Isolated bus system for spaceflight power supply, control method thereof and spaceflight power supply system

Abstract

The invention belongs to the technical field of spaceflight power supplies, and provides an isolated bus system for a spaceflight power supply, a control method of the isolated bus system and a spaceflight power supply system.The isolated bus system comprises a direct current bus, a detection circuit, a control device, an S3R circuit, an MPPT circuit and a storage battery circuit; the detection circuit detects voltage and current of the DC bus and transmits the voltage and current to the control device. And the control device selects a working mode according to the voltage and current of the direct current bus, and controls the S3R circuit, the MPPT circuit and the storage battery circuit according to the working mode. According to the isolated bus system, the utilization efficiency of a solar panel of a spaceflight power supply is improved, and meanwhile, the size of the spaceflight power supply is integrally reduced.

Description

Technical Field

[0001] This disclosure belongs to the field of aerospace power technology, and particularly relates to an isolation bus system for aerospace power supply, its control method, and an aerospace power supply system. Background Technology

[0002] In existing spacecraft power supply isolation bus architecture designs, most spacecraft with medium to high power outputs employ S3R (sequential switching shunt regulator) technology to meet the overall power regulation needs of the spacecraft. However, during periods of sunlight, due to power regulation requirements, a portion of the electrical energy from the spacecraft's solar panels is diverted by the isolation bus and directly converted into heat energy, which is then consumed on the solar panels. Especially in the early stages of a spacecraft's lifespan, when the solar panels have high power generation efficiency, the proportion of electrical energy wasted as heat is even higher, resulting in lower overall efficiency of the solar panel system. Summary of the Invention

[0003] To address the aforementioned issues, this disclosure provides an isolation bus system for aerospace power supplies, its control method, and the aerospace power supply system itself. Through innovative designs of the S3R and MPPT circuits, the overall size and weight of the aerospace power supply system are significantly reduced. Furthermore, the operating mode of the isolation bus system is selected based on the voltage and current of the DC bus, and the system is controlled according to this operating mode, thereby improving the efficiency of the aerospace power supply's solar cell system.

[0004] In one aspect, this disclosure provides an isolated bus system for aerospace power supplies, including a DC bus, a detection circuit, a control device, an S3R circuit, an MPPT circuit, and a battery circuit; The detection circuit detects the voltage and current of the DC bus and transmits the data to the control device. The control device selects the operating mode based on the voltage and current of the DC bus, and controls the S3R circuit, MPPT circuit and battery circuit according to the operating mode.

[0005] Furthermore, The input of the isolation bus system is connected to the solar panels, and the output of the isolation bus system is connected to the electronic system.

[0006] Furthermore, The battery circuit is connected in parallel to the DC bus and includes a power switch transistor M4 and a battery B1. The drain of the power switch transistor M4 is connected to the DC bus, the source of the power switch transistor M4 is connected to the positive terminal of the battery B1, and the negative terminal of the battery B1 is grounded.

[0007] Furthermore, The S3R circuit is connected in parallel to the DC bus and includes a power switch M1; the drain of the power switch M1 is connected to the DC bus, and the source is grounded.

[0008] Furthermore, The MPPT circuit is connected in parallel to the DC bus and includes power switch M2, power switch M3 and inductor L1. The drain of power switch M3 is connected in series with inductor L1 and then connected across the two ends of the S3R circuit connection point on the DC bus. The source of power switch M3 is connected to the drain of power switch M2 and the source of power switch M2 is grounded.

[0009] Furthermore, The isolation bus system also includes a filter circuit; the filter circuit is connected in parallel to the DC bus, with the parallel connection point located between the MPPT circuit and the battery circuit.

[0010] Secondly, based on the same inventive concept, this disclosure also provides a control method for controlling the aforementioned isolation bus system. The operating mode of the isolation bus system is selected based on the voltage and current of the DC bus, and the isolation bus system is controlled according to the operating mode.

[0011] Furthermore, Controlling the isolation bus system according to the operating mode includes: During the sunshine period, the output power of the solar panel is sufficient to meet the power consumption of the electronic system and there is a margin. When the battery B1 has not reached the charging limit, the control device turns off power switch M1, power switch M2 and power switch M3, and turns on power switch M4 to charge battery B1. During the sunshine period, the output power of the solar panel is greater than the power required by the battery B1 and the electronic system. The control device turns off the power switch M2, power switch M3 and power switch M4, and performs PWM control on the power switch M1 to keep the DC bus voltage VBUS stable. During the sunshine period, the output power of the solar panel cannot meet the power demand of battery B1 and electronic system. The control device turns off power switch M1, power switch M2 and power switch M3 and turns on power switch M4. During the sunshine period, the output power of the solar panel cannot meet the power demand of the battery B1 and the electronic system, and the output current of the solar panel and the discharge current of the battery B1 are greater than the set value. The control device turns off the power switch M1 and turns on the power switch M4, and performs PWM control on the power switches M2 and M3 to enable the solar panel to output maximum power.

[0012] Thirdly, based on the same inventive concept, this disclosure also provides an aerospace power system, including multiple parallel isolated bus systems as described above.

[0013] Furthermore, When it is necessary to disconnect a certain isolation bus system from the aerospace power system, turn on power switch M1 and turn off power switch M2, power switch M3, and power switch M4.

[0014] Compared with the prior art, this disclosure provides an isolated bus system for aerospace power supplies, which has the following advantages: The innovative design of the S3R and MPPT circuits significantly reduces the overall size and weight of the aerospace power system. Simultaneously, the operating mode of the isolation bus system is selected based on the DC bus voltage and current, and the isolation bus system is controlled according to this operating mode, thereby improving the efficiency of the aerospace power solar cell system.

[0015] Other features and advantages of this disclosure will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the disclosure. The objects and other advantages of this disclosure may be realized and obtained by means of the structures pointed out in the description, claims and drawings. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 A topology diagram of an isolated bus system for aerospace power supply according to an embodiment of the present disclosure is shown. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of this disclosure clearer, the technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this disclosure, and not all embodiments. Based on the embodiments of this disclosure, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this disclosure.

[0019] like Figure 1As shown, an isolated bus system for aerospace power supply according to an embodiment of this disclosure includes a DC bus, a detection circuit 2, a control device 3, an S3R circuit, an MPPT (Maximum power point tracking) circuit, and a battery circuit.

[0020] The detection circuit 2 detects the voltage VBUS and current of the DC bus and transmits them to the control device 3.

[0021] The control device 3 selects the operating mode based on the voltage VBUS and the current, and controls the S3R circuit, MPPT circuit and battery circuit according to the operating mode.

[0022] The S3R circuit is connected in parallel to the DC bus and includes a power switch M1. The power switch M1 is preferably a power device such as an IGBT, MOSFET, SiC MOSFET, or GaN HEMT. The drain of the power switch M1 is connected to the DC bus, and its source is grounded.

[0023] The MPPT circuit is connected in parallel to the DC bus and includes power switching transistors M2 and M3 and inductor L1. Power switching transistors M2 and M3 are preferably power devices such as IGBTs, MOSFETs, SiC MOSFETs, or GaN HEMTs. The drain of power switching transistor M3 is connected in series with inductor L1 and then across the two ends of the S3R circuit connection point on the DC bus. The source of power switching transistor M3 is connected to the drain of power switching transistor M2, and the source of power switching transistor M2 is grounded.

[0024] The battery circuit is connected in parallel to the DC bus and includes a power switch transistor M4 and a battery B1. The drain of the power switch transistor M4 is connected to the DC bus, the source of the power switch transistor M4 is connected to the positive terminal of the battery B1, and the negative terminal of the battery B1 is grounded.

[0025] Furthermore, the isolation bus system also includes a filter circuit connected in parallel to the DC bus, with the parallel connection point located between the MPPT circuit and the battery circuit. The filter circuit is preferably a capacitor C1.

[0026] Furthermore, the input end of the isolation bus system is connected to the solar panel 1, and the output end of the isolation bus system is connected to the electronic system 4.

[0027] The solar panel 1 consists of a photovoltaic (PV) device array, which comprises n parallel-connected PV device groups, where n is a natural number. Each PV device group consists of several PV devices SG1 connected in series with a power diode.

[0028] Electronic system 4 is connected after the access point of power switch M4 on the DC bus.

[0029] The aerospace power supply isolation bus system of this disclosure has the following operating modes: 1) Charging mode: During the sunshine period, the output power of the solar panel 1 is sufficient to meet the power consumption of the electronic system 4 with a margin, and the battery B1 does not reach the charging limit condition.

[0030] Control device 3 shuts off power switches M1, M2, and M3, and turns on power switch M4 to charge battery B1. At this time, the output current of solar panel 1 flows directly to battery B1 and electronic system 4.

[0031] 2) Traffic splitting mode: During periods of sunshine, the output power of the solar panel 1 exceeds the power required by the battery B1 and the electronic system 4.

[0032] Control device 3 shuts off power switches M2, M3, and M4, and performs PWM (Pulse Width Modulation) control on power switch M1 to keep the DC bus voltage VBUS stable and prevent overcharging of battery B1. At this time, part of the output current of solar panel 1 flows to battery B1 and electronic system 4, and part is released to GND through power switch M1.

[0033] 3) Combined power supply mode: During periods of sunshine, the output power of solar panel 1 cannot meet the power requirements of battery B1 and electronic system 4.

[0034] Control device 3 shuts off power switches M1, M2, and M3, and turns on power switch M4. At this time, all the output current of solar panel 1 flows to electronic system 4, and is supplemented by battery B1 to supply power to the DC bus.

[0035] 4) MPPT mode: During periods of sunshine, the output power of solar panel 1 cannot meet the power requirements of battery B1 and electronic system 4, and the output current of solar panel 1 and the discharge current of battery B1 exceed the set values. These set values ​​are sufficient to meet the power requirements of electronic system 4.

[0036] Control device 3 turns off power switch M1 and turns on power switch M4, and performs PWM control on power switches M2 and M3 to enable the solar panel to output maximum power. At this time, part of the current from the solar panel 1 is directly supplied to the battery B1 and electronic system 4 through the DC bus, and part is supplied to the battery B1 and electronic system 4 through power switches M2 and M3 and inductor L1.

[0037] This disclosure also provides a control method for controlling the aerospace power supply isolation bus system of the aforementioned embodiments. The method selects the operating mode of the isolation bus system based on the voltage and current of the DC bus, and controls the isolation bus system according to the operating mode: During periods of sunshine, if the output power of the solar panel 1 is sufficient for the electronic system 4 and the battery B1 has not reached its charging limit, the control device 3 turns off power switches M1, M2, and M3, and turns on power switch M4; During periods of sunshine, if the output power of the solar panel 1 is greater than the power required by the battery B1 and the electronic system 4, the control device 3 turns off power switches M2 and M3, and turns on power switch M4. When power switch M4 is turned off, PWM control is applied to power switch M1 to keep the DC bus voltage VBUS stable. During the solar irradiation period, the output power of solar panel 1 cannot meet the power demand of battery B1 and electronic system 4. Therefore, control device 3 turns off power switches M1, M2, and M3, and turns on power switch M4. During the solar irradiation period, the output power of solar panel 1 cannot meet the power demand of battery B1 and electronic system 4, and the output current of the discharge current of solar panel 1 and battery B1 is greater than the set value. Therefore, control device 3 turns off power switch M1, turns on power switch M4, and applies PWM control to power switches M2 and M3.

[0038] Based on the same inventive concept, this disclosure also provides an aerospace power system, including multiple parallel isolated bus systems. When it is necessary to disconnect a certain isolated bus system from the aerospace power system, power switch M1 is turned on, and power switches M2, M3, and M4 are turned off.

[0039] The isolation bus system and aerospace power system described in this disclosure can realize the S3R (Sequential Switching) regulation mode of solar panels, and can also make better use of the electrical energy of the spacecraft's solar panels in the early stage of its lifespan, so that the excess electrical energy of the solar panel system can be utilized as much as possible, thereby improving the utilization efficiency of the solar panels. The innovative design of the S3R circuit and MPPT circuit further reduces the overall size and weight of the aerospace power system.

[0040] Although the present disclosure has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present disclosure.

Claims

1. An isolation bus system for aerospace power supplies, characterized in that, The isolation bus system includes a DC bus, a detection circuit, a control device, an S3R circuit, an MPPT circuit, and a battery circuit. The detection circuit detects the voltage and current of the DC bus and transmits the data to the control device. The control device selects the operating mode based on the voltage and current of the DC bus, and controls the S3R circuit, MPPT circuit and battery circuit according to the operating mode.

2. The isolation busbar system according to claim 1, characterized in that, The input of the isolation bus system is connected to the solar panels, and the output of the isolation bus system is connected to the electronic system.

3. The isolation busbar system according to claim 2, characterized in that, The battery circuit is connected in parallel to the DC bus and includes a power switch transistor M4 and a battery B1. The drain of the power switch transistor M4 is connected to the DC bus, the source of the power switch transistor M4 is connected to the positive terminal of the battery B1, and the negative terminal of the battery B1 is grounded.

4. The isolation busbar system according to any one of claims 1-3, characterized in that, The S3R circuit is connected in parallel to the DC bus and includes a power switch M1; the drain of the power switch M1 is connected to the DC bus, and the source is grounded.

5. The isolation busbar system according to claim 4, characterized in that, The MPPT circuit is connected in parallel to the DC bus and includes power switch M2, power switch M3 and inductor L1. The drain of power switch M3 is connected in series with inductor L1 and then connected across the two ends of the S3R circuit connection point on the DC bus. The source of power switch M3 is connected to the drain of power switch M2 and the source of power switch M2 is grounded.

6. The isolation busbar system according to claim 5, characterized in that, The isolation bus system also includes a filter circuit; the filter circuit is connected in parallel to the DC bus, with the parallel connection point located between the MPPT circuit and the battery circuit.

7. A control method for controlling an isolation bus system as described in any one of claims 3-6, characterized in that, The operating mode of the isolation bus system is selected based on the voltage and current of the DC bus, and the isolation bus system is controlled according to the operating mode.

8. The control method according to claim 7, characterized in that, Controlling the isolation bus system according to the operating mode includes: During the sunshine period, the output power of the solar panel is sufficient to meet the power consumption of the electronic system and there is a margin. When the battery B1 has not reached the charging limit, the control device turns off power switch M1, power switch M2 and power switch M3, and turns on power switch M4 to charge battery B1. During the sunshine period, the output power of the solar panel is greater than the power required by the battery B1 and the electronic system. The control device turns off the power switch M2, power switch M3 and power switch M4, and performs PWM control on the power switch M1 to keep the DC bus voltage VBUS stable. During the sunshine period, the output power of the solar panel cannot meet the power demand of battery B1 and electronic system. The control device turns off power switch M1, power switch M2 and power switch M3 and turns on power switch M4. During the sunshine period, the output power of the solar panel cannot meet the power demand of the battery B1 and the electronic system, and the output current of the solar panel and the discharge current of the battery B1 are greater than the set value. The control device turns off the power switch M1 and turns on the power switch M4, and performs PWM control on the power switches M2 and M3 to enable the solar panel to output maximum power.

9. An aerospace power system, characterized in that, The aerospace power system includes multiple parallel isolated bus systems as described in any one of claims 3-6.

10. The aerospace power system according to claim 9, characterized in that, When it is necessary to disconnect a certain isolation bus system from the aerospace power system, turn on power switch M1 and turn off power switch M2, power switch M3, and power switch M4.

Images