A spacecraft power control circuit

Abstract

The application discloses a spacecraft power supply control circuit, comprising a power input control subcircuit, a power filter subcircuit, a power activation subcircuit, a power conversion and output subcircuit and a power collection subcircuit; the spacecraft power supply control circuit realizes the switching, confluence, external power supply and activation of various power supplies of a spacecraft, the output of an ignition signal and the like; and is suitable for fields of aerospace, power supply control and the like, and realizes the demand of the power supply in the spacecraft.

Description

Technical Field

[0001] This invention relates to the field of control circuit technology, and in particular to a spacecraft power control circuit. Background Technology

[0002] In the heating stations managed by Taiyuan No. 2 Heating Co., Ltd., the primary network return water temperature is generally around 40℃, while in some large temperature difference unit heat exchange stations, the primary network return water temperature is generally above 25℃ throughout the heating season. Therefore, installing an electric compression water source heat pump system on the primary network return water pipe can further reduce the primary network return water temperature, realizing the potential utilization of the primary network's heat, thereby extracting more heat for heat supply based on the existing primary network flow rate, and improving the company's heating area development capacity. The aerospace industry has developed rapidly in recent years, with drones and civilian aerospace also becoming very popular in addition to the military sector. Spacecraft generally have multiple power sources, using different power sources to power different modules within the spacecraft under different conditions.

[0003] The stability of the power supply is crucial to the overall stability of the spacecraft flight test, making the design of a universal, stable, and highly adaptable power supply device extremely important. It needs to meet the following criteria:

[0004] (1) Supports multiple power inputs, filters and short-circuit protects the combined power supply, and converts it into a secondary digital power supply to provide to the computer module;

[0005] (2) It outputs the combined power supply to other modules inside the spacecraft and has a control switch;

[0006] (3) It has a power activation output signal to realize power input activation;

[0007] (4) It has a power switch signal that can prevent the power input from merging;

[0008] (5) It has a power detection signal and can detect the input power voltage, the power voltage after the switch, the bus power voltage and the secondary digital power voltage output to the computer module.

[0009] (6) It has an ignition signal output and can output a large current signal in a short time.

[0010] However, existing circuits often lack the flexibility in design and cannot simultaneously meet the above requirements. Summary of the Invention

[0011] The purpose of this invention is to provide a spacecraft power control circuit to solve the technical problem of poor heat supply adaptability in existing systems.

[0012] To achieve the above objectives, the present invention provides the following technical solution: a spacecraft power control circuit, comprising a power input control sub-circuit, a power filtering sub-circuit, a power activation sub-circuit, a power conversion and output sub-circuit, and a power acquisition sub-circuit;

[0013] The input terminal of the power input control sub-circuit is connected to an external power source. It is used to receive the external power source and perform preliminary control before outputting the combined power source to the power filter sub-circuit and the power activation sub-circuit.

[0014] The input terminal of the power filtering sub-circuit is connected to the power input control sub-circuit, which is used to perform surge suppression, short circuit protection, filtering and interference suppression on the combined power supply, and output the filtered clean power supply to the power conversion sub-circuit and the output sub-circuit.

[0015] The input terminal of the power activation sub-circuit is connected to the power input control sub-circuit, which is used to receive the combined power supply and output the corresponding ignition signal and activation signal under the control of the computer module.

[0016] The input terminals of the power conversion and output sub-circuits are all connected to the power filtering sub-circuit, which is used to convert the voltage of the pure power supply and output the adapted power supply to the spacecraft's back-end module under the control of the computer module.

[0017] The input terminals of the power acquisition sub-circuit are respectively connected to the power input control sub-circuit, the power filtering sub-circuit, and the power conversion and output sub-circuit, and are used to acquire power signals from key nodes in the power input control sub-circuit, the power filtering sub-circuit, and the power conversion and output sub-circuit, and process the acquired signals and feed them back to the computer module.

[0018] In one possible implementation, the power input control subcircuit includes a carrier input power control branch, a generator input power branch, and a thermal battery input power control branch.

[0019] The carrier input power control branch includes a first PMOS transistor, a transistor, and a first optocoupler; the source (S) of the first PMOS transistor is connected to the carrier input power supply, the drain (D) of the first PMOS transistor is connected to the common side of the input power supply through a bus diode, the gate (G) of the first PMOS transistor is controlled by the transistor, the transistor is controlled by the first optocoupler, and the first optocoupler is controlled by the computer module and output to an external pull-up and pull-down voltage divider resistor of the carrier power supply;

[0020] The generator input power branch is connected to the input power common side via a bus merging diode;

[0021] The thermal battery input power control branch includes a second PMOS transistor and a second optocoupler. The source (S) of the second PMOS transistor is connected to the thermal battery input power supply, and the drain (D) of the second PMOS transistor is connected to the common side of the input power supply through a bus-combining diode. The gate (G) of the second PMOS transistor is controlled by the second optocoupler. The second optocoupler is controlled by the computer module and has no pull-up or pull-down resistors.

[0022] In one possible implementation, the power supply filter sub-circuit includes a parallel component group, a thermistor, a common-mode filter inductor, and an EMI DC filter;

[0023] The parallel component group is connected in parallel at the combined power supply and includes a bypass coupling capacitor, a filter capacitor, and a TVS transient suppression diode.

[0024] The thermistor is connected in series after the parallel component group for short-circuit protection;

[0025] The common-mode filter inductor is connected in series after the thermistor to suppress common-mode interference;

[0026] The EMI DC filter is connected in series after the common-mode filter inductor to suppress conducted interference and improve electromagnetic compatibility.

[0027] In one possible implementation, the power activation sub-circuit includes two optical MOS solid-state relays;

[0028] The optocoupler side of the optical MOS solid-state relay is connected to the computer module, and the downstream side adopts a C-type connection with a series protection resistor. The optical MOS solid-state relay defaults to a high-impedance output state. When it is turned on under the control of the computer module, it outputs the combined power supply through the series protection resistor to form the engine ignition signal and the hot battery activation signal, respectively, and outputs them through the external connector.

[0029] In one possible implementation, the power conversion and output sub-circuit includes a first DC / DC isolated power converter, a second DC / DC isolated power converter, and a TLP3547 optical MOS solid-state relay;

[0030] The first DC / DC isolated power converter is used to convert the clean power supply into digital power.

[0031] The second DC / DC isolated power converter is used to convert the pure power supply into an analog power supply;

[0032] The TLP3547 optical MOS solid-state relay is connected to the computer module on the optocoupler side and connected to the clean power supply on the downstream side. When it is turned on under the control of the computer module, it directly outputs the clean power supply.

[0033] The digital power supply, the analog power supply, and the clean power supply are all output to the spacecraft's back-end module via external connectors.

[0034] In one possible implementation, the power acquisition sub-circuit includes a resistor divider unit, an ADC analog-to-digital converter, and an integrated DC / DC isolated signal driver;

[0035] The resistor voltage divider unit is used to convert the nominal value of the acquired power signal to 2.5V. The power signal includes the source voltage of the carrier input power PMOS transistor, the drain voltage of the carrier input power PMOS transistor, the generator input power voltage, the source voltage of the thermal battery input power PMOS transistor, the drain voltage of the thermal battery input power PMOS transistor, the combined power voltage, the filtered pure power voltage, and the digital power voltage.

[0036] The positive input terminal of the ADC is connected to the voltage-divided power supply signal, and the negative input terminal is connected to the reference ground of the corresponding power supply, which is used to convert the analog voltage signal into a digital signal.

[0037] The integrated DC / DC isolation signal driver is used to isolate the computer module's SPI bus from the ADC analog-to-digital converter's SPI signal, and to convert digital power into isolated power to supply power to the ADC analog-to-digital converter.

[0038] In one possible implementation, an ignition signal output sub-circuit is also included;

[0039] The ignition signal output sub-circuit includes multiple optical MOS solid-state relays. The optical coupler side of the optical MOS solid-state relays is connected to the computer module, and the downstream side adopts a C-type connection and is connected to the pure power supply.

[0040] The ignition signal output sub-circuit supports 10 ignition signal outputs and outputs ignition signals to external connectors when turned on under the control of the computer module.

[0041] One possible implementation also includes a discrete input and output signal retrieval sub-circuit;

[0042] The discrete input and output signal sampling sub-circuit includes two four-channel AC optocouplers and four four-channel DC optocouplers.

[0043] The four-channel AC optocoupler is used to acquire discrete quantities from other external modules. The input side uses a two-wire system with a 4K ohm current-limiting resistor in series, and the isolation side is connected to the computer module.

[0044] The four-channel DC optocoupler is used to recover two thermal battery signals and 10 ignition signals. The negative terminal of the input side is connected to the power ground signal, the positive terminal is connected to the signal to be recovered through an ohmic current-limiting resistor, and the isolation side is connected to the computer module.

[0045] In one possible implementation, the voltage controlled by the pull-up and pull-down voltage divider resistors of the carrier power supply connected to the first optocoupler in the carrier input power supply control branch is around 10V.

[0046] When the carrier input power is powered on, the transistor is turned on by default, the first PMOS transistor is turned on, and the carrier input power flows in;

[0047] When the computer module controls the first optocoupler to output a low level, the transistor is turned off, the first PMOS transistor is turned off, and the carrier input power supply is turned off.

[0048] In one possible implementation, if the second optocoupler of the thermal battery input power control branch has no pull-up or pull-down resistors, the second PMOS transistor is turned off by default.

[0049] When the computer module controls the optocoupler to output a low level, the second PMOS transistor is turned on, and the thermal battery power flows in and is connected to the input power common side through the bus merging diode.

[0050] The technical effects and advantages of this invention are as follows:

[0051] The technical solution of this application can effectively control and manage multiple power sources within a spacecraft. By rationally setting components such as optocouplers and PMOS transistors, it achieves precise control of different power sources, improves the adaptability and reliability of the power system, and effectively solves the problem that existing circuit designs lack flexibility and cannot meet the control requirements of multiple power sources. This is of great significance for ensuring the stability of spacecraft flight tests. Attached Figure Description

[0052] Figure 1 A schematic diagram of a spacecraft power control circuit provided in an embodiment of this application;

[0053] Figure 2 A schematic diagram of another spacecraft power control circuit provided in an embodiment of this application. Detailed Implementation

[0054] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0055] The following disclosure provides numerous different embodiments or examples for implementing various structures of this embodiment. To simplify the disclosure of this embodiment, components and arrangements of specific examples are described below. Of course, these are merely examples and are not intended to limit the scope of this embodiment. Furthermore, reference numerals and / or letters may be repeated in different examples of this embodiment. Such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed.

[0056] Figure 1 A schematic diagram of a spacecraft power control circuit provided in this application embodiment is shown below. Figure 1 As shown, the power control circuit includes a power input control sub-circuit, a power filtering sub-circuit, a power activation sub-circuit, a power conversion and output sub-circuit, and a power acquisition sub-circuit.

[0057] The input terminal of the power input control sub-circuit is connected to an external power source. It is used to receive the external power source and perform preliminary control before outputting the combined power source to the power filter sub-circuit and the power activation sub-circuit.

[0058] The input terminal of the power filtering sub-circuit is connected to the power input control sub-circuit, which is used to perform surge suppression, short circuit protection, filtering and interference suppression on the combined power supply, and output the filtered clean power supply to the power conversion sub-circuit and the output sub-circuit.

[0059] The input terminal of the power activation sub-circuit is connected to the power input control sub-circuit, which is used to receive the combined power supply and output the corresponding ignition signal and activation signal under the control of the computer module.

[0060] The input terminals of the power conversion and output sub-circuits are all connected to the power filtering sub-circuit, which is used to convert the voltage of the pure power supply and output the adapted power supply to the spacecraft's back-end module under the control of the computer module.

[0061] The input terminals of the power acquisition sub-circuit are respectively connected to the power input control sub-circuit, the power filtering sub-circuit, and the power conversion and output sub-circuit, and are used to acquire power signals from key nodes in the power input control sub-circuit, the power filtering sub-circuit, and the power conversion and output sub-circuit, and process the acquired signals and feed them back to the computer module.

[0062] In one optional embodiment of the present invention, the power input control sub-circuit includes a carrier input power control branch, a generator input power branch, and a thermal battery input power control branch;

[0063] The carrier input power control branch includes a first PMOS transistor, a transistor, and a first optocoupler; the source (S) of the first PMOS transistor is connected to the carrier input power supply, the drain (D) of the first PMOS transistor is connected to the common side of the input power supply through a bus diode, the gate (G) of the first PMOS transistor is controlled by the transistor, the transistor is controlled by the first optocoupler, and the first optocoupler is controlled by the computer module and output to an external pull-up and pull-down voltage divider resistor of the carrier power supply;

[0064] The generator input power branch is connected to the input power common side via a bus merging diode;

[0065] The thermal battery input power control branch includes a second PMOS transistor and a second optocoupler. The source (S) of the second PMOS transistor is connected to the thermal battery input power supply, and the drain (D) of the second PMOS transistor is connected to the common side of the input power supply through a bus-combining diode. The gate (G) of the second PMOS transistor is controlled by the second optocoupler. The second optocoupler is controlled by the computer module and has no pull-up or pull-down resistors.

[0066] In one optional embodiment of the present invention, the power supply filter sub-circuit includes a parallel component group, a thermistor, a common-mode filter inductor, and an EMI DC filter;

[0067] The parallel component group is connected in parallel at the combined power supply and includes a bypass coupling capacitor, a filter capacitor, and a TVS transient suppression diode.

[0068] The thermistor is connected in series after the parallel component group for short-circuit protection;

[0069] The common-mode filter inductor is connected in series after the thermistor to suppress common-mode interference;

[0070] The EMI DC filter is connected in series after the common-mode filter inductor to suppress conducted interference and improve electromagnetic compatibility.

[0071] In an optional embodiment of the present invention, the power activation sub-circuit includes two optical MOS solid-state relays;

[0072] The optocoupler side of the optical MOS solid-state relay is connected to the computer module, and the downstream side adopts a C-type connection with a series protection resistor. The optical MOS solid-state relay defaults to a high-impedance output state. When it is turned on under the control of the computer module, it outputs the combined power supply through the series protection resistor to form the engine ignition signal and the hot battery activation signal, respectively, and outputs them through the external connector.

[0073] In an optional embodiment of the present invention, the power conversion and output sub-circuit includes a first DC / DC isolated power converter, a second DC / DC isolated power converter, and a TLP3547 optical MOS solid-state relay;

[0074] The first DC / DC isolated power converter is used to convert the clean power supply into digital power.

[0075] The second DC / DC isolated power converter is used to convert the pure power supply into an analog power supply;

[0076] The TLP3547 optical MOS solid-state relay is connected to the computer module on the optocoupler side and connected to the clean power supply on the downstream side. When it is turned on under the control of the computer module, it directly outputs the clean power supply.

[0077] The digital power supply, the analog power supply, and the clean power supply are all output to the spacecraft's back-end module via external connectors.

[0078] In one optional embodiment of the present invention, the power acquisition sub-circuit includes a resistor voltage divider unit, an ADC analog-to-digital converter, and an integrated DC / DC isolated signal driver;

[0079] The resistor voltage divider unit is used to convert the nominal value of the acquired power signal to 2.5V. The power signal includes the source voltage of the carrier input power PMOS transistor, the drain voltage of the carrier input power PMOS transistor, the generator input power voltage, the source voltage of the thermal battery input power PMOS transistor, the drain voltage of the thermal battery input power PMOS transistor, the combined power voltage, the filtered pure power voltage, and the digital power voltage.

[0080] The positive input terminal of the ADC is connected to the voltage-divided power supply signal, and the negative input terminal is connected to the reference ground of the corresponding power supply, which is used to convert the analog voltage signal into a digital signal.

[0081] The integrated DC / DC isolation signal driver is used to isolate the computer module's SPI bus from the ADC analog-to-digital converter's SPI signal, and to convert digital power into isolated power to supply power to the ADC analog-to-digital converter.

[0082] In one optional embodiment of the present invention, an ignition signal output sub-circuit is further included;

[0083] The ignition signal output sub-circuit includes multiple optical MOS solid-state relays. The optical coupler side of the optical MOS solid-state relays is connected to the computer module, and the downstream side adopts a C-type connection and is connected to the pure power supply.

[0084] The ignition signal output sub-circuit supports 10 ignition signal outputs and outputs ignition signals to external connectors when turned on under the control of the computer module.

[0085] In one optional embodiment of the present invention, a discrete input and output signal retrieval sub-circuit is further included;

[0086] The discrete input and output signal sampling sub-circuit includes two four-channel AC optocouplers and four four-channel DC optocouplers.

[0087] The four-channel AC optocoupler is used to acquire discrete quantities from other external modules. The input side uses a two-wire system with a 4K ohm current-limiting resistor in series, and the isolation side is connected to the computer module.

[0088] The four-channel DC optocoupler is used to recover two thermal battery signals and 10 ignition signals. The negative terminal of the input side is connected to the power ground signal, the positive terminal is connected to the signal to be recovered through an ohmic current-limiting resistor, and the isolation side is connected to the computer module.

[0089] In one optional embodiment of the present invention, the voltage controlled by the pull-up and pull-down voltage divider resistors of the carrier power supply connected to the first optocoupler in the carrier input power supply control branch is about 10V.

[0090] When the carrier input power is powered on, the transistor is turned on by default, the first PMOS transistor is turned on, and the carrier input power flows in;

[0091] When the computer module controls the first optocoupler to output a low level, the transistor is turned off, the first PMOS transistor is turned off, and the carrier input power supply is turned off.

[0092] In an optional embodiment of the present invention, when the second optocoupler of the thermal battery input power control branch has no pull-up or pull-down resistors, the second PMOS transistor is turned off by default.

[0093] When the computer module controls the optocoupler to output a low level, the second PMOS transistor is turned on, and the thermal battery power flows in and is connected to the input power common side through the bus merging diode.

[0094] Figure 2 A schematic diagram of another spacecraft power control circuit provided in this application embodiment is shown below. Figure 2As shown, the hardware circuit design mainly includes a power input control circuit, a power filtering circuit, a power activation circuit, a power conversion and output circuit, a power acquisition circuit, a discrete input circuit, and an ignition signal output and feedback circuit.

[0095] I. Power Input Control Circuit

[0096] The power input control circuit is mainly divided into three parts: carrier input power, generator input power, and thermal battery input power. These three external power inputs are taken from the external connector.

[0097] (1) The aircraft input power supply outputs power upon power-up and can be shut down under the control of the computer module, providing the initial power for the entire aircraft. A control circuit is built using PMOS transistors, transistors, and optocouplers. The aircraft input power supply is connected to the source (S) terminal of the PMOS transistor. The drain (D) terminal of the PMOS transistor is connected to the output side of the aircraft power supply. The gate (G) terminal of the PMOS transistor is controlled by the optocoupler, whose shutdown is controlled by the computer module. The optocoupler defaults to open-circuit (OC) output and is connected to external pull-up and pull-down resistors of the aircraft power supply, maintaining a voltage of approximately 10V. When the optocoupler is on, the transistor is on by default, the PMOS transistor is on, and the aircraft input power supply flows in through the PMOS transistor. If the computer module needs to shut down the aircraft power supply input, it controls the optocoupler to output a low level to shut down the transistor, the PMOS transistor, and the aircraft input power supply. The output aircraft power supply is connected to the common side of the input power supply via a bus-combining diode.

[0098] (2) The generator input power is uncontrolled and is directly input into the busbar diode.

[0099] (3) The thermal battery power input uses a PMOS and optocoupler to build the control circuit input. The PMOS is off by default. The power input side is connected to the source (S) terminal of the PMOS, the drain (D) terminal of the PMOS is connected to the output side of the thermal battery power supply, the gate (G) terminal of the PMOS is controlled by the optocoupler, and the optocoupler is controlled by the computer module. The optocoupler outputs an open-circuit (OC) output by default, without any pull-up or pull-down resistors, and the PMOS is off. When active, the computer controls the optocoupler to turn on, and the output low level controls the PMOS to turn on. The thermal battery power supply is connected to the common side of the input power supply through the PMOS and the merging diode is connected to the common side of the input power supply.

[0100] II. Power Activation Circuit

[0101] The power activation circuit is used for engine ignition and activating the thermal battery. It outputs a combined power supply signal. Two TLP3547 opto-MOS solid-state relays are used as the drive circuit. The optocoupler side is controlled by the computer circuit, and the subsequent stage uses a C-type connection. The default output is in a high-impedance state. When active, the optocoupler conducts, outputting the combined power supply from the subsequent stage. A protective resistor is connected in series. Based on the resistance value of the series resistor, a large current ignition signal is generated, which is connected to the external connector for engine ignition and thermal battery activation.

[0102] III. Power Input Filtering Protection Circuit

[0103] The power input filtering and protection circuit is a circuit that performs power surge protection, short circuit protection, and power filtering on the input combined power supply.

[0104] The merged power supply is connected in parallel with a bypass coupling capacitor, a filter capacitor, and a TVS for surge suppression, and a series thermistor for short-circuit protection; after passing through a common-mode filter inductor, common-mode interference is suppressed; subsequently, it is passed to an EMI DC filter to suppress conducted interference and improve electromagnetic compatibility.

[0105] IV. Power Conversion and Output Circuit

[0106] Power conversion and output circuits are used to supply power to computer modules and other modules.

[0107] (1) The filtered 28V power supply is converted into a 5V digital power supply through a DC / DC isolated power supply conversion;

[0108] (2) The filtered 28V power supply is converted into ±15V analog power supply by DC / DC isolation power supply conversion;

[0109] (3) One TLP3547 optical MOS solid-state relay is used, which is controlled by the computer module and outputs the combined power supply;

[0110] (4) The combined power supply and the converted power supply are connected to the external connector. The user provides the power required by the subsequent modules according to their own needs.

[0111] V. Ignition Signal Output Circuit

[0112] The ignition signal output circuit implements the ignition signal output, supporting 10 channels of 10A ignition signal output and feedback. It uses a TLP3547 opto-MOS solid-state relay; the optocoupler side is controlled by the computer circuit, and the subsequent stage uses a C-type connection. The default output state is high impedance; when effective, the optocoupler conducts, outputting the combined power supply from the subsequent stage to the external connector. Users can connect an external current-limiting resistor as needed.

[0113] VI. Discrete Input and Output Signal Acquisition Circuit

[0114] The discrete input and output signal acquisition circuit has two functions: first, it acquires the discrete status of other external modules and transmits the acquired discrete signals to the computer module to determine the spacecraft's flight status; second, it acquires the output activation and ignition signals to check whether the output signals are normal.

[0115] (1) The discrete input uses two four-channel AC optocouplers with a current-limiting resistor of 4K ohms. The input side of the optocoupler uses a two-wire system; the isolation side of the optocoupler is connected to the computer module to transmit the acquired discrete quantity to the computer.

[0116] (2) Output signal retrieval: Two thermal battery signals and 10 ignition signals are acquired. Four 4-channel DC optocouplers are used, with a current-limiting resistor of 4K ohms. The negative terminal of the optocoupler input is connected to the power ground signal after parallel connection, and the positive terminal is connected to the signal through the current-limiting resistor. The isolation side of the optocoupler is connected to the computer module to transmit the acquired discrete quantities to the computer.

[0117] VII. Power Acquisition Circuit

[0118] The power acquisition circuit realizes the power signal monitoring of this device, including the source and drain terminals of the carrier input power PMOS, the source and drain terminals of the generator input power, the source and drain terminals of the thermal battery power PMOS and the combined power supply, and the 5V power supply.

[0119] (1) Power acquisition is performed using an ADC. The nominal power value is converted to 2.5V by a resistor divider at the 8 power signal acquisition points. The signal is directly connected to the positive terminal of the ADC acquisition input, and the negative terminal is connected to the reference ground signal of the corresponding power supply.

[0120] (2) An integrated DC / DC isolated signal driver is used to isolate the SPI bus of the computer module and the SPI signal of the ADC, and the 5V digital power supply is converted into a 5V isolated power supply as the ADC power supply, which is grounded with the power supply under test.

[0121] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented using software plus a general-purpose hardware platform, or of course, using hardware. Based on this understanding, the above technical solutions, in essence or the parts that contribute to the related technology, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the circuits described in the various embodiments or some parts of the embodiments.

[0122] It should be understood that the terminology used herein is for the purpose of describing particular exemplary embodiments only and is not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “described” as used herein may also include the plural forms. The terms “comprising,” “including,” “containing,” and “having” are inclusive and therefore indicate the presence of the stated features, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, elements, components, and / or combinations thereof. The method steps, processes, and operations described herein are not construed as requiring them to be performed in a particular order described or illustrated unless the order of performance is explicitly indicated. It should also be understood that additional or alternative steps may be used.

[0123] The above description is merely a specific embodiment of the present invention, enabling those skilled in the art to understand or implement the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined in these embodiments may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the present invention is not to be limited to the embodiments shown in this embodiment, but is to be accorded the widest scope consistent with the principles and novel features claimed in this embodiment.

Claims

1. A spacecraft power control circuit, characterized in that, It includes a power input control subcircuit, a power filtering subcircuit, a power activation subcircuit, a power conversion and output subcircuit, and a power acquisition subcircuit. The input terminal of the power input control sub-circuit is connected to an external power source. It is used to receive the external power source and perform preliminary control before outputting the combined power source to the power filter sub-circuit and the power activation sub-circuit. The input terminal of the power filtering sub-circuit is connected to the power input control sub-circuit, which is used to perform surge suppression, short circuit protection, filtering and interference suppression on the combined power supply, and output the filtered clean power supply to the power conversion sub-circuit and the output sub-circuit. The input terminal of the power activation sub-circuit is connected to the power input control sub-circuit, which is used to receive the combined power supply and output the corresponding ignition signal and activation signal under the control of the computer module. The input terminals of the power conversion and output sub-circuits are all connected to the power filtering sub-circuit, which is used to convert the voltage of the pure power supply and output the adapted power supply to the spacecraft's back-end module under the control of the computer module. The input terminals of the power acquisition sub-circuit are respectively connected to the power input control sub-circuit, the power filtering sub-circuit, and the power conversion and output sub-circuit, and are used to acquire power signals from key nodes in the power input control sub-circuit, the power filtering sub-circuit, and the power conversion and output sub-circuit, and process the acquired signals and feed them back to the computer module.

2. The circuit according to claim 1, characterized in that, The power input control subcircuit includes a carrier input power control branch, a generator input power branch, and a thermal battery input power control branch. The carrier input power control branch includes a first PMOS transistor, a transistor, and a first optocoupler; the source (S) of the first PMOS transistor is connected to the carrier input power supply, the drain (D) of the first PMOS transistor is connected to the common side of the input power supply through a bus diode, the gate (G) of the first PMOS transistor is controlled by the transistor, the transistor is controlled by the first optocoupler, and the first optocoupler is controlled by the computer module and output to an external pull-up and pull-down voltage divider resistor of the carrier power supply; The generator input power branch is connected to the input power common side via a bus merging diode; The thermal battery input power control branch includes a second PMOS transistor and a second optocoupler. The source (S) of the second PMOS transistor is connected to the thermal battery input power supply, and the drain (D) of the second PMOS transistor is connected to the common side of the input power supply through a bus-combining diode. The gate (G) of the second PMOS transistor is controlled by the second optocoupler. The second optocoupler is controlled by the computer module and has no pull-up or pull-down resistors.

3. The circuit according to claim 1, characterized in that, The power supply filter sub-circuit includes a parallel component group, a thermistor, a common-mode filter inductor, and an EMI DC filter; The parallel component group is connected in parallel at the combined power supply and includes a bypass coupling capacitor, a filter capacitor, and a TVS transient suppression diode. The thermistor is connected in series after the parallel component group for short-circuit protection; The common-mode filter inductor is connected in series after the thermistor to suppress common-mode interference; The EMI DC filter is connected in series after the common-mode filter inductor to suppress conducted interference and improve electromagnetic compatibility.

4. The circuit according to claim 1, characterized in that, The power activation sub-circuit includes two optical MOS solid-state relays; The optocoupler side of the optical MOS solid-state relay is connected to the computer module, and the downstream side adopts a C-type connection with a series protection resistor. The optical MOS solid-state relay defaults to a high-impedance output state. When it is turned on under the control of the computer module, it outputs the combined power supply through the series protection resistor to form the engine ignition signal and the hot battery activation signal, respectively, and outputs them through the external connector.

5. The circuit according to claim 1, characterized in that, The power conversion and output sub-circuit includes a first DC / DC isolated power converter, a second DC / DC isolated power converter, and a TLP3547 optical MOS solid-state relay. The first DC / DC isolated power converter is used to convert the clean power supply into digital power. The second DC / DC isolated power converter is used to convert the pure power supply into an analog power supply; The TLP3547 optical MOS solid-state relay is connected to the computer module on the optocoupler side and connected to the clean power supply on the downstream side. When it is turned on under the control of the computer module, it directly outputs the clean power supply. The digital power supply, the analog power supply, and the clean power supply are all output to the spacecraft's back-end module via external connectors.

6. The circuit according to claim 1, characterized in that, The power acquisition sub-circuit includes a resistor voltage divider unit, an ADC analog-to-digital converter, and an integrated DC / DC isolated signal driver. The resistor voltage divider unit is used to convert the nominal value of the acquired power signal to 2.5V. The power signal includes the source voltage of the carrier input power PMOS transistor, the drain voltage of the carrier input power PMOS transistor, the generator input power voltage, the source voltage of the thermal battery input power PMOS transistor, the drain voltage of the thermal battery input power PMOS transistor, the combined power voltage, the filtered pure power voltage, and the digital power voltage. The positive input terminal of the ADC is connected to the voltage-divided power supply signal, and the negative input terminal is connected to the reference ground of the corresponding power supply, which is used to convert the analog voltage signal into a digital signal. The integrated DC / DC isolation signal driver is used to isolate the computer module's SPI bus from the ADC analog-to-digital converter's SPI signal, and to convert digital power into isolated power to supply power to the ADC analog-to-digital converter.

7. The circuit according to claim 1, characterized in that, It also includes an ignition signal output sub-circuit; The ignition signal output sub-circuit includes multiple optical MOS solid-state relays. The optical coupler side of the optical MOS solid-state relays is connected to the computer module, and the downstream side adopts a C-type connection and is connected to the pure power supply. The ignition signal output sub-circuit supports 10 ignition signal outputs and outputs ignition signals to external connectors when turned on under the control of the computer module.

8. The circuit according to claim 1, characterized in that, It also includes discrete input and output signal retrieval sub-circuits; The discrete input and output signal sampling sub-circuit includes two four-channel AC optocouplers and four four-channel DC optocouplers. The four-channel AC optocoupler is used to acquire discrete quantities from other external modules. The input side uses a two-wire system with a 4K ohm current-limiting resistor in series, and the isolation side is connected to the computer module. The four-channel DC optocoupler is used to recover two thermal battery signals and 10 ignition signals. The negative terminal of the input side is connected to the power ground signal, the positive terminal is connected to the signal to be recovered through an ohmic current-limiting resistor, and the isolation side is connected to the computer module.

9. The circuit according to claim 2, characterized in that, In the carrier input power control branch, the voltage controlled by the pull-up and pull-down voltage divider resistors of the carrier power supply connected to the first optocoupler is around 10V. When the carrier input power is powered on, the transistor is turned on by default, the first PMOS transistor is turned on, and the carrier input power flows in; When the computer module controls the first optocoupler to output a low level, the transistor is turned off, the first PMOS transistor is turned off, and the carrier input power supply is turned off.

10. The circuit according to claim 2, characterized in that, When the second optocoupler in the thermal battery input power control branch has no pull-up or pull-down resistors, the second PMOS transistor is turned off by default. When the computer module controls the optocoupler to output a low level, the second PMOS transistor is turned on, and the thermal battery power flows in and is connected to the input power common side through the bus merging diode.

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