A spacecraft bidirectional energy grid connection simulation test system and test method

Abstract

The simulation test system and method of the present invention dynamically simulates the power generation capacity and load characteristics of the visiting aircraft, and fully verifies the normal mode and fault mode of the two-way grid-connected power supply access, regulation, and exit, thereby solving the problems of low efficiency, insufficient verification effectiveness, and insufficient adequacy of the existing grid-connected power supply verification between long-term on-orbit spacecraft and visiting aircraft. By simulating the energy state of the visiting aircraft based on real flight data or ground test data, it is closer to the actual on-orbit flight state, thereby improving the effectiveness of the test. Using this system and method, the simulation verification test of the grid-connected power supply between the space station and manned spacecraft and cargo spacecraft has been successfully completed.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft testing technology, and in particular to a spacecraft bidirectional energy grid-connected simulation test system and a test method. Background Art

[0002] The grid-connected power supply system between spacecraft represented by the space station assumes the important function of supporting the energy networking of the spacecraft complex. With the change of flight mission and attitude, the power generation capacity and load of the spacecraft complex are in a dynamic change process. Long-term in-orbit spacecraft represented by the space station need to have the ability to conduct two-way grid-connected power supply with visiting spacecraft. On the premise of sufficient energy, the long-term in-orbit spacecraft needs to ensure the energy balance of each visiting spacecraft, provide the surplus energy of the long-term in-orbit spacecraft to the visiting spacecraft, balance the power generation and power consumption of the long-term in-orbit spacecraft and the visiting spacecraft, and obtain energy from the visiting spacecraft when the energy of the long-term in-orbit spacecraft is insufficient, so as to achieve the energy fusion use during long-term flight in various configurations and attitudes. For this reason, it is necessary to carry out the design verification of the two-way grid-connected power supply between the long-term in-orbit spacecraft and the visiting spacecraft in the complex state. In the early stage, the one-way indirect grid-connected power supply interface test verification between the spacecraft was carried out. At the current stage, the two-way energy grid connection between the long-term in-orbit spacecraft and the visiting spacecraft will be carried out to realize the joint power supply of the long-term in-orbit spacecraft and the visiting spacecraft and improve the energy management efficiency.

[0003] In the process of development and verification, the following methods are generally used: 1. Carry out system-level cascade tests on real aircraft, physically connect the long-term in-orbit spacecraft with the real visiting aircraft, and verify the bidirectional grid-connected power supply function and performance through collaborative testing. 2. Use key stand-alone equipment to carry out special tests. 3. Use electronic loads or power supplies to perform interface matching tests. The existing test systems and methods have the following problems: ① Real aircraft are transported from different regions to the same test site for joint testing, which consumes huge manpower, material resources and time, and the development progress of each aircraft product is difficult to coordinate, and joint testing cannot be carried out for a long time. For visiting aircraft developed later, joint testing is even more difficult. ② When using key stand-alone equipment to carry out special tests, the equipment needs to be removed from the aircraft, which also has problems in time, material resources and progress, and the comprehensiveness of full-loop verification at the system level is insufficient. ③ Using a single electronic load or power supply to perform static interface matching checks can only verify the correctness of the interface in a single power supply direction, and cannot carry out dynamic process verification, and the verification effectiveness and sufficiency are insufficient. Summary of the invention

[0004] In view of this, the present invention provides a spacecraft bidirectional energy grid-connected simulation test system and test method, which can realize long-term verification, effective verification, and full verification of bidirectional grid-connected power supply between long-term in-orbit spacecraft and visiting aircraft.

[0005] To achieve the above purpose, the technical solution of the present invention is as follows:

[0006] A bidirectional energy grid-connected test system between spacecrafts of the present invention comprises a power supply simulator, a load simulator, a power supply characteristic monitoring device and an energy grid-connected test controller; wherein the power supply simulator is connected to the load simulator through a power supply positive line and a power supply return line; the load simulator is connected to the grid-connected controller of a long-term on-orbit spacecraft through the power supply positive line and the power supply return line; the power supply positive line and the power supply return line respectively lead out branch lines, and the branch lines are connected to the power supply characteristic monitoring device; the energy grid-connected test controller is connected to the power supply simulator, the load simulator and the power supply characteristic monitoring device through a network, sends control instructions to the power supply simulator, the load simulator and the power supply characteristic monitoring device respectively, and receives working status data sent by the power supply simulator, the load simulator and the power supply characteristic monitoring device respectively; the power supply simulator, under the control of the energy grid-connected test controller, outputs variable power supply to supply power to the load simulator and the long-term on-orbit spacecraft; the load simulator, under the control of the energy grid-connected test controller, outputs variable load to receive power from the power supply simulator and the long-term on-orbit spacecraft; the power supply characteristic monitoring device collects power supply parameters on the grid-connected power supply line in real time, and sends the collected power supply parameters to the energy grid-connected controller.

[0007] Among them, the functions of the energy grid-connected test controller are: 1. Receive and display in real time the power supply parameters sent by the power supply characteristic monitoring device; 2. Control the power output of the power supply simulator in real time; 3. Control the load output of the load simulator in real time; 4. Convert the set working mode, parameters and curves into control data and send them to the power supply simulator and load simulator; 5. Support test data storage, query and graphical display.

[0008] Among them, the energy grid-connected test controller includes a parameter parsing and configuration module, a data acquisition and display module, a power supply control module, a load control module and a data analysis module; the parameter parsing module is responsible for loading the real flight data or ground test data of the visiting aircraft energy system, and after data analysis and calculation, the set working mode, parameters and curves are converted into control data and sent to the power supply control module and the load control module to realize real-time control of the power supply simulator and the load simulator; the data acquisition and display module is responsible for receiving and displaying the power supply parameters sent by the power supply characteristic monitoring equipment in real time; the power supply control module receives the control data sent by the parameter parsing module, and controls the power supply output of the power supply simulator in real time; the load control module receives the control data sent by the parameter parsing module, and controls the load output of the load simulator in real time; the data analysis module is responsible for test data storage, query and graphical display.

[0009] The power supply parameters include voltage, current, ripple and jump.

[0010] The present invention also provides a method for testing bidirectional energy grid connection between spacecrafts, and the system of the present invention is used for testing. The bidirectional grid connection power supply includes: ① forward grid connection power supply, that is, the long-term on-orbit spacecraft supplies power to the visiting spacecraft through the grid connection controller; ② reverse grid connection power supply, that is, the visiting spacecraft supplies power to the long-term on-orbit spacecraft through the grid connection controller;

[0011] In the forward grid-connected power supply state, long-term on-orbit spacecraft have two power supply modes: constant voltage mode and constant current mode. The two power supply modes are determined according to the power supply capacity and load size. The visiting spacecraft has only one constant voltage mode power supply mode. In the reverse grid-connected power supply state, long-term on-orbit spacecraft has only one constant current mode power supply mode, and the visiting spacecraft has only one constant voltage mode power supply mode.

[0012] In the forward grid-connected power supply state, the grid-connected controller of the long-term in-orbit spacecraft completes the grid-connected power supply access with the visiting spacecraft in constant current mode, enters the constant current mode forward grid-connected power supply, and switches from the constant current mode forward grid-connected power supply to the constant voltage mode forward grid-connected power supply according to the flight state, or switches from the constant voltage mode forward grid-connected power supply to the constant current mode forward grid-connected power supply according to the flight state. The grid-connected controller of the long-term in-orbit spacecraft completes the grid-connected power supply exit with the visiting spacecraft in the constant current mode;

[0013] In the reverse grid-connected power supply state, the long-term on-orbit spacecraft grid-connected controller completes grid-connected power supply access with the visiting spacecraft in constant current mode, enters constant current mode reverse grid-connected power supply, and completes grid-connected power supply exit with the visiting spacecraft in constant current mode;

[0014] The energy grid-connected test controller loads the real data of the power system and load of the visiting aircraft during the in-orbit flight or the test data obtained from the ground test, and converts the measured data or simulated data into control data after analysis through calculation, and sends it to the power supply simulator and load simulator in real time to control the power supply and load output, and simulate the energy status of the visiting aircraft during the in-orbit flight;

[0015] Under the control and monitoring of the energy grid-connected test controller, the bidirectional grid-connected simulation test system is used to simulate the joint test of the visiting spacecraft and the long-term in-orbit spacecraft, completing the dynamic test coverage of all modes of bidirectional grid-connected power supply between the long-term in-orbit spacecraft and the visiting spacecraft.

[0016] Among them, the constant current mode of the forward grid-connected power supply is specifically as follows: the grid-connected controller of the long-term in-orbit spacecraft turns on the forward power supply switch, sets the power supply voltage to be higher than the power supply voltage of the energy grid-connected test system, sets the output current limiting value, so that the current limiting value is less than the load output by the load simulator, the grid-connected controller output is in constant current mode, and the power supply simulator is in constant voltage mode, forming a state in which the grid-connected controller and the power supply simulator jointly supply power to the load simulator.

[0017] Among them, the forward grid-connected power supply and constant voltage mode are specifically as follows: the grid-connected controller of the long-term in-orbit spacecraft turns on the forward power supply switch, sets the power supply voltage to be higher than the power supply voltage of the energy grid-connected test system, sets the output current limiting value so that the current limiting value is greater than the load output by the load simulator, and the grid-connected controller output is in constant voltage mode, and the power supply simulator has no output, forming a state in which the grid-connected controller independently supplies power to the load simulator.

[0018] Among them, the constant current mode of the reverse grid-connected power supply is specifically: the grid-connected controller of the long-term in-orbit spacecraft turns on the reverse power supply switch, sets the input current limiting value, so that the current limiting value + the load output of the load simulator is less than the output power of the power supply simulator, the grid-connected controller output is in constant current mode, and the power supply simulator is in constant voltage mode, forming a state in which the power supply simulator simultaneously supplies power to the long-term in-orbit spacecraft and the load simulator.

[0019] Beneficial effects:

[0020] 1. The simulation test system and method of the present invention dynamically simulates the power generation capacity and load characteristics of the visiting aircraft, and fully verifies the normal mode and fault mode of the two-way grid-connected power supply access, regulation, and exit, thereby solving the problems of low efficiency, insufficient verification effectiveness, and sufficiency in the existing grid-connected power supply verification between long-term in-orbit spacecraft and visiting aircraft. By simulating the energy status of the visiting aircraft based on real flight data or ground test data, it is closer to the actual in-orbit flight status, thereby improving the effectiveness of the test. Using this system and method, the simulation verification test of the grid-connected power supply between the space station and manned spacecraft and cargo spacecraft has been successfully completed.

[0021] 2. The system and method of the present invention realize the whole process of grid connection, dynamic control and grid exit of long-term in-orbit spacecraft and visiting spacecraft, comprehensively covers the flight plan and improves the test coverage.

[0022] 3. The system and method of the present invention cover all modes of bidirectional grid-connected power supply between long-term in-orbit spacecraft and visiting aircraft, effectively improving the adequacy of the test. The system and method of the present invention have been used to complete the bidirectional grid-connected power supply test and verification between the space station and a single visiting aircraft and multiple visiting aircraft, complete the coverage of the forward constant current mode, the forward constant voltage mode, and the reverse constant current mode, complete the coverage test of constant power and power jump in each mode, and complete the investigation and verification test of switching between modes.

[0023] 4. The system and method of the present invention provide important reference data for the long-term in-orbit spacecraft and visiting aircraft in-orbit flight, and support the interpretation and monitoring of the flight status of real in-orbit flight. The application of the system and method of the present invention provides comprehensive test data support for the grid-connected power supply of the space station and the visiting aircraft during the key technology verification phase of the space station, which strongly supports the in-orbit flight control. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 The present invention is a block diagram of a bidirectional energy grid connection test system for a long-term on-orbit spacecraft and a visiting aircraft.

[0025] Figure 2 This is a forward grid-connected power supply flow chart of the bidirectional energy grid-connected test system of the present invention.

[0026] Figure 3 This is a reverse grid-connected power supply flow chart of the bidirectional energy grid-connected testing system of the present invention. DETAILED DESCRIPTION

[0027] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0028] The present invention provides a spacecraft bidirectional energy grid connection test system, such as Figure 1 As shown, the system includes: a power supply simulator, a load simulator, a power supply characteristic monitoring device and an energy grid-connected test controller.

[0029] Among them, the power supply simulator and the load simulator are connected through the power supply positive line and the power supply return line, and the power supply output of the power supply simulator can supply power to the load of the load simulator through the channel positive line and the power supply return line; the load simulator is connected to the grid connection controller of the long-term in-orbit spacecraft through the power supply positive line and the power supply return line, and the power supply output of the long-term in-orbit spacecraft grid connection controller can supply power to the load of the load simulator through the channel positive line and the power supply return line, and the long-term in-orbit spacecraft conducts energy grid connection with the visiting aircraft through the grid connection controller; the power supply positive line and the power supply return line respectively lead out branch lines, and the branch lines are connected to the power supply characteristic monitoring equipment; the energy grid connection test controller is connected to the power supply simulator, the load simulator and the power supply characteristic monitoring equipment through the network, sends control instructions to the power supply simulator, the load simulator and the power supply characteristic monitoring equipment respectively, and receives the working status data sent by the power supply simulator, the load simulator and the power supply characteristic monitoring equipment respectively.

[0030] The system forms a path for the power supply simulator and the long-term on-orbit spacecraft grid controller to supply power to the load simulator in parallel through this connection, and forms a path for the power supply simulator to supply power to the long-term on-orbit spacecraft grid controller. The power supply path state is consistent with the on-orbit flight state. At the same time, the state monitoring of the power supply parameters at the grid interface is realized.

[0031] Specifically, the function of the power supply simulator is to simulate the power supply system of the visiting spacecraft, and under the control of the energy grid test controller, output variable power supply to supply power to the load simulator and long-term in-orbit spacecraft.

[0032] The functions of the load simulator are: to simulate the load of a visiting spacecraft, to output a variable load under the control of the energy grid test controller, and to receive power from the power supply simulator and the long-term on-orbit spacecraft.

[0033] The function of the power supply characteristic monitoring device is to collect the power supply parameters on the grid-connected power supply line in real time, including voltage, current, ripple, jump, etc. The collected power supply parameters are sent to the energy grid-connected controller.

[0034] The functions of the energy grid-connected test controller are: ① Receive and display the power supply parameters sent by the power supply characteristic monitoring device in real time; ② Control the power supply output of the power supply simulator in real time; ③ Control the load output of the load simulator in real time; ④ Convert the set working mode, parameters, and curves into control data and send them to the power supply simulator and load simulator. ⑤ Support test data storage, query and graphical display. Specifically, the energy grid-connected test controller includes a parameter parsing and configuration module, a data acquisition and display module, a power supply control module, a load control module and a data analysis module; the parameter parsing module is responsible for loading the real flight data or ground test data of the visiting aircraft energy system, and after data parsing and calculation, converts the set working mode, parameters, and curves into control data and sends them to the power supply control module and the load control module to realize real-time control of the power supply simulator and the load simulator; the data acquisition and display module is responsible for receiving and displaying the power supply parameters sent by the power supply characteristic monitoring device in real time; the power supply control module receives the control data sent by the parameter parsing module and controls the power supply output of the power supply simulator in real time; the load control module receives the control data sent by the parameter parsing module and controls the load output of the load simulator in real time; the data analysis module is responsible for test data storage, query and graphical display.

[0035] The bidirectional grid-connected power supply of the present invention includes: ① forward grid-connected power supply, that is, the long-term in-orbit spacecraft supplies power to the visiting aircraft through the grid-connected controller; ② reverse grid-connected power supply, that is, the visiting aircraft supplies power to the long-term in-orbit spacecraft through the grid-connected controller.

[0036] In the forward grid-connected power supply state, long-term in-orbit spacecraft has two power supply modes: constant voltage mode and constant current mode. The two power supply modes are determined according to the power supply capacity and load size. Visiting spacecraft has only one constant voltage mode power supply mode; in the reverse grid-connected power supply state, long-term in-orbit spacecraft has only one constant current mode power supply mode, and visiting spacecraft has only one constant voltage mode power supply mode.

[0037] Specifically, forward grid-connected power supply (constant current mode): the grid controller of the long-term in-orbit spacecraft turns on the forward power supply switch, sets the power supply voltage higher than the power supply voltage of the energy grid-connected test system, sets the output current limit value so that the current limit value is less than the load output by the load simulator, and the grid controller output is in constant current mode, and the power supply simulator is in constant voltage mode, forming a state in which the grid controller and the power supply simulator jointly supply power to the load simulator.

[0038] Forward grid-connected power supply (constant voltage mode): The grid-connected controller of the long-term in-orbit spacecraft turns on the forward power supply switch, sets the power supply voltage higher than the power supply voltage of the energy grid-connected test system, sets the output current limit value so that the current limit value is greater than the load output by the load simulator, and the grid-connected controller output is in constant voltage mode. The power supply simulator does not output, forming a state in which the grid-connected controller independently supplies power to the load simulator.

[0039] Reverse grid-connected power supply (constant current mode): The grid-connected controller of the long-term on-orbit spacecraft turns on the reverse power supply switch and sets the input current limit value so that the current limit value + the load output of the load simulator is less than the output power of the power supply simulator. The grid-connected controller output is in constant current mode and the power supply simulator is in constant voltage mode, forming a state in which the power supply simulator supplies power to the long-term on-orbit spacecraft and the load simulator at the same time.

[0040] In the forward grid-connected power supply state, the grid-connected controller of the long-term in-orbit spacecraft must complete the grid-connected power supply access with the visiting spacecraft in constant current mode and enter the constant current mode forward grid-connected power supply. It can be converted from the constant current mode forward grid-connected power supply to the constant voltage mode forward grid-connected power supply according to the flight status, or it can be converted from the constant voltage mode forward grid-connected power supply to the constant current mode forward grid-connected power supply according to the flight status. The grid-connected controller of the long-term in-orbit spacecraft must complete the grid-connected power supply exit with the visiting spacecraft in constant current mode.

[0041] In the reverse grid-connected power supply state, the grid-connected controller of the long-term on-orbit spacecraft must complete the grid-connected power supply access with the visiting spacecraft in constant current mode, enter the constant current mode for reverse grid-connected power supply, and complete the grid-connected power supply exit with the visiting spacecraft in constant current mode.

[0042] The energy grid-connected test controller loads the real data of the power system and load of the visiting aircraft during its in-orbit flight or the test data obtained from ground tests, and converts the measured data or simulated data into control data after analysis through calculation. The data is sent to the power supply simulator and load simulator in real time to control the power supply and load output and simulate the energy status of the visiting aircraft during its in-orbit flight.

[0043] Under the control and monitoring of the energy grid-connected test controller, the bidirectional grid-connected simulation test system is used to simulate the joint test of visiting spacecraft and long-term in-orbit spacecraft, and can complete the dynamic test coverage of all modes of bidirectional grid-connected power supply between long-term in-orbit spacecraft and visiting spacecraft.

[0044] The forward grid-connected power supply flow chart of the bidirectional energy grid-connected test system of the present invention is as follows: Figure 2 As shown, the forward grid connection and exit process includes the following steps:

[0045] The energy grid-connected test controller loads the real data of the power system and load of the visiting aircraft during its in-orbit flight or the test data obtained from ground tests, and converts the measured data or simulated data into control data after analysis through calculation. The data is sent to the power supply simulator and load simulator in real time to control the power supply and load output, simulate the energy status of the visiting aircraft during its in-orbit flight, and monitor the power supply parameters at the grid-connected interface through the power supply characteristic monitoring equipment.

[0046] The long-term on-orbit spacecraft starts the grid-connected controller, sets the output voltage higher than the output voltage of the power supply simulator, and sets the output current to the minimum access value. Turn on the forward power supply switch of the grid-connected controller. The output current of the grid-connected controller is the minimum value, and the grid-connected controller is in a constant current output state.

[0047] The power supply characteristic monitoring device monitors the forward output voltage and output current, and the power supply simulator maintains the constant voltage power supply mode.

[0048] The grid-connected controller of the long-term on-orbit spacecraft increases the output current limit value to ensure that the current limit value is not greater than the load output by the load simulator, and controls the grid-connected controller to be in a constant current output state. Enter the power supply simulator (constant voltage mode) and the grid-connected controller (constant current mode) joint power supply state.

[0049] The energy grid test controller dynamically adjusts based on the energy data of the visiting spacecraft and monitors the working status of the joint power supply. The grid controller of the long-term on-orbit spacecraft adjusts the current output limit according to the load curve and controls the grid controller to be in a constant current output state.

[0050] The energy grid-connected test controller controls the load simulator to quickly reduce the load, so that the current limit value of the long-term on-orbit spacecraft grid-connected controller is greater than the load output by the load simulator. The long-term on-orbit spacecraft grid-connected controller switches from the constant current output state to the constant voltage output state, and the power supply characteristic monitoring device monitors the voltage and current fluctuation data of the switching process. Enter the grid-connected controller (constant voltage mode) single power supply state.

[0051] The energy grid test controller controls the load simulator to quickly increase the load, so that the current limit value of the long-term on-orbit spacecraft grid controller is less than the load output by the load simulator. The long-term on-orbit spacecraft grid controller switches from the constant current output state to the constant voltage output state, and the power supply characteristic monitoring device monitors the voltage and current fluctuation data of the switching process. Enter the joint power supply state of the power supply simulator (constant voltage mode) and the grid controller (constant current mode).

[0052] The long-term on-orbit spacecraft grid-connected controller gradually adjusts the output current limit value until it reaches the minimum current limit value, controls the grid-connected controller to be in a constant current output state, and turns off the forward power supply switch. The energy grid-connected test controller restores the independent state of the power supply simulator (constant voltage mode) and returns to the initial state before grid connection.

[0053] The reverse grid-connected power supply flow chart of the bidirectional energy grid-connected test system of the present invention is as follows: Figure 3 As shown, the reverse grid connection and exit process includes the following steps:

[0054] The energy grid-connected test controller loads the real data of the power system and load of the visiting aircraft during its in-orbit flight or the test data obtained from ground tests, and converts the measured data or simulated data into control data after analysis through calculation. The data is sent to the power supply simulator and load simulator in real time to control the power supply and load output, simulate the energy status of the visiting aircraft during its in-orbit flight, and monitor the power supply parameters at the grid-connected interface through the power supply characteristic monitoring equipment.

[0055] The long-term on-orbit spacecraft starts the grid-connected controller and turns on the reverse power supply switch. The power supply characteristic monitoring device monitors the output power changes and fluctuations, the power supply simulator maintains the constant voltage power supply mode, and the long-term on-orbit spacecraft grid-connected controller monitors the input voltage, sets the input current limit, and is in the constant current input state.

[0056] The grid-connected controller of a long-term on-orbit spacecraft increases the input current limit value, controls the grid-connected controller to be in a constant current input state, and the power supply characteristic monitoring device monitors the output power changes and fluctuations, controls the power supply simulator to adjust the output power, and maintains the constant voltage power supply mode. The power supply simulator enters the constant voltage mode and supplies power to the load simulator and the grid-connected controller at the same time. The grid-connected controller of a long-term on-orbit spacecraft enters the reverse grid power supply (constant current mode) state.

[0057] The energy grid test controller dynamically adjusts based on the energy data of the visiting spacecraft and monitors the power supply working status. The grid controller of the long-term on-orbit spacecraft adjusts the current output limit according to the load curve and controls the grid controller to be in a constant current input state.

[0058] The long-term on-orbit spacecraft grid-connected controller gradually adjusts the input current limit value until it reaches the minimum current limit value, and controls the grid-connected controller to be in a constant current output state. Turn off the reverse power supply switch. The energy grid-connected test controller restores the independent state of the power supply simulator (constant voltage mode) and returns to the initial state before grid connection.

[0059] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for testing bidirectional energy grid connection between spacecraft, characterized in that: Bidirectional grid-connected power supply includes: ① forward grid-connected power supply, that is, the long-term on-orbit spacecraft supplies power to the visiting spacecraft through the grid-connected controller; ② reverse grid-connected power supply, that is, the visiting spacecraft supplies power to the long-term on-orbit spacecraft through the grid-connected controller; In the forward grid-connected power supply state, long-term on-orbit spacecraft have two power supply modes: constant voltage mode and constant current mode. The two power supply modes are determined according to the power supply capacity and load size. The visiting spacecraft has only one constant voltage mode power supply mode. In the reverse grid-connected power supply state, long-term on-orbit spacecraft has only one constant current mode power supply mode, and the visiting spacecraft has only one constant voltage mode power supply mode. In the forward grid-connected power supply state, the grid-connected controller of the long-term in-orbit spacecraft completes the grid-connected power supply access with the visiting spacecraft in constant current mode, enters the constant current mode forward grid-connected power supply, and switches from the constant current mode forward grid-connected power supply to the constant voltage mode forward grid-connected power supply according to the flight state, or switches from the constant voltage mode forward grid-connected power supply to the constant current mode forward grid-connected power supply according to the flight state. The grid-connected controller of the long-term in-orbit spacecraft completes the grid-connected power supply exit with the visiting spacecraft in the constant current mode; In the reverse grid-connected power supply state, the long-term on-orbit spacecraft grid-connected controller completes grid-connected power supply access with the visiting spacecraft in constant current mode, enters constant current mode reverse grid-connected power supply, and completes grid-connected power supply exit with the visiting spacecraft in constant current mode; The energy grid-connected test controller loads the real data of the power system and load of the visiting aircraft during the in-orbit flight or the test data obtained from the ground test, and converts the measured data or simulated data into control data after analysis through calculation, and sends it to the power supply simulator and load simulator in real time to control the power supply and load output, and simulate the energy status of the visiting aircraft during the in-orbit flight; Under the control and monitoring of the energy grid-connected test controller, the bidirectional grid-connected simulation test system is used to simulate the joint test of the visiting spacecraft and the long-term on-orbit spacecraft, and complete the dynamic test coverage of all modes of bidirectional grid-connected power supply between the long-term on-orbit spacecraft and the visiting spacecraft; The constant current mode of the forward grid-connected power supply is specifically as follows: the grid-connected controller of the long-term on-orbit spacecraft turns on the forward power supply switch, sets the power supply voltage to be higher than the power supply voltage of the energy grid-connected test system, sets the output current limit value so that the current limit value is less than the load output by the load simulator, the grid-connected controller output is in the constant current mode, the power supply simulator is in the constant voltage mode, and the grid-connected controller and the power supply simulator jointly supply power to the load simulator; The forward grid-connected power supply and constant voltage mode is specifically as follows: the grid-connected controller of the long-term on-orbit spacecraft turns on the forward power supply switch, sets the power supply voltage to be higher than the power supply voltage of the energy grid-connected test system, sets the output current limit value so that the current limit value is greater than the load output by the load simulator, the grid-connected controller output is in the constant voltage mode, the power supply simulator does not output, and the grid-connected controller forms a state of independently supplying power to the load simulator; The constant current mode of the reverse grid-connected power supply is specifically as follows: the grid-connected controller of the long-term in-orbit spacecraft turns on the reverse power supply switch, sets the input current limiting value, so that the current limiting value + the load output by the load simulator is less than the output power of the power supply simulator, the grid-connected controller output is in constant current mode, and the power supply simulator is in constant voltage mode, forming a state in which the power supply simulator simultaneously supplies power to the long-term in-orbit spacecraft and the load simulator.

2. A two-way energy grid connection test system between spacecraft, characterized in that: Used to implement the bidirectional energy grid-connected test method between spacecraft as described in claim 1, the system includes a power supply simulator, a load simulator, a power supply characteristic monitoring device and an energy grid-connected test controller; wherein the power supply simulator and the load simulator are connected through a power supply positive line and a power supply return line; the load simulator is connected to the grid-connected controller of a long-term in-orbit spacecraft through the power supply positive line and the power supply return line; the power supply positive line and the power supply return line respectively lead out branch lines, and the branch lines are connected to the power supply characteristic monitoring device; the energy grid-connected test controller is connected to the power supply simulator, the load simulator and the power supply characteristic monitoring device through a network, sends control instructions to the power supply simulator, the load simulator and the power supply characteristic monitoring device respectively, and receives working status data sent by the power supply simulator, the load simulator and the power supply characteristic monitoring device respectively; the power supply simulator, under the control of the energy grid-connected test controller, outputs variable power supply to supply power to the load simulator and the long-term in-orbit spacecraft; the load simulator, under the control of the energy grid-connected test controller, outputs variable load to receive power from the power supply simulator and the long-term in-orbit spacecraft; the power supply characteristic monitoring device collects power supply parameters on the grid-connected power supply line in real time, and sends the collected power supply parameters to the energy grid-connected controller.

3. The system according to claim 2, characterized in that The functions of the energy grid-connected test controller are: ① receiving and displaying in real time the power supply parameters sent by the power supply characteristic monitoring device; ② controlling the power supply output of the power supply simulator in real time; ③ Real-time control of the load output of the load simulator; ④ Convert the set working mode, parameters and curves into control data and send them to the power supply simulator and load simulator; ⑤ Support test data storage, query and graphical display.

4. The system according to claim 3, characterized in that The energy grid-connected test controller includes a parameter analysis and configuration module, a data acquisition and display module, a power supply control module, a load control module and a data analysis module; the parameter analysis module is responsible for loading the real flight data or ground test data of the visiting aircraft energy system, and after data analysis and calculation, converts the set working mode, parameters and curves into control data and sends them to the power supply control module and the load control module to achieve real-time control of the power supply simulator and the load simulator; the data acquisition and display module is responsible for receiving and displaying the power supply parameters sent by the power supply characteristic monitoring device in real time; the power supply control module receives the control data sent by the parameter analysis module and controls the power supply output of the power supply simulator in real time; The load control module receives the control data sent by the parameter analysis module and controls the load output of the load simulator in real time; the data analysis module is responsible for test data storage, query and graphical display.

5. The system according to any one of claims 2 to 4, characterized in that: The power supply parameters include voltage, current, ripple and jump.

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