External control type intelligent power distribution circuit for spacecraft

Abstract

The invention provides an external control type intelligent power distribution circuit for a spacecraft. The external control type intelligent power distribution circuit is characterized in that a power driving control circuit has a power bus control output function; the voltage and current telemetering sampling circuit has a function of collecting voltage and current of a power bus and a function of indicating the working state of the circuit in real time; the abnormal work protection and state acquisition circuit has the functions of automatically disconnecting power output and simultaneously acquiring abnormal state voltage when the load works abnormally; the instruction latch circuit has the functions of turning an OC instruction commonly used by a spacecraft into an emitter following instruction, latching for a long time and continuously outputting; according to the invention, remote measurement signals of voltage and current of a power bus can be collected in real time to accurately monitor the working state of the load, and the system has the functions of autonomous protection and state collection during abnormal working, can accurately and timely protect the safety of the load in the abnormal working state, and can more effectively analyze the fault mode of the circuit at the same time.

Description

Technical Field

[0001] The present invention relates to the technical field of power distribution circuits, and in particular to an externally controlled intelligent power distribution circuit for spacecraft. Background Art

[0002] With the rapid development of spacecraft applications, the load power demand of spacecraft is constantly increasing, and the power bus voltage of spacecraft has gradually increased from the original 28V to 42V or 100V. At present, the load power distribution of spacecraft is controlled by relays. Different types of relays need to be selected for different power buses to redesign the circuit, which is very inconvenient. At the same time, the circuit of this control method occupies a large space, is heavy, and has low integration. The high voltage makes the relay more likely to produce arcing, which seriously affects the service life of the single machine. The traditional relay control power distribution technology can no longer adapt to the new control requirements.

[0003] There is an urgent need to design an externally controlled intelligent power distribution circuit for spacecraft that can meet the needs of different satellite buses, does not require repeated circuit design, has high integration, can collect telemetry signals of power bus voltage and current in real time to achieve accurate monitoring of the load working status, has autonomous protection and status acquisition functions in the event of abnormal operation, can accurately and timely protect load safety in abnormal working conditions, and can more effectively analyze circuit failure modes.

[0004] Patent document CN109545621A (application number: 201811307896.2) discloses a drive circuit for aerospace high-power contactors, including: a closed drive circuit and a machine shutoff drive circuit. However, the disadvantage of this patent document is that the drive circuit needs to be designed with a reverse peak elimination circuit to suppress the back electromotive force, and anti-interference design is required for electromagnetic interference. In addition, the power bus has poor adaptability, does not have a current collection function, and can automatically disconnect the power output in an abnormal working state and indicate an abnormal state.

[0005] Patent document CN105135031A (application number: 201510466076.8) discloses a spacecraft chemical thruster solenoid valve control and state acquisition circuit that uses weak current to accurately control strong current, and is only applicable to the drive control of the 28V bus voltage of the spacecraft. Compared with the patent, the present invention proposes a spacecraft external control type intelligent power distribution circuit with strong power bus adaptability, current acquisition function, command latching, autonomous disconnection of power output in abnormal working state, abnormal state indication and other functions.

[0006] Patent document CN204190351U (201420707757.X) discloses a power distribution short-circuit protection device, which can realize that when a load short-circuit occurs, the load will automatically cut off the power. However, the disadvantage of this patent document is that it uses relays as power control devices, which occupy a large space, are heavy, have low integration, and do not have current collection and other functions. Compared with this patent, the present invention proposes a power busbar with strong adaptability and high integration for spacecraft external control intelligent power distribution circuit, and has current collection function, abnormal state indication and other functions.

[0007] Patent document CN107809231A (application number: 201710876192.6) discloses a satellite-borne heater power field effect drive control and status acquisition circuit and method, which can achieve precise control of strong electricity through weak current drive. The disadvantage is that the above circuit cannot latch instructions, and the above circuit does not have functions such as telemetry current acquisition and abnormal status indication.

[0008] Patent document CN207410318U (application number: 201721425047.8) discloses an excitation circuit for increasing the driving voltage of a power field effect tube. The patent uses a single-chip microcomputer, a voltage regulator chip and a series of resistors and capacitors to realize the driving circuit of the power MOS tube, and the driving circuit is complex. Compared with the patent, the present invention proposes a spacecraft externally controlled intelligent power distribution circuit with strong power bus adaptability, high integration, current collection function, abnormal state indication and other functions. Summary of the invention

[0009] In view of the defects in the prior art, an object of the present invention is to provide an externally controlled intelligent power distribution circuit for spacecraft.

[0010] According to the present invention, an externally controlled intelligent power distribution circuit for spacecraft includes: a power drive control circuit, a voltage and current telemetry sampling circuit, an abnormal operation protection and status acquisition circuit, and an instruction latch circuit;

[0011] The power drive control circuit is connected to the voltage and current telemetry sampling circuit; the voltage and current telemetry sampling circuit is connected to the abnormal operation protection and status acquisition circuit; the abnormal operation protection and status acquisition circuit is connected to the instruction latch circuit;

[0012] The power drive control circuit is used to control the power bus output;

[0013] The voltage and current telemetry sampling circuit is used to collect the power bus voltage and current and indicate the circuit working status in real time;

[0014] The abnormal operation protection and status acquisition circuit is used to autonomously disconnect the power output when the load operates abnormally, and collect the abnormal state voltage at the same time;

[0015] The instruction latch circuit is used to flip the OC instruction, latch it for a long time and output it continuously.

[0016] Preferably, the power drive control circuit comprises: a transistor Q1, resistors R1 to R6, and PMOS tubes PQ1 to PQ2;

[0017] The resistor R1 is connected in series with the base of the transistor Q1, the resistor R2 is connected in parallel to the base terminal and the emitter terminal of the transistor Q1, the resistor R3 and the resistor R4 are connected in parallel to the resistor R5 and the resistor R6 and in series with the collector terminal of the transistor Q1, the resistor R5 is connected in series to the gate terminal of the PMOS tube PQ1, and the resistor R6 is connected in series to the gate terminal of the PMOS tube PQ2.

[0018] Preferably, in the power drive control circuit, the transistor Q1 is used to control the on / off of the power PMOS transistors PQ1 to PQ2.

[0019] Preferably, the voltage and current telemetry sampling circuit includes: voltage stabilizing diodes V1-V3, resistors R7-R15, transistors Q2-Q4 and capacitors C1-C2;

[0020] The diode V1 is connected in series with the resistor R7 and then grounded; the emitter of the transistor Q2 is connected to the resistor R8, the collector is connected to the resistor R10, and the base is connected to the base of the transistor Q3; the emitter of the transistor Q3 is connected to the resistor R9, the collector is connected to the resistor R11, one end of the sampling resistor is connected to the resistor R8, and the other end is connected to the resistor R9; the voltage regulator diode V2 is connected in parallel with the resistor R15 and in series with the resistor R14; the capacitors C1 and C2 are connected in series with the resistor R13 and the voltage regulator diode V3, and are connected to one end of the resistor R12; the collector of the voltage regulator transistor is connected to one end of the resistor R12, the emitter is connected to one end of the resistor R8, and the base is connected to one end of the resistor R11.

[0021] Preferably, in the voltage and current telemetry sampling circuit, the power bus passes through the sampling resistor and then amplifies the signal in the form of a voltage signal through a transistor and a resistor, and collects the voltage of the sampling resistor; the working current of the power bus is calculated by Ohm's law, and the power bus voltage is collected in real time by means of a resistor voltage divider.

[0022] Preferably, the abnormal operation protection and status acquisition circuit includes: comparators U1B-U1C, latch U2A, resistors R20-R24, tantalum capacitor C4, capacitor C5 and voltage stabilizing diode V4;

[0023] The resistor R22 is connected in parallel with the capacitor C5, one end of which is grounded, and the other end is connected to the resistor R21. The positive input of the comparator U1B is connected to the resistor R20 and the capacitor C4, and the output is connected to the positive input of the comparator U1C. The reset end of the latch is connected to the output end of the comparator U1A, the set end is connected to the output end of the comparator U1B, and the output end is connected to the resistor R23. The resistor R24 ​​is connected in parallel with the voltage regulator diode V4, one end of which is grounded, and the other end is connected to the resistor R23.

[0024] Preferably, when the load is working in an abnormal state, the current state sampling voltage of the abnormal operation protection and state acquisition circuit will increase abnormally, and after being compared with a fixed reference voltage through an integration circuit and a comparison circuit, a high-level instruction is output, and the power output is autonomously disconnected through a latch.

[0025] Preferably, the instruction latch circuit includes: comparators U1A, U1C, latch U2B, resistors R16-R19, resistors R25-R28, capacitors C3, C6;

[0026] After the resistor R17 is connected in parallel with the capacitor C3, one end is connected to the resistor R16 and the negative input end of the comparator U1A, and the other end is grounded; one end of the resistor R19 is grounded, and the other end is connected to the resistor R18 and the output end of the comparator U1A; after the resistor R26 is connected in parallel with the capacitor C6, one end is connected to the resistor R16 and the negative input end of the comparator U1D, and the other end is grounded; one end of the resistor R28 is grounded, and the other end is connected to the resistor R27 and the output end of the comparator U1D; the set end of the latch U2B is connected to the output of the comparator U1D, and the reset end is connected to the output of the comparator U1B.

[0027] Preferably, the instruction latch circuit realizes flipping the OC instructions commonly used by the spacecraft into shoot-and-follow instructions, and latching the instantaneous instructions into instructions for long-term continuous output.

[0028] A spacecraft provided according to the present invention includes the above-mentioned externally controlled intelligent power distribution circuit for spacecraft.

[0029] Compared with the prior art, the present invention has the following beneficial effects:

[0030] 1. The power drive control circuit realizes precise control of strong electricity through precise control of weak electricity. It has simple structure and high reliability. It also avoids the harm of relay control, which may cause arcing of relays due to high voltage and affect the service life of the single machine.

[0031] 2. The voltage and current telemetry sampling circuit has the function of collecting the power bus voltage and current, indicating the circuit working status in real time, and realizing the electrical isolation between the power line and the telemetry, thus ensuring the safety of the circuit;

[0032] 3. The command latch circuit can realize the flipping of the commonly used OC commands of spacecraft into shoot-follow commands, and latch the instantaneous commands into long-term continuous output commands, avoiding the back electromotive force generated by the relay action, thus ensuring the safety of the circuit;

[0033] 4. The abnormal working protection and status acquisition circuit can autonomously disconnect the power output when the load works abnormally, thereby realizing autonomous protection of the load in abnormal working state. It can accurately and timely protect the load safety in abnormal working state, and more effectively analyze the circuit failure mode.

[0034] 5. The present invention can collect the telemetry signals of the power bus voltage and current in real time to realize accurate monitoring of the load working status. It has the functions of autonomous protection and status collection in case of abnormal working. It can accurately and timely protect the load safety in abnormal working state, and more effectively analyze the circuit fault mode. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0036] Figure 1 It is a schematic diagram of the power drive control circuit.

[0037] Figure 2 It is a schematic diagram of the voltage and current telemetry sampling circuit.

[0038] Figure 3 It is a schematic diagram of abnormal working protection and status acquisition circuit.

[0039] Figure 4 This is a schematic diagram of the instruction latch circuit.

[0040] Figure 5 It is a schematic diagram of an externally controlled intelligent power distribution circuit for spacecraft. DETAILED DESCRIPTION

[0041] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0042] Example 1

[0043] According to the present invention, an externally controlled intelligent power distribution circuit for spacecraft includes: a power drive control circuit, a voltage and current telemetry sampling circuit, an abnormal operation protection and status acquisition circuit, and an instruction latch circuit.

[0044] The power bus is controlled to output through the power drive control circuit;

[0045] The voltage and current telemetry sampling circuit collects the power bus voltage and current, and indicates the circuit working status in real time;

[0046] The abnormal operation protection and status acquisition circuit will automatically disconnect the power output when the load is working abnormally, and collect the abnormal state voltage at the same time;

[0047] The instruction latch circuit flips the OC instructions commonly used by spacecraft into follow-up instructions, and latches them for a long time and continuously outputs them;

[0048] The power drive control circuit comprises: a transistor Q1, resistors R1-R6, and PMOS tubes PQ1-PQ2;

[0049] The resistor R1 is connected in series with the base of the transistor Q1, the resistor R2 is connected in parallel with the base terminal and the emitter terminal of the transistor Q1, the resistors R3 and R4 are connected in parallel with the resistors R5 and R6 and in series with the collector terminal of the transistor Q1, the resistor R5 is connected in series with the gate terminal of the PMOS tube PQ1, and the resistor R6 is connected in series with the gate terminal of the PMOS tube PQ2.

[0050] The power drive control circuit controls the on and off of the power PMOS tube through the triode, and realizes the precise control of the strong current through the precise control of the weak current, and has a simple structure and high reliability.

[0051] The voltage and current remote sensing sampling circuit includes: voltage stabilizing diodes V1-V3, resistors R7-R15, transistors Q2-Q4, and capacitors C1-C2;

[0052] The diode V1 is connected in series with the resistor R7 and then grounded; the emitter of the transistor Q2 is connected to the resistor R8, the collector is connected to the resistor R10, and the base is connected to the base of the transistor Q3; the emitter of the transistor Q3 is connected to the resistor R9, the collector is connected to the resistor R11, one end of the sampling resistor is connected to the resistor R8, and the other end is connected to the resistor R9; the voltage regulator diode V2 is connected in parallel with the resistor R15 and in series with the resistor R14; the capacitors C1 and C2 are connected in series with the resistor R13 and the voltage regulator diode V3, and are connected to one end of the resistor R12; the collector of the voltage regulator transistor is connected to one end of the resistor R12, the emitter is connected to one end of the resistor R8, and the base is connected to one end of the resistor R11;

[0053] The voltage and current telemetry sampling circuit, after the power bus passes through the sampling resistor, is amplified by a transistor and a resistor in the form of a voltage signal, and the voltage of the sampling resistor is collected. The working current of the power bus is calculated by Ohm's law, and the power bus voltage is collected in real time by means of a resistor voltage divider;

[0054] The abnormal operation protection and status acquisition circuit includes comparators U1B-U1C, latch U2A, resistors R20-R24, tantalum capacitor C4, capacitor C5, and voltage stabilizing diode V4;

[0055] The resistor R22 is connected in parallel with the capacitor C5, one end of which is grounded, and the other end is connected to the resistor R21. The positive input of the comparator U1B is connected to the resistor R20 and the capacitor C4, and the output is connected to the positive input of the comparator U1C. The reset end of the latch is connected to the output end of the comparator U1A, the set end is connected to the output end of the comparator U1B, and the output end is connected to the resistor R23. The resistor R24 ​​is connected in parallel with the voltage regulator diode V4, one end of which is grounded, and the other end is connected to the resistor R23.

[0056] The abnormal operation protection and state acquisition circuit is such that when the load is operating in an abnormal state, the current state sampling voltage will increase abnormally, and after being compared with a fixed reference voltage through an integration circuit and a comparison circuit, a high-level instruction is output, and the power output is autonomously disconnected through a latch, thereby realizing autonomous protection of a single machine in an abnormal working state.

[0057] The instruction latch circuit includes comparators U1A, U1C, latch U2B, resistors R16-R19, resistors R25-R28, capacitors C3, C6;

[0058] After the resistor R17 is connected in parallel with the capacitor C3, one end is connected to the resistor R16 and the negative input end of the comparator U1A, and the other end is grounded; one end of the resistor R19 is grounded, and the other end is connected to the resistor R18 and the output end of the comparator U1A; after the resistor R26 is connected in parallel with the capacitor C6, one end is connected to the resistor R16 and the negative input end of the comparator U1D, and the other end is grounded; one end of the resistor R28 is grounded, and the other end is connected to the resistor R27 and the output end of the comparator U1D; the set end of the latch U2B is connected to the output of the comparator U1D, and the reset end is connected to the output of the comparator U1B.

[0059] The command latch circuit can flip the OC command commonly used in spacecraft into a shoot-and-follow command, and latch the instantaneous command into a command for long-term continuous output, thereby avoiding the back electromotive force generated by the action of the relay and ensuring the safety of the circuit.

[0060] Example 2

[0061] Embodiment 2 is a preferred embodiment of Embodiment 1

[0062] According to the present invention, an externally controlled intelligent power distribution circuit for a spacecraft includes the following steps:

[0063] Normal working status:

[0064] Step 1, power distribution is turned on: when the power-on command inputs the OC command of 80ms, the level is flipped by comparing with the reference voltage 4, and then the control signal is latched and the 10V voltage is output through the set end of the latch U2A;

[0065] Step 2: When the control signal is 10V, the transistor works in the saturation region, and the resistors R3 and R4 form a path for voltage division, thereby controlling the conduction of the PMOS tubes PQ1 and PQ2 to achieve the output of the bus voltage.

[0066] Step 3, power distribution shutdown: the shutdown command needs to input an 80ms OC command, and the level is flipped by comparing it with the reference voltage 1, and then the control signal is latched and the 0V voltage is output through the reset end of the latch U2A;

[0067] Step 4: When the control signal is 0V, the transistor works in the cut-off region, and the resistors R3 and R4 cannot form a path, thereby controlling the PMOS tubes PQ1 and PQ2 to be turned off, thereby realizing the shutdown of the bus voltage;

[0068] Step 5: Voltage and current telemetry sampling: The bus voltage is converted into voltage through a sampling resistor and a current sampling circuit, thereby collecting current signals. The voltage signal is collected by dividing the bus voltage to enable the spacecraft to monitor the circuit working status.

[0069] Abnormal working status:

[0070] When the load is working in an abnormal state, the current state sampling voltage will increase abnormally, and will be compared with the reference voltage 2 through the abnormal protection circuit to achieve the level flip, and then compared with the reference voltage 3 through the filter circuit to achieve the level flip again, and then the signal passes through the reset end of the latch to achieve the latching of the control signal and the output of 0V voltage, so as to achieve the self-shutdown of the circuit in the abnormal state, thereby realizing the autonomous protection of the single machine in the abnormal working state;

[0071] At the same time, the voltage signal generated by the abnormal state is latched through the set end of the latch U2B to realize the abnormal state latch, and then sampled through the resistor voltage division method, so as to better realize the analysis of the abnormal working state. In addition, the abnormal working state can be cleared through the shutdown command.

[0072] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0073] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. An externally controlled intelligent power distribution circuit for a spacecraft, characterized in that: include: Power drive control circuit, voltage and current telemetry sampling circuit, abnormal operation protection and status acquisition circuit, and instruction latch circuit; The power drive control circuit is connected to the voltage and current telemetry sampling circuit; the voltage and current telemetry sampling circuit is connected to the abnormal operation protection and status acquisition circuit; the abnormal operation protection and status acquisition circuit is connected to the instruction latch circuit; The power drive control circuit is used to control the power bus output; The voltage and current telemetry sampling circuit is used to collect the power bus voltage and current and indicate the circuit working status in real time; The abnormal operation protection and status acquisition circuit is used to autonomously disconnect the power output when the load operates abnormally, and collect the abnormal state voltage at the same time; The instruction latch circuit is used to flip the OC instruction, latch it for a long time and output it continuously.

2. The externally controlled intelligent power distribution circuit for spacecraft according to claim 1, characterized in that: The power drive control circuit includes: a transistor Q1, resistors R1-R6, and PMOS tubes PQ1-PQ2; The resistor R1 is connected in series with the base of the transistor Q1, the resistor R2 is connected in parallel to the base terminal and the emitter terminal of the transistor Q1, the resistor R3 and the resistor R4 are connected in parallel to the resistor R5 and the resistor R6 and in series with the collector terminal of the transistor Q1, the resistor R5 is connected in series to the gate terminal of the PMOS tube PQ1, and the resistor R6 is connected in series to the gate terminal of the PMOS tube PQ2.

3. The externally controlled intelligent power distribution circuit for spacecraft according to claim 2, characterized in that: In the power drive control circuit, the transistor Q1 is used to control the on / off of the power PMOS transistors PQ1 to PQ2.

4. The externally controlled intelligent power distribution circuit for spacecraft according to claim 1, characterized in that: The voltage and current remote sensing sampling circuit includes: voltage stabilizing diodes V1-V3, resistors R7-R15, transistors Q2-Q4 and capacitors C1-C2; The diode V1 is connected in series with the resistor R7 and then grounded; the emitter of the transistor Q2 is connected to the resistor R8, the collector is connected to the resistor R10, and the base is connected to the base of the transistor Q3; the emitter of the transistor Q3 is connected to the resistor R9, the collector is connected to the resistor R11, one end of the sampling resistor is connected to the resistor R8, and the other end is connected to the resistor R9; the voltage regulator diode V2 is connected in parallel with the resistor R15 and in series with the resistor R14; the capacitors C1 and C2 are connected in series with the resistor R13 and the voltage regulator diode V3, and are connected to one end of the resistor R12; the collector of the voltage regulator transistor is connected to one end of the resistor R12, the emitter is connected to one end of the resistor R8, and the base is connected to one end of the resistor R11.

5. The externally controlled intelligent power distribution circuit for spacecraft according to claim 4, characterized in that: In the voltage and current telemetry sampling circuit, the power bus passes through the sampling resistor and then is amplified in the form of a voltage signal through a transistor and a resistor to collect the voltage of the sampling resistor; the working current of the power bus is calculated by Ohm's law, and the power bus voltage is collected in real time by means of a resistor voltage divider.

6. The externally controlled intelligent power distribution circuit for spacecraft according to claim 1, characterized in that: The abnormal operation protection and status acquisition circuit includes: comparators U1B-U1C, latch U2A, resistors R20-R24, tantalum capacitor C4, capacitor C5 and voltage stabilizing diode V4; The resistor R22 is connected in parallel with the capacitor C5, one end of which is grounded, and the other end is connected to the resistor R21. The positive input of the comparator U1B is connected to the resistor R20 and the capacitor C4, and the output is connected to the positive input of the comparator U1C. The reset end of the latch is connected to the output end of the comparator U1A, the set end is connected to the output end of the comparator U1B, and the output end is connected to the resistor R23. The resistor R24 ​​is connected in parallel with the voltage regulator diode V4, one end of which is grounded, and the other end is connected to the resistor R23.

7. The externally controlled intelligent power distribution circuit for spacecraft according to claim 6, characterized in that: The abnormal operation protection and state acquisition circuit, when the load is working in an abnormal state, the current state sampling voltage will increase abnormally, and after being compared with a fixed reference voltage through an integration circuit and a comparison circuit, a high-level instruction is output, and the power output is autonomously disconnected through a latch.

8. The externally controlled intelligent power distribution circuit for spacecraft according to claim 1, characterized in that: The instruction latch circuit includes: comparators U1A, U1C, latch U2B, resistors R16-R19, resistors R25-R28, capacitors C3, C6; After the resistor R17 is connected in parallel with the capacitor C3, one end is connected to the resistor R16 and the negative input end of the comparator U1A, and the other end is grounded; one end of the resistor R19 is grounded, and the other end is connected to the resistor R18 and the output end of the comparator U1A; after the resistor R26 is connected in parallel with the capacitor C6, one end is connected to the resistor R16 and the negative input end of the comparator U1D, and the other end is grounded; one end of the resistor R28 is grounded, and the other end is connected to the resistor R27 and the output end of the comparator U1D; the set end of the latch U2B is connected to the output of the comparator U1D, and the reset end is connected to the output of the comparator U1B.

9. The externally controlled intelligent power distribution circuit for spacecraft according to claim 8, characterized in that: The instruction latch circuit can realize the flipping of the OC instructions commonly used by the spacecraft into the shoot-and-follow instructions, and can latch the instantaneous instructions into the instructions that are continuously output for a long time.

10. A spacecraft, characterized in that: Including the externally controlled intelligent power distribution circuit for spacecraft as described in any one of claims 1 to 9.

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