Satellite detonating device unlocking circuit and spacecraft

Abstract

The invention discloses an unlocking circuit and method for a satellite initiation device 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] The present invention relates to the technical field of spacecraft control systems, and in particular to an unlocking circuit of a satellite detonator and a spacecraft. Background Art

[0002] When a spacecraft is performing a mission, its ancillary equipment (such as solar panels, antennas or instrument payloads) usually needs to be unlocked and deployed during orbital operation to complete functions such as power generation, communication or scientific observation. During the launch phase, these ancillary equipment must be in a locked state to ensure that they can withstand high-intensity vibration, impact and other external factors during the launch process. In order to achieve reliable unlocking of the locking device and equipment deployment, an unlocking circuit is usually designed to drive the actuator to complete the unlocking action.

[0003] In the prior art, the unlocking device is mostly driven by a heat source, among which memory alloys are widely used in unlocking circuits due to their excellent deformation ability and high reliability. After power is turned on, the memory alloy deforms through resistance heating, driving the unlocking mechanism to release the locking device. However, the performance of the memory alloy is easily affected by the external ambient temperature. For example, under low temperature conditions, the heating efficiency of the memory alloy decreases and the unlocking time is prolonged; under high temperature conditions, the unlocking time may be shortened. How to ensure that the unlocking circuit works stably and reliably in a complex space environment is a key technical problem in current spacecraft design.

[0004] Due to the large difference between the ambient temperature and the outer space environment, the unlocking circuit needs to adapt to a variety of test conditions to verify its reliability in orbit. However, how to accurately control the power-on time of the memory alloy in ground testing so that it can meet the unlocking time requirements and avoid overheating damage is an urgent problem to be solved by technicians in this field. Summary of the invention

[0005] The purpose of the present application is to provide a satellite detonation device unlocking circuit, method and spacecraft, which can solve the problems existing in the prior art of the spacecraft unlocking circuit during ground testing and on-orbit operation, such as the difficulty in accurately controlling the unlocking time, the unstable performance of the memory alloy affected by the ambient temperature, and the lack of a protection mechanism.

[0006] To achieve the above objectives: In a first aspect, an embodiment of the present application provides an unlocking circuit of a satellite detonator, comprising: Battery pack; A positive line switch circuit connected to the positive terminal of the battery pack; A detonation switch circuit, one end of which is connected to the positive line switch circuit, and the other end of which is connected to M satellite detonation assemblies arranged in parallel; wherein M is an integer, and M≥1; The satellite detonation assembly includes N detonation switch units arranged in series, and each of the detonation switch units is connected to a satellite detonation device; wherein N is an integer, and N≥1.

[0007] Furthermore, the unlocking circuit further 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 a variable resistor and / or a fixed resistor.

[0008] Furthermore, the unlocking circuit further includes: Each detonating switch unit is made of a memory alloy material, and the detonating unit switch is deformed by heat to unlock the satellite detonating device.

[0009] Furthermore, the unlocking component includes: A temperature detection unit is used to detect the temperature of the environment of the satellite detonation assembly.

[0010] Furthermore, the unlocking component also includes: A current detection unit is connected to the satellite detonation component and is used to detect the current size of the unlocking component in real time.

[0011] Furthermore, the unlocking component also includes: A control module, wherein the control module is used to control the power module to turn on and off the unlocking component.

[0012] In a second aspect, an embodiment of the present application provides a method for unlocking the unlocking circuit of the detonating device, comprising: Obtaining the unlocking time of the satellite detonation component when it is powered on and heated at different ambient temperatures and different currents, and generating a temperature-current-time comparison table; The power-on time of the unlocking circuit is adjusted according to the temperature-current-time comparison table.

[0013] Further, the unlocking circuit includes a resistance control module; Obtaining the unlocking time of the satellite detonation component when it is powered on and heated at different ambient temperatures and different currents; Generate a temperature-current-time comparison table based on the unlocking time; During the ground test phase, the temperature value of the environment in which the satellite detonation assembly is located is obtained; Adjusting the resistance value of the resistance control module according to the temperature value of the environment to adjust the current; Generate a preset time for unlocking the circuit according to the temperature value and the current size by comparing the temperature-current-time comparison table; During the on-orbit operation phase, the preset time is obtained according to the temperature-current-time comparison table, and the preset time is extended to the actual time.

[0014] In a third aspect, an embodiment of the present application provides a spacecraft, which uses the unlocking circuit of the above-mentioned satellite detonator. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 A schematic diagram of an unlocking circuit of a satellite detonator provided in an embodiment of the present invention; Figure 2 An electrical schematic diagram of an electric lock circuit of a satellite detonator provided by an embodiment of the present invention; Figure 3 A flow chart of a method for unlocking a satellite detonator provided in an embodiment of the present invention; Figure 4 A specific flow chart of the satellite detonator unlocking method provided in an embodiment of the present invention.

[0016] In the figure: 1. Battery pack; 2. Positive line switch circuit; 3. Detonator switch circuit; 31. Detonator switch unit; 4. Resistance control module; 5. Temperature detection unit; 6. Current detection unit. DETAILED DESCRIPTION

[0017] Exemplary embodiments will be described in detail herein, examples of which are shown in the accompanying drawings. When the following description refers to the drawings, the same numbers in different drawings represent the same or similar elements unless otherwise indicated. The implementations described in the following exemplary embodiments do not represent all implementations consistent with the present application. Instead, they are merely examples of devices and methods consistent with some aspects of the present application as detailed in the appended claims.

[0018] It should be noted that, in this article, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "includes a ..." does not exclude the existence of other identical elements in the process, method, article or device including the element. In addition, components, features, and elements with the same name in different embodiments of the present application may have the same meaning or different meanings, and their specific meanings need to be determined by their explanation in the specific embodiment or further combined with the context of the specific embodiment.

[0019] It should be understood that, although the terms first, second, third, etc. may be used to describe various information in this article, these information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of this article, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Depending on the context, the word "if" as used herein can be interpreted as "at the time of..." or "when..." or "in response to determination". Furthermore, as used in this article, the singular forms "one", "one" and "the" are intended to also include plural forms, unless there is an opposite indication in the context. It should be further understood that the terms "comprising", "including" indicate that there are described features, steps, operations, elements, components, projects, kinds, and / or groups, but do not exclude the existence, occurrence or addition of one or more other features, steps, operations, elements, components, projects, kinds, and / or groups. The terms "or" and "and / or" used herein are interpreted as inclusive, or mean any one or any combination. Thus, “A, B, or C” or “A, B and / or C” means “any of the following: A; B; C; A and B; A and C; B and C; A, B, and C.” An exception to this definition will occur only when a combination of elements, functions, steps, or operations are inherently mutually exclusive in some manner.

[0020] It should be understood that, although the various steps in the flowchart in the embodiment of the present application are displayed in sequence according to the indication of the arrows, these steps are not necessarily performed in sequence according to the order indicated by the arrows. Unless there is a clear explanation in this article, the execution of these steps does not have a strict order restriction, and it can be performed in other orders. Moreover, at least a portion of the steps in the figure may include a plurality of sub-steps or a plurality of stages, and these sub-steps or stages are not necessarily performed at the same time, but can be performed at different times, and their execution order is not necessarily performed in sequence, but can be performed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.

[0021] It should be noted that in this article, step codes such as S101, S102, etc. are used for the purpose of expressing the corresponding content more clearly and concisely, and do not constitute a substantial limitation on the sequence. When implementing the step, those skilled in the art may execute S102 first and then S101, etc., but these should all be within the scope of protection of this application.

[0022] It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0023] In the subsequent description, the suffixes such as "module", "component" or "unit" used to represent elements are only used to facilitate the description of the present application, and have no specific meanings. Therefore, "module", "component" or "unit" can be used in a mixed manner.

[0024] See also Figure 1 and Figure 2 , is an unlocking circuit of a satellite detonating device provided in an embodiment of the present application, comprising a battery pack 1, a positive line switch circuit 2, a detonating switch circuit 3 and a plurality of satellite detonating components. The battery pack 1 provides power for the unlocking circuit, and the positive line switch circuit 2 is used to control the on and off of the unlocking circuit. One end of the detonating switch circuit 3 is connected to the positive line switch circuit 2, and the other end is connected to a plurality of satellite detonating components connected in parallel.

[0025] Specifically, each satellite detonation assembly includes a plurality of detonation switch units 31 arranged in series, and each detonation switch unit 31 is respectively connected to a satellite detonation device. The series design increases the total resistance of the circuit, thereby reducing the total current passing through the circuit, extending the power-on heating time, meeting the precise control requirements for the power-on time during ground testing, and avoiding the situation where the detonation switch unit 31 is overheated and burned due to too long power-on time.

[0026] During operation, when the positive line switch circuit 2 is closed, the battery pack 1 supplies power to each satellite detonator assembly through the detonator switch circuit 3. The detonator current passes through the series detonator switch unit 31 in each satellite detonator assembly in turn, and provides power-on heating energy to the connected satellite detonator, triggering the detonator to complete the unlocking operation. The design of the series-connected detonator switch unit 31 ensures the stability of the circuit current and the controllability of the power-on time, thereby ensuring the safety and reliability of the unlocking operation.

[0027] In this embodiment, the design of the detonating switch unit 31 arranged in series can not only prolong the heating time and meet the demand for precise control of the heating process during ground testing, but also avoid the problem of overheating and burning of the detonating switch unit 31 caused by too long power-on time. It is suitable for ground testing and orbit unlocking operation scenarios of satellites.

[0028] Furthermore, the unlocking circuit of the satellite detonator includes a resistance control module 4, which is connected in series with the detonator switch circuit 3 or the satellite detonator assembly to adjust the total resistance value of the unlocking circuit, thereby controlling the power-on current and the heating time.

[0029] Specifically, the resistance control module 4 is composed of at least one fixed resistor and / or an adjustable resistor. The fixed resistor is used to provide 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 test requirements.

[0030] During the ground test, the controllability of the unlocking circuit power-on time can be ensured by adjusting the resistance value of the adjustable resistor according to the ambient temperature: In a low temperature environment, since the memory alloy heats up slowly, the heating time required for unlocking is longer. To ensure that the unlocking operation can be completed within a reasonable time, the resistance of the resistance control module 4 can be reduced and the current can be increased to accelerate the heating process of the memory alloy, thereby ensuring that the detonator can complete the unlocking operation within a reasonable time.

[0031] In a high temperature environment, since the memory alloy heats up quickly and the heating time is shorter, in order to avoid the memory alloy from burning due to too long power-on time, the resistance of the resistance control module 4 can be increased to reduce the current, thereby extending the power-on time.

[0032] The resistance control module 4 is arranged in series in the unlocking circuit to adjust the total resistance of the circuit. When the circuit is powered on, the resistance control module 4 works in series with the detonation switch circuit 3, and its resistance directly affects the total resistance of the circuit, thereby adjusting the current passing through the circuit. After the satellite detonation assembly receives the appropriate power-on current, it heats the memory alloy in the unlocking device to complete the unlocking operation.

[0033] Through the resistance control module 4 in this embodiment, the unlocking circuit can adapt to the power-on requirements under different environmental conditions, realize precise control of the power-on time, ensure the safety and reliability of the unlocking operation, and effectively avoid damage to the detonating device caused by overcurrent or overheating.

[0034] Furthermore, in the satellite detonator unlocking circuit, each detonator switch unit 31 is made of a memory alloy material. The memory alloy has good thermal response characteristics and can produce a shape memory effect when heated, thereby achieving deformation to complete the unlocking operation.

[0035] Specifically, the detonation switch unit 31 in this embodiment adopts a memory alloy pin puller, which is a highly reliable mechanical structure. The shape recovery force generated by the memory alloy material after being powered on and heated drives the compression release device to complete the unlocking process. The detonation switch unit 31 is connected to the satellite detonation device. Through this design, the requirements for satellite sailboard deployment can be met.

[0036] During operation, when the unlocking circuit is energized, the detonating current passes through the serially connected detonating switch units 31, providing heating energy for each detonating switch unit 31. The memory alloy material rapidly heats up after being heated, and deforms according to its shape memory characteristics, triggering the pin puller to release the clamping device, thereby achieving the unlocking operation of the detonating device. The memory alloy of the detonating switch unit 31 is controlled by resistance limitation when it is energized and heated, so that its heating time is precisely controllable, which can ensure the smooth completion of the unlocking action and avoid material damage caused by overheating.

[0037] By using memory alloy material as the core component of the detonation switch unit 31, the detonation device unlocking circuit in this embodiment can achieve deformation action after heating, and complete the reliable unlocking of the satellite detonation device. The application of memory alloy material not only improves the reliability of the unlocking device, but also can accurately adjust the power-on time through the resistance control module 4 to meet the needs of satellite ground testing and orbit entry operations, thereby achieving safe and reliable unlocking operations.

[0038] Furthermore, the satellite detonation device unlocking circuit includes a temperature detection unit 5, and the temperature detection unit 5 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.

[0039] Specifically, the temperature detection unit 5 is arranged near the satellite detonation assembly or in the unlocking assembly to obtain the ambient temperature information in real time. The temperature detection unit 5 can adopt a high-precision temperature sensor, such as a thermistor, a thermocouple or a semiconductor temperature sensor. The detected temperature information will be transmitted to an external control unit or a microcontroller so as to dynamically adjust the power-on time and current of the unlocking circuit according to the current ambient temperature, thereby ensuring the safety and reliability of the unlocking operation.

[0040] In a low temperature environment, the heating efficiency of the 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 memory alloy can reach the heating temperature required for unlocking, thereby completing the unlocking action.

[0041] In a high temperature environment, the memory alloy pin puller heats up quickly. When the temperature detection unit 5 detects that the ambient temperature is high, it can shorten the power-on time or reduce the current in time to prevent the memory alloy from being damaged due to overheating and ensure the safety of the detonator.

[0042] Furthermore, the satellite detonator unlocking circuit includes a current detection unit 6, which is connected to the satellite detonator component and is used to monitor the working current of the unlocking component in real time to ensure the safety and controllability of the unlocking operation process.

[0043] Specifically, the current detection unit 6 is arranged in the power supply circuit of the satellite detonation assembly, and can realize real-time detection of the current magnitude through a Hall current sensor, a shunt resistor or other current measuring device. The current detection unit 6 can transmit the detected current value to an external control unit or a microcontroller. By monitoring the actual current, the control unit can dynamically adjust the working parameters of the unlocking circuit to ensure that the current operates within a safe range.

[0044] Furthermore, the satellite detonator unlocking circuit includes a control module, which is used to control the on-off operation of the unlocking component by the power module, thereby achieving precise control of the unlocking process.

[0045] The control module is connected to the power 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 state of the unlocking component by the power module according to the monitoring results. The control module ensures that the working current and power-on time of the unlocking component meet the requirements of the unlocking operation by closing or disconnecting the power supply path of the power module.

[0046] Furthermore, one end of the detonation switch circuit 3 is connected to the positive line switch circuit 2, and the other end is connected to two satellite detonation assemblies arranged in parallel. The positive line switch circuit 2 controls the opening and closing of the power supply to ensure that the current can be supplied to the detonation circuit. Each satellite detonation assembly includes three detonation switch units 31 arranged in series. Each detonation switch unit 31 connected in series is respectively connected to the three ends of the satellite sailboard. Through the parallel arrangement, the two detonation assemblies work together to respectively control the unlocking of the locking devices at the three ends of the satellite sailboard, thereby ensuring the smooth deployment of the satellite sailboard.

[0047] Each satellite detonation assembly includes three detonation switch units 31 arranged in series. Each detonation switch unit 31 is made of memory alloy material. When current passes through, the memory alloy deforms due to heat, thereby driving the mechanical device to unlock the satellite detonation device. Each detonation switch unit 31 connected in series is respectively connected to the three ends of the satellite sailboard. When current flows through the detonation switch unit 31, the unlocking action is performed synchronously to ensure that each end of the sailboard can be unlocked smoothly.

[0048] Based on the same inventive concept as the above embodiments, the above embodiments are described in detail below through a specific application scenario: In order to verify the performance of memory alloys under actual conditions, experiments were carried out on the ground. The specific conditions and data are as follows: Temperature conditions: The ground experiment was carried out at room temperature of 25°C.

[0049] According to experimental verification results, the energy required for the memory alloy to complete expansion at room temperature is approximately 15J.

[0050] The total resistance of each detonator assembly is 3.1Ω (including the memory alloy resistance 0.7Ω × 3 and the circuit line resistance of 1Ω). According to Ohm's law, the current is:

[0051] According to the energy formula:

[0052] Under the condition of supply current of 3.87A, the time required for expansion is 1.2 seconds.

[0053] on the contrary: If the three memory alloy elements (resistance is R=0.7ΩR = 0.7ΩR=0.7Ω) are changed to a parallel structure, the supply voltage is still 12V.

[0054] The formula for parallel resistance is:

[0055] The current at this time is:

[0056] According to the energy formula:

[0057] Under the condition of supply current of 17.2A, the time required for expansion is 0.073 seconds.

[0058] In the parallel structure, the power-on time of each 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 strict requirements on the power supply design and easily leads to power overload or circuit stability degradation. In addition, the power-on time is too short to be accurately controlled, which increases the risk of unlocking action failure, especially in ground testing. It is difficult to ensure stability.

[0059] In contrast, the unlocking time under the series structure is 1.2 seconds and the current is moderate (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, and is suitable for ground test environments.

[0060] Based on the same inventive concept as the aforementioned embodiment, an embodiment of the present invention provides an unlocking method for an unlocking circuit of a detonator, which mainly includes two parts: a ground testing phase and an on-orbit operation phase, to ensure that the satellite detonator assembly is stably unlocked under different temperature environments.

[0061] See also Figure 3 , the unlocking method of the detonator unlocking circuit includes: Step S101: Obtain the unlocking time of the satellite detonation component when it is powered on and heated under different ambient temperatures and different currents, and generate a temperature-current-time comparison table.

[0062] During the ground test phase, laboratory equipment was used to simulate various temperature conditions (such as -30°C, 0°C, 25°C and 65°C), combined with different supply currents (such as 2A, 3A, 5A, etc.), to measure the power-on time required for the memory alloy to complete the unlocking action under different conditions. For example, when the supply current is 3A and the temperature is -30°C, the unlocking time is 1.8 seconds; when the supply current is 5A and the temperature is 25°C, the unlocking time is shortened to 0.68 seconds. Based on these experimental results, a temperature-current-time comparison table was compiled to provide data support for the subsequent time adjustment of the unlocking circuit.

[0063] Step S102: adjusting the power-on time of the unlocking circuit according to the temperature-current-time comparison table.

[0064] During the operation phase, the current ambient temperature is monitored in real time through the temperature sensor, and the corresponding unlocking time is matched with the comparison table. For example, when the temperature sensor detects that the ambient temperature is 10°C, the comparison table shows that the recommended power-on time is 1.2 seconds. The unlocking circuit control module sets the power-on time according to the data and performs the unlocking operation. If the power-on time exceeds 2 times the theoretical value but the unlocking operation is not completed, the system will trigger the alarm device and stop the power supply to avoid damage to the memory alloy due to overheating.

[0065] Furthermore, Step S201: Obtaining the unlocking time of the satellite detonation component when it is powered on and heated under different ambient temperatures and different currents.

[0066] Step S202: Generate a temperature-current-time comparison table according to the unlocking time.

[0067] According to the experimental results, the generated comparison table will serve as the basis for subsequent unlocking circuit time adjustment.

[0068] Step S203: During the ground test phase, the temperature value of the environment in which the satellite detonation assembly is located is obtained.

[0069] During the ground test phase, the temperature of the environment where the satellite detonation assembly is located is monitored in real time through a temperature sensor. For example, the ambient temperature monitored during the experiment was 15°C.

[0070] Step S204: adjusting the resistance of the resistance control module according to the temperature of the environment to adjust the current.

[0071] According to the temperature value obtained in step S203, the resistance control module dynamically adjusts the resistance of the unlocking circuit to adjust the power supply current. For example, when the ambient temperature is 15°C, the resistance control module adjusts the circuit resistance to adjust the power supply current to 3.87A to meet the unlocking conditions.

[0072] Step S205: Generate a preset time for unlocking the circuit according to the temperature value and the current magnitude by comparing the temperature-current-time comparison table.

[0073] Combined with the temperature-current-time comparison table generated in step S202, the current temperature value (such as 15°C) and the power supply current (such as 3.87A) are matched to obtain the preset time required for unlocking. For example, the comparison table shows that the preset time under the current conditions is 1.2 seconds.

[0074] Step S206: During the on-track operation phase, the preset time is obtained according to the temperature-current-time comparison table, and the preset time is extended to the actual time.

[0075] During the on-orbit operation phase, the corresponding preset time is matched by real-time monitoring of temperature (such as -100°C) combined with the temperature-current-time comparison table, and appropriately extended to the actual time to adapt to the low temperature environment of outer space. For example, under extremely low temperature conditions, the comparison table shows that the preset time is 2 seconds, the extension factor is 2, and the actual power-on time is adjusted to 4 seconds to ensure the successful completion of the unlocking action.

[0076] Through the above steps, the present invention realizes the reliability and adaptability of the unlocking circuit in ground testing and on-orbit operation. In the ground testing stage, the unlocking performance is verified by dynamically adjusting the current and unlocking time; in the on-orbit operation stage, the power-on time strategy is extended to adapt to the extreme low temperature environment in outer space, ensuring the safety and stability of the unlocking action.

[0077] Furthermore, the detonator unlocking circuit includes an alarm device.

[0078] When the power-on time of the ground test exceeds twice the theoretical value (for example, the theoretical time is 1.5 seconds, and it is triggered when it exceeds 3 seconds), the alarm device will emit an audible and visual prompt, and the system will automatically cut off the power supply to protect the safety of the memory alloy. After the alarm is triggered, the tester needs to check the power supply status, temperature conditions and the operation of the unlocking device, and restart the test after eliminating possible abnormalities.

[0079] This embodiment not only ensures the safety of the unlocking circuit during ground testing by adding an alarm device and an automatic power-off mechanism, but also effectively avoids the problem of memory alloy damage caused by long-term power-on.

[0080] Based on the same inventive concept as the above embodiments, the embodiments of the present invention provide a spacecraft for performing unlocking operations of key spacecraft equipment, such as sailboard deployment, antenna release, etc. The unlocking circuit realizes reliable unlocking of the locking device of the spacecraft equipment through the coordinated operation of two parallel detonation components.

[0081] The unlocking circuit of the spacecraft includes two satellite detonation components arranged in parallel, each component is composed of three detonation switch units 31 connected in series, and the detonation switch unit 31 uses a memory alloy material as the core driving element. After being powered on, the memory alloy material deforms due to heat, driving the mechanical structure to complete the unlocking action. The two parallel detonation components do not operate independently, but cooperate to complete the unlocking operation. Each component acts on different ends of the sailboard locking device. The synchronous operation of the two components ensures that the sailboard locking device can be unlocked in a coordinated manner, thereby achieving the normal deployment of the equipment.

[0082] During the ground test phase, in order to verify the reliability and performance of the unlocking circuit, the resistance value of the unlocking circuit is dynamically adjusted through the resistance control module 4 to ensure that the unlocking time is controlled within the set range (such as 1-3 seconds). At the same time, the unlocking circuit includes an alarm device. If the power-on time exceeds twice the theoretical value but the unlocking operation is not completed, the system will trigger an alarm and automatically power off to protect the 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.

[0083] After the spacecraft enters orbit, the unlocking circuit monitors the external ambient temperature in real time through the temperature sensor, and dynamically adjusts the unlocking time to adapt to the actual environmental conditions in combination with the temperature-current-time comparison table generated by ground tests. The two parallel detonation components work together to ensure that both ends of the sailboard locking device can be unlocked synchronously, thereby ensuring the smooth deployment of the sailboard.

[0084] By integrating the unlocking circuit into the spacecraft, the stability and reliability of the equipment unlocking operation in complex environments are ensured. Especially in mission-critical scenarios, such as sailboard deployment, antenna release or payload unlocking, the design of the unlocking circuit can achieve efficient and safe unlocking operations, ensuring the normal operation of the spacecraft and the completion of its intended mission.

[0085] The technical features of the above-described embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above-described 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.

[0086] In this document, the terms "comprises," "comprising," or any other variations thereof, are intended to cover a non-exclusive inclusion of elements other than those listed and may also include additional elements not expressly listed.

[0087] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. An unlocking circuit for a satellite detonator, characterized in that: include: Battery pack; A positive line switch circuit connected to the positive terminal of the battery pack; A detonation switch circuit, one end of which is connected to the positive line switch circuit, and the other end of which is connected to M satellite detonation assemblies arranged in parallel; wherein M is an integer, and M≥1; The satellite detonation assembly comprises N detonation switch units arranged in series, each of which is connected to a satellite detonation device; Wherein N is an integer, and N≥1.

2. The satellite detonator unlocking circuit according to claim 1, characterized in that: The unlocking circuit further comprises: 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 a variable resistor and / or a fixed resistor.

3. The satellite detonator unlocking circuit according to claim 1, characterized in that: The unlocking circuit further includes: Each detonating switch unit is made of a memory alloy material, and the detonating unit switch is deformed by heat to unlock the satellite detonating device.

4. The satellite detonator unlocking circuit according to any one of claims 1 to 3, characterized in that: The unlocking component comprises: A temperature detection unit is used to detect the temperature of the environment of the satellite detonation assembly.

5. The satellite detonator unlocking circuit according to claim 4, characterized in that: The unlocking component also includes: A current detection unit is connected to the satellite detonation component and is used to detect the current size of the unlocking component in real time.

6. The satellite detonator unlocking circuit according to claim 5, characterized in that: The unlocking component also includes: A control module, wherein the control module is used to control the power module to turn on and off the unlocking component.

7. The satellite detonator 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 assemblies arranged in parallel; The satellite detonation assembly comprises three detonation switch units arranged in series, and each of the detonation switch units is connected to a satellite detonation device.

8. An unlocking method using the unlocking circuit of the detonating device according to any one of claims 4 to 7, characterized in that: include, Obtaining the unlocking time of the satellite detonation component when it is powered on and heated at different ambient temperatures and different currents, and generating a temperature-current-time comparison table; The power-on time of the unlocking circuit is adjusted according to the temperature-current-time comparison table.

9. The unlocking method according to claim 8, characterized in that: The unlocking circuit includes a resistance control module; Obtaining the unlocking time of the satellite detonation component when it is powered on and heated at different ambient temperatures and different currents; Generate a temperature-current-time comparison table based on the unlocking time; During the ground test phase, the temperature value of the environment in which the satellite detonation assembly is located is obtained; Adjusting the resistance value of the resistance control module according to the temperature value of the environment to adjust the current; Generate a preset time for unlocking the circuit according to the temperature value and the current size by comparing the temperature-current-time comparison table; During the on-orbit operation phase, the preset time is obtained according to the temperature-current-time comparison table, and the preset time is extended to the actual time.

10. A spacecraft, characterized in that: It comprises the satellite detonator unlocking circuit as described in any one of claims 1-7.

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