GB/T 34515-2026 Thermal balance test method for spacecraft English, Anglais, Englisch, Inglés, えいご
This is a draft translation for reference among interesting stakeholders. The finalized translation (passing through draft translation, self-check, revision and verification) will be delivered upon being ordered.
ICS
CCS
National Standard of the People's Republic of China
GB/T 34515-2026
Thermal balance test method for spacecraft
航天器热平衡试验方法
Issue date: 2026-01-28 Implementation date: 2027-02-01
Issued by the General Administration of Quality Supervision, Inspection and Quarantine of the People's Republic of China
the Standardization Administration of the People's Republic of China
Contents
Foreword
1 Scope
2 Normative References
3 Terms and Definitions
4 Purpose of the Test
5 Test Requirements
5.1 Test Model Requirements
5.2 Space Environment Simulator Volume Requirements
5.3 Test Model Installation Requirements
5.4 Test Environment Requirements
5.5 Earth Resistance Requirements
6 Thermal Simulation Methods
6.1 External Heat Flux Simulation
6.2 Internal Heat Source Simulation
7 Test Cases
7.1 Types of Test Cases
7.2 Principles for Determining Test Cases
7.3 Criteria for Temperature Stabilisation
8 Data Measurement
8.1 External Heat Flux Measurement
8.2 Temperature Measurement
8.3 Space Environment Simulator Pressure Measurement
8.4 Contamination Measurement
9 Test Equipment
9.1 Space Environment Simulator
9.2 External Heat Flux Simulation Device
9.3 Data Acquisition and Processing Device
9.4 DC Power Supply Device
9.5 Test Tooling
9.6 Other Devices
10 Test Procedure
10.1 Test Equipment Status Check
10.2 Test Model Status Check
10.3 Combined Status Check of Test Model and Space Environment Simulator
10.4 Test Start up
10.5 Test Operation
10.6 Test Shutdown
10.7 Test Withdrawal
11 Test Interruption and Handling
11.1 General
11.2 Handling of Test Equipment Failures
11.3 Handling of Test Model Failures
12 Test Evaluation and Data Utilisation
12.1 Test Error Analysis
12.2 Test Evaluation
12.3 Test Data Utilisation
12.4 Test Report
Annex A (Normative) Spectral Matching Requirements for Solar Simulators
Spacecraft thermal balance test method
1 Scope
This document specifies the purpose, test requirements, thermal simulation methods, test cases, data measurement, test equipment, test procedure, test interruption and handling, test evaluation and data utilisation for spacecraft thermal balance tests.
This document applies to system level, sub system level and module level thermal balance tests of spacecraft.
2 Normative References
The following document is essential for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition (including any amendments) applies.
GB/T 29085-2012 Technical requirements for pollution control of satellite
3 Terms and Definitions
The following terms and definitions apply to this document.
3.1 thermal balance test
A thermal test conducted under simulated space environmental conditions to verify the spacecraft‘s thermal design and thermal analytical model, and to assess the spacecraft’s thermal control functions.
3.2 orbital heating
Thermal radiation from the Sun and planets that is incident on the external surfaces of a spacecraft during its operation in space.
3.3 infrared radiation heater
A radiation heating device composed of infrared radiation sources such as infrared lamp arrays, infrared heating cages, infrared heating panels and infrared heating rods.
3.4 contact electrical resistance heater
An electric heater attached to the surface or inside of a test model to simulate surface absorbed heat flux or internal heat sources.
NOTE: Typically a constantan foil heater.
3.5 solar simulator
An optical device consisting of a measurement system, optical system, mechanical structure system and electrical control system, used to simulate the radiation characteristics of the Sun.
NOTE: The radiation characteristics of the Sun include irradiance instability, irradiance non uniformity, irradiance, spectral irradiance and beam collimation angle, etc.
3.6 motion simulator
A mechanical device inside a space environment simulator used to simulate various attitudes of a spacecraft relative to solar radiation.
3.7 incident flux simulating method
A method that simulates the spatial external heat flux, spectrum and direction incident on the surface of a spacecraft.
3.8 absorbed flux simulating method
A method that simulates the spatial external heat flux absorbed on the surface of a spacecraft.
3.9 case
A specific operating state defined by the combination of the spacecraft‘s space thermal environment and the operating modes of the spacecraft’s equipment.
3.10 thermal analytical model
A mathematical model describing heat transfer and fluid flow in a spacecraft under specified operating conditions and operating environment.
3.11 test model
A physical model of a spacecraft or module used for thermal balance testing.
3.12 hot case
A case in which the predicted temperature of equipment reaches its maximum value over the life cycle.
3.13 cold case
A case in which the predicted temperature of equipment reaches its minimum value over the life cycle.
3.14 temperature monitoring point
A representative temperature measurement point on the test model used to determine temperature stabilisation during the thermal balance test.
4 Purpose of the Test
The purposes of the spacecraft thermal balance test are as follows:
a) To verify the correctness of the spacecraft‘s thermal design;
b) To verify the correctness of the spacecraft’s thermal analytical model and to provide data for refining the thermal analytical model.
5 Test Requirements
5.1 Test model requirements
The test model shall meet the following requirements:
a) The external shape, structure, materials, layout of instruments and equipment, cable network, various thermal control measures and products shall conform to the requirements of the development state;
b) The external dimensions, surface condition, installation and connection methods, internal heat generation and heat capacity of the instruments and equipment shall conform to the requirements of the development state;
c) Taking into account the capabilities of the test equipment, safety and special requirements of instruments and equipment, individual instruments and equipment may be replaced by process parts, qualification parts or simulated parts whose thermal performance parameters meet the requirements;
d) The thermal performance of the external surface coatings shall be the same as that of the development state;
e) Large external components such as large antennas and solar arrays may not participate in the test, but their impact on the test shall be assessed and corresponding measures shall be taken in the thermal boundary simulation as necessary;
f) For test models with sealed modules, appropriate measures shall be taken during the test to suppress the influence of natural convection of the gas inside the sealed module;
g) Parts that exchange heat with the test model but do not participate in the test shall be replaced by substitute structures that participate in the test and simulate the thermal boundary;
h) The propellant tank shall be filled with a protective gas.
5.2 Space environment simulator volume requirements
The volume of the space environment simulator shall meet the following requirements:
a) When using the incident flux simulating method, the ratio of the space environment simulator to the characteristic dimension (e.g., length, diameter) of the test model shall not be less than 3;
b) When using the absorbed flux simulating method, the ratio of the space environment simulator to the characteristic dimension (e.g., length, diameter) of the test model shall not be less than 2.
5.3 Test model installation requirements
The installation of the test model in the space environment simulator shall be based on a comprehensive analysis of the following factors:
a) Installation method and orientation;
b) Type of space environment simulator (vertical, horizontal);
c) The layout and direction of heat pipes on the test model, so that the heat pipes are placed horizontally or can function properly;
d) Orientation of the main heat dissipation surfaces;
e) External dimensions of the test model;
f) Layout and structural form of the external heat flux simulation device.
5.4 Test environment requirements
A workspace for testing or other test operations on the test model before and after the test shall be provided. The workspace environment shall meet the following requirements:
Standard
GB/T 34515-2026 Thermal balance test method for spacecraft (English)
GB/T 34515-2026 Thermal balance test method for spacecraft English, Anglais, Englisch, Inglés, えいご
This is a draft translation for reference among interesting stakeholders. The finalized translation (passing through draft translation, self-check, revision and verification) will be delivered upon being ordered.
ICS
CCS
National Standard of the People's Republic of China
GB/T 34515-2026
Thermal balance test method for spacecraft
航天器热平衡试验方法
Issue date: 2026-01-28 Implementation date: 2027-02-01
Issued by the General Administration of Quality Supervision, Inspection and Quarantine of the People's Republic of China
the Standardization Administration of the People's Republic of China
Contents
Foreword
1 Scope
2 Normative References
3 Terms and Definitions
4 Purpose of the Test
5 Test Requirements
5.1 Test Model Requirements
5.2 Space Environment Simulator Volume Requirements
5.3 Test Model Installation Requirements
5.4 Test Environment Requirements
5.5 Earth Resistance Requirements
6 Thermal Simulation Methods
6.1 External Heat Flux Simulation
6.2 Internal Heat Source Simulation
7 Test Cases
7.1 Types of Test Cases
7.2 Principles for Determining Test Cases
7.3 Criteria for Temperature Stabilisation
8 Data Measurement
8.1 External Heat Flux Measurement
8.2 Temperature Measurement
8.3 Space Environment Simulator Pressure Measurement
8.4 Contamination Measurement
9 Test Equipment
9.1 Space Environment Simulator
9.2 External Heat Flux Simulation Device
9.3 Data Acquisition and Processing Device
9.4 DC Power Supply Device
9.5 Test Tooling
9.6 Other Devices
10 Test Procedure
10.1 Test Equipment Status Check
10.2 Test Model Status Check
10.3 Combined Status Check of Test Model and Space Environment Simulator
10.4 Test Start up
10.5 Test Operation
10.6 Test Shutdown
10.7 Test Withdrawal
11 Test Interruption and Handling
11.1 General
11.2 Handling of Test Equipment Failures
11.3 Handling of Test Model Failures
12 Test Evaluation and Data Utilisation
12.1 Test Error Analysis
12.2 Test Evaluation
12.3 Test Data Utilisation
12.4 Test Report
Annex A (Normative) Spectral Matching Requirements for Solar Simulators
Spacecraft thermal balance test method
1 Scope
This document specifies the purpose, test requirements, thermal simulation methods, test cases, data measurement, test equipment, test procedure, test interruption and handling, test evaluation and data utilisation for spacecraft thermal balance tests.
This document applies to system level, sub system level and module level thermal balance tests of spacecraft.
2 Normative References
The following document is essential for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition (including any amendments) applies.
GB/T 29085-2012 Technical requirements for pollution control of satellite
3 Terms and Definitions
The following terms and definitions apply to this document.
3.1 thermal balance test
A thermal test conducted under simulated space environmental conditions to verify the spacecraft‘s thermal design and thermal analytical model, and to assess the spacecraft’s thermal control functions.
3.2 orbital heating
Thermal radiation from the Sun and planets that is incident on the external surfaces of a spacecraft during its operation in space.
3.3 infrared radiation heater
A radiation heating device composed of infrared radiation sources such as infrared lamp arrays, infrared heating cages, infrared heating panels and infrared heating rods.
3.4 contact electrical resistance heater
An electric heater attached to the surface or inside of a test model to simulate surface absorbed heat flux or internal heat sources.
NOTE: Typically a constantan foil heater.
3.5 solar simulator
An optical device consisting of a measurement system, optical system, mechanical structure system and electrical control system, used to simulate the radiation characteristics of the Sun.
NOTE: The radiation characteristics of the Sun include irradiance instability, irradiance non uniformity, irradiance, spectral irradiance and beam collimation angle, etc.
3.6 motion simulator
A mechanical device inside a space environment simulator used to simulate various attitudes of a spacecraft relative to solar radiation.
3.7 incident flux simulating method
A method that simulates the spatial external heat flux, spectrum and direction incident on the surface of a spacecraft.
3.8 absorbed flux simulating method
A method that simulates the spatial external heat flux absorbed on the surface of a spacecraft.
3.9 case
A specific operating state defined by the combination of the spacecraft‘s space thermal environment and the operating modes of the spacecraft’s equipment.
3.10 thermal analytical model
A mathematical model describing heat transfer and fluid flow in a spacecraft under specified operating conditions and operating environment.
3.11 test model
A physical model of a spacecraft or module used for thermal balance testing.
3.12 hot case
A case in which the predicted temperature of equipment reaches its maximum value over the life cycle.
3.13 cold case
A case in which the predicted temperature of equipment reaches its minimum value over the life cycle.
3.14 temperature monitoring point
A representative temperature measurement point on the test model used to determine temperature stabilisation during the thermal balance test.
4 Purpose of the Test
The purposes of the spacecraft thermal balance test are as follows:
a) To verify the correctness of the spacecraft‘s thermal design;
b) To verify the correctness of the spacecraft’s thermal analytical model and to provide data for refining the thermal analytical model.
5 Test Requirements
5.1 Test model requirements
The test model shall meet the following requirements:
a) The external shape, structure, materials, layout of instruments and equipment, cable network, various thermal control measures and products shall conform to the requirements of the development state;
b) The external dimensions, surface condition, installation and connection methods, internal heat generation and heat capacity of the instruments and equipment shall conform to the requirements of the development state;
c) Taking into account the capabilities of the test equipment, safety and special requirements of instruments and equipment, individual instruments and equipment may be replaced by process parts, qualification parts or simulated parts whose thermal performance parameters meet the requirements;
d) The thermal performance of the external surface coatings shall be the same as that of the development state;
e) Large external components such as large antennas and solar arrays may not participate in the test, but their impact on the test shall be assessed and corresponding measures shall be taken in the thermal boundary simulation as necessary;
f) For test models with sealed modules, appropriate measures shall be taken during the test to suppress the influence of natural convection of the gas inside the sealed module;
g) Parts that exchange heat with the test model but do not participate in the test shall be replaced by substitute structures that participate in the test and simulate the thermal boundary;
h) The propellant tank shall be filled with a protective gas.
5.2 Space environment simulator volume requirements
The volume of the space environment simulator shall meet the following requirements:
a) When using the incident flux simulating method, the ratio of the space environment simulator to the characteristic dimension (e.g., length, diameter) of the test model shall not be less than 3;
b) When using the absorbed flux simulating method, the ratio of the space environment simulator to the characteristic dimension (e.g., length, diameter) of the test model shall not be less than 2.
5.3 Test model installation requirements
The installation of the test model in the space environment simulator shall be based on a comprehensive analysis of the following factors:
a) Installation method and orientation;
b) Type of space environment simulator (vertical, horizontal);
c) The layout and direction of heat pipes on the test model, so that the heat pipes are placed horizontally or can function properly;
d) Orientation of the main heat dissipation surfaces;
e) External dimensions of the test model;
f) Layout and structural form of the external heat flux simulation device.
5.4 Test environment requirements
A workspace for testing or other test operations on the test model before and after the test shall be provided. The workspace environment shall meet the following requirements:
