A control system and method for multi-satellite dynamic power distribution

Abstract

An embodiment of the present invention discloses a control system and method for multi-satellite dynamic power distribution. The control system includes: a power supply unit, a test control unit, and multiple satellites to be tested; wherein, the power supply unit includes multiple solar array simulators and multiple DC regulated power supplies, which are used to provide DC power to the multiple satellites to be tested respectively; the test control unit is configured to: based on the power distribution connection relationship between the target solar array simulator determined from the multiple solar array simulators and / or the target DC regulated power supply determined from the multiple DC regulated power supplies and the target satellite to be tested among the multiple satellites to be tested, transmit the DC power provided by the target solar array simulator and / or the target DC regulated power supply to the target satellite to be tested among the multiple satellites to be tested.

Description

Technical Field

[0001] The embodiments of the present invention relate to the technical field of power distribution control, and in particular, to a control system and method for multi-satellite dynamic power distribution. Background Art

[0002] With the development of commercial satellites, the demand for mass production and constellation development of satellites is becoming more and more urgent. At present, at different stages of satellite general assembly, the power supply requirements are also different; at the same time, during the satellite testing process, a group of satellites produced in batches will also have different power supply requirements due to different working modes. Generally speaking, according to different working modes, the power consumption of a single satellite is 200-3000W. During the ground general assembly stage of the satellite, a solar array simulator is usually used for power supply, and sometimes a DC regulated power supply is also used to charge the battery. Currently, during the testing process, the commonly used test power distribution equipment for satellites is a one-to-one connection method, that is, a set of power distribution equipment (which may include multiple or multiple channels of power distribution equipment, such as solar array simulators, DC regulated power supplies, etc.) fixedly supplies power to a single satellite, and the corresponding relationship between the power distribution equipment and the satellite is determined during the testing process of the satellite; however, at different stages of satellite general assembly and testing, based on different power supply requirements, and usually the high-power working mode time is short, so the power distribution equipment corresponding to each satellite is idle for most of the time, resulting in the ineffective utilization of the power distribution equipment in this case.

[0003] Of course, in some testing processes, multiple ground power distribution equipment will also be combined into a group to supply power to one or more satellites. However, although this method can supply power to multiple satellites at the same time, it still needs to configure the number of power distribution equipment according to the maximum power consumption required by each satellite, and it is impossible to dynamically configure the power distribution equipment for each satellite according to the actual power consumption requirements of the satellite, because the corresponding relationship between the satellite and the power distribution equipment has been determined when designing the cables for the power distribution equipment corresponding to each satellite, so it is impossible to modify its corresponding relationship at the general assembly site and the testing site. Summary of the Invention

[0004] In view of this, the embodiments of the present invention are expected to provide a control system and method for multi-satellite dynamic power distribution; it can dynamically adjust the corresponding relationship between the power distribution equipment and the satellite according to the actual working mode requirements of the satellite, and improve the utilization rate of the power distribution equipment.

[0005] The technical solution of the embodiments of the present invention is realized as follows:

[0006] In a first aspect, the embodiments of the present invention provide a control system for multi-satellite dynamic power distribution, the control system includes: a power supply unit, a test control unit, and multiple satellites to be tested; wherein, the input end of the test control unit is connected to the power supply unit, and the output end of the test control unit is respectively connected to multiple satellites to be tested; wherein,

[0007] The power supply unit includes a plurality of solar array simulators and a plurality of DC regulated power supplies, which are used to provide DC power for the plurality of satellites to be tested respectively;

[0008] The test control unit is configured to: based on the power distribution connection relationship between the target solar array simulator determined from the plurality of solar array simulators and / or the target DC regulated power supply determined from the plurality of DC regulated power supplies and the target satellite to be tested among the plurality of satellites to be tested, transmit the DC power provided by the target solar array simulator and / or the target DC regulated power supply to the target satellite to be tested among the plurality of satellites to be tested.

[0009] In a second aspect, an embodiment of the present invention provides a control method for multi-satellite dynamic power distribution. The control method can be applied to the control system described in the first aspect. The control method includes:

[0010] Determine a target solar array simulator from the plurality of solar array simulators and / or a target DC regulated power supply from the plurality of DC regulated power supplies, and determine the power distribution connection relationship between the target solar array simulator and / or the target DC regulated power supply and the target satellite to be tested;

[0011] According to the power distribution connection relationship between the target solar array simulator and / or the target DC regulated power supply and the target satellite to be tested, transmit the DC power provided by the target solar array simulator and / or the target DC regulated power supply to the target satellite to be tested among the plurality of satellites to be tested.

[0012] An embodiment of the present invention provides a control system and method for multi-satellite dynamic power distribution; wherein, the test control unit in the control system can be based on the target solar array simulator determined from the plurality of solar array simulators and / or the target DC regulated power supply determined from the plurality of DC regulated power supplies, and according to the power distribution connection relationship between the target solar array simulator and / or the target DC regulated power supply and the target satellite to be tested, transmit the DC power provided by the target solar array simulator and / or the target DC regulated power supply to the target satellite to be tested among the plurality of satellites to be tested, so as to dynamically adjust the power distribution corresponding relationship between the plurality of solar array simulators and / or the plurality of DC regulated power supplies in the power supply unit and the plurality of satellites to be tested without power-off of the satellites to be tested, meet the power distribution requirements of different working modes or different stages of the satellites to be tested, and improve the utilization rate of the power supply unit. Description of the Drawings

[0013] Figure 1 It is a schematic diagram of the composition of a control system for multi-satellite dynamic power distribution provided by an embodiment of the present invention;

[0014] Figure 2 Another schematic diagram of the composition of a control system for multi-satellite dynamic power distribution provided by an embodiment of the present invention;

[0015] Figure 3 A schematic diagram of the internal power distribution control method of a test control unit provided by an embodiment of the present invention;

[0016] Figure 4 Another schematic diagram of the internal power distribution control method of a test control unit provided by an embodiment of the present invention;

[0017] Figure 5 Another schematic diagram of the internal power distribution control method of a test control unit provided by an embodiment of the present invention;

[0018] Figure 6 Another schematic diagram of the internal power distribution control method of a test control unit provided by an embodiment of the present invention;

[0019] Figure 7 A schematic diagram of the flow of a control method for multi-satellite dynamic power distribution provided by an embodiment of the present invention. Detailed implementation manners

[0020] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention.

[0021] Refer to Figure 1 , which shows a control system 1 for multi-satellite dynamic power distribution provided by an embodiment of the present invention. The control system 1 specifically includes: a power supply unit 11, a test control unit 12, and a plurality of satellites to be tested 13. Among them, the input end of the test control unit 12 is connected to the power supply unit 11, and the output end of the test control unit 12 is respectively connected to a plurality of the satellites to be tested 13. Among them,

[0022] The power supply unit 11 includes a plurality of solar array simulators 111 and a plurality of DC regulated power supplies 112, which are used to provide DC power for a plurality of the satellites to be tested 13 respectively;

[0023] The test control unit 12 is configured to: based on the power distribution connection relationship between the target solar array simulator determined from a plurality of the solar array simulators 111 and / or the target DC regulated power supply determined from a plurality of the DC regulated power supplies 112 and the target satellite to be tested among a plurality of the satellites to be tested 13, transmit the DC power provided by the target solar array simulator and / or the target DC regulated power supply to the target satellite to be tested among a plurality of the satellites to be tested 13.

[0024] It should be noted that in the embodiments of the present invention, the type of the power supply unit 11 is not limited to the solar array simulator 111 and / or the DC regulated power supply 112. In the specific implementation process, the type of the power supply unit 11 can be selected according to the power supply requirements of the satellite 13 to be tested.

[0025] It should be noted that multiple solar array simulators 111 and multiple DC regulated power supplies 112 are both used to convert commercial power into DC power to meet the power supply requirements of multiple satellites 13 to be tested; in the embodiments of the present invention, any one of the multiple solar array simulators 111 and any one of the multiple DC regulated power supplies 112 can be used to supply power to the same satellite 13 to be tested. Of course, the power supply output cables of the above multiple solar array simulators 111 and multiple DC regulated power supplies 112 can be set to one path or multiple paths.

[0026] For Figure 1 the test control unit 12 in the control system 1 shown in

[0027] It should be noted that in the specific implementation process, the number of solar array simulators 111 and DC regulated power supplies 112 can be set according to actual needs; of course, the number of solar array simulators 111 and DC regulated power supplies 112 can be different, and the number of solar array simulators 111, DC regulated power supplies 112, and satellites 13 to be tested can also be different.

[0028] For Figure 1 the control system 1 shown in Figure 2As shown, the control system 1 further includes a control computer 14, a network switch 15, and a plurality of ground test connectors 16. Among them, the control computer 14 is respectively connected to the power supply unit 11 and the test control unit 12 through the network switch 15.

[0029] The control computer 14 is configured to:

[0030] Determine the target solar array simulator that provides DC power to the target satellite to be tested from multiple solar array simulators 111; and / or, determine the target DC regulated power supply that provides DC power to the target satellite to be tested from multiple DC regulated power supplies 112; and,

[0031] Determine the power distribution connection relationships between the target solar array simulator and / or the DC regulated power supply and the target satellite to be tested respectively; and,

[0032] Real-time monitor the power supply status of the satellite 11 to be tested.

[0033] The network switch 15 is configured to:

[0034] Real-time interact with the data signals between the power supply unit 11 and the control computer 14; and,

[0035] Real-time interact with the data signals between the test control unit 12 and the control computer 14.

[0036] A plurality of the ground test connectors 16 are respectively connected to the test control unit 12 and a plurality of satellites 13 to be tested, and are used to receive the DC power provided by the power supply unit 11 and output the DC power to the satellite 13 to be tested.

[0037] It can be understood that the test control unit 12, the solar array simulator 111, and the DC regulated power supply 112 are respectively connected to the network switch 15 and the control computer 14 through Ethernet, which can facilitate the expansion of the power distribution connection relationship and the remote operation of the process personnel.

[0038] On the other hand, it should be noted that the ground test connector 16 is provided with a Controller Area Network (CAN) bus interface, which is used to support data communication with the satellite 13 to be tested through the CAN bus. It should be noted that in the specific implementation process, all the CAN bus interfaces can be set on the same ground test connector 16, or can be correspondingly set on different ground connectors 16.

[0039] For Figure 1The system 1 shown, in some possible embodiments, when the DC power supplies output by the multiple solar array simulators and the multiple DC regulated power supplies can be respectively transmitted to the test control unit 12 through the multiple first input ends and the multiple second input ends, and can be respectively transmitted to the multiple satellites to be tested through the multiple first output ends and the multiple second output ends,

[0040] the test control unit 12 is configured to be provided with multiple-way relays on each first transmission line and each second transmission line, and each relay can be selectively opened or closed so that the DC power supply provided by the target solar array simulator and / or the target DC regulated power supply can be respectively transmitted to the target satellite to be tested through the corresponding first target transmission line in the multiple first transmission lines and the corresponding second target transmission line in the multiple second transmission lines;

[0041] wherein, the first transmission line represents the transmission line between the first input end and the first output end; the second transmission line represents the transmission line between the second input end and the second output end.

[0042] For example, as Figure 3 shown, taking the DC power supplies provided by 6 solar array simulators 111 and 6 DC regulated power supplies 112 and being respectively transmitted to the test control unit 12 through 6 first input ends and 6 second input ends, and the above-mentioned DC power supplies being respectively transmitted to 6 satellites to be tested 13 through 6 first output ends and 6 second output ends in the test control unit 12 as an example, the dynamic power distribution process is described in detail. It can be Figure 3 seen that 6-way relays are provided on each first transmission line and each second transmission line between the first input end and the first output end and between the second input end and the second output end. It should be noted that in Figure 3 one switch represents one relay. It can be understood that Figure 3 the 6 first input ends and the 6 second input ends in are respectively used to be connected to the output cables of 6 solar array simulators 111 and 6 DC regulated power supplies 112 so that the DC power supplies provided by the solar array simulators 111 and the DC regulated power supplies 112 can be respectively transmitted to the test control unit 12, and the 6 first output ends and the 6 second output ends are respectively connected to the ground test connector 16 so that the DC power supplies provided by the solar array simulators 111 and the DC regulated power supplies 112 can be transmitted to the corresponding satellites to be tested 13. It should be noted that in the initial stage of power distribution, each satellite to be tested 13 can be powered by 1 solar array simulator 111 and 1 DC regulated power supply 112. In this case, each satellite to be tested 13 is connected to the corresponding numbered solar array simulator 111 and DC regulated power supply 112.

[0043] When starting to work, first set the initial power distribution relationship. For example, the solar array simulator 111-1 and the DC regulated power supply 112-1 supply power to the satellite under test 13-1 through the first output terminal 1 and the second output terminal 1 respectively, the solar array simulator 111-2 and the DC regulated power supply 112-2 supply power to the satellite under test 13-2 through the first output terminal 2 and the second output terminal 2 respectively, the solar array simulator 111-3 and the DC regulated power supply 112-3 supply power to the satellite under test 13-3 through the first output terminal 3 and the second output terminal 3 respectively, the solar array simulator 111-4 and the DC regulated power supply 112-4 supply power to the satellite under test 13-4 through the first output terminal 4 and the second output terminal 4 respectively, the solar array simulator 111-5 and the DC regulated power supply 112-5 supply power to the satellite under test 13-5 through the first output terminal 5 and the second output terminal 5 respectively, the solar array simulator 111-6 and the DC regulated power supply 112-6 supply power to the satellite under test 13-6 through the first output terminal 6 and the second output terminal 6 respectively. At this time, the relays K1, K8, K15, K22, K29, K36; K37, K44, K51, K58, K65, K72 in the test control unit 12 are closed, and the rest of the relays remain open. Then set the first output terminal 1 to the first output terminal 6 and the second output terminal 1 to the second output terminal 6 to be all open. At this time, each satellite under test 13 starts to charge.

[0044] Next, if the satellite under test 13-1 needs to enter the high-power working mode as the target satellite under test, and it is determined that the solar array simulators 111-2 and 111-3 corresponding to the satellites under test 13-2 and 13-3 are connected to the satellite under test 13-1 as the target solar array simulators respectively to meet the high-power working mode of the satellite under test 13-1, then in the specific implementation, first close the first output terminal 2 and the first output terminal 3 corresponding to the solar array simulators 111-2 and 111-3 respectively, and set the relays K8 and K15 in the test control unit 12 to be open, and the relays K7 and K13 to be closed, and then open the first output terminal 2 and the first output terminal 3 corresponding to the solar array simulators 111-2 and 111-3 respectively, so as to complete the switching of the power distribution connection relationship in the control system 1. At the same time, during the whole switching process, the satellites under test 13-2 and 13-3 can continue to charge through the DC regulated power supplies 112-2 and 112-3 respectively without power-off operation. Similarly, if the DC regulated power supplies 112-2 and 112-3 can also meet the high-power power supply requirements of the satellite under test 13-1 as the target DC regulated power supplies, the DC regulated power supplies 112-2 and 112-3 can also be connected to the satellite under test 13-1 according to the above similar power distribution switching method according to the actual power supply requirements.

[0045] On the other hand, if the control system 1 needs to supply power to the satellite 13 to be tested in different stages, such as the general assembly stage, the overall satellite test stage, or the environmental test stage, etc. Specifically, for example, after the satellite 13-1 to be tested has completed power supply in one stage, in the embodiment of the present invention, it is first necessary to disconnect the battery inside the satellite 13-1 to be tested after the power supply is completed, and close the corresponding first output terminal 1 and second output terminal 1 of the solar array simulator 111-1 and the DC regulated power supply 112-1 connected to the satellite 13-1 to be tested. At the same time, disconnect the relays on the corresponding first transmission line and second transmission line of the satellite 13-1 to be tested. At this time, the satellite 13-1 to be tested is completely powered off, so the ground test connector 16-1 can be disconnected to continue subsequent processes or operations. The power-off process of the entire satellite 13-1 to be tested does not affect the charging of other satellites to be tested.

[0046] On the other hand, if the number of the first output terminals and the second output terminals connected by each satellite 13 to be tested at the initial stage of power distribution is large, that is to say, each satellite 13 to be tested is powered by multiple solar array simulators 111 and multiple DC regulated power supplies 112 at the same time. For example, the satellite 13-1 is respectively connected to the first output terminal 1 to the first output terminal 3 and the second output terminal 1 to the second output terminal 3, and the satellite 13-2 is respectively connected to the first output terminal 4 to the first output terminal 6 and the second output terminal 4 to the second output terminal 6; correspondingly, in the specific implementation process, it is also possible to use Figure 3 the switching mode of each relay in the test control unit 12 shown in the figure to perform dynamic power distribution for each satellite 13 to be tested.

[0047] It should be noted that for Figure 3 the power distribution control method shown in the figure can meet the situation where the number of satellites 13 to be tested is less than the total number of solar array simulators 111 and DC regulated power supplies 112. In some examples, the number of satellites 13 to be tested is less than the number of solar array simulators 111 or DC regulated power supplies 112. Secondly, it can be understood that the total number of relays is the total number of solar array simulators 111 and DC regulated power supplies 112 multiplied by the number of satellites 13 to be tested. That is to say, the same number of relays as the number of the first output terminals or the second output terminals are respectively arranged on each first transmission line and each second transmission line.

[0048] For Figure 1 the control system 1 shown in the figure, in some possible implementation manners, when the DC power supplies output by the multiple solar array simulators and / or the multiple DC regulated power supplies can be respectively transmitted to the test control unit 12 through multiple third input terminals, and can be respectively transmitted to the multiple satellites 13 to be tested through multiple third output terminals,

[0049] The test control unit 12 is configured to set multi-way relays on each third transmission line, and each relay can be selectively turned on or off so that the DC power supply provided by the target solar array simulator and / or the target DC regulated power supply can be transmitted to the target satellite to be tested through the corresponding third target transmission line among multiple third transmission lines respectively;

[0050] Wherein, the third transmission line represents the transmission line between the third input end and the third output end.

[0051] For example, as Figure 4 shown, taking the DC power supplies output by 6 solar array simulators 111 and 6 DC regulated power supplies 112 being transmitted to the test control unit 12 through 12 third input ends respectively, and the above-mentioned DC power supplies being transmitted to 6 satellites to be tested 13 through 12 third output ends in the test control unit 12 as an example, the dynamic power distribution process will be described in detail. From Figure 4 it can be seen that 12-way relays are arranged on each third transmission line between the third input end and the third output end. It should be noted that in Figure 4 one switch represents one relay. It can be understood that Figure 4 each third input end in is used to be connected to the output cable of the corresponding solar array simulator 111 or DC regulated power supply 112 respectively so that the DC power supply provided by the solar array simulator 111 or DC regulated power supply 112 can be transmitted to the corresponding satellite to be tested 13. It should be noted that in the initial stage of power distribution, each satellite to be tested 13 can be powered by 1 solar array simulator 111 and 1 DC regulated power supply 112. In this case, each satellite to be tested 13 is connected to the solar array simulator 111 and DC regulated power supply 112 with corresponding numbers. Of course, for Figure 4 the power distribution control method shown, it is also possible to provide DC power for the satellites to be tested 13 only through 12 solar array simulators 111 or 12 DC regulated power supplies 112.

[0052] When starting to work, first set the initial power distribution relationship. For example, the solar array simulator 111-1 and the DC regulated power supply 112-1 supply power to the satellite under test 13-1 through the third output terminal 1 and the third output terminal 7 respectively, the solar array simulator 111-2 and the DC regulated power supply 112-2 supply power to the satellite under test 13-2 through the third output terminal 2 and the third output terminal 8 respectively, the solar array simulator 111-3 and the DC regulated power supply 112-3 supply power to the satellite under test 13-3 through the third output terminal 3 and the third output terminal 9 respectively, the solar array simulator 111-4 and the DC regulated power supply 112-4 supply power to the satellite under test 13-4 through the third output terminal 4 and the third output terminal 10 respectively, the solar array simulator 111-5 and the DC regulated power supply 112-5 supply power to the satellite under test 13-5 through the third output terminal 5 and the third output terminal 11 respectively, the solar array simulator 111-6 and the DC regulated power supply 112-6 supply power to the satellite under test 13-6 through the third output terminal 6 and the third output terminal 12 respectively. At this time, the relays K1, K14, K27, K40, K53, K66, K73, K86, K99, K112, K125, K138 in the test control unit 12 are closed, and the rest of the relays remain open. Then set the third output terminals 1 to 12 to be all open. At this time, each satellite under test 13 starts to charge.

[0053] Next, if the satellite under test 13-1 needs to enter the high-power working mode as the target satellite under test, and it is necessary to connect the solar array simulators 111-2 and 111-3 corresponding to the satellites under test 13-2 and 13-3 to the satellite under test 13-1 as the target solar array simulators respectively to meet the high-power working mode of the satellite under test 13-1, then in the specific implementation, first close the third output terminals 2 and 3 corresponding to the solar array simulators 111-2 and 111-3 respectively, and set the relays K14 and K27 in the test control unit 12 to be open, and the relays K13 and K25 to be closed, and then open the third output terminals 2 and 3 corresponding to the solar array simulators 111-2 and 111-3 again, so as to complete the switching of the power distribution connection relationship in the control system 1. At the same time, during the entire switching process, the satellites under test 13-2 and 13-3 can continue to charge through the DC regulated power supplies 112-2 and 112-3 respectively without power-off operation. Similarly, if the DC regulated power supplies 112-2 and 112-3 can also meet the high-power power supply requirements of the satellite under test 13-1 as the target DC regulated power supplies, the DC regulated power supplies 112-2 and 112-3 can also be connected to the satellite under test 13-1 according to the above similar power distribution switching method according to the actual power supply requirements.

[0054] On the other hand, if the control system 1 needs to supply power to the satellite 13 to be tested in different stages, such as the general assembly stage, the overall satellite test stage, or the environmental test stage, etc. Specifically, for example, after the satellite 13-1 to be tested has completed power supply in one stage, in the embodiment of the present invention, it is first necessary to disconnect the battery inside the satellite 13-1 to be tested after the power supply is completed, and close the corresponding third output terminals 1 and 7 of the solar array simulator 111-1 and the DC regulated power supply 112-1 connected to the satellite 13-1 to be tested, and at the same time disconnect the relay on the corresponding third transmission line of the satellite 13-1 to be tested. At this time, the satellite 13-1 to be tested is completely powered off, so the ground test connector 16-1 can be disconnected to continue subsequent processes or operations. The power-off process of the entire satellite 13-1 to be tested does not affect the charging of other satellites to be tested.

[0055] On the other hand, if the number of third output terminals connected by each satellite 13 to be tested is large at the initial stage of power distribution, that is to say, each satellite 13 to be tested is powered by multiple solar array simulators 111 and multiple DC regulated power supplies 112 at the same time. For example, the satellite 13-1 to be tested is respectively connected to the third output terminals 1 to 3 and the third output terminals 7 to 9, and the satellite 13-2 to be tested is respectively connected to the third output terminals 4 to 6 and the third output terminals 10 to 12; correspondingly, in the specific implementation process, it is also possible to use Figure 4 the switching method of each relay in the test control unit 12 shown in the figure to perform dynamic power distribution for each satellite 13 to be tested.

[0056] It should be noted that when using two types of power supply units, namely the solar array simulator 111 and the DC regulated power supply 112, to charge the satellite 13 to be tested, for Figure 4 the power distribution control method shown in the figure can meet the situation where the number of satellites 13 to be tested is less than the total number of the solar array simulators 111 and the DC regulated power supplies 112. In some examples, it can meet the power distribution situation where the number of satellites 13 to be tested is less than the number of the solar array simulators 111 or the DC regulated power supplies 112. Secondly, it can be understood that the total number of relays is the number of input terminals multiplied by the number of output terminals, that is, each third transmission line is provided with the same number of relays as the number of third output terminals.

[0057] For Figure 1 the control system 1 shown in the figure, in some possible implementation manners, when the DC power supplies output by the multiple solar array simulators and / or the multiple DC regulated power supplies can be respectively transmitted to the test control unit 12 through multiple fourth input terminals, and can be respectively transmitted to the multiple satellites 13 to be tested through multiple fourth output terminals,

[0058] The test control unit 12 is configured to be provided with a single-pole multi-throw switch on each of the fourth transmission lines, and each of the single-pole multi-throw switches can be selectively opened or closed so that the DC power supply provided by the target solar array simulator and / or the target DC regulated power supply can be transmitted to the target satellite to be tested through the corresponding fourth target transmission line among the multiple fourth transmission lines respectively;

[0059] Wherein, the fourth transmission line represents the transmission line between the fourth input end and the fourth output end.

[0060] For example, as Figure 5 shown, taking the power supply unit 11 including 3 solar array simulators 111 and 3 DC regulated power supplies 112 providing DC power, the test control unit 12 is respectively provided with 6 fourth input ends and 6 fourth output ends, and the number of satellites 13 to be tested is 3 as an example, the dynamic power distribution process will be described in detail. From Figure 5 it can be seen that a single-pole six-throw switch is provided on each of the fourth transmission lines between the fourth input end and the fourth output end. It can be understood that Figure 5 each of the fourth input ends is used to be connected to the output cable of the corresponding solar array simulator 111 or DC regulated power supply 112 respectively so that the DC power supply provided by the solar array simulator 111 or DC regulated power supply 112 can be transmitted to the test control unit 12, and each of the fourth output ends is respectively connected to the ground test connector 16 so that the DC power supply provided by the solar array simulator 111 or DC regulated power supply 112 can be transmitted to the corresponding satellite 13 to be tested. It should be noted that in the initial stage of power distribution, each satellite 13 to be tested can be powered by 1 solar array simulator 111 and 1 DC regulated power supply 112. In this case, each satellite 13 to be tested is connected to the solar array simulator 111 and DC regulated power supply 112 with corresponding numbers. Of course, for Figure 5 the power distribution control method shown, it is also possible to provide DC power for the satellite 13 to be tested only through 6 solar array simulators 111 or 6 DC regulated power supplies 112.

[0061] When starting to work, first set the initial power distribution relationship; for example, the solar array simulator 111-1 supplies power to the satellite under test 13-1 through the fourth output terminal 1, the solar array simulator 111-2 supplies power to the satellite under test 13-2 through the fourth output terminal 2, the solar array simulator 111-3 supplies power to the satellite under test 13-3 through the fourth output terminal 3, the DC regulated power supply 112-1 supplies power to the satellite under test 13-1 through the fourth output terminal 4, the DC regulated power supply 112-2 supplies power to the satellite under test 13-2 through the fourth output terminal 5 respectively, and the DC regulated power supply 112-3 supplies power to the satellite under test 13-3 through the fourth output terminal 6 respectively. At this time, the closing status of the single-pole six-throw switch in the test control unit 12 is as Figure 5 shown. The switches K1_1, K2_2, K3_3, K4_1, K5_2, K6_3 are closed, and the rest remain in the open state. Then set the fourth output terminal 1 to the fourth output terminal 6 to be all open. At this time, each satellite under test 13 starts to charge.

[0062] Next, if the satellite under test 13-1, as the target satellite under test, needs to enter the high-power working mode, and it is determined that the solar array simulators 111-2 and 111-3 corresponding to the satellites under test 13-2 and 13-3 are used as the target solar array simulators and are respectively connected to the satellite under test 13-1 to meet the high-power working mode of the satellite under test 13-1, first close the fourth output terminals 2 and 3 corresponding to the solar array simulators 111-2 and 111-3 respectively, and set the switches K2_1 and K3_1 in the test control unit 12 to be closed, and then open the fourth output terminals 2 and 3 corresponding to the solar array simulators 111-2 and 111-3 respectively, so as to complete the switching of the power distribution connection relationship in the control system 1. At the same time, during the whole switching process, the satellites under test 13-2 and 13-3 can continue to charge through the DC regulated power supplies 112-2 and 112-3 respectively without power-off operation. Similarly, if the DC regulated power supplies 112-2 and 112-3, as the target DC regulated power supplies, can also meet the high-power power supply requirements of the satellite under test 13-1, the DC regulated power supplies 112-2 and 112-3 can also be connected to the satellite under test 13-1 according to the actual power supply requirements in a similar power distribution switching manner as above.

[0063] On the other hand, if the control system 1 needs to supply power to the satellite 13 to be tested in different stages, such as the general assembly stage, the overall satellite test stage, or the environmental test stage, etc. Specifically, for example, after the satellite 13-1 to be tested has completed power supply in one stage, in the embodiment of the present invention, it is first necessary to disconnect the battery inside the satellite 13-1 to be tested after the power supply is completed, and close the corresponding fourth output terminals 1 and 4 of the solar array simulator 111-1 and the DC regulated power supply 112-1 connected to the satellite 13-1 to be tested, and at the same time disconnect the corresponding switches K1_1 and K4_1 of the satellite 13-1 to be tested. At this time, the satellite 13-1 to be tested is completely powered off, so the ground test connector 16-1 can be disconnected to continue subsequent processes or operations. The power-off process of the entire satellite 13-1 to be tested does not affect the charging of other satellites to be tested.

[0064] It should be noted that when using two types of power supply units, namely the solar array simulator 111 and the DC regulated power supply 112, to charge the satellite 13 to be tested, for Figure 5 the shown power distribution control method can meet the situation where the number of satellites 13 to be tested is less than the total number of the solar array simulator 111 and the DC regulated power supply 112. In some examples, it can meet the power distribution situation where the number of satellites 13 to be tested is less than the number of the solar array simulator 111 or the DC regulated power supply 112.

[0065] For Figure 1 the shown control system 1, in some possible implementation manners, when the DC power supplies output by multiple solar array simulators 111 and / or multiple DC regulated power supplies 112 can be respectively transmitted to the test control unit 12 through multiple fifth input terminals, and can be respectively transmitted to multiple satellites 13 to be tested through multiple fifth output terminals,

[0066] the test control unit 12 is configured to be provided with double-pole multi-throw switches on each two fifth transmission lines respectively, and each double-pole multi-throw switch can be selectively opened or closed so that the DC power supplies provided by the target solar array simulator and / or the target DC regulated power supply can be respectively transmitted to the target satellite 13 to be tested through the corresponding fifth target transmission lines among multiple fifth transmission lines;

[0067] Among them, the fifth transmission line represents the transmission line between the fifth input terminal and the fifth output terminal.

[0068] For example, as Figure 6Taking the DC power supplies output by 3 solar array simulators and 3 DC regulated power supplies as an example, the DC power supplies are respectively transmitted to the test control unit 12 through 12 fifth input terminals, and the above DC power supplies are respectively transmitted to 3 satellites to be tested 13 through 12 fifth output terminals in the test control unit 12. The dynamic power distribution process will be described in detail. From Figure 6 It can be seen that a double-pole twelve-throw switch is provided on the fifth transmission line between every two fifth input terminals and every two fifth output terminals. It can be understood that Figure 6 every two of the fifth input terminals are used to be respectively connected to the output cables of the corresponding solar array simulator 111 or DC regulated power supply 112 so that the DC power supply provided by the solar array simulator 111 or DC regulated power supply 112 can be transmitted to the test control unit 12, and every two of the fifth output terminals are respectively connected to the ground test connector 16 so that the DC power supply provided by the solar array simulator 111 or DC regulated power supply 112 can be transmitted to the corresponding satellite to be tested 13. Specifically, for example Figure 6 the fifth input terminals 1-1 and 1-2 corresponding to the switch K1_1 and the switch K1_2 in are respectively connected to the positive and negative poles of the power supply output cable of the same solar array simulator 111, and the corresponding fifth output terminals 1-1 and 1-2 are connected to the positive and negative poles of the same ground test connector 16 to supply power to the same satellite to be tested 13. It should be noted that in the initial stage of power distribution, each satellite to be tested 13 can be powered by 1 solar array simulator 111 and 1 DC regulated power supply 112. In this case, each satellite to be tested 13 is connected to the solar array simulator 111 and DC regulated power supply 112 with corresponding numbers. Of course, for Figure 6 the power distribution control method shown can also provide DC power for the satellites to be tested 13 only through 6 solar array simulators 111 or 6 DC regulated power supplies.

[0069] It should be noted that Figure 6 the power distribution control method shown can make there be no electrical connection between different satellites to be tested to avoid power supply interference between the satellites to be tested.

[0070] When starting to work, first set the initial power distribution relationship; for example, the solar array simulator 111-1 supplies power to the satellite under test 13-1 through the fifth output terminal 1-1 and the fifth output terminal 1-2, the solar array simulator 111-2 supplies power to the satellite under test 13-2 through the fifth output terminal 2-1 and the fifth output terminal 2-2, the solar array simulator 111-3 supplies power to the satellite under test 13-3 through the fifth output terminal 3-1 and the fifth output terminal 3-2, the DC regulated power supply 112-1 supplies power to the satellite under test 13-1 through the fifth output terminal 4-1 and the fifth output terminal 4-2, the DC regulated power supply 112-2 supplies power to the satellite under test 13-2 through the fifth output terminal 5-1 and the fifth output terminal 5-2, the DC regulated power supply 112-3 supplies power to the satellite under test 13-3 through the fifth output terminal 6-1 and the fifth output terminal 6-2. At this time, the closing conditions of the single-pole six-throw switches in the test control unit 12 are as Figure 5 shown, the switches K1_1_1, K1_2_1, K2_1_2, K2_2_2, K3_1_3, K3_2_3, K4_1_1, K4_2_1, K5_1_2, K5_2_2, K6_1_3 and K6_2_3 are closed, and the rest remain in the open state. Then set the fifth output terminal 1-1 to the fifth output terminal 6-2 to be all open. At this time, each satellite under test 13 starts to charge.

[0071] Next, if the satellite under test 13-1 needs to enter the high-power working mode as the target satellite under test, and it is necessary to connect the solar array simulators 111-2 and 111-3 corresponding to the satellites under test 13-2 and 13-3 to the satellite under test 13-1 respectively as the target solar array simulators to meet the high-power working mode of the satellite under test 13-1, first close the fifth output terminals 2-1, 2-2, 3-1 and 3-2 corresponding to the solar array simulators 111-2 and 111-3 respectively, and correspondingly switch the switches in the test control unit 12 to K2_1_1, K2_2_1, K3_1_1, K3_2_1, so as to complete the switching of the power distribution connection relationship in the control system 1. At the same time, during the entire switching process, the satellites under test 13-2 and 13-3 can continue to charge through the DC regulated power supplies 112-2 and 112-3 respectively, without the need for power-off operation. Similarly, if the DC regulated power supplies 112-2 and 112-3 can also meet the high-power power supply requirements of the satellite under test 13-1 as the target DC regulated power supplies, the DC regulated power supplies 112-2 and 112-3 can also be connected to the satellite under test 13-1 according to the actual power supply requirements in a similar power distribution switching manner as above.

[0072] On the other hand, if it is necessary to control the power supply of the satellite 13 to be tested by the control system 1 at different stages, such as the general assembly stage, the overall satellite test stage, or the environmental test stage, etc. Specifically, for example, after the satellite 13-1 to be tested has completed the power supply for one stage, in the embodiment of the present invention, it is first necessary to disconnect the battery inside the satellite 13-1 that has completed the power supply, and turn off the corresponding fifth output terminals 1-1, 1-2, 4-1, and 4-2 of the solar array simulator 111-1 and the DC regulated power supply 112-1 connected to the satellite 13-1 to be tested, and at the same time disconnect the double-pole multi-throw switch corresponding to the satellite 13-1 to be tested. At this time, the satellite 13-1 to be tested is completely powered off, so the ground test connector 16-1 can be disconnected to continue the subsequent processes or operations. The power-off process of the entire satellite 13-1 to be tested does not affect the charging of other satellites to be tested.

[0073] It should be noted that when using two types of power supply units, namely the solar array simulator 111 and the DC regulated power supply 112, to charge the satellite 13 to be tested, for Figure 6 the power distribution control method shown can meet the situation where the number of satellites 13 to be tested is less than the total number of the solar array simulator 111 and the DC regulated power supply 112. In some examples, it can meet the power distribution situation where the number of satellites 13 to be tested is less than the number of the solar array simulator 111 or the DC regulated power supply 112.

[0074] For Figure 1 the control system 1 shown, in some possible implementation manners, as Figure 2 shown, an external display unit 121, an emergency power-off switch 122, and a manual operation keyboard 123 are provided outside the test control unit 12; among them,

[0075] the display unit 121 is used to monitor the power supply status of the satellite 13 to be tested in real time;

[0076] the emergency power-off switch 122 is used to quickly disconnect the power supply of the satellite 13 to be tested in an emergency;

[0077] the manual operation keyboard 123 is used to manually control the power supply status of the satellite 13 to be tested.

[0078] It can be understood that in the specific implementation process, a display unit 121, an emergency power-off switch 122, and a manual operation keyboard 123 are provided outside the test control unit 12, so that the process personnel can conveniently understand the power supply status of the satellite 13 to be tested on site, perform manual control, or quickly disconnect the power supply of the satellite 13 to be tested in an emergency.

[0079] It should be noted that, in the specific implementation process, an emergency power-off switch can also be externally connected to the test control unit 12. In addition, in the specific implementation process, the solar array simulator, the DC regulated power supply, the test control unit 12, the display unit 121, the emergency power-off switch, and the manual operation keyboard 123 are installed at the production line site, and the control computer 14 can be installed in the test room or the operation room to facilitate real-time monitoring of the power distribution and testing of the satellite 13 to be tested.

[0080] For Figure 1 the control system 1 shown, in some possible implementation manners, such as Figure 2 shown, a plurality of wired instruction lines 124 are arranged inside the test control unit 12, and the plurality of wired instruction lines 124 are all connected to the corresponding satellite 13 to be tested for sending control instructions to the corresponding satellite 13 to be tested. Specifically, the wired instruction line connected to the satellite 13 to be tested is used to send control instructions to the satellite to be tested, such as battery connection access, battery connection disconnection, main / backup machine switching and other instructions. It can be understood that since a battery is arranged inside the satellite 13 to be tested, if only the output ends corresponding to the solar array simulator 111 and the DC regulated power supply 112 are turned off, the satellite 13 to be tested cannot be completely powered off. Usually, it is necessary to first send a wired instruction to disconnect the battery connection, and then turn off the output ends corresponding to the solar array simulator 111 and the DC regulated power supply 112, so as to completely power off the satellite 13 to be tested. It should be noted that Figure 2 only one wired instruction line 124 is exemplarily shown between each satellite 13 to be tested and the test control unit 12, and the number of wired instruction lines can be determined according to the actual situation.

[0081] In addition, for the above implementation manners, in some examples, such as Figure 2 shown, a timing control logic unit 125 is further arranged inside the test control unit 12, and the timing control logic unit 125 is used to apply timing control to the wired instructions to complete the emergency power-off of the satellite 13 to be tested. Specifically, when an emergency occurs and the emergency power-off switch 122 needs to be pressed, first send an instruction to disconnect the battery connection through the wired instruction line 124, then disconnect the relay or switch inside the test control unit 12, and at the same time feedback the power-off situation to the control computer 14 through the Ethernet. It should be noted that the disconnection of the relay or switch inside the test control unit 12 is only completed inside the test control unit 12 without the intervention of the control computer 14.

[0082] Specifically, the steps to implement an emergency power-off operation for the satellite under test 13 are as follows: First, set the correspondence between the wired instruction sequence numbers, the satellite under test 13, and the internal instructions of the satellite under test 13. It should be noted that the internal instructions of the satellite under test 13 refer to the functions for the satellite under test 13 to execute wired instructions. Understandably, the correspondence between each wired instruction line 124 led out by the test control unit 12 and the above-mentioned internal instructions of the satellite under test 13 needs to be determined during the initial configuration. For example, the first to eighth wired instruction lines of the satellite under test 13 respectively correspond to internal instructions such as battery connection, battery disconnection, host switching, standby switching, solar panel deployment, reserved, reserved, and reserved. The test control unit 12 connects the first to eighth wired instruction lines to the satellite under test 13-1. Therefore, it is necessary to configure the display names of the first to eighth wired instruction lines and the instruction numbers corresponding to the emergency power-off in the control computer 14. For example, the display name of the second wired instruction line is "2 Battery Disconnection" so as to be able to send the correct wired instruction and the test control unit 12 can execute the emergency power-off instruction. Of course, according to actual requirements, the fourth to twelfth or the twentieth to twenty-eighth wired instruction lines can also be connected to the satellite under test 13-1, and only the corresponding relationship needs to be set in the control computer 14 during the initial configuration.

[0083] For example, taking 6 satellites under test 13 as an example, and each satellite under test 13 has 8 wired instruction lines 124, and taking the second one as the battery power-off instruction, there are 48 wired instruction lines 124 set inside the test control unit 12. Among them, the first to eighth wired instruction lines 124 are connected to the satellite under test 13-1, the ninth to sixteenth wired instruction lines 124 are connected to the satellite under test 13-2, the seventeenth to twenty-fourth wired instruction lines 124 are connected to the satellite under test 13-3, the twenty-fifth to thirty-second wired instruction lines 124 are connected to the satellite under test 13-4, the thirty-third to fortieth wired instruction lines 124 are connected to the satellite under test 13-5, and the forty-first to forty-eighth wired instruction lines 124 are connected to the satellite under test 13-6. Then, the second, tenth, eighteenth, twenty-sixth, thirty-fourth, and forty-second wired instruction lines 124 of the test control unit 12 are respectively used to send the battery power-off instructions for the satellites under test 13-1 to 13-6.

[0084] Next, after pressing the emergency power-off switch 122 corresponding to the satellite 13 to be tested, the test control unit 12 first sends a wired instruction for powering off the battery of the corresponding satellite 13 to be tested. For example, when the emergency power-off switch 122 corresponding to the satellite 13-2 to be tested is pressed, the wired instruction sent by the test control unit 12 is transmitted to the corresponding satellite 13-2 to be tested through the 10th wired instruction line 124 so that the battery of the satellite 13-2 to be tested is powered off. It should be noted that in the specific implementation process, the wired instruction line 124 can be set to repeatedly send several wired control instructions according to the actual situation to ensure the successful execution of the instruction. Again, the test control unit 12 disconnects the connection with the satellite 13-2 to be tested, that is, the relay or switch on the transmission line connected to the satellite 13-2 to be tested is disconnected, thereby completing the emergency power-off operation. Finally, after the emergency power-off operation is completed, the test control unit 12 sends the current power-off status to the control computer 14 through the Ethernet for the next operation. It can be understood that the above entire power-off operation is only performed on the satellite 13-2 to be tested and does not affect the power supply status of other satellites to be tested.

[0085] In addition, for Figure 1 the control system 1 shown, in some possible implementation manners, as Figure 2 shown, a wired telemetry unit 125 is further provided inside the test control unit 12 to real-time monitor various power supply parameters inside the satellite 13 to be tested, such as the bus voltage and load current parameters, and send these parameters to the control computer 14 or display them on the display unit 121 to facilitate the on-site real-time monitoring of the power supply status of the satellite 13 to be tested by the process personnel.

[0086] It should be noted that in the specific implementation process, Figure 2 the satellite ground power supply, satellite wired instructions, and satellite wired measurement signal interfaces in

[0087] can be set on the same ground test connector 16, or can be correspondingly set on different ground connectors 16. Figure 7 Referring to

[0088] S701, determine the target solar array simulator from multiple solar array simulators and / or determine the target DC regulated power supply from multiple DC regulated power supplies, and determine the power distribution connection relationship between the target solar array simulator and / or the target DC regulated power supply and the target satellite to be tested;

[0089] S702. Transmit the DC power supply provided by the target solar array simulator and / or the target DC regulated power supply to the target satellite under test among the multiple satellites under test according to the power distribution connection relationship between the target solar array simulator and / or the target DC regulated power supply and the target satellite under test.

[0090] Understandably, since Figure 7 the control method shown can be applied to the control system 1 described in the foregoing technical solution, for the specific details of the control method, reference can be made to the detailed description of each component in the control system 1 in the foregoing technical solution, which will not be elaborated here.

[0091] For Figure 7 the control method shown, in some examples, the control method further includes that when the test of the target satellite under test is completed, while performing a power-off operation on the target satellite under test, the other satellites under test can remain powered on.

[0092] It should be noted that: among the technical solutions described in the embodiments of the present invention, they can be combined arbitrarily without conflict.

[0093] As described above, the above are only the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A control system for multi-satellite dynamic power distribution, characterized in that, the control system includes: a power supply unit, a test control unit, and multiple satellites to be tested; wherein, the input end of the test control unit is connected to the power supply unit, and the output end of the test control unit is respectively connected to multiple satellites to be tested; wherein, the power supply unit includes multiple solar array simulators and multiple DC regulated power supplies, which are used to provide DC power for multiple satellites to be tested respectively; the test control unit is configured to: based on the power distribution connection relationship between the target solar array simulator determined from multiple solar array simulators and / or the target DC regulated power supply determined from multiple DC regulated power supplies and the target satellite to be tested among multiple satellites to be tested, transmit the DC power provided by the target solar array simulator and / or the target DC regulated power supply to the target satellite to be tested among multiple satellites to be tested; wherein, the test control unit is further configured to: when the target satellite to be tested is in a high-power working mode or different stages, dynamically switch the power distribution connection relationship, so that the DC power provided by the target solar array simulator and / or the target DC regulated power supply is respectively output to the target satellite to be tested; and when the DC power output by multiple solar array simulators and multiple DC regulated power supplies is respectively transmitted to the test control unit through multiple first input ends and multiple second input ends, and is respectively transmitted to multiple satellites to be tested through multiple first output ends and multiple second output ends, the test control unit is configured to: a multi-way relay is provided on each first transmission line and each second transmission line, and each relay can be opened or closed, so that the DC power provided by the target solar array simulator and / or the target DC regulated power supply is respectively transmitted to the target satellite to be tested through the corresponding first target transmission line among multiple first transmission lines and the corresponding second target transmission line among multiple second transmission lines; wherein, the first transmission line represents the transmission line between the first input end and the first output end; the second transmission line represents the transmission line between the second input end and the second output end.

2. The control system according to claim 1, characterized in that, the control system further includes a control computer, a network switch, and multiple ground test connectors; wherein, the control computer is respectively connected to the power supply unit and the test control unit through the network switch; the control computer is configured to: determine the target solar array simulator that provides DC power for the target satellite to be tested from multiple solar array simulators; and / or, determine the target DC regulated power supply that provides DC power for the target satellite to be tested from multiple DC regulated power supplies; and, determine the power distribution connection relationship between the target solar array simulator and / or the DC regulated power supply and the target satellite to be tested; and, real-time monitor the power supply status of the satellite to be tested. The network switch is configured to: Interactively transmit data signals between the power supply unit and the control computer in real time; and Interactively transmit data signals between the test control unit and the control computer in real time; A plurality of the ground test connectors are respectively connected to the test control unit and a plurality of the satellites to be tested, and are used for receiving the DC power supply provided by the power supply unit and outputting the DC power supply to the satellites to be tested.

3. The control system according to claim 1, characterized in that when the DC power supplies output by a plurality of the solar array simulators and / or a plurality of the DC regulated power supplies can be respectively transmitted to the test control unit through a plurality of third input ends and can be respectively transmitted to a plurality of the satellites to be tested through a plurality of third output ends, the test control unit is configured to be provided with a multi-way relay on each third transmission line, and each relay can be selectively opened or closed so that the DC power supply provided by the target solar array simulator and / or the target DC regulated power supply can be respectively transmitted to the target satellite to be tested through the corresponding third target transmission line among a plurality of the third transmission lines; wherein, the third transmission line represents the transmission line between the third input end and the third output end.

4. The control system according to claim 1, characterized in that when the DC power supplies output by a plurality of the solar array simulators and / or a plurality of the DC regulated power supplies can be respectively transmitted to the test control unit through a plurality of fourth input ends and can be respectively transmitted to a plurality of the satellites to be tested through a plurality of fourth output ends, the test control unit is configured to be provided with a single-pole multi-throw switch on each fourth transmission line, and each single-pole multi-throw switch can be selectively opened or closed so that the DC power supply provided by the target solar array simulator and / or the target DC regulated power supply can be respectively transmitted to the target satellite to be tested through the corresponding fourth target transmission line among a plurality of the fourth transmission lines; wherein, the fourth transmission line represents the transmission line between the fourth input end and the fourth output end.

5. The control system according to claim 1, characterized in that when the DC power supplies output by a plurality of the solar array simulators and / or a plurality of the DC regulated power supplies can be respectively transmitted to the test control unit through a plurality of fifth input ends and can be respectively transmitted to a plurality of the satellites to be tested through a plurality of fifth output ends, the test control unit is configured to be provided with a double-pole multi-throw switch on every two fifth transmission lines, and each double-pole multi-throw switch can be selectively opened or closed so that the DC power supply provided by the target solar array simulator and / or the target DC regulated power supply can be respectively transmitted to the target satellite to be tested through the corresponding fifth target transmission line among a plurality of the fifth transmission lines; wherein, the fifth transmission line represents the transmission line between the fifth input end and the fifth output end.

6. The control system according to claim 1, characterized in that An external part of the test control unit is provided with a display unit, an emergency power-off switch, and a manual operation keyboard; among them, the display unit is used for real-time monitoring of the power supply status of the satellite to be tested; the emergency power-off switch is used for quickly cutting off the power supply of the satellite to be tested in an emergency; the manual operation keyboard is used for manually controlling the power supply status of the satellite to be tested.

7. The control system according to claim 1, characterized in that a plurality of wired command lines are arranged inside the test control unit, and the plurality of wired command lines are all connected to the corresponding satellite to be tested for sending control commands to the corresponding satellite to be tested.

8. The control system according to claim 7, characterized in that a timing control logic unit is further arranged inside the test control unit, and the timing control logic unit is used for applying timing control to the wired commands to complete the emergency power-off of the satellite to be tested.

9. A control method for multi-satellite dynamic power distribution, characterized in that the control method can be applied to the control system according to any one of claims 1 to 8, and the control method includes: determining a target solar array simulator and / or a target DC regulated power supply from a plurality of the solar array simulators, and determining the power distribution connection relationship between the target solar array simulator and / or the target DC regulated power supply and the target satellite to be tested; transmitting the DC power supplied by the target solar array simulator and / or the target DC regulated power supply to the target satellite to be tested among a plurality of the satellites to be tested according to the power distribution connection relationship between the target solar array simulator and / or the target DC regulated power supply and the target satellite to be tested; wherein, when the target satellite to be tested is in a high-power working mode or different stages, the power distribution connection relationship is dynamically switched so that the DC power supplied by the target solar array simulator and / or the target DC regulated power supply is respectively output to the target satellite to be tested; and when the DC power output by a plurality of the solar array simulators and a plurality of the DC regulated power supplies is respectively transmitted to the test control unit through a plurality of first input ends and a plurality of second input ends, and is respectively transmitted to a plurality of the satellites to be tested through a plurality of first output ends and a plurality of second output ends, a plurality of multi-way relays are arranged on each first transmission line and each second transmission line, and each relay can be opened or closed so that the DC power supplied by the target solar array simulator and / or the target DC regulated power supply is respectively transmitted to the target satellite to be tested through a corresponding first target transmission line among a plurality of the first transmission lines and a corresponding second target transmission line among a plurality of the second transmission lines; wherein, the first transmission line represents a transmission line between the first input end and the first output end; the second transmission line represents a transmission line between the second input end and the second output end.

10. The control method according to claim 9, characterized in that The control method further includes that when the target satellite to be tested is completed with the test, while performing a power-off operation on the target satellite to be tested, other satellites to be tested can avoid performing the power-off operation.

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