Thermal Vacuum Test

Fire Resistance and Flame Retardant Testing Process for Rail Transit and Building Materials

The main purposes of thermal balance testing can be summarized as follows:

1) Obtaining temperature distribution data;

2) Verifying the correctness of thermal design and modifications;

3) Correcting and improving the mathematical model for thermal control analysis;

4) Determining the high and low temperature ranges for thermal vacuum testing based on the thermal balance test temperature;

5) Assessing the ability of the thermal control subsystem to maintain components, subsystems, and the entire spacecraft within the specified operating temperature range.

Spacecraft thermal vacuum testing can be divided into qualification-level thermal vacuum testing and acceptance-level thermal vacuum testing. The requirements for the purposes of these two tests differ in GJB 1027A-2005.

Qualification-level thermal vacuum testing is mainly for spacecraft in the development stage, aiming to assess the spacecraft's structural and operational performance resistance to environmental stress and verify the rationality of its design. Acceptance-level thermal vacuum testing is mainly for prototype or launched spacecraft, aiming to expose potential defects in the materials and manufacturing processes, thereby improving the reliability of spacecraft flight.

Covering GJB 1027A-2005 and related industry or enterprise standards, such as QJ 2630.1-1994 "Space Environment Test Method for Satellite Components - Thermal Vacuum Test" and QJ1446A-1998 "Satellite Thermal Vacuum Test Method", etc.

CNAS

Testing Cycle

1-2 weeks

Service Background

Vacuum thermal environment simulation testing of spacecraft has become one of the most crucial aspects of the spacecraft development phase. It can verify the rationality of the thermal control design of spacecraft such as satellites, revise design models, and verify the operational status of internal instruments and equipment, as well as the compatibility and performance between various subsystems. It can also be used to check spacecraft functions and manufacturing processes, expose potential design flaws, and detect early failures.

During the development phase, all spacecraft must undergo vacuum thermal environment simulation testing. For spacecraft in the prototype development stage, qualification-level vacuum thermal testing is required. For launched spacecraft, whether it's the first launch or a relaunch, acceptance-level vacuum thermal testing is necessary.

GRGTEST, with years of experience in rail transit testing, has formed a professional team of 8 PhDs and 59 Masters. Our research directions are synchronized with the most advanced research progress in the industry, and our testing equipment consists of multiple sets of top-tier equipment.

Thermal Vacuum Environment Simulation Equipment:

1. The average temperature under low-temperature heat sink conditions does not exceed 100K, and the average heating/cooling rate is better than 1℃/min;

2. The unloaded ultimate vacuum degree is better than 1×10⁻⁵ Pa, and the loaded vacuum degree is better than 1×10⁻³ Pa;

3. Typical product temperature range: -90℃~90℃.

1. Volume: 1.2 m³ (mm): φ1000*1200;

2. Heat sink dimensions (mm): φ800*1200;

Temperature range: -70℃～+150℃;

3. Ultimate vacuum (room temperature, empty chamber):

5. 0x10⁻⁴ Pa;

4. Temperature change rate (vacuum inside the chamber less than 10 Pa, heat sink surface): Heating: ≥3.0℃/min, from -55.0℃ to +70.0℃; Cooling: ≥3.0℃/min, from +70.0℃ to -55.0℃.

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