CN111525545A - Grid-connected power supply system and method for two cabins - Google Patents

Abstract

The invention discloses a two-cabin grid-connected power supply system and a method, wherein the system comprises a first cabin and a second cabin, wherein the first cabin comprises a first storage battery pack, the second cabin comprises a second storage battery pack, the second cabin further comprises a grid-connected control unit, and a first storage battery pack bus and a second storage battery pack bus are connected through the grid-connected control unit. According to the invention, the optimal configuration and fault reconstruction of the electric energy of the two cabin sections are realized through a grid-connected power supply technology, the management capability and the intelligent level of the power supply mode between the two cabin sections are improved, and the adaptability and the reliability of a spacecraft power supply system are improved.

Description

Grid-connected power supply system and method for two cabins

technical field

The invention relates to the technical field of spacecraft power supply, in particular to a grid-connected power supply system and method for two cabin sections.

Background technique

With the development of aerospace technology, multi-cabin combined spacecraft has become a common technical solution for complex mission spacecraft such as space stations, manned spaceflight, and deep space exploration. Usually, each cabin has an independent power supply system to supply power to the load, which can be operated independently or connected to the grid. The introduction of grid-connected power supply technology enhances the flexibility and reliability of the spacecraft power system, and the subsequent multi-module grid-connected power supply system design and power management strategies have gradually become a new research direction.

At present, the grid-connected power supply system of multi-cabin spacecraft at home and abroad is connected to the grid-connected controller in series between the fully-regulated busbars to realize grid-connected power supply, and does not have the function of supplementary charging for the battery pack; the power management strategy is still in the exploratory stage, showing the power supply It is characterized by a single model, weak self-service management capability, and low level of intelligence. The two-way grid-connected power supply between the 120V busbar and the 28V busbar can be realized between the busbars of the USOS module in the US part of the International Space Station and the FGB module in the Russian part through the grid-connected controllers ARCU and RACU. Power supply: After the USOS is assembled, the output power of the FGB battery array decreases due to occlusion, and the USOS supplies power to the FGB through the ARCU. Regardless of light or ground shadow, the power provided by the grid-connected controller is used preferentially, and the energy dispatching scheme is single; the service cabin of CE-5T1 supplies power to the returner in one direction through the control switch and the inter-device cable in the combined mode. Before the separation, the returner was transferred to the internal power through the ground remote control command; a one-way grid-connected controller was designed between the load bus and the platform bus inside the GF-3 satellite. Only when the platform bus failed, the load bus passed the grid-connected controller. Provides power to the platform bus. For spacecraft with comparable power supply capabilities, there is no successful case to learn from how to independently realize the optimal configuration and fault reconstruction of the electric energy of the two modules through the grid-connected power supply technology.

SUMMARY OF THE INVENTION

The present invention proposes a grid-connected power supply system and method for two compartments, aiming to independently realize the optimal configuration and fault reconstruction of the electric energy of the two compartments through the grid-connected power supply technology, so as to improve the management capability and intelligence of the power supply mode between the two compartments. level, increasing the adaptability and reliability of the spacecraft power system.

In order to achieve the above object, the present invention provides a grid-connected power supply system with two cabin sections, the system includes a first cabin section and a second cabin section, wherein the first cabin section includes a first solar cell array, and A first power supply/charging current shunt adjustment module connected to the first solar cell array, a first discharge adjustment module connected to the first power supply/charge current distribution adjustment module, and a first battery pack, and the second cabin section includes a first two solar cell arrays, a second power supply/charging shunt adjustment module connected to the second solar cell array, a second discharge adjustment module connected to the second power supply/charge shunt adjustment module, and a second battery pack, the The second cabin section further includes a grid-connected control unit, and the first battery pack busbar and the second battery pack busbar are connected through the grid-connected control unit;

The grid-connected control unit includes a unidirectional isolated buck-boost converter DC/DC1 and a unidirectional isolated buck-boost converter DC/DC2, and the input end of the converter DC/DC1 is provided with a fuse F1, switch C1, the output end is provided with an isolation diode D1, which is used for the second compartment to supply power to the first compartment, the input end of the converter DC/DC2 is provided with a fuse F2, a switch C2, and the output The end is provided with an isolation diode D2, which is used for the first cabin section to supply power to the second cabin section.

In order to achieve the above object, the present invention also proposes a grid-connected power supply method for two cabins, the method is applied to the above-mentioned system, and the method includes the following steps:

When the first cabin section and the second cabin section are in a combined flight mode, obtain a first battery pack voltage U1 and a second battery pack voltage U2;

Comparing the first battery pack voltage U1 with the preset normal value lower limit voltage K1, and comparing the second battery pack voltage U2 with the preset normal value lower limit voltage K2;

According to the comparison result, a power supply strategy between the first cabin section and the second cabin section is configured by the grid-connected control unit, wherein the power supply strategy includes a normal energy mode, a first fault energy mode, and a third Two failure energy modes.

A further technical solution of the present invention is that, according to the comparison result, the step of configuring the power supply strategy between the first cabin section and the second cabin section through the grid-connected control unit includes:

If U1>K1, and U2>K2, enter the normal energy mode;

If U1≤K1, enter the first fault energy mode;

If U2≤K2, enter the second fault capable power supply mode.

A further technical solution of the present invention is that the step of entering the normal energy mode includes:

If none of the first solar cell arrays are split, and the number of splits in the second solar cell array in the split state is greater than 2, the grid connection control unit controls the second module to flow to the first solar cell. cabin power supply;

If none of the second solar cell arrays is shunted, and the number of divisions in the first solar cell array in the shunting state is greater than 2, the grid-connected control unit controls the first compartment to the second cabin power supply;

If the SAm array of the first solar cell array is shunted, or the second solar cell array is not shunted, the first cabin section and the second cabin section are independently powered;

If the SAn array of the second solar cell array is shunted, or the first cell array is not shunted, the second cabin section and the first cabin section are powered independently.

A further technical solution of the present invention is that the step of entering the first fault energy mode includes:

If the voltage U2 of the second battery pack is lower than the preset grid-connected turn-on voltage lower limit K4, turn off the loads connected to the first battery pack and the second battery pack;

If U2>K4, control the second cabin section to supply power to the first cabin section through the grid-connected control unit;

If U1>K1, or U2≤K4, the grid-connected control unit controls the second cabin section to stop supplying power to the first cabin section.

A further technical solution of the present invention is that the step of entering the second fault energy mode includes:

If the voltage U1 of the first battery pack is lower than the preset grid-connected turn-on voltage lower limit K3, turn off the loads connected to the first battery pack and the second battery pack;

If U1>K3, control the first cabin section to supply power to the second cabin section through the grid-connected control unit;

If U2>K4, or U1≤K3, the grid connection control unit controls the first cabin section to stop supplying power to the second cabin section.

A further technical solution of the present invention is that when the first cabin section and the second cabin section are in the combined flight mode, before the step of acquiring the first battery pack voltage U1 and the second battery pack voltage U2, the step further includes:

determining whether the first cabin segment and the second cabin segment are in a separate flight mode or a combined flight mode;

If the first cabin section and the second cabin section are in the independent flight mode, turning off the grid-connected control unit;

If the first cabin section and the second cabin section are in a combined flight mode, the step of obtaining the first battery pack voltage U1 and the second battery pack voltage U2 is performed.

A further technical solution of the present invention is that when the fuse C2 is closed and the fuse C1 is opened, the second cabin section supplies power to the first cabin section; when the fuse C1 is closed, the fuse C2 is turned off When on, the first cabin section supplies power to the second cabin section.

A further technical solution of the present invention is that the working states of the arrays of the first solar cell array and the second solar cell array are determined by detecting the output voltages of the arrays at all levels. When the output voltage of the arrays is lower than a preset gate When the limit value is K5, it is determined that this level of split array works in the shunt mode.

A further technical solution of the present invention is that the use points of the output voltages of the sub-arrays at all levels are set at the access points of the positive and negative terminals of the sub-array power supply at the inlet end of the corresponding power supply/charging shunt adjustment module.

The beneficial effects of the two-cabin grid-connected power supply system and method of the present invention are:

1. A grid-connected control unit is set between the busbar of the first battery pack and the busbar of the second battery pack, which can not only supply power to the load but also charge the battery pack;

2. It can identify normal energy mode and fault energy mode and control it autonomously, realize the sharing and optimization of energy between cabins, and increase the adaptability and reliability of the spacecraft power system;

3. In the normal energy mode, the grid-connected power supply for other cabins is only allowed when the solar cell array in this cabin has excess energy for shunting, which increases the utilization rate of solar cell array power and avoids the need for batteries in this cabin. Group unnecessary discharge;

4. In the fault energy mode, as long as the battery pack in this cabin is capable, it will supply power to the faulty cabin through the grid-connected control unit. On the premise of ensuring the load power demand, the troubleshooting time can be obtained as much as possible, which improves the power supply system of the whole device. reliability;

5. The present invention does not need to distinguish between the lighted area and the shadowed area, the control method is simple, and the adaptability is strong.

Description of drawings

Fig. 1 is the energy system structure diagram of the preferred embodiment of the grid-connected power supply system of two cabins according to the present invention;

FIG. 2 is a schematic flow chart of a preferred embodiment of the grid-connected power supply method for two cabins according to the present invention;

Figure 3 is a flow chart of normal/failure energy mode switching;

Fig. 4 is the energy dispatch flow chart under the normal energy mode;

Fig. 5 is the energy dispatch flow chart under the first fault energy mode;

Fig. 6 is the energy dispatch flow chart under the second fault energy mode;

The realization, functional characteristics and advantages of the present invention will be further described with reference to the accompanying drawings in conjunction with the embodiments.

Detailed ways

It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention.

Considering that the current power management strategy used for power supply between multi-cabin spacecraft mainly has the shortcomings of single power supply mode, weak independent management capability, and low level of intelligence, the present invention proposes a grid-connected power supply for two cabin sections. The invention relates to a system and a method, in particular to a grid-connected power supply system for two cabins and an autonomous energy scheduling method.

The technical scheme adopted by the present invention is mainly: in the combined flight mode, the grid-connected control unit is connected between the battery bus bars to realize grid-connected power supply between the two cabin sections; It can identify the normal energy mode (battery bank voltage is higher than the lower voltage limit) and the fault energy mode (battery bank voltage is lower than the lower voltage limit) and carry out autonomous control; the normal energy mode can be controlled by sufficient energy compartments (the number of shunt arrays > 2) The busbar supplies power independently to the busbars of the energy-deficient cabins (all the arrays are not divided) to improve the utilization rate of the solar array; in the fault energy mode, the normal cabin can be used for emergency response to the faulty cabin under the premise that the voltage of the battery bank is higher than the grid-connected turn-on voltage. Power supply to win troubleshooting time for emergency power supply. In this way, the sharing and optimization of energy between the modules is realized, and the adaptability and reliability of the spacecraft power system are improved.

Specifically, please refer to FIG. 1 , which is a structural diagram of an energy system of a preferred embodiment of a two-cabin grid-connected power supply system according to the present invention.

As shown in FIG. 1 , in this embodiment, the grid-connected power supply system for two cabin sections includes a first cabin section and a second cabin section, wherein the first cabin section includes a first solar cell array, a The first power supply/charging shunt adjustment module connected to the solar cell array, the first discharge adjustment module and the first battery group connected to the first power supply/charge shunt adjustment module, supply power for the fully regulated bus load load1_1 and the battery bus load load2_1 .

The second cabin section includes a second solar cell array, a second power supply/charging shunt adjustment module connected to the second solar cell array, and a second discharge adjustment module connected to the second power supply/charge shunt adjustment module and the second battery pack to supply power for the fully regulated bus load load1_2 and the battery bus load load2_2.

The second cabin section further includes a grid-connected control unit, and the first battery pack busbar and the second battery pack busbar are connected through the grid-connected control unit.

The grid-connected control unit includes a unidirectional isolated buck-boost converter DC/DC1 and a unidirectional isolated buck-boost converter DC/DC2, and the input end of the converter DC/DC1 is provided with a fuse F1, switch C1, the output end is provided with an isolation diode D1, which is used for the second compartment to supply power to the first compartment, the input end of the converter DC/DC2 is provided with a fuse F2, a switch C2, and the output The end is provided with an isolation diode D2, which is used for the first cabin section to supply power to the second cabin section.

When the first cabin section and the second cabin section fly alone, they can both work under the orbital conditions of alternating light and shadow, and can meet the power supply requirements of different types of loads, and the grid-connected control unit is turned off. The sub-arrays in the first cabin section are gradually shunted from the mth stage (SAm) to the first stage, and the sub-arrays in the second cabin section are gradually diverted from the nth stage (SAn) to the first stage.

In the combined flight mode of the first cabin section and the second cabin section, the grid connection control unit is connected between the first battery pack busbar and the second battery pack busbar to realize grid-connected power supply between the two cabin sections. The working modes of grid-connected power supply include the following three: the first compartment supplies power to the second compartment (C2 is closed, C1 is disconnected, and DC/DC2 works), and the second compartment supplies power to the first compartment (C1 is closed, C2 Disconnected, DC/DC1 works), the first compartment and the second compartment are independently powered (C1, C2 are disconnected, DC/DC1, DC/DC2 do not work).

The beneficial effects of the two-cabin grid-connected power supply system of the present invention are:

1. A grid-connected control unit is set between the busbar of the first battery pack and the busbar of the second battery pack, which can not only supply power to the load but also charge the battery pack;

2. It can identify normal energy mode and fault energy mode and control it autonomously, realize the sharing and optimization of energy between cabins, and increase the adaptability and reliability of the spacecraft power system;

3. In the normal energy mode, the grid-connected power supply for other cabins is only allowed when the solar cell array in this cabin has excess energy for shunting, which increases the utilization rate of solar cell array power and avoids the need for batteries in this cabin. Group unnecessary discharge;

4. In the fault energy mode, as long as the battery pack in this cabin is capable, it will supply power to the faulty cabin through the grid-connected control unit. On the premise of ensuring the load power demand, the troubleshooting time can be obtained as much as possible, which improves the power supply system of the whole device. reliability;

5. The present invention does not need to distinguish between the lighted area and the shadowed area, the control method is simple, and the adaptability is strong.

Please refer to FIG. 2 , in order to achieve the above-mentioned purpose, the present invention also proposes a grid-connected power supply method for two compartments. FIG. 2 is a schematic flowchart of a preferred embodiment of the grid-connected power supply method for two compartments according to the present invention. The grid-connected power supply system of the two cabins shown in 1.

As shown in FIG. 2 , in this embodiment, the grid-connected power supply method for the two cabin sections includes the following steps:

Step S10, when the first cabin section and the second cabin section are in the combined flight mode, obtain a first battery pack voltage U1 and a second battery pack voltage U2.

In this embodiment, a grid-connected control unit is connected between the first battery pack busbar and the second battery pack busbar, so as to realize grid-connected power supply between the first cabin section and the second cabin section.

Step S20, the first battery pack voltage U1 is compared with a preset normal value lower limit voltage K1, and the second battery pack voltage U2 is compared with a preset normal value lower limit voltage K2.

Among them, please refer to Table 1 for the lower limit voltage K1 of the preset normal value and the lower limit voltage K2 of the preset normal value. Table 1 shows the lower limit of the voltage normal value of the lithium-ion battery pack (7 cells in series) for the 30V bus, and the grid-connected opening Thresholds for the lower voltage limit and the upper limit of the shunt value.

Step S30, according to the comparison result, configure a power supply strategy between the first cabin section and the second cabin section through the grid-connected control unit, wherein the power supply strategy includes a normal energy mode, a first faulty energy source mode and a second failure energy mode.

Specifically, according to the comparison result, the step of configuring the power supply strategy between the first cabin section and the second cabin section by the grid-connected control unit includes:

Step S301, if U1>K1, and U2>K2, enter the normal energy mode.

Wherein, if none of the first solar cell arrays are split, and the number of splits in the split state of the second solar cell array is greater than 2, the grid-connected control unit controls the second module to flow to the The first compartment is powered.

If none of the second solar cell arrays is shunted, and the number of divisions in the first solar cell array in the shunting state is greater than 2, the grid-connected control unit controls the first compartment to the second Cabin power supply.

If the SAm array of the first solar cell array is split, or the second solar cell array is not split, the first cabin section and the second cabin section are powered independently.

If the SAn array of the second solar cell array is shunted, or the first cell array is not shunted, the second cabin section and the first cabin section are powered independently.

Step S302, if U1≤K1, enter the first fault energy mode.

Wherein, if the voltage U2 of the second battery pack is lower than the preset grid-connected turn-on voltage lower limit K4, the loads connected to the first battery pack and the second battery pack are turned off.

If U2>K4, the grid-connected control unit controls the second cabin section to supply power to the first cabin section.

If U1>K1, or U2≤K4, the grid-connected control unit controls the second cabin section to stop supplying power to the first cabin section.

Step S303, if U2≤K2, enter the second fault capable power supply mode.

Wherein, if the voltage U1 of the first battery pack is lower than the preset grid-connected turn-on voltage lower limit K3, the loads connected to the first battery pack and the second battery pack are turned off.

If U1>K3, the grid-connected control unit controls the first cabin section to supply power to the second cabin section.

If U2>K4, or U1≤K3, the grid connection control unit controls the first cabin section to stop supplying power to the second cabin section.

Please refer to Table 1 for the lower limit of the grid-connected turn-on voltage K3 and the lower limit of the grid-connected turn-on voltage K4.

It can be understood that, in this embodiment, when the first cabin section and the second cabin section are in the combined flight mode, the step of acquiring the first battery pack voltage U1 and the second battery pack voltage U2 is performed before the step. Include the following steps:

It is judged whether the first cabin segment and the second cabin segment are in a single flight mode or a combined flight mode.

If the first cabin section and the second cabin section are in the independent flight mode, the grid connection control unit is turned off.

If the first cabin section and the second cabin section are in a combined flight mode, the step of obtaining the first battery pack voltage U1 and the second battery pack voltage U2 is performed.

It is worth mentioning that, in this embodiment, the grid-connected control unit includes a unidirectional isolated buck-boost converter DC/DC1 and a unidirectional isolated buck-boost converter DC/DC2. The input end of DC1 is provided with a fuse F1 and a switch C1, and the output end is provided with an isolation diode D1, which is used for the second compartment to supply power to the first compartment, and the input end of the converter DC/DC2 is provided with A fuse F2, a switch C2, and an isolation diode D2 are provided at the output end for the first cabin section to supply power to the second cabin section. When the fuse C2 is closed and the fuse C1 is disconnected, the second compartment supplies power to the first compartment; when the fuse C1 is closed and the fuse C2 is disconnected, the first compartment The segment supplies power to the second compartment.

In this embodiment, the working states of the arrays of the first solar cell array and the second solar cell array are determined by detecting the output voltages of the arrays. When the output voltage of the arrays is lower than the preset threshold value K5 When , it is judged that the splitting array of this level works in the shunt mode.

The adopting points of the output voltages of the sub-arrays at all levels are set at the access points of the positive and negative terminals of the sub-array power supply at the inlet end of the corresponding power supply/charging shunt adjustment module.

The power supply method for connecting two cabins to the grid in this embodiment will be described in further detail below with reference to FIG. 1 to FIG. 6 .

The two-cabin grid-connected power supply method in this embodiment is applied to the two-cabin grid-connected power supply system shown in FIG. 1 . A spacecraft consists of cabin section 1 and cabin section 2. The power supply system of cabin section 1 includes a solar cell array, a power supply/charge shunt adjustment module, a discharge adjustment module, and a battery pack, which supplies power for the fully regulated bus load load1_1 and the battery bus load load2_1. The power supply system of cabin section 2 includes solar cell array, power supply/charging shunt adjustment module, discharge adjustment module, battery pack, grid-connected control unit, and supplies power for fully regulated bus load load1_2 and battery bus load load2_2. When the two cabins are in combined flight mode, the grid-connected control unit is connected between the busbars of the battery packs to realize the grid-connected power supply between the two cabins. The grid-connected power supply unit is composed of two independent unidirectional isolation buck-boost DC/DC converters. The input section of the DC/DC1 converter is provided with fuse F1 and switch C1, and the output end is provided with an isolation diode D1 for The cabin section 2 supplies power to the cabin section 1; the input section of the DC/DC2 converter is provided with a fuse F2 and a switch C2, and the output end is provided with an isolation diode D2, which is used for the cabin section 1 to supply power to the cabin section 2.

The control flow chart of the energy scheduling method is shown in Figure 2 to Figure 6. The thresholds of the lower limit of the normal voltage, the lower limit of the grid-connected turn-on voltage and the upper limit of the shunt value of the lithium-ion battery pack (7 cells in series) for the 30V bus are shown in Table 1. shown.

In the separate flight mode, the two cabins can work under the orbital conditions of alternating light and shadow, and can meet the power supply requirements of different types of loads, and the grid-connected control unit is turned off. The sub-arrays of cabin 1 are gradually divided from the mth stage (SAm) to the first stage, and the sub-arrays of cabin 2 are gradually divided from the nth stage (SAn) to the first stage.

In the combined flight mode of the two cabins, the grid-connected control unit is connected between the busbars of the battery packs to realize the grid-connected power supply between the two cabins. The working modes of grid-connected power supply include the following three: cabin section 1 supplies power to cabin section 2 (C2 is closed, C1 is open, DC/DC2 works), cabin section 2 supplies power to cabin section 1 (C1 is closed, C2 is disconnected, DC /DC1 works), independent power supply for cabin 1 and cabin 2 (C1, C2 are disconnected, DC/DC1, DC/DC2 do not work).

The normal/faulty energy mode switching flow chart is shown in Figure 3. When the grid-connected power supply function is disabled, the grid-connected control unit is turned off, and cabin 1 and cabin 2 are powered independently; when the grid-connected power supply function is enabled, the detection module 1. The battery pack voltage U1, when U1 is higher than the lower limit voltage K1 of the normal value, check the voltage U2 of the battery pack in compartment 2, when U2 is higher than the lower limit voltage K2 of the normal value, it is determined that the combination is working in the normal energy mode; when U1≤K1 Enter fault energy mode 1; when U2≤K2, enter fault energy mode 2.

The energy scheduling method in the normal energy mode is shown in Figure 4. When the solar cell arrays SA1 to SAm in cabin 1 are not shunted, and the number of divisions in the shunting state of the solar cell array in cabin 2 is greater than 2, C1 will be closed autonomously. , DC/DC1 starts to work, supply power from cabin 2 to cabin 1, and DC/DC1 is in constant current mode; when the SAm of the solar cell array in cabin 1 is split, or the solar cell arrays SA1 to SAn in cabin 2 are not Shunt, disconnect C1 autonomously, DC/DC1 stops working, and cabin 1 and cabin 2 are powered independently. When the solar cell arrays SA1 to SAn in cabin 2 are not shunted, and the number of divisions in the shunting state of the solar cell arrays in cabin 1 is greater than 2, C2 will be closed autonomously, and DC/DC2 will start to work, from cabin 1 to cabin 2 Power supply, DC/DC2 is in constant current mode; when the SAn of the solar cell array in cabin 2 is split, or the solar cell arrays SA1 to SAm in cabin 1 are not split, C2 is disconnected autonomously, DC/DC2 stops working, and the cabin is 1 and compartment 2 are powered independently.

The energy scheduling method in the fault energy mode is shown in Figure 5 and Figure 6. In the first fault energy mode, when the voltage U2 of the battery pack in compartment 2 is lower than the lower limit K4 of the grid-connected turn-on voltage, the only way to reduce the load is to turn off the load. The energy demand of the cabin is used to win the troubleshooting time; when U2>K4, C1 is automatically closed, DC/DC1 starts to work, and the power is supplied from cabin 2 to cabin 1, and DC/DC1 is in constant current mode; when U1>K1 or U2 When ≤K4, disconnect C1 autonomously, DC/DC1 does not work, and exits the fault mode. In the second fault energy mode, when the voltage U1 of the battery pack in compartment 1 is lower than the lower limit K3 of the grid-connected turn-on voltage, the troubleshooting time can only be gained by turning off the load to reduce the energy demand of each compartment; when U1>K3, it is automatically closed C2, DC/DC2 starts to work, supply power from cabin 1 to cabin 2, DC/DC2 is in constant current mode; when U2>K2 or U1≤K3, C2 is automatically disconnected, DC/DC2 does not work, and exits the fault mode.

It should be noted that, in the solar cell array, the working state of each stage of the sub-array can be judged by detecting the output voltage of the sub-array. Split mode.

Table 1 Threshold settings

The beneficial effects of the two-cabin grid-connected power supply method of the present invention are:

1. A grid-connected control unit is set between the busbar of the first battery pack and the busbar of the second battery pack, which can not only supply power to the load but also charge the battery pack;

2. It can identify normal energy mode and fault energy mode and control it autonomously, realize the sharing and optimization of energy between cabins, and increase the adaptability and reliability of the spacecraft power system;

3. In the normal energy mode, the grid-connected power supply for other cabins is only allowed when the solar cell array in this cabin has excess energy for shunting, which increases the utilization rate of solar cell array power and avoids the need for batteries in this cabin. Group unnecessary discharge;

4. In the fault energy mode, as long as the battery pack in this cabin is capable, it will supply power to the faulty cabin through the grid-connected control unit. On the premise of ensuring the load power demand, the troubleshooting time can be obtained as much as possible, which improves the power supply system of the whole device. reliability;

5. The present invention does not need to distinguish between the lighted area and the shadowed area, the control method is simple, and the adaptability is strong.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any equivalent structure or process transformation made by using the contents of the description and drawings of the present invention, or directly or indirectly applied in other related technical fields , are similarly included in the scope of patent protection of the present invention.

Claims (10)

1. A two-cabin grid-connected power supply system, characterized in that the system includes a first cabin section and a second cabin section, wherein the first cabin section includes a first solar cell array, and the first a first power supply/charging shunt adjustment module connected to the solar cell array, a first discharge adjustment module connected to the first power supply/charge shunt adjustment module, and a first battery pack, and the second cabin section includes a second solar cell array , a second power supply/charging shunt adjustment module connected with the second solar cell array, a second discharge adjustment module and a second battery pack connected with the second power supply/charge shunt adjustment module, the second cabin section It also includes a grid-connected control unit, and the first battery pack busbar and the second battery pack busbar are connected through the grid-connected control unit; The grid-connected control unit includes a unidirectional isolated buck-boost converter DC/DC1 and a unidirectional isolated buck-boost converter DC/DC2, and the input end of the converter DC/DC1 is provided with a fuse F1, switch C1, the output end is provided with an isolation diode D1, which is used for the second compartment to supply power to the first compartment, the input end of the converter DC/DC2 is provided with a fuse F2, a switch C2, and the output The end is provided with an isolation diode D2, which is used for the first cabin section to supply power to the second cabin section. 2. A grid-connected power supply method for two cabins, wherein the method is applied to the system according to claim 1, and the method comprises the following steps: When the first cabin section and the second cabin section are in a combined flight mode, obtain a first battery pack voltage U1 and a second battery pack voltage U2; Comparing the first battery pack voltage U1 with the preset normal value lower limit voltage K1, and comparing the second battery pack voltage U2 with the preset normal value lower limit voltage K2; According to the comparison result, a power supply strategy between the first cabin section and the second cabin section is configured by the grid-connected control unit, wherein the power supply strategy includes a normal energy mode, a first fault energy mode, and a third Two failure energy modes. 3 . The grid-connected power supply method for two cabin sections according to claim 2 , wherein, according to the comparison result, the grid-connected control unit is used to configure between the first cabin section and the second cabin section. 4 . The steps of the power supply strategy include: If U1>K1, and U2>K2, enter the normal energy mode; If U1≤K1, enter the first fault energy mode; If U2≤K2, enter the second fault capable power supply mode. 4. The grid-connected power supply method for two compartments according to claim 3, wherein the step of entering the normal energy mode comprises: If none of the first solar cell arrays are split, and the number of splits in the second solar cell array in a split state is greater than 2, the grid-connected control unit controls the second module to flow to the first solar cell. cabin power supply; If none of the second solar cell arrays is shunted, and the number of divisions in the first solar cell array in the shunting state is greater than 2, the grid-connected control unit controls the first compartment to the second cabin power supply; If the SAm array of the first solar cell array is shunted, or the second solar cell array is not shunted, the first cabin section and the second cabin section are independently powered; If the SAn array of the second solar cell array is shunted, or the first cell array is not shunted, the second cabin section and the first cabin section are powered independently. 5. The grid-connected power supply method for two compartments according to claim 3, wherein the step of entering the first fault energy mode comprises: If the voltage U2 of the second battery pack is lower than the preset grid-connected turn-on voltage lower limit K4, turn off the loads connected to the first battery pack and the second battery pack; If U2>K4, control the second cabin section to supply power to the first cabin section through the grid-connected control unit; If U1>K1, or U2≤K4, the grid-connected control unit controls the second cabin section to stop supplying power to the first cabin section. 6. The grid-connected power supply method for two compartments according to claim 3, wherein the step of entering the second fault energy mode comprises: If the voltage U1 of the first battery pack is lower than the preset grid-connected turn-on voltage lower limit K3, turn off the loads connected to the first battery pack and the second battery pack; If U1>K3, control the first cabin section to supply power to the second cabin section through the grid-connected control unit; If U2>K4, or U1≤K3, the grid connection control unit controls the first cabin section to stop supplying power to the second cabin section. 7 . The grid-connected power supply method for two compartments according to any one of claims 2 to 6 , wherein when the first compartment and the second compartment are in a combined flight mode, the first The steps of a battery pack voltage U1 and a second battery pack voltage U2 further include: determining whether the first cabin segment and the second cabin segment are in a separate flight mode or a combined flight mode; If the first cabin section and the second cabin section are in the independent flight mode, turning off the grid-connected control unit; If the first cabin section and the second cabin section are in a combined flight mode, the step of obtaining the first battery pack voltage U1 and the second battery pack voltage U2 is performed. 8 . The grid-connected power supply method for two compartments according to claim 2 , wherein when the fuse C2 is closed and the fuse C1 is opened, the second The first cabin section supplies power; when the fuse C1 is closed and the fuse C2 is opened, the first cabin section supplies power to the second cabin section. 9 . The grid-connected power supply method for two compartments according to any one of claims 2 to 6 , wherein the working states of the first solar cell array and the second solar cell array at all levels are detected by detecting each The output voltage of the sub-array is determined. When the output voltage of the sub-array is lower than the preset threshold value K5, it is determined that the sub-array works in the shunt mode. 10 . The grid-connected power supply method for two compartments according to claim 9 , wherein the output voltages of the split arrays at all levels are set at the positive and negative of the split array power supply at the inlet end of the corresponding power supply/charging shunt adjustment module. 11 . terminal access.

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