CN105186671B - A kind of pair of cabin combined type spacecraft joint electric power system and method - Google Patents

Abstract

The present invention provides a combined power supply system and method for a double-chamber combined spacecraft, wherein the system includes: an ascending cabin power system and a landing cabin power system; wherein, the ascending cabin power supply system includes: a first solar battery array, a first charging shunt regulator module, discharge regulation module and storage battery pack; the power supply system of the landing module includes: the second solar cell array and the second charge shunt regulation module; the power supply object of the dual-cabin combined spacecraft joint power supply system is each load in the spacecraft, and the load includes: Fully regulated and unregulated bus loads in the ascent compartment, and fully regulated and unregulated bus loads in the landing compartment. The combined power supply system and method of the dual-chamber combined spacecraft provided by the present invention can not only ensure the power supply requirements of the combined flight of the spacecraft, but also ensure the power supply requirements of the independent flight of the cabins.

Description

A combined power supply system and method for a dual-chamber combined spacecraft

technical field

The invention belongs to the design field of spacecraft power supply systems, and in particular relates to a dual-chamber combined spacecraft combined power supply system and method.

Background technique

The dual-cabin composite spacecraft is a common form of space vehicles, and has been widely used in returnable satellites, spacecraft, and lunar exploration projects. As space exploration target tasks become more and more abundant, especially manned space exploration missions represented by the space station, and deep space exploration missions represented by lunar landing, patrol exploration, and sample return missions, the dual-cabin combination method is often used to complete the scheduled detection Task. my country's returnable satellites and "Shenzhou" series spacecraft are generally composed of orbital modules, propulsion modules, and returners. The Chang'e-3 probe is composed of a lander and a patrol device. The return device is composed of four devices. In addition, in deep space exploration missions such as Mars exploration, the orbiting probe usually carries the landing probe, such as the Mars Express and Beagle 2 missions, and the two jointly complete the detection of the target celestial body.

After a conventional spacecraft is launched into orbit by a carrier, it generally does not change its combination form during the mission, and its power system is usually an independent power system. The dual-cabin combined spacecraft completes different tasks at different stages during the mission period, and there will be changes in the combination form such as cabin separation, rendezvous and docking, and the different power supply requirements between the cabins according to the task arrangement. Therefore, the power system design of the dual-cabin combined spacecraft It is more complex and needs to be designed according to the characteristics of the task.

For independent flying spacecraft, about 95% of spacecraft at home and abroad use a solar array-battery pack power supply system. During the light period, the solar array supplies power and charges the battery pack, and during the shadow period, the battery pack supplies power to ensure the full mission cycle of the spacecraft. Power requirements.

For a dual-cabin combined spacecraft, the power supply method between the modules needs to be designed according to the tasks of each module. Since the weight of the spacecraft directly affects the launch cost, it is necessary to design a joint power supply for the combined spacecraft with a joint working mode, and fully consider the means of time-sharing multiplexing of equipment and modules to achieve the purpose of weight reduction.

At present, the power supply methods of the dual-cabin combination spacecraft can be roughly divided into three categories: 1) There is no power supply relationship between the cabins, and each cabin is powered independently to meet their respective load requirements; 2) The cabin is unidirectionally powered. 3) Two-way power supply between cabins, and two-way power supply includes two situations, one is grid-connected mutual supplementary power supply, and the other is joint power supply. The two-way power supply between the American power system and the Russian power system in the International Space Station is achieved through grid-connected power supply. The connection between the Tiangong-1 target aircraft and the Shenzhou spacecraft is also achieved through grid-connected power supply. Between the Tiangong-1 target aircraft and the Shenzhou spacecraft powered by.

Taking the combined power supply mode of the space station power system as an example, the block diagram of the international space station power system is shown in Figure 1, including a 120V DC power system (USOS) built in the United States and a 28V DC power system (FGB) built in Russia. The two sets of power systems can be interconnected and allow mutual power transmission. Both sets of power systems use solar cell array-battery pack power supply system. During the light period, the solar cell array supplies power and charges the battery pack for energy storage, and during the shadow period, the battery pack supplies power. The power system in the United States provides about 78kW, and the power system in Russia provides about 29kW. Usually, two sets of power systems meet their respective load requirements. When mutual supplementary power supply is required, there are two types of equipment in the International Space Station to realize the energy transmission of the two power systems of the United States and Russia and the conversion of the busbar system. A step-down converter ARCU (American-to-Russian Converter Unit) is used to realize high-voltage to low-voltage conversion from USOS to FGB, and a step-up converter RACU (Russian-to-American Converter Unit) is used to realize conversion from FGB to USOS low-voltage to high-voltage conversion.

It can be seen from the figure that in order to realize the joint power supply between the two cabins, it is necessary to realize the voltage conversion through the ARCU and RACU. On the one hand, the weight of the power system of the space station will be increased. consumption and reduce reliability.

Contents of the invention

In order to solve the above problems, the present invention provides a combined power supply system and method for a dual-cabin combined spacecraft, which can not only ensure the power supply requirements of the combined flight of the spacecraft, but also ensure the power supply requirements of the independent flight of the cabin.

The dual-chamber combined spacecraft combined power supply system of the present invention includes: an ascent cabin power supply system and a landing cabin power supply system; wherein, the ascending cabin power supply system includes: a first solar battery array, a first charging shunt regulation module, and a discharge regulation module and battery packs; the power supply system of the landing module includes: the second solar cell array and the second charging shunt adjustment module; Regulated and unregulated bus loads, and fully regulated and unregulated bus loads for landing bays;

The connection relationship is:

The lead-out line of the positive end of the first solar battery array is the first full-regulation bus, and the lead-out line of the negative end is the first power supply return line; Between the busbar and the first power supply return line; the lead-out line of the positive terminal of the battery pack is the first unregulated busbar, the lead-out line of the negative end of the battery pack is connected with the first power supply return line, and the unregulated busbar loads of the ascending cabin are respectively connected in series between the first unregulated bus and the first power supply return line; the discharge regulation module is connected in series between the first fully regulated bus and the positive terminal of the battery, and regulates the current output from the battery to the first fully regulated bus;

The lead-out line of the positive terminal of the second solar battery array is the second fully-regulated busbar, and the lead-out line of the negative-end is the second power supply circuit; Two power supply loops are connected; the fully regulated bus loads of the landing cabin are respectively connected in series between the second fully regulated bus and the second power supply loop, and the non-regulated bus loads of the landing cabin are respectively connected in series between the second non-regulated bus and the second between power supply loops;

The first fully regulated busbar and the second fully regulated busbar are connected by a fully regulated busbar power supply cable; the first non-regulated busbar and the second non-regulated busbar are connected by an incompletely regulated busbar power supply cable; the first power supply loop cable and the second The two power supply return cables are connected by the return cable, and the fully-adjustable bus power supply cable, the partially-adjustable bus power supply cable and the return cable form the cabin cable of the double-cabin combined spacecraft;

Among them, the first charge shunt regulation module is used to consume the excess current on the first fully regulated bus and the first non-regulated bus, provide all loads in the ascending compartment with a current that meets the load requirements, and provide the battery pack with a current that meets the charging electric rate requirements. current;

In the combined working mode, the second charging and shunting regulation module is used to consume the excess current on the cable between cabins, the second fully regulated busbar and the second unregulated busbar, to provide current that meets the load requirements for all loads in the two cabins and for the battery pack Provide a current that meets the charging electric rate requirements;

In the single working mode, the second charging shunt regulating module is used to consume excess current on the second fully regulated bus and the second unregulated bus, and provide current meeting load requirements for all loads in the landing module.

The present invention also provides a power supply method based on the power supply system described in claim 1, which includes:

Step 1. The power supply mode of the dual-cabin combined spacecraft from launch to the lunar surface, and before the separation of the double-cabins is the combined working mode. The specific content of the combined working mode is as follows:

1) Photoperiod:

The first solar cell array in the ascending compartment does not work, the second solar cell array in the landing compartment and the battery pack in the ascending compartment form a combined power supply mode, that is, the output power of the second solar cell array is divided into two parts: one part is fully regulated for the landing compartment Bus load and unregulated bus load supply power; part of the fully regulated bus load and non-regulated bus load are powered by fully regulated bus power supply cables and partially regulated bus power cables in the ascending compartment;

If the output power of the second solar cell array in the landing compartment is greater than the total demand of all loads in the two compartments but less than or equal to the total demand of all loads in the two compartments plus the charging power demand of the battery pack, then it will supply power to all the loads in the two compartments and at the same time pass the cable between the two compartments. Battery pack charging; if the output power of the second solar cell array in the landing cabin is greater than the total demand of all loads in the two cabins and the charging power demand of the battery pack, then the second charging shunt adjustment module will perform shunting and then supply power to all the loads in the two cabins and the battery pack Charge;

2) Shadow period:

The first solar cell array in the ascending compartment and the second solar cell array in the landing compartment are not working, and the detector is powered by the battery pack in the ascending compartment, that is, the output power of the battery pack is divided into 4 parts: one part is the unregulated bus load of the ascending compartment Power supply; one part supplies power to the fully regulated bus load of the ascending cabin after passing through the discharge regulation module; one part supplies power to the non-regulated bus load of the landing cabin through the incompletely regulated bus cable; one part supplies power to the fully regulated bus load of the landing cabin through the fully regulated bus cable;

Step 2: After the ascension module and the landing module of the dual-cabin combined spacecraft are separated, the landing module continues to work on the lunar surface, the ascension module leaves the lunar surface, and the power supply mode is the single-cabin working mode. The specific content of the single-cabin working mode for:

(1) Landing module:

During the light period, the output power of the second solar cell array supplies power for the fully regulated bus load and the non-regulated bus load of the landing module; After shunting, it supplies power to the fully regulated bus load and unregulated bus load of the landing module;

During the shadow period, the landing module does not work;

(2) After the ascending cabin moves to the designated orbit, the first solar cell array is deployed to form a joint power supply mode of the first solar cell array and battery pack. The specific power supply content is as follows:

During the light period, the first solar battery array is used as the power supply, and its output power supplies power for the fully regulated bus load and the unregulated bus load of the ascending cabin. If the output power of the solar battery array is greater than the total demand of the ascending cabin load but less than or equal to The demand plus the charging power demand of the battery pack will supply power to all the loads in the ascending cabin and charge the battery pack at the same time; if the output power of the solar array is greater than the total demand of the loading in the ascending cabin and the charging power demand of the battery pack, it will be carried out through the first charging shunt adjustment module. After shunting, it supplies power to all loads in the ascending cabin and charges the battery pack at the same time;

During the shadow period, the battery pack in the ascending cabin is used as the power supply, and the output power is divided into two parts: one part directly supplies power to the unregulated bus load in the ascending cabin; the other part supplies power to the fully regulated bus load in the ascending cabin through the discharge regulation module.

Beneficial effect:

A combined power supply method and system for a double-compartment combined spacecraft disclosed in the present invention realizes combined power supply through the time-division multiplexing of battery packs and discharge adjustment modules, which can not only ensure the power supply requirements of the combined flight of the spacecraft, but also ensure the stability of the cabin. The power supply demand during independent flight not only optimizes the design of the power system in the spacecraft cabin, but also achieves the purpose of reducing the weight of the power system of the spacecraft. Moreover, the weight of the spacecraft power supply system can be reduced through the time-division multiplexing of the battery pack and the discharge regulation module, thereby achieving the purpose of saving the launch cost of the spacecraft.

Description of drawings

Fig. 1 is the schematic diagram of the space station power supply of prior art;

Fig. 2 is a schematic diagram of the joint power supply system of a dual-cabin combined spacecraft;

Figure 3 is a schematic diagram of the joint power supply system of the double-cabin combined spacecraft during the light period;

Figure 4 is a schematic diagram of the combined power supply system of the dual-cabin combined spacecraft during the shadow period;

Figure 5 is a schematic diagram of the power supply system for ascending the cabin after the cabin is separated;

Fig. 6 is a schematic diagram of the power supply system of the landing module after the module is separated.

detailed description

A lunar probe consists of an ascending module (the first module) and a landing module (the second module), which mainly complete lunar surface sampling and lunar surface take-off tasks. Among them, the first cabin is the main cabin, which is required to be able to work under the orbital conditions of light and shadow alternately in the combination flight mode or the single flight mode, and the second cabin is the auxiliary cabin, which can be operated under the light and shadow alternately in the combination mode work under orbital conditions, and only work or not work during the light period after the cabin is separated.

The present invention provides a combined power supply system for a double-chamber combined spacecraft, which includes: a power supply system for an ascending cabin (first cabin) and a power supply system for a landing cabin (second cabin); as shown in FIG. 2 . The ascending cabin (first cabin) power supply system includes: a first solar battery array, a first charging and shunting regulating module, a discharging regulating module, and a battery pack. The power supply system of the landing module (the second module) includes: the second solar battery array, and the second charging shunt regulation module. The power supply objects are various loads in the spacecraft, and the loads include: the fully regulated bus load and the unregulated bus load of the ascending cabin, and the fully regulated bus load and the unregulated bus load of the landing cabin.

The connection relationship between the various components in the combined power supply system is:

The positive lead-out line of the first solar cell array is the first full-regulation bus, and the negative-end lead-out is the first power supply loop; Between a fully regulated busbar and the first power supply loop; the positive terminal lead-out line of the storage battery pack is the first unregulated busbar, the negative terminal lead-out line of the battery pack is connected to the first power supply loop line, and the unregulated busbar load of the ascending cabin is 1 ~m are connected in series between the first unregulated busbar and the first power supply return line respectively; the discharge regulation module is connected in series between the first fully regulated busbar and the positive terminal of the battery, and the current output from the battery to the first fully regulated busbar make adjustments;

The lead-out line of the positive terminal of the second solar battery array is the second fully-regulated busbar, and the lead-out line of the negative-end is the second power supply circuit; The two power supply return lines are connected; the full-adjustment bus loads 1'~n' of the landing cabin are respectively connected in series between the second full-regulation bus and the second power supply return line, and the non-adjustment bus loads 1'~m' of the landing cabin are connected in series respectively. Connected between the second unregulated busbar and the second power supply return line;

The first fully regulated busbar and the second fully regulated busbar are connected by a fully regulated busbar power supply cable; the first non-regulated busbar and the second non-regulated busbar are connected by an incompletely regulated busbar power supply cable; the first power supply loop cable and the second The two power supply return cables are connected through return cables. Fully adjustable busbar power supply cables, incompletely adjustable busbar power supply cables, and return cables form cabin cables;

Among them, the first charge shunt regulation module is used to consume the excess current on the first fully regulated bus and the first non-regulated bus, provide all loads in the ascending compartment with a current that meets the load requirements, and provide the battery pack with a current that meets the charging electric rate requirements. current;

In the combined working mode, the second charging and shunting regulation module is used to consume the excess current on the cable between cabins, the second fully regulated busbar and the second unregulated busbar, to provide current that meets the load requirements for all loads in the two cabins and for the battery pack Provide a current that meets the charging electric rate requirements;

In the single working mode, the second charging shunt regulation module is used to consume the excess current on the second fully regulated busbar and the second unregulated busbar, and provide current that meets the load requirements for all loads in the landing module;

In the single working mode, the discharge regulation module regulates the current output from the storage battery to the first full-regulation bus, and provides current that meets the load requirements for the full-regulation bus loads 1 to n of the ascending compartment;

In the combined working mode, the discharge regulation module regulates the current output from the battery to the first full-regulation bus and the current output to the second full-regulation bus through the full-regulation bus cable, so as to load 1 ~n and the fully regulated bus loads 1'~n' of the landing module provide the current according to the load requirements.

The present invention also provides a power supply method for a combined power supply system of a double-chamber combined spacecraft, including:

Step 1: From the launch of the lunar probe to the working section of the lunar surface, the first solar cell array of the ascending module (first module) is in a retracted state and cannot be used for power generation, and the second solar cell array of the landing module (second module) is in the Expand Power Generation Status. At this time, the power supply of the lunar probe is provided by the joint power supply composed of the second solar cell array of the landing module (second cabin) and the battery pack of the ascending cabin (first cabin), and realizes the combined power supply through the multiplexing battery pack and the discharge regulation module. powered by.

The power supply mode is combined working mode, and the specific content of the combined working mode is as follows:

1) Photoperiod:

The joint power supply mode of the second solar cell array in the landing cabin (the second cabin) and the battery pack in the ascending cabin (the first cabin) is shown in Fig. 3 . The output power of the second solar cell array in the landing cabin (second cabin) is divided into two parts: one part supplies power for the fully regulated bus load 1'~n' and the unregulated bus load 1'~m' of the landing cabin (second cabin) ; Part of it supplies power to the fully regulated bus load 1~n and the non-regulated bus load 1~m of the ascending cabin (first cabin) through the cabin cable;

If the output power of the second solar cell array in the landing cabin (the second cabin) is greater than the total load demand of the two cabins but less than or equal to the total load demand of the two cabins plus the charging power demand of the battery, it will supply power to the loads of the two cabins and at the same time through the cabin cable Charge the battery pack in the ascending cabin (the first cabin); if the output power of the solar array in the landing cabin (the second cabin) is greater than the total load demand of the two cabins and the charging power demand of the battery pack, it will be shunted through the second charging shunt adjustment module Then supply power to all loads in the two cabins and charge the batteries.

2) Shadow period:

The detector in the shadow period is powered by the battery pack in the ascending cabin (the first cabin), and the power supply schematic diagram is shown in Figure 4. The output power of the battery pack is divided into 4 parts: one part directly supplies power for the unregulated bus load 1~m of the ascending cabin (the first cabin); the other part provides power for the fully regulated bus load 1~n of the ascending cabin (the first cabin) through the discharge regulation module Power supply; part of the power supply for the unregulated bus load 1'~m' of the landing cabin (second cabin) through the cabin cable; part of the power supply for the fully regulated bus load 1 of the landing cabin (second cabin) through the cabin cable after passing through the discharge regulation module '~n' power supply.

Step 2: Before the lunar surface and the module are separated, the ascending module (the first module) and the landing module (the second module) provide joint power supply through the cable between the modules. The specific power supply content is the same as that in step 2. Before the lunar probe takes off on the lunar surface, the ascending module (the first module) is separated from the landing module (the second module), the landing module (the second module) continues to work on the lunar surface, and the ascending module (the first module) leaves the lunar surface. The power supply mode is single-chamber working mode.

After separation, the landing module (the second module) is only required to be able to work during the day and night of the moon (i.e. when the second solar cell array generates power). The power supply diagram of the landing cabin (second cabin) is shown in Figure 6, and the specific power supply content is as follows:

1) During the light period, the output power of the second solar cell array in the landing module (second cabin) supplies power for the fully regulated bus load 1'~n' and the non-regulated bus load 1'~m' of the landing module (second cabin); If the output power of the solar battery array is greater than the total demand of the load, then it will be divided by the second charging shunt adjustment module and then the fully regulated bus load 1'~n' and the non-regulated bus load 1'~m of the landing cabin (second cabin) 'powered by.

2) During the shadow period, since the landing module (second cabin) has no battery pack, the landing module (second cabin) does not work.

After the ascending module (the first module) moves to the designated orbit, the first solar cell array of the ascending module (the first module) is deployed, and the ascending module (the first module) forms its own joint power supply mode of the solar cell array and the battery pack. The schematic diagram of the power supply for the ascending cabin (the first cabin) is shown in Figure 5, and the specific power supply content is as follows:

3) During the light period, the first solar battery array in the ascending cabin (the first cabin) is used as the power supply, and its output power supplies power for the fully regulated bus load 1~n and the unregulated bus load 1~m in the ascending cabin (first cabin), If the output power of the solar cell array is greater than the total demand of the load but less than or equal to the total load demand of the ascending compartment plus the charging power demand of the battery, it will supply power to all the loads of the ascending compartment and charge the battery pack of the ascending compartment (the first compartment); If the output power of the battery array is greater than the total load demand of the ascending cabin and the charging power demand of the battery pack, then the first charging shunt adjustment module performs shunting and then fully adjusts the bus load 1~n and unregulated bus load 1 for the ascending cabin (the first cabin) ~ m power supply, and charge the battery pack.

4) During the shadow period, the battery pack of the ascending cabin (the first cabin) is used as the power supply, and the output power is divided into two parts: one part directly supplies power for the unregulated bus load 1~m of the ascending cabin (the first cabin); the other part passes through the discharge regulation module Supply power to the fully regulated bus loads 1~n of the ascending cabin (the first cabin).

Of course, the present invention can also have other various embodiments, and those skilled in the art can make various corresponding changes and deformations according to the present invention without departing from the spirit and essence of the present invention, but these corresponding Changes and deformations should belong to the scope of protection of the appended claims of the present invention.

Claims (2)

1. A combined power supply system for a double-chamber combined spacecraft, characterized in that it includes: an ascending cabin power system and a landing cabin power system; wherein the ascending cabin power system includes: a first solar cell array, a first charging shunt adjustment module , a discharge regulation module and a storage battery pack; the power supply system of the landing module includes: the second solar cell array and the second charge shunt regulation module; the power supply object of the combined power supply system of the double-cabin spacecraft is each load in the spacecraft, and the load includes: Fully regulated and unregulated bus loads for the ascent compartment, and fully regulated and unregulated bus loads for the landing compartment; The connection relationship is: The lead-out line of the positive end of the first solar battery array is the first full-regulation bus, and the lead-out line of the negative end is the first power supply return line; Between the busbar and the first power supply return line; the lead-out line of the positive terminal of the battery pack is the first unregulated busbar, the lead-out line of the negative end of the battery pack is connected with the first power supply return line, and the unregulated busbar loads of the ascending cabin are respectively connected in series between the first unregulated bus and the first power supply return line; the discharge regulation module is connected in series between the first fully regulated bus and the positive terminal of the battery, and regulates the current output from the battery to the first fully regulated bus; The lead-out line of the positive terminal of the second solar battery array is the second fully-regulated busbar, and the lead-out line of the negative-end is the second power supply circuit; Two power supply loops are connected; the fully regulated bus loads of the landing cabin are respectively connected in series between the second fully regulated bus and the second power supply loop, and the non-regulated bus loads of the landing cabin are respectively connected in series between the second non-regulated bus and the second between power supply loops; The first fully regulated busbar and the second fully regulated busbar are connected by a fully regulated busbar power supply cable; the first non-regulated busbar and the second non-regulated busbar are connected by an incompletely regulated busbar power supply cable; the first power supply loop cable and the second The two power supply return cables are connected by the return cable, and the fully-adjustable bus power supply cable, the partially-adjustable bus power supply cable and the return cable form the cabin cable of the double-cabin combined spacecraft; Among them, the first charge shunt regulation module is used to consume the excess current on the first fully regulated bus and the first non-regulated bus, provide all loads in the ascending compartment with a current that meets the load requirements, and provide the battery pack with a current that meets the charging electric rate requirements. current; In the combined working mode, the second charging and shunting regulation module is used to consume the excess current on the cable between cabins, the second fully regulated busbar and the second unregulated busbar, to provide current that meets the load requirements for all loads in the two cabins and for the battery pack Provide a current that meets the charging electric rate requirements; In the single working mode, the second charging shunt regulating module is used to consume excess current on the second fully regulated bus and the second unregulated bus, and provide current meeting load requirements for all loads in the landing module. 2. A power supply method based on the power supply system according to claim 1, characterized in that, comprising: Step 1, the power supply mode of the dual-cabin combined spacecraft from launch to the lunar surface, and before the lunar surface and the double-cabins are separated is the combined working mode. The specific content of the combined working mode is as follows: 1) Photoperiod: The first solar cell array in the ascending compartment does not work, the second solar cell array in the landing compartment and the battery pack in the ascending compartment form a combined power supply mode, that is, the output power of the second solar cell array is divided into two parts: one part is fully regulated for the landing compartment Bus load and unregulated bus load supply power; part of the fully regulated bus load and non-regulated bus load are powered by fully regulated bus power supply cables and partially regulated bus power cables in the ascending compartment; If the output power of the second solar cell array in the landing compartment is greater than the total demand of all loads in the two compartments but less than or equal to the total demand of all loads in the two compartments plus the charging power demand of the battery pack, then it will supply power to all the loads in the two compartments and at the same time pass the cable between the two compartments. Battery pack charging; if the output power of the second solar cell array in the landing cabin is greater than the total demand of all loads in the two cabins and the charging power demand of the battery pack, then the second charging shunt adjustment module will perform shunting and then supply power to all the loads in the two cabins and the battery pack Charge; 2) Shadow period: The first solar cell array in the ascending compartment and the second solar cell array in the landing compartment are not working, and the detector is powered by the battery pack in the ascending compartment, that is, the output power of the battery pack is divided into 4 parts: one part is the unregulated bus load of the ascending compartment Power supply; one part supplies power to the fully regulated bus load of the ascending cabin after passing through the discharge regulation module; one part supplies power to the non-regulated bus load of the landing cabin through the incompletely regulated bus cable; one part supplies power to the fully regulated bus load of the landing cabin through the fully regulated bus cable; Step 2: After the ascension module and the landing module of the dual-cabin combined spacecraft are separated, the landing module continues to work on the lunar surface, the ascension module leaves the lunar surface, and the power supply mode is the single-cabin working mode. The specific content of the single-cabin working mode for: (1) Landing module: During the light period, the output power of the second solar cell array supplies power for the fully regulated bus load and the non-regulated bus load of the landing module; After shunting, it supplies power to the fully regulated bus load and unregulated bus load of the landing module; During the shadow period, the landing module does not work; (2) After the ascending cabin moves to the designated orbit, the first solar cell array is deployed to form a joint power supply mode of the first solar cell array and battery pack. The specific power supply content is as follows: During the light period, the first solar battery array is used as the power supply, and its output power supplies power for the fully regulated bus load and the unregulated bus load of the ascending cabin. If the output power of the solar battery array is greater than the total demand of the ascending cabin load but less than or equal to The demand plus the charging power demand of the battery pack will supply power to all the loads in the ascending cabin and charge the battery pack at the same time; if the output power of the solar array is greater than the total demand of the loading in the ascending cabin and the charging power demand of the battery pack, it will be carried out through the first charging shunt adjustment module. After shunting, it supplies power to all loads in the ascending cabin and charges the battery pack at the same time; During the shadow period, the battery pack in the ascending cabin is used as the power supply, and the output power is divided into two parts: one part directly supplies power to the unregulated bus load in the ascending cabin; the other part supplies power to the fully regulated bus load in the ascending cabin through the discharge regulation module.