieving deformation to complete the unlocking operation.

[0049] Specifically, in this embodiment, the detonation switch unit 31 employs a shape memory alloy puller. This puller is a highly reliable mechanical structure that uses the shape recovery force generated by the shape memory alloy material after being heated to drive the clamping release device to complete the unlocking process. The detonation switch unit 31 is connected to the satellite detonation device; this design meets the requirements for satellite solar panel deployment.

[0050] During operation, when the unlocking circuit is energized, the detonation current flows through the series-connected detonation switch units 31, providing heating energy to each unit. The shape memory alloy material rapidly heats up and deforms according to its shape memory properties, triggering the pin puller to release the clamping device and unlock the detonation device. The shape memory alloy of the detonation switch unit 31 is controlled by resistance during heating, ensuring precise control of the heating time. This ensures smooth unlocking while preventing material damage due to overheating.

[0051] By employing shape memory alloy as the core component of the detonation switch unit 31, the detonation device unlocking circuit in this embodiment can achieve deformation action after heating, thus reliably unlocking the satellite detonation device. The application of shape memory alloy not only improves the reliability of the unlocking device but also allows for precise adjustment of the energizing time through the resistance control module 4, meeting the requirements of satellite ground testing and orbit insertion operations, thereby achieving a safe and reliable unlocking operation.

[0052] Furthermore, the satellite detonation device unlocking circuit includes a temperature detection unit 5, which is used to detect the temperature of the environment in which the satellite detonation component is located, so as to realize temperature monitoring and adjustment during the unlocking process.

[0053] Specifically, the temperature detection unit 5 is located near the satellite detonation assembly or within the unlocking circuit to acquire ambient temperature information in real time. The temperature detection unit 5 can employ a high-precision temperature sensor, such as a thermistor, thermocouple, or semiconductor temperature sensor. The detected temperature information is transmitted to an external control unit or microcontroller to dynamically adjust the energizing time and current of the unlocking circuit according to the current ambient temperature, thereby ensuring the safety and reliability of the unlocking operation.

[0054] In low-temperature environments, the heating efficiency of the shape memory alloy pin puller is low. The temperature detection unit 5 can detect the current ambient temperature and appropriately extend the power-on time or increase the current through the control unit to ensure that the shape memory alloy can reach the heating temperature required for unlocking, thereby completing the unlocking action.

[0055] In high-temperature environments, the shape memory alloy pin puller heats up quickly. The temperature detection unit 5 can detect when the ambient temperature is high and promptly shorten the power-on time or reduce the current to prevent the shape memory alloy from being damaged due to overheating and ensure the safety of the detonation device.

[0056] Furthermore, the satellite detonation device unlocking circuit includes a current detection unit 6, which is connected to the satellite detonation assembly and is used to monitor the operating current of the unlocking circuit in real time to ensure the safety and controllability of the unlocking operation process.

[0057] Specifically, the current detection unit 6 is installed in the power supply circuit of the satellite detonation assembly. It can detect the current magnitude in real time through a Hall current sensor, shunt resistor, or other current measuring device. The current detection unit 6 can transmit the detected current value to an external control unit or microcontroller. By monitoring the actual current, the control unit can dynamically adjust the operating parameters of the unlocking circuit to ensure that the current operates within a safe range.

[0058] Furthermore, the satellite detonation device unlocking circuit includes a control module, which controls the power supply module to switch the unlocking circuit on and off, thereby achieving precise control of the unlocking process.

[0059] The control module is connected to the power supply module and is used to receive real-time monitoring data from the temperature detection unit 5 and the current detection unit 6, and adjust the power supply status of the power supply module to the unlocking circuit according to the monitoring results. The control module ensures that the operating current and energizing time of the unlocking circuit meet the requirements of the unlocking operation by closing or opening the power supply path of the power supply module.

[0060] Furthermore, one end of the detonation switch circuit 3 is connected to the mains switch circuit 2, and the other end is connected to two satellite detonation assemblies connected in parallel. The mains switch circuit 2 controls the switching of the power supply to ensure that current can be supplied to the detonation circuit. Each satellite detonation assembly includes three detonation switch units 31 connected in series. Each series-connected detonation switch unit 31 is connected to one of the three ends of the satellite solar panel. Through parallel connection, the two detonation assemblies work together to control the unlocking of the locking devices at the three ends of the satellite solar panel, thereby ensuring the smooth deployment of the satellite solar panel.

[0061] Each satellite detonation assembly includes three detonation switch units 31 connected in series. Each detonation switch unit 31 is made of shape memory alloy. When current flows through it, the shape memory alloy deforms due to heat, thereby driving a mechanical device to unlock the satellite detonation device. Each series-connected detonation switch unit 31 is connected to one of the three ends of the satellite solar panel. When current flows through the detonation switch unit 31, the unlocking action is performed simultaneously, ensuring that each end of the solar panel can be successfully unlocked.

[0062] Based on the same inventive concept as the foregoing embodiments, the foregoing embodiments will be described in detail below through a specific application scenario:

[0063] To verify the performance of shape memory alloys under real-world conditions, a ground-based deployment experiment was conducted. The specific conditions and data are as follows:

[0064] Temperature conditions: Ground experiments were conducted at room temperature of 25℃.

[0065] According to experimental results, the energy required for shape memory alloys to complete their unfolding at room temperature is approximately 15 J.

[0066] The total resistance of each detonation assembly is 3.1Ω (including 0.7Ω × 3 shape memory alloy resistors and 1Ω circuit resistance). According to Ohm's law, the current is:

[0067]

[0068] According to the energy formula:

[0069] Under a power supply current of 3.87A, the deployment time is 1.2 seconds.

[0070] on the contrary:

[0071] If the three shape memory alloy elements (each with a resistance of R=0.7Ω) are connected in parallel, the power supply voltage will still be 12V.

[0072] The formula for parallel resistors is:

[0073]

[0074] The current at this time is:

[0075]

[0076] According to the energy formula:

[0077] Under a power supply current of 17.2A, the deployment time is 0.073 seconds.

[0078] In the parallel configuration, the energizing time of each shape memory alloy element is only 0.073 seconds. Although the unlocking time is extremely short, the current of a single element is as high as 17.2A, which places stringent requirements on the power supply design and can easily lead to power supply overload or decreased circuit stability. In addition, the short energizing time is difficult to control precisely, increasing the risk of unlocking failure, especially making it difficult to guarantee stability in ground testing.

[0079] In contrast, the series structure has an unlocking time of 1.2 seconds and a moderate current (3.87A), which not only reduces the load on the power supply but also facilitates precise control of the power-on time, ensuring the stability and reliability of the unlocking process, making it suitable for ground testing environments.

[0080] Based on the same inventive concept as the foregoing embodiments, this utility model embodiment provides an unlocking method for the unlocking circuit of the detonation device, which mainly includes two parts: a ground testing phase and an on-orbit operation phase, to ensure that the satellite detonation component can be stably unlocked under different temperature environments.

[0081] See Figure 3The unlocking method for the detonation device unlocking circuit includes:

[0082] Step S101: Obtain the unlocking time of the satellite detonation component under different ambient temperatures and different currents, and generate a temperature-current-time comparison table.

[0083] During the ground testing phase, various temperature conditions (such as -30℃, 0℃, 25℃, and 65℃) were simulated using laboratory equipment, combined with different supply currents (such as 2A, 3A, and 5A), to measure the time required for the shape memory alloy to complete the unlocking action under different conditions. For example, when the supply current was 3A and the temperature was -30℃, the unlocking time was 1.8 seconds; when the supply current was 5A and the temperature was 25℃, the unlocking time was shortened to 0.68 seconds. Based on these experimental results, a temperature-current-time comparison table was compiled to provide data support for subsequent timing adjustments of the unlocking circuit.

[0084] Step S102: Adjust the power-on time of the unlocking circuit according to the temperature-current-time reference table.

[0085] During operation, the ambient temperature is monitored in real time by a temperature sensor, and the corresponding unlocking time is determined by referring to a lookup table. For example, when the temperature sensor detects an ambient temperature of 10℃, the lookup table indicates a recommended power-on time of 1.2 seconds. The unlocking circuit control module sets the power-on time based on this data and executes the unlocking operation. If the power-on time exceeds twice the theoretical value but the unlocking operation is not completed, the system will trigger an alarm and cut off power supply to prevent the shape memory alloy from being damaged by overheating.

[0086] Furthermore,

[0087] Step S201: Obtain the unlocking time of the satellite detonation assembly under different ambient temperatures and different currents.

[0088] Step S202: Generate a temperature-current-time comparison table based on the unlocking time.

[0089] Based on the experimental results, the generated comparison table will serve as the basis for subsequent adjustment of the unlocking circuit time.

[0090] Step S203: During the ground testing phase, obtain the temperature value of the environment where the satellite detonation components are located.

[0091] During the ground testing phase, the ambient temperature of the satellite's detonation components was monitored in real time using temperature sensors. For example, the ambient temperature was monitored to be 15°C during the experiment.

[0092] Step S204: Adjust the resistance value of the resistance control module according to the ambient temperature value to adjust the current magnitude.

[0093] Based on the temperature value obtained in step S203, the resistance value of the unlocking circuit is dynamically adjusted using the resistance control module, thereby adjusting the power supply current. For example, when the ambient temperature is 15℃, the resistance control module adjusts the circuit resistance to adjust the power supply current to 3.87A to meet the unlocking requirements.

[0094] Step S205: Generate the preset time for the unlocking circuit by referring to the temperature-current-time reference table based on the temperature value and current magnitude.

[0095] Using the temperature-current-time lookup table generated in step S202, match the current temperature value (e.g., 15℃) and power supply current (e.g., 3.87A) to determine the preset time required for unlocking. For example, the lookup table shows that the preset time under the current conditions is 1.2 seconds.

[0096] Step S206: During the on-orbit operation phase, obtain the preset time according to the temperature-current-time reference table, and extend the preset time to the actual time.

[0097] During the on-orbit operation phase, the corresponding preset time is determined by real-time temperature monitoring (e.g., -100℃) and a temperature-current-time lookup table. This preset time is then appropriately extended to the actual time to adapt to the low-temperature environment of outer space. For example, under extremely low temperature conditions, the lookup table shows a preset time of 2 seconds, with an extension factor of 2, and the actual power-on time is adjusted to 4 seconds to ensure the successful completion of the unlocking action.

[0098] Through the above steps, this invention achieves the reliability and adaptability of the unlocking circuit in both ground testing and on-orbit operation. During ground testing, unlocking performance is verified by dynamically adjusting the current and unlocking time; during on-orbit operation, a strategy of extending the power-on time is used to adapt to the extreme low-temperature environment of outer space, ensuring the safety and stability of the unlocking action.

[0099] Furthermore, the detonation device unlocking circuit includes an alarm device.

[0100] When the power-on time during ground testing exceeds twice the theoretical value (e.g., if the theoretical time is 1.5 seconds, exceeding 3 seconds will trigger an alarm), the alarm device will issue an audible and visual warning, and the system will automatically cut off power to protect the shape memory alloy. After the alarm is triggered, the test personnel must check the power supply status, temperature conditions, and the operation of the unlocking device, and eliminate any possible abnormalities before restarting the test.

[0101] In addition, during the testing process, key data such as ambient temperature, power supply current, and power-on time were recorded for each test, and a temperature-current-time comparison table was generated. This comparison table not only provides data support for ground testing but also provides a reliable reference for adjusting the unlocking time during on-orbit operation.

[0102] This embodiment, by adding an alarm device and an automatic power-off mechanism, not only ensures the safety of the unlocking circuit during ground testing, but also effectively avoids the problem of shape memory alloy damage caused by prolonged power supply.

[0103] Based on the same inventive concept as the foregoing embodiments, this utility model embodiment provides a spacecraft for performing unlocking operations on key spacecraft equipment, such as solar panel deployment and antenna release. The unlocking circuit achieves reliable unlocking of the spacecraft equipment locking devices through the coordinated operation of two parallel detonation components.

[0104] The spacecraft's unlocking circuit comprises two parallel satellite detonation assemblies. Each assembly consists of three series-connected detonation switch units 31, with shape memory alloy material serving as the core driving element. When energized, the shape memory alloy material deforms upon heating, driving the mechanical structure to complete the unlocking action. The two parallel detonation assemblies do not operate independently but work together to complete the unlocking operation. Each assembly acts on a different end of the solar panel locking device; the synchronized operation of the two assemblies ensures that the solar panel locking device unlocks in a coordinated manner, thereby enabling the normal deployment of the equipment.

[0105] During ground testing, to verify the reliability and performance of the unlocking circuit, the resistance value of the unlocking circuit was dynamically adjusted via resistor control module 4 to ensure that the unlocking time was controlled within a set range (e.g., 1-3 seconds). Simultaneously, the unlocking circuit includes an alarm device; if the power-on time exceeds twice the theoretical value without completing the unlocking operation, the system will trigger an alarm and automatically cut off power to protect the shape memory alloy material from overheating damage. This design effectively ensures the safety of ground testing and provides reliable data reference for the on-orbit operation phase.

[0106] After the spacecraft enters orbit, the unlocking circuit monitors the external ambient temperature in real time using a temperature sensor and dynamically adjusts the unlocking time to adapt to actual environmental conditions, based on a temperature-current-time reference table generated from ground tests. Two parallel detonation components work together to ensure that both ends of the solar panel locking device unlock synchronously, thus guaranteeing the smooth deployment of the solar panel.

[0107] By integrating this unlocking circuit into the spacecraft, the stability and reliability of the device's unlocking operation are ensured in complex environments. Especially in mission-critical scenarios, such as solar panel deployment, antenna release, or payload unlocking, this unlocking circuit design enables efficient and safe unlocking operations, ensuring the spacecraft operates normally and completes its intended mission.

[0108] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0109] In this document, the terms “comprising,” “including,” or any other variations thereof are intended to cover non-exclusive inclusion, which includes not only the elements listed but also other elements not expressly listed.

[0110] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.

Claims

1. A satellite detonation device unlocking circuit, characterized in that, include: Battery pack; A positive line switch circuit is connected to the positive terminal of the battery pack. The detonation switch circuit has one end connected to the positive line switch circuit and the other end connected to M satellite detonation assemblies arranged in parallel; where M is an integer and M≥1. The satellite detonation assembly includes N detonation switch units arranged in series, and each detonation switch unit is connected to a satellite detonation device. Where N is an integer, and N≥1.

2. The satellite detonation device unlocking circuit according to claim 1, characterized in that, The unlocking circuit also includes: A resistance control module, wherein the resistance module is connected in series with the detonation switch circuit or the satellite detonation assembly; The resistance control module includes variable resistors and / or fixed resistors.

3. The satellite detonation device unlocking circuit according to claim 1, characterized in that, The unlocking circuit also includes, Each detonation switch unit is made of shape memory alloy material, and the detonation switch unit unlocks the satellite detonation device by thermal deformation.

4. The satellite detonation device unlocking circuit according to any one of claims 1-3, characterized in that, The unlocking circuit includes, A temperature detection unit is used to detect the temperature of the environment in which the satellite detonation assembly is located.

5. The satellite detonation device unlocking circuit according to claim 4, characterized in that, The unlocking circuit also includes, A current detection unit, connected to the satellite detonation assembly, is used to detect the current magnitude of the unlocking circuit in real time.

6. The satellite detonation device unlocking circuit according to claim 5, characterized in that, The unlocking circuit also includes, A control module is provided to control the power supply module's connection and disconnection of the unlocking circuit.

7. The satellite detonation device unlocking circuit according to claim 1, characterized in that, One end of the detonation switch circuit is connected to the positive line switch circuit, and the other end is connected to two satellite detonation components arranged in parallel. The satellite detonation assembly includes three detonation switch units arranged in series, each of which is connected to a satellite detonation device.

8. A spacecraft, characterized in that, Includes the satellite detonation device unlocking circuit as described in any one of claims 1-7.

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