Satellite load detection circuit, detection method, electronic equipment and program product

Abstract

The invention provides a satellite load detection circuit, a detection method, an electronic device and a program product, through the design of parallel connection of a detection branch and a main loop, a main current is mainly transmitted through a first branch only comprising a first fuse, and a second detection branch only bears a small part of a sampling current. The Hall sensor, the sampling resistor and other detection devices do not need to bear the total current for a long time, the electric energy loss in the detection link is greatly reduced, the calorific value is remarkably reduced accordingly, the small-size and universal Hall sensor (without a large-size magnetic core) can be selected, and the hardware purchase cost is greatly reduced. The double branches are both provided with fuses (the first fuse of the first branch and the second fuse of the second branch), independent overcurrent protection of the main loop and the detection branch is achieved, any branch can be quickly fused when an overcurrent fault occurs, fault diffusion is avoided, the fault resistance and operation reliability of the whole circuit are further improved, and the service life of the main loop and the detection branch is prolonged. And the application requirements of high reliability and long service life of satellite loads are met.

Description

Technical Field

[0001] This application relates to the field of electronic technology, and more specifically, to a satellite payload detection circuit, detection method, electronic device, and program product. Background Technology

[0002] In existing satellite payload power supply solutions, the input current of the primary power supply is typically detected by inserting a linear Hall sensor element in series on the main circuit. Existing Hall devices come in two forms: Integrated conductor-type sensor IC: This is currently the most common form of current detection integrated on a single board. The surface-mount packaged chip integrates a low-resistance current conductor and a high-precision linear Hall effect circuit. The current being measured flows directly through the internal conductor, and the resulting magnetic field is detected by the Hall element and converted into a proportional voltage output.

[0003] Traditional magnetic core sensors: This is another important form. The sensor (usually a standalone Hall chip, such as a linear Hall sensor) works in conjunction with an external magnetic core. The conductor being measured passes through the magnetic core, and the magnetic field generated by its current is concentrated by the core and detected by the Hall element. This method can achieve electrical isolation and the measurement of larger currents; however, it is much larger and heavier than chip-type Hall circuits, and is not commonly used for heavy loads.

[0004] Current technology typically places the Hall sensor immediately after the power interface. The total current value is directly and linearly converted into an analog voltage signal, and the subsequent AD conversion can achieve real-time current detection with relatively simple steps. However, this approach has several drawbacks. First, if a chip-type Hall sensor is used, it generates significant heat. Furthermore, in satellite systems, electrical resources are extremely precious, and this series connection to the main circuit will consume a large amount of power over a long period. More importantly, having the Hall sensor conductor connected in series with the main circuit introduces the risk of device fatigue and short circuit, significantly reducing the reliability of the entire satellite payload. Second, if a traditional magnetic core sensor is used, due to the large main circuit current, a large magnetic core is required to meet the measured current range. Additionally, a specially designed structural support for the large magnetic core to meet reliability requirements is necessary, which is extremely costly for satellite payloads with strict space and weight control requirements. Summary of the Invention

[0005] The purpose of this application is to provide a satellite payload detection circuit, detection method, electronic device and program product to solve the problems of high energy consumption, high heat generation, low reliability and high cost in existing detection schemes.

[0006] This application provides a satellite payload detection circuit, which is connected in series between a power interface and a subsequent circuit. The satellite payload detection circuit includes: a first branch and a second branch connected in parallel, and a computing module. The first branch includes a first fuse; The second branch includes a first resistor, a second fuse, and a Hall sensor connected in series; The Hall sensor outputs a voltage V at its signal output terminal. OUT To the computing module; The calculation module is used to calculate based on voltage V OUT Calculate the total current output from the power interface.

[0007] In the above technical solution, by designing the detection branch in parallel with the main circuit, the main current is primarily transmitted through the first branch, which contains only the first fuse. The second detection branch only carries a small portion of the sampling current. Detection devices such as Hall sensors and sampling resistors do not need to carry the total current for extended periods, significantly reducing power loss in the detection process and consequently reducing heat generation. Furthermore, small-sized, universal Hall sensors can be used (eliminating the need for large magnetic cores), significantly reducing hardware procurement costs. Both branches are equipped with fuses (first fuse for the first branch, second fuse for the second branch), achieving independent overcurrent protection for the main circuit and the detection branch. Overcurrent faults in either branch can be quickly blew, preventing fault propagation and further enhancing the overall circuit's fault tolerance and operational reliability, meeting the high reliability and long lifespan requirements of satellite payloads.

[0008] In some optional implementations, the computing module is used for: According to voltage V OUT The total current is calculated using the first calculation formula; Based on the total current and the threshold value K, determine whether the first fuse has blown; If the total current is less than the threshold value K, then the first fuse has not blown, and the total current is taken as the detection result. If the total current is greater than or equal to the threshold value K, the first fuse will blow, based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

[0009] In the above technical solution, the threshold value K can be pre-calibrated based on the circuit topology parameters, fuse rated parameters, and Hall sensor sampling accuracy. The judgment logic is based on the current signal calculated by hardware sampling, which can accurately distinguish between the two states of the fuse being normally conducting and the fuse being blown open. Subsequently, different calculation methods are used to determine the total current output by the power interface for the two different states.

[0010] In some optional implementations, the first calculation formula is: I IN = (V OUT -V OUT，0A )×(R1+R2+R3+R4) / (R1×S); Among them, I IN V is the total current, S is the sensitivity of the Hall sensor, and V is the total current. OUT，0A R1 is the zero-current output voltage of the Hall sensor, R2 is the resistance value of the first fuse, R3 is the resistance value of the first resistor, and R4 is the resistance value of the Hall sensor.

[0011] In some optional implementations, the second calculation formula is: I IN =(V OUT -V OUT，0A ) / S; Among them, I IN V is the total current, S is the sensitivity of the Hall sensor, and V is the total current. OUT，0A This is the zero-current output voltage of the Hall sensor.

[0012] In some alternative implementations, the threshold value K: K=α×Imax×(R1+R2+R3+R4) / R1; Where Imax is the value of I when the first fuse fails to blow. IN The maximum value, α, is the safety factor to prevent false triggering, 0.8 < α < 1.0; In the above technical solution, Imax directly corresponds to the rated operating conditions of the satellite payload power system. The threshold value K is set to anchor the upper limit of the current during normal circuit operation, ensuring that the fuse triggers only in scenarios exceeding normal operating conditions where the fuse is indeed likely to blow. This avoids invalid judgments caused by the threshold deviating from the actual operating range of the circuit, making the judgment logic more condition-specific. By introducing a safety factor α (0.8 < α < 1.0) to prevent false triggering, a reasonable safety threshold range is set for the fuse triggering. This effectively offsets current detection errors caused by device parameter drift and small fluctuations in sampling signals under complex aerospace conditions such as high and low temperatures, vibration, and voltage fluctuations, preventing false fuse blowouts due to accidental signal fluctuations.

[0013] In some alternative implementations, the threshold value K: K = β × I0; Where β is the full-scale safety factor, I0 is the full-scale range of the Hall sensor, and 0.5 < β < 0.8.

[0014] In the above technical solution, the setting of the full-scale safety factor β ensures that the threshold value K is always lower than the full-scale I0 of the Hall sensor, which not only avoids the failure of judgment caused by the threshold exceeding the sensor sampling range, but also reserves a reasonable safety buffer for the fuse triggering judgment.

[0015] In some optional implementations, the computing module is used for: According to voltage V OUT The total current is calculated using the first calculation formula; Based on the total current change rate and the change rate threshold, determine whether the first fuse has blown; If the rate of change of the total current is less than the rate of change threshold, then the first fuse has not blown, and the total current is taken as the detection result. If the rate of change of the total current is greater than or equal to the rate of change threshold, then the first fuse blows, based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

[0016] In the above technical solution, the first fuse blows out as a sudden fault. At the moment of blow, the circuit topology changes abruptly, and the total current obtained by the first calculation formula will show a step change. Based on this core physical characteristic of the fault, this solution determines the blown state by the rate of change of current.

[0017] This application provides a satellite payload detection method, applied to the computation module of a satellite payload detection circuit as described in any of the above claims, the method comprising: According to voltage V OUT The total current is calculated using the first calculation formula; Based on the total current and the threshold value K, determine whether the first fuse has blown; If the total current is less than the threshold value K, then the first fuse has not blown, and the total current is taken as the detection result. If the total current is greater than or equal to the threshold value K, the first fuse will blow, based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

[0018] In some alternative implementations, it also includes: According to voltage V OUT The total current is calculated using the first calculation formula; Based on the total current change rate and the change rate threshold, determine whether the first fuse has blown; If the rate of change of the total current is less than the rate of change threshold, then the first fuse has not blown, and the total current is taken as the detection result. If the rate of change of the total current is greater than or equal to the rate of change threshold, then the first fuse blows, based on the voltage V. OUTThe second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

[0019] In some optional implementations, the first calculation formula is: I IN = (V OUT -V OUT，0A )×(R1+R2+R3+R4) / (R1×S); The second calculation formula is: I IN =(V OUT -V OUT，0A ) / S; Among them, I IN V is the total current, S is the sensitivity of the Hall sensor, and V is the total current. OUT，0A R1 is the zero-current output voltage of the Hall sensor, R2 is the resistance value of the first fuse, R3 is the resistance value of the first resistor, and R4 is the resistance value of the Hall sensor.

[0020] An electronic device provided in this application includes a processor and a memory, wherein the memory stores machine-readable instructions executable by the processor, and the machine-readable instructions, when executed by the processor, perform any of the methods described above.

[0021] This application provides a computer program product, including a computer program / instruction, which, when executed by a processor, implements the steps of any of the methods described above. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments of this application will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This application provides a schematic diagram of a satellite payload detection circuit connection. Figure 2 A flowchart illustrating the steps of a satellite payload detection method provided in this application embodiment; Figure 3 A flowchart illustrating another satellite payload detection method provided in this application embodiment; Figure 4 This application illustrates one possible structure of an electronic device provided in an embodiment of the present application. Detailed Implementation

[0024] The technical solutions in the embodiments of this application will now be described with reference to the accompanying drawings.

[0025] Please refer to Figure 1 , Figure 1 A satellite payload detection circuit is provided in an embodiment of this application. The satellite payload detection circuit is connected in series between the power interface and the subsequent circuit. The satellite payload detection circuit includes: a first branch and a second branch connected in parallel, and a computing module. The first branch includes a first fuse; The second branch includes a first resistor, a second fuse, and a Hall sensor connected in series; The Hall sensor outputs a voltage V at its signal output terminal. OUT To the computing module; The calculation module is used to calculate based on voltage V OUT Calculate the total current output from the power interface.

[0026] The arithmetic module includes an analog-to-digital converter (ADC) and a CPU. The ADC converts the analog voltage signal detected by the Hall sensor into a digital signal, and the CPU calculates the total current based on this digital signal. The arithmetic module may also include a signal conditioning and amplification module to condition and amplify the analog voltage signal detected by the Hall sensor.

[0027] In the above technical solution, by designing the detection branch in parallel with the main circuit, the main current is primarily transmitted through the first branch, which contains only the first fuse. The second detection branch only carries a small portion of the sampling current. Detection devices such as Hall sensors and sampling resistors do not need to carry the total current for extended periods, significantly reducing power loss in the detection process and consequently reducing heat generation. Furthermore, small-sized, universal Hall sensors can be used (eliminating the need for large magnetic cores), significantly reducing hardware procurement costs. Both branches are equipped with fuses (first fuse for the first branch, second fuse for the second branch), achieving independent overcurrent protection for the main circuit and the detection branch. Overcurrent faults in either branch can be quickly blew, preventing fault propagation and further enhancing the overall circuit's fault tolerance and operational reliability, meeting the high reliability and long lifespan requirements of satellite payloads.

[0028] In some optional implementations, the computing module is used for: According to voltage V OUT The total current is calculated using the first calculation formula. The first calculation formula is a conversion formula for the total current derived from the sampling current of the Hall sensor. By incorporating the resistance parameters of all branches, the current splitting law of the parallel topology is accurately matched, thereby achieving accurate conversion from the small current of the detection branch to the total power supply current.

[0029] Based on the total current and the threshold value K, it is determined whether the first fuse has blown; the second calculation formula is the basic sampling conversion formula of the Hall sensor, which does not require additional shunt coefficient conversion and directly converts the voltage output signal of the sensor into the actual current, because at this time the current of the detection branch is exactly equal to the total power supply current.

[0030] If the total current is less than the threshold value K, then the first fuse has not blown, and the total current is taken as the detection result. If the total current is greater than or equal to the threshold value K, the first fuse will blow, based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

[0031] In the above technical solution, the threshold value K can be pre-calibrated based on the circuit topology parameters, fuse rated parameters, and Hall sensor sampling accuracy. The judgment logic is based on the current signal calculated by hardware sampling, which can accurately distinguish between the two states of the fuse being normally conducting and the fuse being blown open. Subsequently, different calculation methods are used to determine the total current output by the power interface for the two different states.

[0032] In some optional implementations, the first calculation formula is: I IN = (V OUT -V OUT，0A )×(R1+R2+R3+R4) / (R1×S); Among them, I IN V is the total current, S is the sensitivity of the Hall sensor, and V is the total current. OUT，0A R1 is the zero-current output voltage of the Hall sensor, R2 is the resistance value of the first fuse, R3 is the resistance value of the first resistor, and R4 is the resistance value of the Hall sensor.

[0033] In some optional implementations, the second calculation formula is: I IN =(V OUT -V OUT，0A ) / S; Among them, I IN V is the total current, S is the sensitivity of the Hall sensor, and V is the total current. OUT，0A This is the zero-current output voltage of the Hall sensor.

[0034] In some alternative implementations, the threshold value K: K=α×Imax×(R1+R2+R3+R4) / R1; Where Imax is the value of I when the first fuse fails to blow. IN The maximum value, α, is the safety factor to prevent false triggering, 0.8 < α < 1.0; In the above technical solution, Imax directly corresponds to the rated operating conditions of the satellite payload power system. The threshold value K is set to anchor the upper limit of the current during normal circuit operation, ensuring that the fuse triggers only in scenarios exceeding normal operating conditions where the fuse is indeed likely to blow. This avoids invalid judgments caused by the threshold deviating from the actual operating range of the circuit, making the judgment logic more condition-specific. By introducing a safety factor α (0.8 < α < 1.0) to prevent false triggering, a reasonable safety threshold range is set for the fuse triggering. This effectively offsets current detection errors caused by device parameter drift and small fluctuations in sampling signals under complex aerospace conditions such as high and low temperatures, vibration, and voltage fluctuations, preventing false fuse blowouts due to accidental signal fluctuations.

[0035] In some alternative implementations, the threshold value K: K = β × I0; Where β is the full-scale safety factor, I0 is the full-scale range of the Hall sensor, and 0.5 < β < 0.8.

[0036] In the above technical solution, the setting of the full-scale safety factor β ensures that the threshold value K is always lower than the full-scale I0 of the Hall sensor, which not only avoids the failure of judgment caused by the threshold exceeding the sensor sampling range, but also reserves a reasonable safety buffer for the fuse triggering judgment.

[0037] In some optional implementations, the computing module is used for: According to voltage V OUT The total current is calculated using the first calculation formula; Based on the total current change rate and the change rate threshold, determine whether the first fuse has blown; If the rate of change of the total current is less than the rate of change threshold, then the first fuse has not blown, and the total current is taken as the detection result. If the rate of change of the total current is greater than or equal to the rate of change threshold, then the first fuse blows, based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

[0038] The rate of change threshold can be obtained through actual measurement or simulation. For example, by using a circuit bench test to simulate all scenarios of fuse failure, such as rated failure and overload failure of the first fuse, the total current change curve at the moment of failure is collected, and the minimum current change rate of multiple tests is calculated. This minimum current change rate is then used as the rate of change threshold.

[0039] In the above technical solution, the first fuse blows out as a sudden fault. At the moment of blow, the circuit topology changes abruptly, and the total current obtained by the first calculation formula will show a step change. Based on this core physical characteristic of the fault, this solution determines the blown state by the rate of change of current.

[0040] Please refer to Figure 2 , Figure 2 A flowchart of a satellite payload detection method provided in this application embodiment is applied to the computation module of a satellite payload detection circuit as described in any of the above claims. The method includes: Step S11, based on voltage V OUT The total current is calculated using the first calculation formula; Step S12: Determine whether the first fuse has blown based on the total current and the threshold value K; Step S13: If the total current is less than the threshold value K, the first fuse has not blown, and this total current is taken as the detection result; if the total current is greater than or equal to the threshold value K, the first fuse has blown, and the result is determined based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

[0041] In one specific embodiment, the first and second fuses are of the same type, with a cold-state resistance of 2mΩ. The first resistor has a resistance of 16mΩ, and the internal conductor of the Hall sensor has a fixed resistance of 2mΩ. In this embodiment, the total resistance of the second branch is 10 times that of the first branch.

[0042] The Hall sensor can be a TCS1101A3U-Q1, with a sensitivity of ΔVout / ΔIin = 200mV / A and a zero-current output voltage of Vout,0A = 0.1V. In this circuit, Vs = 3.3V. The total current of the two branches is 11 × I. IN Therefore, the current and voltage transfer functions of the Hall sensor in the second branch are: V OUT =(0.2×I IN ) / 11+V OUT,0A ; Since the ratio of the total current to the current in the second branch is a constant 1:11, the total current can be calculated by measuring the current in the second branch. Therefore, a large current in the total circuit can be measured using a small-rated Hall sensor. For example, a 20A Hall sensor can theoretically measure a maximum total current of 220A in this circuit.

[0043] This embodiment uses a chip-type Hall sensor, which is much smaller in size than a magnetic core-type Hall sensor with the same current detection level. Therefore, a Hall sensor with a range that meets the total current size can be selected and placed after the second fuse. Importantly, in satellite payload power supplies, this method is far more reliable than testing the current on the main circuit. The analysis is as follows: During normal operation of the satellite payload, neither the first nor the second fuse experienced overcurrent failure, and the calculation was performed in the manner described above.

[0044] The second fuse on the satellite payload power board serves as a hot backup for the first fuse. The first fuse carries the majority of the current during normal operation, resulting in greater fatigue strength and a faster lifespan. In special circumstances, such as a transient current exceeding the first fuse's breaking current value during satellite operation, the first fuse will blow. In this case, the second fuse, acting as a hot backup, will carry the total current. Therefore, the second branch carries all the total current, and the Hall sensor will output an analog output voltage value 11 times the original value. The AD converter converts this analog signal to a digital signal and sends it to the CPU. When the CPU detects that the current value has reached the threshold K of the switching formula, it automatically switches to the following formula for calculation: V OUT =0.2×II N +V OUT,0A ; In this embodiment, a chip-type Hall sensor is used. This sensor is small and lightweight, requiring no special structural reinforcement design, and generates very little heat under normal conditions, saving on satellite power and structural costs. Regarding reliability, because of the hot backup branch, in the event of an abnormal tripping of the first fuse in the first branch, the second branch can ensure that the detection function and performance remain unchanged by switching the calculation method. This improves reliability while reducing costs.

[0045] In summary, this embodiment has the following advantages: This embodiment uses a chip-based Hall sensor, which saves valuable internal satellite space and structural design costs, and reduces structural complexity.

[0046] Under normal operating conditions, neither the first nor the second fuse blows, and the total load current is calculated according to the first calculation formula. After the first fuse abnormally blows, the total load current calculation formula automatically switches to the second calculation formula. The Hall sensor's current detection range is selected with sufficient redundancy, satisfying both small size and surface-mount packaging requirements, while ensuring the continued normal operation of the satellite payload's current detection function even after the first fuse abnormally blows. Current detection is achieved at low cost, and compared to other detection methods, the overall reliability of the payload is improved.

[0047] In satellite payload power circuits, for reliability and safety reasons, it is necessary to avoid the use of resistive sampling sensors in the main circuit. This solution avoids this problem by detecting small currents in the branch circuit, resulting in very low heat generation and power consumption. Furthermore, the failure probability of the devices in the branch circuit will not increase the failure rate of the main channel. Even if the sensor fails, it will not affect the operation of the entire payload.

[0048] Please refer to Figure 3 , Figure 3 Another satellite payload detection method flowchart provided in this application embodiment, applied to the computation module of a satellite payload detection circuit as described in any of the above claims, the method includes: Step S21, based on voltage V OUT The total current is calculated using the first calculation formula; Step S22: Determine whether the first fuse has blown based on the total current change rate and the change rate threshold. Step S23: If the rate of change of the total current is less than the rate of change threshold, the first fuse has not blown, and the total current is taken as the detection result; if the rate of change of the total current is greater than or equal to the rate of change threshold, the first fuse has blown, and the voltage V is used as the detection result. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

[0049] In some optional implementations, the first calculation formula is: I IN = (V OUT -V OUT，0A )×(R1+R2+R3+R4) / (R1×S); The second calculation formula is: I IN =(V OUT -V OUT，0A ) / S; Among them, I IN V is the total current, S is the sensitivity of the Hall sensor, and V is the total current. OUT，0A R1 is the zero-current output voltage of the Hall sensor, R2 is the resistance value of the first fuse, R3 is the resistance value of the first resistor, and R4 is the resistance value of the Hall sensor.

[0050] Figure 4 This illustration shows a possible structure of an electronic device provided in an embodiment of this application. (Refer to...) Figure 4 The electronic device includes a processor, memory, and a communication interface, which are interconnected and communicate with each other via a communication bus and / or other forms of connection mechanism (not shown).

[0051] The memory includes one or more (only one is shown in the figure), which can be, but is not limited to, Random Access Memory (RAM), Read Only Memory (ROM), Programmable Read-Only Memory (PROM), Erasable Programmable Read-Only Memory (EPROM), Electrically Erasable Programmable Read-Only Memory (EEPROM), etc. The processor and other possible components can access the memory to read and / or write data to it.

[0052] The processor comprises one or more (only one is shown in the figure), which can be an integrated circuit chip with signal processing capabilities. The aforementioned processor can be a general-purpose processor, including a Central Processing Unit (CPU), a Microcontroller Unit (MCU), a Network Processor (NP), or other conventional processors; it can also be a special-purpose processor, including a Neural-network Processing Unit (NPU), a Graphics Processing Unit (GPU), a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field-Programmable Gate Array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. Furthermore, when there are multiple processors, some can be general-purpose processors, and others can be special-purpose processors.

[0053] The communication interface includes one or more (only one is shown in the figure), which can be used to communicate directly or indirectly with other devices to exchange data. The communication interface may include interfaces for wired and / or wireless communication.

[0054] One or more computer program instructions may be stored in the memory, and the processor may read and execute these computer program instructions to implement the methods provided in the embodiments of this application.

[0055] Understandable. Figure 4 The structure shown is for illustrative purposes only; the electronic device may also include structures that are more advanced than those shown. Figure 4 The more or fewer components shown, or having the same Figure 4 The different structures shown. Figure 4 The components shown can be implemented using hardware, software, or a combination thereof. Electronic devices may be physical devices, such as PCs, laptops, tablets, mobile phones, servers, embedded devices, etc., or they may be virtual devices, such as virtual machines, virtualized containers, etc. Furthermore, electronic devices are not limited to a single device; they can also be a combination of multiple devices or a cluster of a large number of devices.

[0056] This application provides a computer program product, including a computer program / instruction, which, when executed by a processor, implements the steps of any of the methods described above.

[0057] In the embodiments provided in this application, it should be understood that the disclosed apparatus and methods can be implemented in other ways. The apparatus embodiments described above are merely illustrative. For example, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. Furthermore, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Additionally, the displayed or discussed mutual couplings, direct couplings, or communication connections may be through some communication interfaces; indirect couplings or communication connections between devices or units may be electrical, mechanical, or other forms.

[0058] Furthermore, the units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0059] Furthermore, the functional modules in the various embodiments of this application can be integrated together to form an independent part, or each module can exist independently, or two or more modules can be integrated to form an independent part.

[0060] In this document, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, without necessarily requiring or implying any such actual relationship or order between these entities or operations.

[0061] The above description is merely an embodiment of this application and is not intended to limit the scope of protection of this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application.

Claims

1. A satellite payload detection circuit, characterized in that, The satellite payload detection circuit is connected in series between the power interface and the subsequent circuit. The satellite payload detection circuit includes: a first branch and a second branch connected in parallel, and a computing module. The first branch includes a first fuse; The second branch includes a first resistor, a second fuse, and a Hall sensor connected in series; The Hall sensor outputs a voltage V at its signal output terminal. OUT To the computing module; The calculation module is used to calculate based on voltage V OUT Calculate the total current output from the power interface.

2. The circuit as described in claim 1, characterized in that, The computing module is used for: According to voltage V OUT The total current is calculated using the first calculation formula; Based on the total current and the threshold value K, determine whether the first fuse has blown; If the total current is less than the threshold value K, then the first fuse has not blown, and the total current is taken as the detection result. If the total current is greater than or equal to the threshold value K, the first fuse will blow, based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

3. The circuit as described in claim 2, characterized in that, The first calculation formula is: I IN = (V OUT -V OUT，0A )×(R1+R2+R3+R4) / (R1×S); Among them, I IN V is the total current, S is the sensitivity of the Hall sensor, and V is the total current. OUT，0A R1 is the zero-current output voltage of the Hall sensor, R2 is the resistance value of the first fuse, R3 is the resistance value of the first resistor, and R4 is the resistance value of the Hall sensor.

4. The circuit as described in claim 2, characterized in that, The second calculation formula is: I IN =(V OUT -V OUT，0A ) / S; Among them, I IN V is the total current, S is the sensitivity of the Hall sensor, and V is the total current. OUT，0A This is the zero-current output voltage of the Hall sensor.

5. The circuit as described in claim 2, characterized in that, The threshold value K: K=α×Imax×(R1+R2+R3+R4) / R1; Where Imax is the value of I when the first fuse fails to blow. IN The maximum value, α is the safety factor to prevent false triggering, 0.8 < α < 1.

0.

6. The circuit as described in claim 2, characterized in that, The threshold value K: K = β × I0; Where β is the full-scale safety factor, I0 is the full-scale range of the Hall sensor, and 0.5 < β < 0.

8.

7. The circuit as described in claim 1, characterized in that, The computing module is used for: According to voltage V OUT The total current is calculated using the first calculation formula; Based on the total current change rate and the change rate threshold, determine whether the first fuse has blown; If the rate of change of the total current is less than the rate of change threshold, then the first fuse has not blown, and the total current is taken as the detection result. If the rate of change of the total current is greater than or equal to the rate of change threshold, then the first fuse blows, based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

8. A satellite payload detection method, characterized in that, The method, applied to the computation module of the satellite payload detection circuit as described in any one of claims 1-7, comprises: According to voltage V OUT The total current is calculated using the first calculation formula; Based on the total current and the threshold value K, determine whether the first fuse has blown; If the total current is less than the threshold value K, then the first fuse has not blown, and the total current is taken as the detection result. If the total current is greater than or equal to the threshold value K, the first fuse will blow, based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

9. The method as described in claim 8, characterized in that, Also includes: According to voltage V OUT The total current is calculated using the first calculation formula; Based on the total current change rate and the change rate threshold, determine whether the first fuse has blown; If the rate of change of the total current is less than the rate of change threshold, then the first fuse has not blown, and the total current is taken as the detection result. If the rate of change of the total current is greater than or equal to the rate of change threshold, then the first fuse blows, based on the voltage V. OUT The second calculation formula is used to recalculate the total current, and the recalculated total current is used as the detection result.

10. The method as described in claim 8 or 9, characterized in that, The first calculation formula is: I IN = (V OUT -V OUT，0A )×(R1+R2+R3+R4) / (R1×S); The second calculation formula is: I IN =(V OUT -V OUT，0A ) / S; Among them, I IN V is the total current, S is the sensitivity of the Hall sensor, and V is the total current. OUT，0A R1 is the zero-current output voltage of the Hall sensor, R2 is the resistance value of the first fuse, R3 is the resistance value of the first resistor, and R4 is the resistance value of the Hall sensor.

11. An electronic device, characterized in that, include: A processor and a memory, the memory storing machine-readable instructions executable by the processor, which, when executed by the processor, perform the method as described in any one of claims 8-10.

12. A computer program product comprising a computer program / instructions, characterized in that, When the computer program / instructions are executed by the processor, they implement the steps of the method described in any one of claims 8-10.

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