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GB/T 47449-2026Test methods for the grid-connected power supply of manned spacecraft (English PDF)

载人航天器并网供电测试方法

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Issued by

SAMR; SAC

Level / Type

National · Recommended

Issue date

April 30, 2026

Implementation date

November 1, 2026

Scope

GB/T 47449-2026 is the English-translated version of 载人航天器并网供电测试方法.

GB/T 47449-2026 is the Chinese national standard covering connecting the power systems of two spacecraft - when a vehicle docks with a station the two electrical systems have to be paralleled without disturbing either, and this is how that is tested before flight. First edition, in force since 1 November 2026. It was issued on 30 April 2026 and takes effect on 1 November 2026, as a first edition. This page is published from the official record of the 2026 edition; the clause text of a standard this recent is not yet in circulation, and the figures, limits and tables it contains are those of the document itself, delivered in full with the English translation.

Document preview — GB/T 47449-2026

National Standard of the People's Republic of China

ICS: 49.020
Classification: V 71

Issued by: State Administration for Market Regulation; Standardization Administration of the PRC

1 Scope
4 General Requirements
5 Test Items
7 Test Requirements
7.3 Grid-connected current regulation test
7.5 Constant Current Grid-Connected Performance Test
7.6 Grid-connected voltage regulation test
7.8 Constant Voltage Grid Connection Performance Test
7.9 Grid Connection Mode Switching Process Test

1 Scope

4.4 Test Status The test status requirements are as follows:

a) The spacecraft providing the power supply should be tested as a complete unit or test system with the same electrical performance at its grid-connected power supply interface as in its on-orbit condition. The space station, as the power supply... When an electric spacecraft participates in the test, a ground-based accompanying electrical system or a grid-connected power supply interface simulation system can be used, including a grid-connected controller and a grid-connected control system. The power supply cable, primary power supply, power distribution system, and bus load transmitted from the controller to the grid connection point.

b) Powered spacecraft should be tested using a complete device or test system with the same electrical performance as in-orbit conditions via a grid-connected power supply interface; a prototype is preferred. Electrical equipment or samplers, including grid connection interface equipment, power supply cables from the grid connection point to the grid connection interface equipment, primary power supply, and power distribution. System, bus load.

c) The primary power supply for the powered spacecraft should use the same power controller as in orbit, and should be equipped with a solar array simulator and energy storage system. Battery pack or storage battery simulator.

d) The load on the powered spacecraft bus should be configured according to the on-orbit condition, and the peak power, step change, and other characteristics of the load power should be consistent with the on-orbit condition. When the difference is significant, ground-based equipment such as electronic loads can be used as alternatives.

e) Before conducting grid-connected power supply tests, both the power supply spacecraft and the power receiving spacecraft should complete their own energy system tests and connect to the grid power supply. Check the status of relevant equipment.

f) The grounding of the power supply spacecraft and the power receiving spacecraft shall be consistent with the on-orbit status and comply with the provisions of GB/T 29084.

g) Both the power supply spacecraft and the power receiving spacecraft are equipped with a test support system that supports the operation of the entire ship or simulation system, and has telemetry receiving and judgment capabilities. It has read and command sending capabilities, and can set the grid-connected voltage and grid-connected current.

h) Grid-connected test equipment can be configured to perform real-time measurement of voltage and current waveforms as needed for testing.

i) For a spacecraft grid-connected power supply system with bidirectional power supply capability, a spacecraft can act as either a power supply spacecraft or a power receiving spacecraft. The direction of energy transmission is determined by the current grid-connected power supply.

4.5 Testing and Monitoring Requirements The testing and monitoring requirements are as follows:

a) For each test item, the input voltage, input current, output voltage, output current, and grid connection voltage of the grid-connected controller should be monitored and recorded. Monitoring and recording the bus voltage and primary power output of the powered spacecraft, including voltage setpoints, grid current setpoints, and module operating status. Key parameters such as output current, load current, and primary power supply operating status;

b) During the test, the waveforms of the grid connection point voltage (or the grid controller output voltage) and the grid current should be dynamically monitored. Pay attention to the grid connection mode switching, the dynamic adjustment process of the primary bus voltage of the powered spacecraft, and the changes in the operating status of the primary power supply. Condition.

4.6 Testing Equipment The testing equipment requirements are as follows:

4 General Requirements

4.1 Test Objective The purpose of grid connection power supply testing is to verify the correctness of the grid connection power supply interface design for visiting spacecraft and other powered spacecraft, and its compatibility with the power supply systems of space stations and other similar facilities. The compatibility and power supply safety of the Tianqi grid-connected power supply interface were comprehensively verified, covering grid-connected power supply operating modes and different grid-connected voltages/currents. The parameters are set under steady-state conditions and the grid connection/exit process and the dynamic process of grid connection mode switching.

4.2 Test Basis Before grid-connected power supply testing, a corresponding test plan or outline should be formulated based on the provisions of this document and the specific conditions of the grid-connected power supply interface. The documents that serve as the basis for conducting testing.

4.3 Testing System The grid-connected power supply test system includes a power supply spacecraft, a power receiving spacecraft, and corresponding test support systems and grid-connected test equipment. For spacecraft... During the space station project, visiting spacecraft need to obtain grid-connected power from the space station while docked. In this state, the space station powers the spacecraft. The spacecraft is a powered spacecraft, and its grid connection point is typically the floating disconnector of the docking mechanism circuit. This applies to other manned spaceflight missions, such as manned lunar exploration. The power supply spacecraft and the power receiving spacecraft should be determined based on the grid connection relationship between spacecraft. The grid connection controller is generally located in the power supply spacecraft. The test system consists of the following components, as shown in Figure 1. Figure

5 Test Items

Grid-connected power supply testing should cover the status of the grid-connected power supply interface, the voltage performance of the powered spacecraft bus, and power supply safety during the grid-connected power supply process. For various situations that may affect performance, and based on the working mode of grid-connected power supply and the influencing factors of grid-connected power supply characteristics, the grid-connected power supply test items are detailed below. Table 1.

7 Test Requirements

7.1 Grid-connected power supply test setup The test system and test status should be prepared in accordance with the requirements of

4.3 and 4.4, and the following settings should be completed.

a) Select a typical interface that the powered spacecraft needs to receive grid-connected power from and configure it to connect the power supply spacecraft and the powered spacecraft. Connect the components and test them one by one.

b) After testing a typical interface, disconnect the connection and then reconnect to other interfaces, focusing on projects with different statuses. test.

c) For multiple visiting spacecraft simultaneously docking at the space station and receiving grid power, multiple spacecraft can be operated simultaneously according to their on-orbit operating conditions. Grid-connected power supply testing of the visiting aircraft; or testing using a combination of a single visiting aircraft and an equivalent simulation system. The entire aircraft should be tested, covering every interface.

d) The test items can be set up and carried out independently, or they can be combined with system-level flight simulation to test long-term stable working conditions and sunny/shaded areas. Testing of the film zone process.

7.2 Grid Connection Process Testing After setting the primary power supply and load of both the power supply and receiving spacecraft according to their on-orbit conditions, the test was conducted using the following method.

a) Check and confirm that the primary power supply and power distribution system of the power supply spacecraft are functioning normally, and that the primary power supply and power distribution system of the power receiving spacecraft are also functioning normally. Normal working condition;

b) Configure the grid-connected controller status and execute the power-on and power conversion module startup sequences for the grid-connected controller inputs.

c) Set the initial grid connection voltage, which should preferably be lower than the bus voltage of the powered spacecraft;

d) Set the grid-connected current; the value should not exceed 1A.

e) Sequentially connect the power supply output switch of the grid-connected controller and the power receiving switch of the spacecraft;

f) Set the grid-connected voltage to the specified grid-connected voltage value;

g) Based on the on-orbit grid connection status, the operating domain of the primary power supply of the powered spacecraft is covered, generally including the current distribution domain, discharge domain, and Charging domain, etc.;

7.3 Grid-connected current regulation test

7.3.1 Nominal Current Test The grid-connected current parameters for spacecraft such as space stations can be set in multiple ranges. The nominal grid-connected current is the current used under normal on-orbit conditions for long-term operation. The current setting value is as follows: visiting spacecraft and other powered spacecraft may have one or more nominal grid current settings. The test method is as follows:

a) Set the grid-connected current tiers to the nominal grid-connected current values used in orbit;

b) If there are multiple nominal grid-connected current ratings, complete the setting tests for each rating in ascending order;

c) The amplitude interval of the step adjustment should meet the step current limit of the busbars of both the power receiving spacecraft and the power supply spacecraft;

d) The time interval for tiered adjustments should comply with the minimum time interval for on-orbit flight control commands or the minimum allowable power supply interface. The required time interval for flow adjustment is generally not less than 1 second;

e) The test time for a nominal current rating should be greater than one orbital cycle, while covering both the sunlit and shadowed areas of the powered spacecraft in orbit. The status of the zone includes the power consumption of each operating area of the primary power supply and the load.

f) After completing the current range setting and the system is operating stably in constant current grid-connected mode, perform a grid-connected current accuracy test, with current measurement points... For grid connection points or power supply outlets of grid-connected controllers;

g) After completing the current setting and the system is operating stably in constant voltage grid-connected mode, the busbar should be tested during the current setting change process. Voltage fluctuations.

7.3.2 Current biasing and traversal test It is advisable to perform a grid-connected current bias test after the nominal current test. The test method is as follows:

a) Set the grid-connected current rating to the maximum allowable grid-connected current value of the interface and perform a pull-off test;

b) Perform a traversal setting test of the grid-connected current range for each current range that may be used in orbit;

c) The interval of the stepped adjustment amplitude should meet the step current limit of the busbars of the powered and powered spacecraft;

e) The test time for a single current setting should continue for a period of time after the setting is completed, generally not less than 5 minutes;

7.5 Constant Current Grid-Connected Performance Test

7.5.1 Steady-state load test When testing the system in constant current mode, the grid-connected current should be set to the nominal grid-connected current. The testing method is as follows:

a) Configure the steady-state load power-on settings and operating status settings for the powered spacecraft bus according to typical on-orbit flight conditions;

b) For powered spacecraft with significant variations in on-orbit bus load power, typical load power states under different operating conditions should be analyzed separately. The tests include maximum power steady-state load conditions and minimum power steady-state load conditions;

c) When conducting steady-state load tests where the grid-connected power exceeds the primary power capacity of the powered spacecraft, ensure that the primary power supply of the powered spacecraft remains constant. The power supply output current should not exceed its maximum output capacity; it is advisable to use a method that alternates between increasing the load and setting the grid current.

d) For powered spacecraft whose busbar power does not reach the maximum on-orbit power during testing, an equivalent load can be used. Alternatives include connecting electronic loads to the power distribution unit;

e) The duration of the steady-state load test should be greater than one orbital cycle, and should cover both the sunlit and shadowed areas of the powered spacecraft in orbit. Status, including the power consumption of each operating domain of the primary power supply and the load;

f) For grid-connected power supply interface equipment, a grid-connected controller or power converter is used, and the voltage is transformed again after receiving power. The steady-state load operation status of spacecraft should be adjusted according to on-orbit conditions, including its grid-connected power supply interface equipment, primary power supply, power distribution system, and... The load is configured in combination.

7.5.2 Typical Load Testing When testing the system in constant current mode, the grid-connected current should be set to the nominal grid-connected current, and testing should be conducted based on steady-state load testing. The exhibition and testing methods are as follows:

a) Select a typical load type based on the power consumption characteristics of the powered spacecraft during the power-on/off process or when switching operating modes. This type of load should cover the power consumption characteristics of the powered spacecraft during the power-on/off process or when switching operating modes. Loads that generate significant inrush current or cause bus voltage fluctuations during power outages, such as loads with large surges upon power-up, or... Loads whose operating current jumps significantly;

b) Select two typical load types based on the power consumption characteristics of the powered spacecraft load during operation, covering loads that will continuously generate power during operation. Loads that cause significant surge current fluctuations or significant bus voltage fluctuations, such as high-power electromechanical equipment like air compressors;

c) When Class I and Class II typical loads contain power supply interfaces with different characteristics such as resistive, inductive, and capacitive, the characteristics of each interface... It is advisable to select at least one unit from one or two types of loads for testing;

d) Perform power-on and power-off tests or operating mode switching tests on a typical load type;

e) Power on the two typical loads and set them to the selected operating mode to conduct a continuous operation test of the typical load;

f) The prototype testing should cover loads with different power supply interface characteristics in both Class I and Class II typical loads; the formal testing can... Appropriately reduce the number of loads and prioritize selecting typical loads that have the greatest impact on bus voltage and current.

7.6 Grid-connected voltage regulation test

7.6.1 Nominal Voltage Test The grid connection voltage parameters for spacecraft such as space stations can be set in multiple levels. The nominal grid connection voltage is the voltage used under normal operating conditions in orbit for a long period of time. The voltage setting value is typically set at a nominal grid voltage level for visiting spacecraft and other powered spacecraft. The testing method is as follows:

a) Set the grid-connected voltage levels to the nominal grid-connected voltage values used in the rail system;

b) If there are multiple nominal grid-connected voltage levels, complete the setting test for each level in ascending order;

c) The amplitude interval of the step adjustment should not exceed the voltage step limit of the power-receiving spacecraft bus, and ensure that no significant voltage increase occurs on the bus. Current surge;

d) The time interval for tiered adjustments should comply with the minimum time interval of the on-orbit command or the minimum voltage adjustment allowed by the grid-connected power supply interface. The interval requirement is generally not less than 1 second;

e) The test time for the nominal voltage level should be greater than one orbital cycle, while covering both the sunlit and shadowed areas of the powered spacecraft in orbit. Status, including the power consumption of each operating domain of the primary power supply and the load;

f) After completing the voltage level setting and the system is operating stably in constant voltage grid-connected mode, perform a grid-connected voltage accuracy test, voltage measurement points. For grid connection points or power supply outlets of grid-connected controllers;

g) After the voltage level setting is completed and the system is operating stably in constant current grid-connected mode, the busbar should be tested during voltage setting changes. Fluctuations in current.

7.6.2 Voltage bias and traversal test It is advisable to perform a grid-connected voltage deviation test after the nominal voltage test. The test method is as follows:

a) Set the grid-connected voltage levels to the maximum allowable grid-connected voltage value at the interface and perform a voltage deviation test;

b) Perform a traversal setting test by setting the grid-connected voltage to all possible voltage levels that may be used in the rail;

d) The time interval for tiered adjustments should comply with the minimum time interval for on-orbit flight control commands or the minimum allowable power supply interface. The pressure adjustment time interval should generally be no less than 1 second;

e) The test time for a single voltage level should continue for a period of time after the setting is completed, generally not less than 5 minutes;

7.8 Constant Voltage Grid Connection Performance Test

7.8.1 Steady-state load test When the system is operating in constant voltage mode, the grid-connected voltage should be set to the nominal grid-connected voltage. The test method is the same as in 7.5.1.

7.8.2 Typical Load Testing When testing the system in constant voltage mode, the grid-connected voltage should be set to the nominal grid-connected voltage, and testing should be conducted based on steady-state load testing. The test method is the same as in 7.5.2.

7.8.3 Maximum Load Step Test When the current variation of the load during normal operation cannot fully cover the load current variation characteristics specified by the grid-connected power supply interface, the most... High load step test. When testing the system in constant voltage mode, it is advisable to set the grid-connected voltage to the nominal grid-connected voltage and to conduct the test after completing the steady-state load test. The testing was conducted using the same method as in 7.5.3.

7.9 Grid Connection Mode Switching Process Test

7.9.1 Mode switching test caused by grid connection parameter adjustment Grid connection parameter adjustment includes current regulation and voltage regulation, both of which can cause mode switching. The test method is as follows:

a) In constant current mode, when the grid-connected current is less than the load current of the powered spacecraft bus, increase the grid-connected current setting value to make the grid-connected current... The current is greater than the load current of the powered spacecraft busbar; the constant current to constant voltage transition process is tested.

b) In constant voltage mode, when the grid-connected current exceeds the load current of the powered spacecraft bus, reduce the grid-connected current setting value to ensure the grid-connected current... The current is less than the load current of the powered spacecraft busbar; test the constant voltage to constant current transition process.

c) In constant current mode, if the grid-connected voltage setpoint is greater than the voltage required for constant current output, decrease the grid-connected voltage setpoint to reduce the grid voltage. If the set value is less than the voltage required for constant current output, test the process of switching from constant current to constant voltage.

d) In constant voltage mode, if the grid-connected voltage setpoint is greater than the voltage required for constant current output, increase the grid-connected voltage setpoint to adjust the grid-connected voltage. The set value is greater than the voltage required for constant current output; test the process of switching from constant voltage to constant current.

e) The grid-connected current and grid-connected voltage should be adjusted according to the maximum allowable step value of the grid-connected power supply interface;

f) The corresponding mode switching conditions in

d) can be selected for testing based on the actual flight status of the powered spacecraft in orbit.

7.9.2 Mode switching test caused by load change Changes in the power consumption of the powered spacecraft's load can trigger mode switching. The test method is as follows:

a) In constant current mode, send a load power-off command or adjust the simulated load power to reduce the load power of the powered spacecraft bus, thus enabling grid connection. The current is greater than the current supplied by the busbar of the powered spacecraft; the constant current to constant voltage transition process is tested.

b) In constant voltage mode, send a load power-on command or adjust the simulated load power to increase the load power of the powered spacecraft bus, thus enabling grid connection. The current is less than the current supplied to the busbar of the powered spacecraft; the constant voltage to constant current transition process is tested.

c) For powered spacecraft experiencing short-term, significant fluctuations in bus load power and meeting the mode switching conditions in a)~b), mode switching should be performed. Testing of the continuous switching process;

d) For powered spacecraft where a high-power load step during the approach and exit phases causes a switch in grid-connected mode, the approach and exit simulation process should be performed... High-power load step test is conducted.

e) The simulation of load change processes should be set up according to the on-orbit operating conditions, covering the maximum current change amplitude, time and rate.

......
This preview omits tables, figures, formulas and parts of the technical clauses. The complete document — 30 pages — is available in the English PDF.

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