Satellite power-off test method for RBC-carrying composite bus system

Abstract

The present invention discloses a satellite power-on and power-off test method of an RBC-loaded composite bus system. First, a pre-power-on VI curve is proposed to solve the RBC protection and bus undervoltage caused by the parallel output of multiple ground power supplies when the traditional test uses the minimum power curve to add power off; and the order of the battery power relay on and off and the VI curve switching is designed to prevent the curve switching from causing transient bus undervoltage; secondly, the ground power supply output power is accurately adjusted to supply power to the non-direct distribution subsystem at the back end of the RBC to avoid the satellite bus undervoltage caused by the load loading at the back end of the RBC; the ground power supply output power is accurately adjusted again to limit the charging current when the battery power relay is on and off to avoid the power relay contact adhesion. The present invention optimizes the satellite power-on and power-off test of the RBC-loaded composite bus system, solves the RBC protection and satellite bus undervoltage problems caused by the minimum power curve plus power off in the traditional test, and effectively avoids the risk of contact adhesion when the battery relay is on and off.

Description

Technical Field

[0001] The invention relates to the technical field of spacecraft power supply and distribution testing, and in particular to a satellite power-on and power-off testing method of an RBC-carrying composite busbar system. Background Art

[0002] The composite bus system power supply and distribution subsystem adopts the topology structure of unregulated bus outputting fully regulated bus through fully regulated bus converter (Regulated Bus Converter, RBC), which has the advantages of small impact of load fluctuation on the performance of fully regulated bus and high power quality density of power supply and distribution subsystem, and is suitable for satellites with high power and pulse load characteristics. Composite bus system satellites are composed of fully regulated bus and unregulated bus, in which the fully regulated bus is obtained by converting the unregulated bus through RBC. However, for RBC loaded composite bus system satellites, bus undervoltage and battery power relay contact adhesion problems are prone to occur during satellite power-off test. The main analysis is as follows.

[0003] In the RBC-loaded composite bus system satellite, the back end of the power supply and distribution subsystem RBC will be equipped with a distribution direct load to reduce the risk of distributor failure and improve the overall reliability of the subsystem. However, due to the influence of the distribution direct load, the RBC is in a loaded state when the satellite is powered on or off, which makes the composite bus system satellite power on and off have higher requirements for the ground power supply. The power supply of the ground power supply needs to reach the power demand value of the RBC back end load within tens of milliseconds, otherwise the on-board RBC will automatically start the power-off protection mechanism, thereby causing the satellite bus to be undervoltage. The ground power supply is a solar array simulator (SAS, Solar Array Simulator).

[0004] When traditional satellite testing and power-off are performed, the satellite test minimum power curve and the parallel output of multiple ground power supplies are generally used to simulate the output characteristics of the solar array when the satellite enters and exits the earth's shadow, and then the whole satellite test is performed; there is a time difference in the parallel output of multiple ground power supplies, and this method is difficult to meet the above-mentioned RBC load and power-off requirements for the consistency of ground power supply power and response time, which is easy to cause RBC protection and bus undervoltage problems. Therefore, it is necessary to redesign the satellite power-off RBC load method to prevent the satellite bus undervoltage problem.

[0005] On the other hand, satellites with a composite bus system adopt a parallel design of battery packs and unregulated busbars. A power relay switch is set between the battery pack and the unregulated busbar, and the parallel control of the two is achieved by controlling the on and off of the power relay. However, when the composite bus system satellite is powered on and off, if the current of the ground power supply curve is not accurately controlled when the power relay is turned on and off, it may cause relay contact adhesion and fusing accidents. When the existing satellite is powered off, the ground power supply is disconnected one by one, and each disconnection must be checked and telemetered, which is relatively inefficient. Therefore, in order to solve this problem, measures must be taken to strictly restrict the charging current size when the battery relay is turned on and off to prevent battery on and off safety accidents.

[0006] In general, the composite bus system satellite power supply and distribution adopts load starting and fully regulated / unregulated hybrid bus design. The satellite power-on and power-off process has strict requirements on the transient power, output time, and power supply curve current of the ground power supply. Bus undervoltage and battery power relay contact adhesion problems are prone to occur during testing. Summary of the invention

[0007] In view of this, the present invention provides a satellite power-on and power-off testing method of an RBC-loaded composite bus system, designs a pre-power-on VI curve, and optimizes the whole satellite power-on and power-off process. It can effectively prevent bus undervoltage from occurring when the RBC is loaded when the satellite is powered on and off during the whole satellite testing phase, and reduce the risk of contact sticking when the battery power relay is turned on and off, thereby improving the power supply safety and reliability of the composite bus system satellite test.

[0008] To optimize the ground power supply VI curve, a single power supply can be used with a pre-powered VI curve: increase the maximum power point current of the VI curve, thereby increasing the maximum power point power of the VI curve.

[0009] The pre-power-on VI curve, its maximum power point current I mp (C0) is the maximum power point current I of the minimum power curve C1 mp (C1) q times, and does not exceed the maximum output current I of the ground power supply GSAS , q∈[10,16]; and the maximum power point current Where Ps(i) is the load power of the ith direct distribution subsystem when the satellite is initially powered on, U mp (C0) is the maximum power point voltage, i≥1, k≥1.1, where k is the current coefficient; and the maximum power point voltage U mp (C0)>U(Bb), where U(Bb) is the actual voltage of the battery pack when the satellite is initially powered on. The initial power-on state of the satellite is when the satellite's power supply and distribution subsystem and the RBC back-end direct power distribution load are working. At this time, a single power supply is used, and the pre-power-on VI curve can be used.

[0010] The design idea is: the total power of the ground power supply meets the RBC back-end direct distribution subsystem, and generally a single ground power supply can be used. When powering on, before setting the satellite test minimum power VI curve, add a pre-power VI curve; when powering off, first restore to the minimum power VI curve, then switch to the pre-power VI curve, and finally turn off the ground power.

[0011] In the above design, since the pre-power-on VI curve C0 is applied during the power-on process, there is no need to consider the inconsistent response time of the output power of multiple ground power supplies, so RBC protection and bus undervoltage can be avoided. It should be noted that, considering the process of ground power switching, if the VI curve is switched when the onboard battery is not connected (the battery power relay switch is not closed), the satellite will have a temporary bus undervoltage at the moment of curve switching. Therefore, in the above design, the battery is connected first, and then the ground power VI curve is switched.

[0012] The specific idea is: when the RBC-loaded composite bus system satellite is initially powered on, the pre-power-on VI curve is set, and a single ground power supply is used. Under the premise of closing the battery power relay switch, the ground power supply outputs the pre-power-on VI curve first, and then switches to the minimum power VI curve; when the RBC-loaded composite bus system satellite is powered off, under the premise of closing the battery power relay switch, the ground power supply VI curve is first set to the minimum power VI curve, and then switched to the pre-power-on VI curve, the battery power relay switch is disconnected, and finally the ground power is turned off.

[0013] Considering that the load of the onboard power supply includes the RBC back-end direct distribution subsystem and the RBC back-end indirect distribution subsystem, the direct distribution subsystem starts working when the satellite is powered on; the indirect distribution subsystem starts working after the entire satellite is powered on and the onboard power distribution switch is set to closed. Using a single power supply can supply power to the RBC back-end direct distribution subsystem, but it is difficult to meet the increased power demand of the indirect distribution subsystem.

[0014] Therefore, when starting the RBC back-end non-direct distribution subsystem, the output power and P(M) of the ground power supply should satisfy: P(M)≥∑(Ps(i))+∑(Pusb(j)), where j≥1, the number of ground power supplies is M, Ps(i) is the load power of the i-th direct distribution subsystem when the satellite is initially powered on, and Pusb(j) is the load power of the j-th RBC back-end non-direct distribution subsystem with power supply demand during the satellite power-on test; the power provided by the ground power supply just meets the power requirements of the satellite's initial power-on (including direct) and non-direct distribution subsystems. The RBC back-end non-direct distribution is completed by the satellite power distribution manager. When outputting M ground power supplies, multiple power supplies can be set to output in parallel. At this time, according to the pre-power-on VI curve, the sum of the power supply power of the M ground power supplies can meet the power requirements of the satellite's initial power-on (including direct) and the RBC back-end non-direct distribution subsystem for the ground power supply power, and will not cause bus undervoltage problems.

[0015] After the non-direct distribution subsystem is powered on, it can transmit the telemetry information of the entire satellite to the ground, which is convenient for comprehensive inspection of the correctness of the status of each satellite subsystem. At the same time, it also ensures that the battery charging current telemetry value can be monitored when the battery switch is turned on to ensure that the telemetry value is within the normal range.

[0016] In order to ensure the safety when the battery switch is turned on (or the battery switch is turned off during power-off), the charging current during the on-off action of the battery relay is strictly constrained, and the following design is performed: the output power and P(N) of the ground power supply used should satisfy: P(N)-[∑(Ps(i))+∑(Pusb(j))]∈(0,Pmax(Bps)), where N is the number of ground power supplies, Pmax(Bps) is the maximum safe charging power when the satellite battery power relay is on and off; Pmax(Bps)=I(Bps)*U(Bps), where U(Bps) is the actual voltage of the battery group when the satellite battery power relay is on and off. The power provided by the ground power supply just meets the power requirements of the initial power-on (including direct-on), non-direct-on distribution subsystem, and battery charging on the satellite.

[0017] In actual operation, considering that the total ground power output is M, the non-direct distribution subsystem is powered on (such as the data management subsystem), which can have the ability to transmit the telemetry information of the entire satellite to the ground, so as to facilitate a comprehensive check of the correctness of the status of each satellite subsystem and whether the satellite telemetry status is normal when the battery power relay is turned on. The two-level power-on method from M→N should be followed.

[0018] In summary, the power-on test method is as follows: first, a single ground power supply is used to power on the RBC back-end direct distribution subsystem according to the pre-power-on VI curve C0 output; then, M ground power supplies are used to power on the RBC back-end direct and indirect distribution subsystems according to the pre-power-on VI curve C0 output; then, N ground power supplies are used to power on the RBC back-end direct and indirect distribution subsystems according to the pre-power-on VI curve C0 output, and the batteries are charged; when the battery power relay is confirmed to be connected, the satellite telemetry state is normal, and then it can be switched to the minimum power VI curve C1; finally, all X ground power supplies are output, the power-on is completed, the initial test state is established, and the satellite test starts;

[0019] The method for power-off test is as follows: restore the satellite to the initial test state, that is, according to the minimum power VI curve C1, all X ground power outputs are used to supply power to the RBC back-end direct and non-direct distribution subsystems and batteries, and other subsystems are powered off; first prohibit all ground power outputs, switch to the pre-power VI curve C0, and then use N ground power outputs; confirm that the satellite telemetry state is normal, then disconnect the battery power relay, and power off the satellite RBC back-end non-direct and direct distribution subsystems in turn.

[0020] During the power-on and power-off process, when checking the telemetry values, if there is a problem with the telemetry, you should stay on site first, eliminate the problem, and then decide whether to continue powering on or power off based on the situation; when troubleshooting the problem, you should first check whether the ground power supply is outputting normally, eliminate the problem with the ground power supply, and then check whether the onboard equipment is abnormal.

[0021] Furthermore, the battery charging current must satisfy 0≤I≤I(Bps);

[0022] Furthermore, the maximum power point voltage U of the pre-power-on VI curve C0 is mp There is no special limitation on the short-circuit voltage and it can be the same as the minimum power VI curve C1.

[0023] A RBC-carrying composite bus system satellite power-off test method, comprising:

[0024] (I) RBC-carrying composite bus system satellite power-on test plan:

[0025] S1: Set the ground power on status;

[0026] S2: Determine the pre-power-on VI curve C0 and calculate the voltage lower limit and current lower limit of its maximum power point;

[0027] S3: Set the ground power VI curve to the pre-power VI curve C0;

[0028] S4: When the satellite is initially powered on, a single ground power supply is used to meet the power requirements of the RBC back-end direct distribution subsystem; the entire satellite bus voltage is established under the RBC load, and the satellite bus voltage and other telemetry values ​​are checked to meet the satellite power-on telemetry criteria;

[0029] S5: Increase the total number of ground power outputs to M, so that the power it provides meets the power requirements of the RBC back-end direct power distribution and indirect power distribution subsystems when initially powered on on the satellite, start the RBC back-end indirect power distribution subsystem, and check the telemetry correctness of each powered-on subsystem;

[0030] After the non-through power distribution subsystem is powered on, it can have the ability to transmit the telemetry information of the entire satellite to the ground, which is convenient for a comprehensive check of the correctness of the status of each subsystem of the satellite.

[0031] S6: Increase the total number of ground power outputs N again, so that the power it provides can meet the power requirements of the initial power-on RBC back-end direct power distribution, non-direct power distribution subsystem and battery charging on the satellite;

[0032] S7: Close the battery power relay switch to confirm that the satellite telemetry state is normal when the battery power relay is turned on;

[0033] S8: Switch the ground power VI curve C0 to the satellite test minimum power VI curve C1;

[0034] S9: Send output instructions to all (1-X) ground power supplies, check the correctness of bus voltage and telemetry of each subsystem, and meet the power requirements of the entire satellite test;

[0035] S10: Establish the initial test state and start the satellite test; the satellite initial test state is: according to the minimum power VI curve C1, all X ground power supplies are output (whose power is greater than the sum of the initial power-on, non-direct power distribution subsystem, and battery charging power on the satellite), to supply power to the RBC back-end direct and non-direct power distribution subsystems and batteries, and the satellite payload, data transmission, thermal control, control and other subsystems have been powered off. At this time, the satellite initial test state is the state of powering up with the minimum power VI curve in the traditional power-on method and preparing for testing.

[0036] (II) RBC-carrying composite bus system satellite power failure test plan:

[0037] E1: Restore the satellite working state to the satellite power-on test state: use all X ground power supplies, whose power is greater than the sum of the initial power-on on the satellite, the non-direct power distribution subsystem, and the battery charging power; confirm that the satellite payload, data transmission, thermal control, control and other subsystems are powered off, and the battery is connected; the satellite initial test state at this time is the state of power-on in the traditional power-on mode, using the minimum power VI curve to power on and ready for testing.

[0038] E2: Switch the ground power supply VI curve to the satellite test minimum power VI curve C1;

[0039] E3: Confirm that the battery power relay switch is in the closed state, send the output inhibition command for all ground power supplies; turn off all ground array outputs. At this time, the satellite is powered by the on-board battery. Because the number of ground power supply output units in S6 is generally much less than half of the power supply output when the satellite power-on is completed, that is, when N << X / 2, at this time, turn off all ground power supplies and then increase to N units of output later, which can improve the satellite power-off efficiency;

[0040] E4: Switch the ground power supply VI curve C1 to the pre-power-on VI curve C0;

[0041] E5: Increase the total number of ground power supply outputs to N, so that the power provided meets the power requirements of the on-board initial power-on RBC back-end direct power distribution, non-direct power distribution subsystems, and battery charging; confirm that the battery charging current telemetry is within the range, and continuously charge for 1 - 2 minutes;

[0042] E6: Disconnect the battery power relay switch;

[0043] E7: Disconnect the non-direct power distribution subsystem at the back end of the RBC that requires power supply during satellite power-on testing;

[0044] E8: Disconnect the direct power distribution subsystem and send the command to inhibit all ground power supply outputs;

[0045] E9: Check the satellite ground wired telemetry and confirm the satellite power-off state;

[0046] E10: Turn off the ground power supply;

[0047] To ensure that when the satellite is powered off, the satellite power supply can be quickly and reliably switched from being powered by X units of the ground power supply VI curve C1 to being powered by N units of the ground power supply pre-power-on VI curve C0, a method is adopted where, with the battery power relay switch in the closed state, first send the output inhibition for all ground power supplies (step E3), and after switching the ground power supply VI curve C1 to the pre-power-on VI curve C0 (step E4), then output N units of ground power supply output (step E5), so as to improve the power-off efficiency and safety.

[0048] Beneficial effects:

[0049] A satellite power-on and power-off test method for an RBC load-bearing composite bus system according to the present invention has the following beneficial effects compared with the prior art:

[0050] (1) The present invention proposes that in the case of RBC load and power-off of a composite bus system satellite, by setting a pre-power-on VI curve C0, a single ground power supply is used to establish the bus voltage of the entire satellite, thereby solving the RBC protection and bus undervoltage problems caused by the delay difference of parallel output of multiple ground power supplies when the minimum power curve C1 is used to perform satellite power-off in traditional testing;

[0051] (2) The present invention proposes that after the entire satellite bus voltage is established, the ground power curve is switched under the premise that the battery relay is closed, thereby avoiding the problem of transient satellite bus undervoltage caused by the curve switching action when the battery relay is not closed;

[0052] (3) The present invention proposes to accurately adjust the power output power of all ground power supplies twice (achieved by adjusting the output current of all ground power supplies) to realize power supply to the RBC back-end non-direct distribution subsystem that has power supply demand during satellite power-on testing, thereby preventing the risk of bus undervoltage; on the other hand, it realizes automatic control of the upper limit of battery charging current, effectively avoiding the risk of contact sticking when the battery relay is closed / opened. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] Figure 1 A schematic diagram of the power-on steps of a satellite with a composite busbar system of RBC according to the present invention;

[0054] Figure 2 It is a schematic diagram of the satellite power-off steps of the RBC-carrying composite bus system of the present invention. DETAILED DESCRIPTION

[0055] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0056] The present invention provides a satellite power-on and power-off test method of an RBC-loaded composite bus system. This patent first proposes to solve the RBC protection and bus undervoltage problems caused by the time difference of parallel output of multiple ground power supplies when the traditional test uses the minimum power curve to perform satellite power-on and power-off. Secondly, by designing the order of switching on and off of the battery power relay and the test VI curve, the transient satellite bus undervoltage caused by the VI curve switching action is prevented; thirdly, by accurately adjusting the output current of the ground power supply twice, on the one hand, the sequential power supply of the non-direct distribution subsystem at the back end of the RBC during the satellite power-on test is realized, avoiding the risk of satellite bus undervoltage caused by the load loading at the back end of the RBC; on the other hand, the charging current during the on-off action of the battery power relay is automatically limited to avoid the risk of adhesion of the power relay contacts.

[0057] Embodiment 1:

[0058] Taking a satellite with a composite busbar system as an example, the satellite measurement and control subsystem belongs to the RBC back-end direct distribution load, and uses a 16-way solar array simulator (SAS, Solar Array Simulator) as the ground power supply. The satellite RBC load and power-off steps are as follows:

[0059] (1) Power-on steps:

[0060] 1) Turn on the SAS device and unplug the battery discharge protection plug;

[0061] 2) According to the total load power of the power distribution subsystem and the RBC back-end direct distribution subsystem when the satellite is initially powered on, the maximum operating point voltage of the pre-power VI curve C0 is calculated to be 100V, and the maximum operating point current is 3A;

[0062] 3) Set the ground SAS power supply VI curve to the pre-power-on VI curve C0;

[0063] 4) Send the first SAS power supply output command, check and confirm that the satellite bus voltage and other telemetry values ​​meet the satellite power-on telemetry criterion range requirements; then send the second SAS output command;

[0064] 5) Send the command to the digital control subsystem to check the correctness of telemetry of each powered subsystem;

[0065] 6) Send the third SAS output command to confirm that the battery charging current telemetry is within the range of 0 to 5A and continue charging for 1 minute; in order to ensure that the battery charging current is stable enough and reduce the risk of power relay connection.

[0066] 7) Send a power relay on command;

[0067] 8) Switch the ground SAS power supply VI curve from the pre-power-on VI curve C0 to the satellite test minimum power curve C1 (the maximum operating point voltage of each array is 100V, and the maximum operating point current is 0.5A);

[0068] 9) Output all 16 square matrices;

[0069] 10) Check the correctness of the bus voltage and telemetry of each subsystem; after confirming that the satellite power-on test status is correct, start the whole satellite test.

[0070] (2) Power off steps:

[0071] 1) Confirm that the satellite payload, data transmission, thermal control, control and other subsystems have been powered off, and the satellite working state has been restored to the satellite power-on test state; the satellite power-on test state uses the minimum power curve C1, and the ground power supply power is greater than the sum of the initial power-on (including direct-through), non-direct-through power distribution subsystem, and battery charging power on the satellite; the battery is in the on state.

[0072] 2) Set the ground SAS power VI curve to the minimum power curve for satellite testing;

[0073] 3) Confirm that the battery power relay switch is in the closed state, and confirm that the on-board battery capacity meets the requirements for one eclipse cycle test. Then turn off all ground array outputs. Because in step 6) of power-on, the output of N = 3 ground arrays is much less than half of the number of SAS power supply circuits X = 16 in the satellite power-on test state, that is, when N << X / 2, turning off all ground power supplies at this time and then outputting from N ground power supplies later can improve the satellite power-off efficiency;

[0074] 4) Set the ground SAS power VI curve to the pre-power-on VI curve C0;

[0075] 5) Send commands for the power output of the first to third ground arrays, check that the telemetry of the battery charging current is within the range of 0 - 5A, and continuously charge for 1 minute;

[0076] 6) Send a command to disconnect the power relay;

[0077] 7) Send a command to disconnect the TM&TC subsystem;

[0078] 8) Send commands to prohibit the output of the first to third ground power supplies and turn off the direct power distribution; Prohibiting output is a state of the ground power supply. To cut off the power of the equipment, the ground power supply needs to be turned off.

[0079] 9) Check whether the satellite bus voltage is 0;

[0080] 10) Turn off the SAS equipment and insert the battery discharge protection plug.

[0081] In summary, the above is only a preferred embodiment of the present invention and is not intended to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A RBC-carrying composite bus system satellite power-off test method, characterized in that: During the power-on test, first use a single ground power supply to power on the RBC back-end direct distribution subsystem according to the pre-power-on VI curve C0 output; then use M ground power supplies to power on the RBC back-end direct and indirect distribution subsystems according to the pre-power-on VI curve C0 output; then use N ground power supplies to power on the RBC back-end direct and indirect distribution subsystems according to the pre-power-on VI curve C0 output, and charge the battery; when it is confirmed that the battery power relay is connected and the satellite telemetry state is normal, it can be switched to the minimum power VI curve C1; finally, output all X ground power supplies, power-on is completed, the initial test state is established, and the satellite test starts; The pre-power-on VI curve C0, its maximum power point current , where q∈ [10,16], is the maximum power point current of the minimum VI power curve C1, is the maximum output current of a single ground power supply; and the maximum power point current ≥ ,in is the maximum power point voltage, i ≥ 1, where k is the current coefficient, k ≥ 1.1, Ps(i) is the load power of the ith direct distribution subsystem when the satellite is initially powered on; the maximum power point voltage >U(Bb), where U(Bb) is the actual voltage of the battery pack during the satellite power-on test; During the power-off test, the satellite is restored to the initial test state, that is, according to the minimum power VI curve C1, all X ground power supplies are output to supply power to the RBC back-end direct and non-direct distribution subsystems and batteries, and other subsystems are powered off; first prohibit all ground power outputs, switch to the pre-power VI curve C0, and then output by N ground power supplies; confirm that the satellite telemetry state is normal, then disconnect the battery power relay, and power off the satellite RBC back-end non-direct and direct distribution subsystems in turn; The total output power of M ground power supplies and P(M) should satisfy: P(M)≥∑(Ps(i))+∑(Pusb(j)), where j≥1, the number of ground power supplies is M, and Pusb(j) is the load power of the jth RBC back-end non-direct power distribution subsystem with power supply demand during satellite power-on test; The total output power P(N) of N ground power supplies should satisfy: P(N)-[∑(Ps(i))+∑(Pusb(j))]∈(0, Pmax(Bps)), Pmax(Bps) is the maximum safe charging power when the satellite battery power relay is on and off; Pmax(Bps)= I(Bps)* U(Bps), where I(Bps) is the maximum safe charging current when the satellite battery power relay is on and off, and U(Bps) is the actual voltage of the battery pack when the satellite battery power relay is on and off.

2. A satellite power-off test method for RBC-carrying composite bus system as claimed in claim 1, characterized in that: The charging current of the battery must satisfy 0≤I≤I(Bps).

3. A satellite power-off test method for RBC-carrying composite bus system as claimed in claim 1, characterized in that: The pre-power VI curve C0 and the minimum power VI curve C1 have the same maximum power point voltage and the same short-circuit voltage.

4. The RBC-carrying composite bus system satellite power-off test method as described in any one of claims 1-3, characterized in that: The satellite power-on steps specifically include: RBC-loaded composite bus system satellite power-on test method: S1: Set the ground power on status; S2: Determine the pre-power-on VI curve C0 and calculate the voltage lower limit and current lower limit of its maximum power point; S3: Set the ground power VI curve to the pre-power VI curve C0; S4: When initially powering up the satellite, a single ground power supply is used to ensure that its power meets the power requirements of the RBC back-end direct power distribution subsystem. The RBC direct power distribution system is powered on to establish the bus voltage of the entire satellite and check that the satellite bus voltage telemetry value meets the satellite power-on telemetry criterion range. S5: Increase the total number of ground power outputs to M, so that the power it provides meets the power requirements of the satellite RBC back-end direct power distribution and indirect power distribution subsystems, start the RBC back-end indirect power distribution subsystem, and check the telemetry correctness of each powered subsystem; S6: Increase the total number of ground power outputs to N again, so that the power it provides meets the power requirements of the RBC back-end direct power distribution, non-direct power distribution subsystem and battery charging; S7: Close the battery power relay switch to confirm that the satellite telemetry is in normal state after the battery is connected; S8: Switch the ground power VI curve C0 to the satellite test minimum power VI curve C1; S9: Send output instructions to all X-station ground power supplies to check the correctness of bus voltage and telemetry of each subsystem; S10: Confirm the satellite power-on test status and start the whole satellite test.

5. A satellite power-off test method for RBC-carrying composite bus system as described in any one of claims 1-3, characterized in that: The satellite power-off steps include: E1: Restore the satellite working state to the initial test state: Use all X ground power supplies, whose power is greater than the sum of the power of the onboard direct and indirect power distribution subsystems and battery charging; confirm that the satellite payload, data transmission, thermal control, and control subsystems are powered off; the battery is connected; E2: Switch the ground power VI curve to the satellite test minimum power VI curve C1; E3: Confirm that the battery power relay switch is in the closed state and send an output prohibition command for all ground power supplies; E4: Switch the ground power VI curve C1 to the pre-power VI curve C0; E5: Set the total number of ground power outputs to N, so that the power it provides meets the power requirements of the initial power-on RBC back-end direct power distribution, non-direct power distribution subsystem and battery charging; confirm that the battery charging current telemetry is within the range and continue charging for 1-2 minutes; E6: Disconnect the battery power relay switch; E7: Disconnect the RBC back-end non-direct power distribution subsystem that needs power supply during satellite power-on test; E8: Disconnect the RBC back-end direct power distribution subsystem that needs to supply power when the satellite is initially powered on, and send a command to disable all ground power outputs; E9: Check satellite ground wired telemetry to confirm satellite power-off status; E10: Turn off the ground power.

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