Method for testing power supply system under satellite shadow entering and exiting working condition

Abstract

The invention relates to a method for testing a power supply system under satellite shadow entering and exiting conditions, and belongs to the field of satellite testing. The method comprises the following steps of: simulating an in-orbit solar wing in-out shadow power supply current change condition through output change of a solar cell simulator of a whole-satellite-level test system, and collecting telemetering data such as charge and discharge current of a power manager and a storage battery of an on-satellite power system; simulation of electrical performance compatibility analysis of a satellite power supply system and a load subsystem under the in-orbit in-out shadow working condition is facilitated, and effective feedback is formed for power supply compatibility between satellite equipment and in-orbit working condition design.

Description

Technical Field

[0001] This invention relates to a satellite entry and exit testing method, applicable to the testing of satellite power supply systems, which can obtain the performance indicators of the satellite power supply system under entry and exit conditions, and belongs to the field of satellite testing. Background Technology

[0002] The cone-shaped shadow cast behind the Earth when sunlight is blocked is called the Earth's shadow. When a satellite is in the Earth's shadow, the solar radiation received by its solar panels is significantly reduced or eliminated, and the onboard equipment is primarily powered by its battery packs, a process known as internal power supply. In contrast, in the sunlit areas, the satellite is typically powered by its solar panels, a process known as external power supply.

[0003] When a satellite needs to periodically enter and exit the Earth's shadow during its on-orbit operation, the transition process between internal and external power supply to the satellite bus voltage causes a slow change in the output current of the solar array. Simultaneously, the power controller charges the batteries, and the bus load fluctuates continuously. This unstable transition process can adversely affect the power supply to onboard equipment, potentially leading to malfunctions in the power controller's cross-domain regulation function and continuous fluctuations in the bus load. Therefore, it is necessary to conduct more in-depth research and testing on its reliability and test coverage. Effective simulation of the power supply characteristics during the shadow entry and exit process is of great significance during the ground testing phase.

[0004] Currently, there are no corresponding testing methods for satellite power supply system performance testing under satellite entry and exit conditions, making it impossible to complete the performance evaluation of satellite power supply system under these conditions. Summary of the Invention

[0005] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a test method for the power supply system under satellite entry and exit conditions, thereby improving the coverage of performance testing of satellite power supply systems.

[0006] The solution to the technical problem of this invention is: a test method for a power supply system under satellite arrival and departure conditions, the method comprising the following steps: S1. Use the satellite's on-orbit entry and exit time-current curve of the solar array as a preset curve, select discrete points from the preset curve, and obtain a set of entry and exit time-current data of the solar array. S2. Input the time-current data of entering and exiting the shadow solar panel into the solar cell simulator in chronological order; S3. Control the solar cell simulator to provide power to the satellite power supply system. The solar cell simulator uses the current value in the time-current data of entering and exiting the solar array as the target current value and the preset voltage value as the target voltage. It indexes the corresponding IV curve from the preset IV curve matrix and simulates the change of solar array current according to the IV curve to make it converge to the preset curve, so as to supply power to the satellite. S4. By setting the on-board load current, the working state of the satellite payload subsystem is set to approximate the actual on-orbit working conditions. S5. Set the on-orbit working mode of the power supply and distribution subsystem, analyze the telemetry data of ground tests under satellite entry and exit conditions, and plot the current curves during the entry and exit test process.

[0007] Preferably, discrete points are selected from a preset curve at preset time intervals.

[0008] Preferably, the on-board load current is set according to the load current change curve during the satellite's on-orbit arrival and departure.

[0009] Preferably, in the on-orbit working mode of the power supply and distribution subsystem, the main power controller is powered on and the backup is powered off, the battery charging and discharging control module is powered on simultaneously, charging is enabled, discharging is enabled, and all battery access switches are turned on; the battery has completed ground charging and has sufficient power; the satellite energy software status is set to enabled. Before image entry: The satellite's power software status is set to sunlight, and the battery is not charging; During the image advance process: The solar cell simulator calls the image advance solar array IV curve matrix to simulate the change process of satellite solar array current during image advance, and the battery gradually enters the discharge mode; Ground shadow: The battery is in discharge mode; The process of image emergence: The solar cell simulator calls the image emergence solar panel IV curve matrix to simulate the change process of solar panel current emergence, and the battery gradually switches from discharge mode to charging mode. After the image is taken out: the battery enters a high-current charging mode.

[0010] Preferably, the current curves include the total output current curve of the solar array, the total charging and discharging current curve of the battery, and the total bus current curve.

[0011] Preferably, the telemetry data includes the power controller bus current, battery charging current, battery discharging current, and battery-side switch status.

[0012] The advantages of this invention compared to the prior art are: (1) This invention fills the gap in satellite power supply system testing under the conditions of entering and exiting the image, improves the comprehensiveness of satellite power supply system testing, and improves the satellite on-orbit full life cycle testing and verification system; (2) The test method of the present invention is designed according to the actual environment of satellite entering and leaving the orbit during satellite operation. The test results can truly reflect the performance indicators of the satellite power supply system under this working condition and have high reliability. (3) The test method of the present invention does not require the addition of new ground test equipment. It can directly use the existing satellite power supply system test equipment for testing, which has good application and promotion value. Attached Figure Description

[0013] Figure 1 The satellite shadow time curves for the north and south solar arrays are shown in this embodiment of the invention. Figure 2 This is the test procedure for the power supply system under satellite entry and exit conditions according to an embodiment of the present invention; Figure 3 This is an embodiment of the present invention. Detailed Implementation The present invention will be further described below with reference to the embodiments.

[0014] like Figure 1 As shown, the satellite's shadow time is a process in which the current of the north solar array and the current of the south solar array gradually decrease to 0 and then slowly increase after the shadow appears. During this time, the satellite payload subsystem is working normally, the battery is discharging and charging, the power controller is switching between different operating domains, and the load current IN1 fluctuates continuously.

[0015] like Figure 2 As shown, this invention provides a test method for a power supply system under satellite arrival and departure conditions, the method comprising the following steps: S1. Use the satellite's on-orbit entry and exit time-current curve of the solar array as a preset curve, select discrete points from the preset curve, and obtain a set of entry and exit time-current data of the solar array; discrete points can be selected from the preset curve according to preset time intervals.

[0016] S2. Input the time-current data of entering and exiting the shadow solar panel into the solar cell simulator in chronological order; S3. Control the solar cell simulator to provide power to the satellite power supply system. The solar cell simulator uses the current value in the time-current data of entering and exiting the solar array as the target current value and the preset voltage value as the target voltage. It indexes the corresponding IV curve from the preset IV curve matrix and simulates the change of solar array current according to the IV curve to make it converge to the preset curve, so as to supply power to the satellite. The IV curve is plotted with current on the ordinate and voltage on the abscissa. By setting the IV test curve adjustment time and the order of calling the test curves under the conditions of satellite entering and exiting shadows during on-orbit operation, the transformation process of the IV curve matrix for the solar array during shadow entry and exit can be formed, i.e., Figure 2 In the IV curve diagram shown, when V is stable, the curve is changed to obtain the change of I, and finally the change process of I is made to converge with the preset curve, which serves as the solar array entry and exit curve change scheme in the satellite power supply system test software; in the satellite test experiment, the solar cell simulator simulates the satellite solar array to supply power to the satellite, and the designed solar array entry and exit curve change scheme is controlled by the test software to power the satellite through the solar cell simulator, thus completing the ground simulation test of solar array entry and exit. S4. By setting the on-board load current, the working state of the satellite payload subsystem is set to approximate the actual on-orbit working conditions. like Figure 1 As shown, during the satellite's entry into and exit from its orbit, the energy output of the solar panels varies with the light intensity. If there is continuous fluctuation in the downstream load current during this stage, and the load current is a variable power pulse load, the power controller may switch between charging and discharging operating domains multiple times to stabilize the bus voltage. In the satellite power supply system simulation test, it is also necessary to consider the downstream load state of the power supply system, that is, to set the operating state of the satellite payload subsystem to approximate the actual on-orbit operating conditions. Therefore, during the ground simulation test of entry into and exit from the orbit, in order to simulate the entry into and exit conditions of the satellite during its on-orbit operation, the on-orbit state simulation setting of the satellite's load current is performed. The on-board load current state is set: the operating state of the satellite payload subsystem is set to approximate the actual on-orbit operating conditions, and the load current IN1 curve is the load current change curve of a certain satellite during its entry into and exit from its orbit. S5. Set the on-orbit working mode of the power supply and distribution subsystem, analyze the telemetry data of ground tests under satellite entry and exit conditions, and plot the current curves during the entry and exit test process.

[0017] The power supply and distribution subsystem is set to on-orbit working mode: the main power controller is powered on and the backup is powered off; the battery charging and discharging control module is powered on simultaneously, charging is enabled, discharging is enabled, and all battery access switches are turned on; the battery has completed ground charging and has sufficient power; the satellite energy software status is set to enabled. Before the camera starts: The power software status is set to daylight, and the battery is not charging; Image advance process: The solar cell simulator calls the image advance solar array IV curve matrix and sets the image advance process of the satellite solar array current, so that the battery gradually enters the discharge mode; Ground shadow: The battery is in discharge mode; Image emergence process: Control the solar cell simulator to simulate the change in solar panel current during image emergence, gradually switching from discharge mode to charging mode, passing through the discharge and charging cross-domain of the power controller; After the image is taken out: the battery enters a high-current charging mode; Analysis of telemetry data from ground tests during satellite entry and exit maneuvers: like Figure 3 As shown, the following current curves are plotted during the solar panel output test: total current of solar panel output, total current of battery charging and discharging, and total current of busbar.

[0018] Interpret the following telemetry data during the input / output test: power controller bus current, battery charging current, battery discharging current, and battery-side switch status.

[0019] Figure 3 To predict the telemetry parameter curves, the current telemetry curves obtained from the tests should maintain a consistent trend, indicating that the satellite power supply system is functioning normally under image entry and exit conditions. A continuously connected telemetry reading on the battery side switch is considered normal.

[0020] In summary, the present invention provides a test method for the power supply system under satellite entry and exit conditions. By simulating the changes in the power supply current of the solar array during entry and exit conditions through the output of the solar cell simulator of the whole satellite test system, and collecting telemetry data such as the power manager of the on-board power system and the charging and discharging current of the battery, it helps to simulate the electrical performance compatibility analysis between the satellite power supply system and the payload subsystem under the on-orbit entry and exit conditions, and provides effective feedback on the power supply compatibility between satellite equipment and the design of on-orbit conditions.

[0021] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A test method for a power supply system under satellite arrival and departure conditions, characterized in that... Includes the following steps: S1. Use the satellite's on-orbit entry and exit time-current curve of the solar array as a preset curve, select discrete points from the preset curve, and obtain a set of entry and exit time-current data of the solar array. S2. Input the time-current data of entering and exiting the shadow solar panel into the solar cell simulator in chronological order; S3. Control the solar cell simulator to provide power to the satellite power supply system. The solar cell simulator uses the current value in the time-current data of entering and exiting the solar array as the target current value and the preset voltage value as the target voltage. It indexes the corresponding IV curve from the preset IV curve matrix and simulates the change of solar array current according to the IV curve to make it converge to the preset curve, so as to supply power to the satellite. S4. By setting the on-board load current, the working state of the satellite payload subsystem is set to approximate the actual on-orbit working conditions. S5. Set the on-orbit working mode of the power supply and distribution subsystem, analyze the telemetry data of ground tests under satellite entry and exit conditions, and plot the current curves during the entry and exit test process.

2. The test method for a power supply system under satellite arrival and departure conditions according to claim 1, characterized in that, Discrete points are selected from a preset curve at preset time intervals.

3. The test method for a power supply system under satellite arrival and departure conditions according to claim 1, characterized in that, The on-board load current is set according to the load current change curve during the satellite's on-orbit arrival and departure.

4. The test method for a power supply system under satellite arrival and departure conditions according to claim 1, characterized in that, In the on-orbit working mode of the power supply and distribution subsystem, the main power controller is powered on and the backup is powered off. The battery charging and discharging control module is powered on simultaneously, charging is enabled, discharging is enabled, and all battery connection switches are turned on. The battery has completed ground charging and has sufficient power. The satellite energy software status is set to enabled. Before image entry: The satellite's power software status is set to sunlight, and the battery is not charging; During the image advance process: The solar cell simulator calls the image advance solar array IV curve matrix to simulate the change process of satellite solar array current during image advance, and the battery gradually enters the discharge mode; Ground shadow: The battery is in discharge mode; The process of image emergence: The solar cell simulator calls the image emergence solar panel IV curve matrix to simulate the change process of solar panel current emergence, and the battery gradually switches from discharge mode to charging mode. After the image is taken out: the battery enters a high-current charging mode.

5. A test method for a power supply system under satellite arrival and departure conditions according to claim 1, characterized in that, The current curves include the total output current curve of the solar array, the total charging and discharging current curve of the battery, and the total current curve of the bus.

6. A test method for a power supply system under satellite arrival and departure conditions according to claim 1, characterized in that, The telemetry data includes the power controller bus current, battery charging current, battery discharging current, and battery-side switch status.

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