Spacecraft carrying equipment power supply circuit

Abstract

The invention provides a power supply circuit for spacecraft carrying equipment. The power supply circuit comprises a power supply switch circuit, a surge current suppression circuit, a fuse circuit, a high-precision current detection circuit, an analog-to-digital converter, a microprocessor, an instruction driving circuit and other modules. The power supply switching circuit realizes an on-orbit switching function of carrying equipment; the surge current suppression circuit suppresses surge current when the carrying equipment is powered up to ensure that the power supply bus of the spacecraft is stable; the fuse circuit is rapidly fused when the carrying equipment power supply positive wire is directly short-circuited to the negative wire or the structural ground, and the fault is isolated; the high-precision current detection circuit, the analog-to-digital converter and the microprocessor realize high-precision detection of the power supply current of the carrying equipment, and the microprocessor compares the acquired digital quantity of the power supply current with a preset protection threshold value. And the microprocessor controls the instruction driving circuit to disconnect the carrying equipment power supply switch to protect the carrying equipment and the spacecraft power supply bus.

Description

Technical Field

[0001] The present application generally relates to a power supply circuit for equipment carried by a spacecraft. Background Art

[0002] Due to test verification needs or international cooperation, spacecraft occasionally need to carry test equipment in addition to the equipment required for normal operation. These onboard equipment need to be powered by the spacecraft and exchange information, so it is necessary to set up a power supply circuit for the onboard equipment. Figure 1 This is the schematic diagram of the existing power supply circuit for the onboard equipment. The positive and negative lines of the power supply bus are both input to the distributor. A relay is set inside the distributor to control the on and off of the positive line of the power supply bus. After passing through the relay, the positive line of the power supply bus is connected to the positive input point of the power supply socket of the onboard equipment through the power supply socket and the power supply cable. The negative line of the power supply bus is connected to the negative input point of the power supply socket of the onboard equipment through the power supply socket and the power supply cable. When the onboard equipment needs to work, the relay is closed to form a power supply circuit so that the onboard equipment can work normally.

[0003] In order to ensure the smooth operation of the spacecraft power supply bus and basic safety requirements, all electrical equipment on the spacecraft must meet electrical characteristics requirements such as surge current requirements, fault detection and isolation requirements. However, onboard equipment, especially internationally cooperated onboard equipment, generally cannot meet the electrical characteristics requirements of domestic spacecraft, and it is impossible to fully understand the electrical characteristics of onboard equipment. In the original power supply circuit, there is only a power switch composed of relays, which obviously cannot meet the electrical characteristics requirements of the spacecraft. After the onboard equipment is powered on, it is very likely that the spacecraft power supply bus cannot operate smoothly, and in serious cases, it affects the safety of the spacecraft bus. Summary of the invention

[0004] In order to ensure the smooth operation and basic safety of the spacecraft power supply bus, the present invention provides an onboard equipment power supply circuit with surge current suppression, fault detection and isolation functions. Even without a comprehensive understanding of the electrical characteristics of the onboard equipment, it can meet the electrical characteristics requirements of the spacecraft and ensure the smooth operation of the spacecraft power supply bus after the onboard equipment is powered on.

[0005] The present application provides a power supply circuit for equipment carried by a spacecraft, wherein the positive line of the power supply busbar of the spacecraft passes through the power supply circuit and is connected to the positive point of the power supply socket input of the carried equipment through the power supply socket and the power supply cable, and the negative line of the power supply busbar of the spacecraft is connected to the negative point of the power supply socket input of the carried equipment through the power supply socket and the power supply cable. The power supply circuit comprises:

[0006] Power supply switch circuit, used to realize the on-orbit switch function of the carried equipment;

[0007] Inrush current suppression circuit, used to suppress surge current when the mounted device is powered on;

[0008] The fuse circuit is used to quickly fuse and isolate the fault when the positive power supply line of the equipment is short-circuited to the negative power supply line, or the positive power supply line is directly short-circuited to the structural ground;

[0009] High-precision current detection circuit, used to detect the power supply current of the mounted equipment;

[0010] An analog-to-digital converter, used for converting a high-precision detection signal output by a high-precision current detection circuit into a digital quantity of a power supply current;

[0011] A command drive circuit for disconnecting a power supply switch circuit of an onboard device;

[0012] A microprocessor is used to compare the collected digital quantity of the power supply current with a preset protection threshold;

[0013] When the power supply current of the onboard device becomes abnormal due to the influence of the space environment or other reasons, causing the digital value of the power supply current collected by the microprocessor to exceed the protection threshold, the microprocessor control instruction drive circuit disconnects the power supply switch circuit of the onboard device.

[0014] According to the power supply circuit provided by the present application,

[0015] The power supply switch circuit includes a command power supply protection resistor R1 and a relay K1;

[0016] The surge current suppression circuit includes a first resistor R2, a second resistor R3, a third resistor R4, a fourth resistor R5, a first capacitor C1, a second capacitor C2, and a power tube Z1;

[0017] The fuse circuit includes fuse F1, which is located in the positive line of the power supply bus.

[0018] According to the power supply circuit provided by the present application,

[0019] The first resistor R2 is connected in series with the relay K1 and then connected in parallel with the second resistor R3;

[0020] The first capacitor C1 and the second capacitor C2 are connected in series and then connected in parallel with the second resistor R3;

[0021] After the first capacitor C1 and the second capacitor C2 are connected in series, one end is connected to the source of the power tube Z1, and the other end is connected to the gate of the power tube Z1 through the fourth resistor R5 and grounded through the third resistor R4.

[0022] According to the power supply circuit provided by the present application,

[0023] One end of the second resistor R3 is connected to the positive line of the power supply bus, and the other end is grounded through the third resistor R4;

[0024] After the first resistor R2 is connected in series with the relay K1, one end is connected to the positive line of the power supply bus, and the other end is grounded through the third resistor R4.

[0025] According to the power supply circuit provided in the present application, when it is necessary to power on the onboard device, the microprocessor sends a power-on instruction through the instruction driving circuit, so that the relay K1 in the power supply switch circuit is disconnected, so that the first capacitor C1 and the second capacitor C2 are charged through the third resistor R4, and the voltage across the second resistor R3 increases with the charging of the first capacitor C1 and the second capacitor C2. The voltage across the second resistor R3 is added to the gate of the power tube Z1 through the fourth resistor R5, and the gate voltage of the power tube Z1 decreases with the increase of the voltage across the second resistor R3. When the source-gate voltage reaches the turn-on voltage of the power tube Z1, the power tube Z1 is turned on to charge the internal interface capacitor of the onboard device.

[0026] According to the power supply circuit provided in the present application, when the relay K1 is turned on, the voltage across the first capacitor C1 and the second capacitor C2 is discharged through the first resistor R2, and the source-gate voltage of the power tube Z1 is reduced and thus disconnected, thereby cutting off the power of the mounted device.

[0027] According to the power supply circuit provided in the present application, in the default state, the relay K1 is disconnected and the mounted device is in an unpowered state.

[0028] According to the power supply circuit provided by the present application, the high-precision current detection circuit includes a Hall current sensor H1, a fifth resistor R6, a third capacitor C3, and an amplifier U1.

[0029] According to the power supply circuit provided in the present application, the Hall current sensor H1 collects the power supply current on the positive line of the power supply bus of the mounted equipment in a non-contact manner, and converts the power supply current into a voltage. The voltage is sent to the analog-to-digital converter through the emitter-follower circuit formed by the amplifier U1. The analog-to-digital converter converts the voltage change into a digital quantity. The microprocessor performs digital averaging filtering on the digital quantity of the power supply current, and realizes high-precision detection of the power supply current through the combination of software and hardware.

[0030] According to the power supply circuit provided in the present application, the microprocessor compares the processed digital quantity of the power supply current with a preset protection threshold. Once the digital quantity representing the power supply current of the onboard device exceeds the protection threshold, the microprocessor sends a power-off command through the instruction driving circuit to disconnect the power supply switch circuit of the onboard device.

[0031] The power supply circuit for the carried equipment proposed in this paper has a simple structure, is safe and reliable, and has low cost. It can utilize the existing analog-to-digital converters, microprocessors, and instruction drive circuits on the spacecraft. By adding switching circuits, surge current suppression circuits, fuse circuits, and high-precision current detection circuits, it can also meet the electrical characteristics requirements of the spacecraft, such as surge current requirements, fault detection and isolation requirements, without fully understanding the electrical characteristics of the carried equipment, thereby ensuring the smooth operation of the spacecraft power supply bus and basic safety requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The following will further explain the above characteristics, technical features, advantages and implementation methods of the present application in a clear and understandable manner through the description of preferred examples and in combination with the accompanying drawings. The following drawings are only intended to illustrate and explain the present application, and do not limit the scope of the present application. Among them:

[0033] Figure 1 This is a schematic diagram of the power supply circuit principle of the existing mounted equipment.

[0034] Figure 2 It is a schematic diagram of the power supply circuit principle of the mounted device of the present invention. DETAILED DESCRIPTION

[0035] In order to have a clearer understanding of the technical features, purposes and effects of the present application, the specific implementation methods of the present application are now described with reference to the accompanying drawings.

[0036] This application proposes a power supply circuit for equipment carried by a spacecraft, such as Figure 2 As shown, including:

[0037] Power supply switch circuit, used to realize the on-orbit switch function of the carried equipment;

[0038] The surge current suppression circuit is used to suppress the surge current when the onboard equipment is powered on, ensuring the stability of the spacecraft power supply bus;

[0039] The fuse circuit is used to quickly fuse and isolate the fault when the positive power supply line of the equipment is short-circuited to the negative power supply line, or the positive power supply line is directly short-circuited to the structural ground;

[0040] High-precision current detection circuit, used to achieve high-precision detection of the power supply current of the mounted equipment;

[0041] An analog-to-digital converter, used for converting a high-precision detection signal output by a high-precision current detection circuit into a digital quantity of a power supply current;

[0042] A command drive circuit for disconnecting a power supply switch circuit of an onboard device;

[0043] A microprocessor is used to compare the collected digital quantity of the power supply current with a preset protection threshold;

[0044] When the power supply current of the onboard equipment becomes abnormal due to the influence of the space environment and other reasons, causing the digital value of the power supply current collected by the microprocessor to exceed the protection threshold, the microprocessor control instruction drive circuit disconnects the power supply switch of the onboard equipment to protect the onboard equipment and the spacecraft power supply bus.

[0045] To ensure that the onboard equipment meets the spacecraft power supply interface requirements as well as fault detection and isolation requirements.

[0046] like Figure 2 As shown, the power supply switch circuit in the power supply circuit of the spacecraft-borne equipment provided by the present application includes a command power supply protection resistor R1 and a relay K1;

[0047] The surge current suppression circuit includes a first resistor R2, a second resistor R3, a third resistor R4, a fourth resistor R5, a first capacitor C1, a second capacitor C2, and a power tube Z1;

[0048] The fuse circuit includes fuse F1, which is located in the positive line of the power supply bus;

[0049] The high-precision current detection circuit includes a Hall current sensor H1, a fifth resistor R6, a third capacitor C3, and an amplifier U1.

[0050] The connection relationship of the above devices is as follows Figure 2 As shown. After the first resistor R2 is connected in series with the relay K1, it is connected in parallel with the second resistor R3. After the first capacitor C1 and the second capacitor C2 are connected in series, they are connected in parallel with the second resistor R3. After the first capacitor C1 and the second capacitor C2 are connected in series, one end is connected to the source of the power tube Z1, and the other end is connected to the gate of the power tube Z1 through the fourth resistor R5, and is grounded through the third resistor R4. One end of the second resistor R3 is connected to the positive line of the power supply bus, and the other end is grounded through the third resistor R4. After the first resistor R2 is connected in series with the relay K1, one end is connected to the positive line of the power supply bus, and the other end is grounded through the third resistor R4.

[0051] In the default state, the onboard device is not powered on. When it is necessary to power on the onboard device, the microprocessor sends a power-on instruction through the instruction drive circuit to disconnect the relay K1 in the power switch circuit, so that the first capacitor C1 and the second capacitor C2 are charged through the third resistor R4, and the voltage across the second resistor R3 slowly increases as the first capacitor C1 and the second capacitor C2 are charged. The voltage across the second resistor R3 is added to the gate of the power tube Z1 through the fourth resistor R5, and the gate voltage of the power tube Z1 decreases as the voltage across the second resistor R3 increases. When the source-gate voltage reaches the turn-on voltage of the power tube Z1, the power tube Z1 is gradually turned on to charge the internal interface capacitor of the onboard device, which can effectively suppress the surge current during the power-on process of the onboard device.

[0052] The Hall current sensor H1 collects the power supply current on the positive line of the power supply bus of the mounted equipment in a non-contact manner, and converts the power supply current into a voltage. The voltage is sent to the analog-to-digital converter through the emitter-follower circuit formed by the amplifier U1. The analog-to-digital converter converts the voltage change into a digital quantity. The microprocessor performs digital average filtering on the digital quantity of the power supply current, and realizes high-precision detection of the power supply current through the combination of software and hardware.

[0053] The microprocessor compares the processed digital quantity of the power supply current with the preset protection threshold. Once the power supply current of the onboard equipment is abnormal due to the influence of the space environment and other reasons, the digital quantity representing the power supply current of the onboard equipment exceeds the protection threshold for 3 consecutive seconds. The microprocessor sends a power-off command through the command drive circuit to turn on the relay K1, and the voltage across the first capacitor C1 and the second capacitor C2 is discharged through the first resistor R2. The power tube Z1 is disconnected, and the onboard equipment is powered off, thereby protecting the power supply safety of the onboard equipment and the spacecraft. The protection threshold and the time to trigger the protection can be modified.

[0054] The function of the fuse circuit is that once the positive power supply line of the onboard equipment is directly short-circuited to the negative power supply line or the spacecraft structure, the fuse will disconnect the positive power supply line within milliseconds to ensure the safety of the spacecraft power supply.

[0055] The power supply circuit for the carried equipment proposed in this paper has a simple structure, is safe and reliable, and has low cost. It can utilize the existing analog-to-digital converters, microprocessors, and instruction drive circuits on the spacecraft. By adding switching circuits, surge current suppression circuits, fuse circuits, and high-precision current detection circuits, it can also meet the electrical characteristics requirements of the spacecraft, such as surge current requirements, fault detection and isolation requirements, without fully understanding the electrical characteristics of the carried equipment, thereby ensuring the smooth operation of the spacecraft power supply bus and basic safety requirements.

[0056] It should be understood that although this specification is described according to various embodiments, not every embodiment contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

[0057] The above description is only an illustrative embodiment of the present application and is not intended to limit the scope of the present application. Any equivalent changes, modifications and combinations made by any technician in the field without departing from the concept and principle of the present application shall fall within the scope of protection of the present application.

Claims

1. A power supply circuit for equipment carried by a spacecraft, wherein the positive line of the power supply busbar of the spacecraft passes through the power supply circuit and is connected to the positive input point of the power supply socket of the carried equipment through the power supply socket and the power supply cable, and the negative line of the power supply busbar of the spacecraft is connected to the negative input point of the power supply socket of the carried equipment through the power supply socket and the power supply cable, and the power supply circuit comprises: Power supply switch circuit, used to realize the on-orbit switch function of the carried equipment; Inrush current suppression circuit, used to suppress surge current when the mounted device is powered on; The fuse circuit is used to quickly fuse and isolate the fault when the positive power supply line of the equipment is short-circuited to the negative power supply line, or the positive power supply line is directly short-circuited to the structural ground; High-precision current detection circuit, used to detect the power supply current of the mounted equipment; An analog-to-digital converter, used for converting a high-precision detection signal output by a high-precision current detection circuit into a digital quantity of a power supply current; A command drive circuit for disconnecting a power supply switch circuit of an onboard device; A microprocessor is used to compare the collected digital quantity of the power supply current with a preset protection threshold; When the power supply current of the onboard device becomes abnormal due to the influence of the space environment or other reasons, causing the digital value of the power supply current collected by the microprocessor to exceed the protection threshold, the microprocessor control instruction drive circuit disconnects the power supply switch circuit of the onboard device.

2. The power supply circuit according to claim 1, wherein: The power supply switch circuit includes a command power supply protection resistor and a relay; The surge current suppression circuit includes a first resistor, a second resistor, a third resistor, a fourth resistor, a first capacitor, a second capacitor, and a power tube; The fuse circuit includes fuses located in the positive line of the power supply bus.

3. The power supply circuit according to claim 2, wherein: The first resistor is connected in series with the relay and then connected in parallel with the second resistor; The first capacitor and the second capacitor are connected in series and then in parallel with the second resistor; After the first capacitor and the second capacitor are connected in series, one end is connected to the source of the power tube, and the other end is connected to the gate of the power tube through the fourth resistor and grounded through the third resistor.

4. The power supply circuit according to claim 3, wherein: One end of the second resistor is connected to the positive line of the power supply bus, and the other end is grounded through a third resistor; After the first resistor is connected in series with the relay, one end is connected to the positive line of the power supply bus, and the other end is grounded through the third resistor.

5. The power supply circuit according to claim 4, wherein: When it is necessary to power on the onboard device, the microprocessor sends a power-on command through the command driving circuit to disconnect the relay in the power supply switch circuit, thereby charging the first capacitor and the second capacitor through the third resistor. The voltage across the second resistor increases as the first capacitor and the second capacitor are charged, and the voltage across the second resistor is added to the gate of the power tube through the fourth resistor. The gate voltage of the power tube decreases as the voltage across the second resistor increases. When the source-gate voltage reaches the turn-on voltage of the power tube, the power tube is turned on to charge the internal interface capacitor of the onboard device.

6. The power supply circuit according to claim 5, wherein: When the relay K1 is turned on, the voltage across the first capacitor and the second capacitor is discharged through the first resistor, and the source-gate voltage of the power tube is reduced and disconnected, so that the mounted device is powered off.

7. The power supply circuit according to claim 5, wherein: In the default state, the relay is disconnected and the mounted device is not powered.

8. The power supply circuit according to claim 1, wherein: The high-precision current detection circuit includes a Hall current sensor, a fifth resistor, a third capacitor, and an amplifier.

9. The power supply circuit according to claim 8, wherein: The Hall current sensor collects the power supply current on the positive line of the power supply bus of the mounted equipment in a non-contact manner, and converts the power supply current into a voltage. The voltage is sent to the analog-to-digital converter through the emitter-follower circuit composed of an amplifier. The analog-to-digital converter converts the voltage change into a digital quantity. The microprocessor performs digital average filtering on the digital quantity of the power supply current, and realizes high-precision detection of the power supply current through the combination of software and hardware.

10. The power supply circuit according to claim 9, wherein: The microprocessor compares the processed digital quantity of the power supply current with the preset protection threshold. Once the digital quantity representing the power supply current of the onboard device exceeds the protection threshold, the microprocessor sends a power-off command through the instruction driving circuit to disconnect the power supply switch circuit of the onboard device.

Images