Method for thermal vacuum testing of a batch of communication satellites

Abstract

This invention relates to a thermal vacuum testing method for mass-produced communication satellites. The method includes obtaining first temperature data for a satellite with a first heat pipe group and a second heat pipe group in a first space attitude through a thermal balance test; obtaining second temperature data by placing the satellite in a second space attitude; and obtaining an evaluation result of the satellite's heat pipe layout based on the first and second temperature data. Based on the evaluation result, the satellite's heat pipe layout can be adjusted until the evaluation result is optimal, ensuring that the satellite's heat amplification and temperature equalization effects are maximized. This testing method, by placing the satellite in different space attitudes, eliminates the influence of gravity during testing, thereby providing a valid reference for the satellite's heat pipe layout and thermal control design.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and specifically to a thermal vacuum testing method for mass-produced communication satellites. Background Technology

[0002] When a satellite operates in the vacuum and black environment of space, it is subjected to external heat flows such as solar radiation, planetary (e.g., Earth's) albedo, and planetary (e.g., Earth's) infrared radiation. Simultaneously, it dissipates heat into the black space through its heat dissipation surfaces and its own body, ultimately achieving a dynamic temperature balance. Satellite ground-based thermal simulation experiments are conducted in a ground-based space environment simulator, simulating a vacuum and black background environment. These thermal experiments verify the correctness of the satellite's thermal control design and thermal analysis model.

[0003] However, in the terrestrial environment, gravity affects the flow of heat transfer media in the satellite's heat pipes, thus impacting the satellite's heat dissipation. For the same heat pipe arrangement, the heat dissipation results obtained from thermal tests in a terrestrial environment will differ significantly from those in a space environment. Therefore, the results obtained from terrestrial thermal tests are insufficient to provide effective reference for the design of satellite heat pipe layout and thermal control. Summary of the Invention

[0004] In view of the above-mentioned problems in the existing technology, the present invention provides a thermal vacuum test method for mass-produced communication satellites, which can eliminate the influence of gravity during the test and provide an effective reference for the heat pipe layout and thermal control design of satellites.

[0005] This invention provides a thermal vacuum testing method for mass-produced communication satellites, comprising the following steps:

[0006] Step S1: Obtain the first temperature data of the satellite with the first heat pipe group and the second heat pipe group set in the first space attitude through a thermal balance test;

[0007] Step S2: Position the satellite in a second spatial attitude to obtain the second temperature data;

[0008] Step S3: Based on the first temperature data and the second temperature data, obtain the evaluation results of the heat pipe layout of the satellite.

[0009] Furthermore, the first temperature data and the second temperature data are the temperatures of each monitoring point and / or functional unit of the satellite when the satellite is in the first space attitude and the second space attitude, respectively.

[0010] Furthermore, the first temperature data and the second temperature data are compared with the simulation results to obtain the approximation of the temperature of the monitoring point and / or functional unit when the satellite is in the first space attitude and the second space attitude.

[0011] Furthermore, in step S3, the temperature difference between each monitoring point and / or functional unit when the satellite is in the first space attitude and the second space attitude is obtained through the first temperature data and the second temperature data, and it is determined whether the temperature difference is within a predetermined range in order to obtain the evaluation result.

[0012] Furthermore, in step S1, the first heat pipe group is arranged along the X-axis direction, and the second heat pipe group is arranged along the Y-axis direction. When the satellite is in the first spatial attitude, the first heat pipe group and the second heat pipe group are parallel to the horizontal plane and the vertical plane, respectively, and when the satellite is in the second spatial attitude, they are parallel to the vertical plane and the horizontal plane, respectively.

[0013] Furthermore, in step S1, the satellite is also equipped with a third heat pipe group to obtain the first temperature data of the satellite with the first heat pipe group, the second heat pipe group and the third heat pipe group in the first space attitude; in step S2, the satellite is placed in the third space state to obtain the third temperature data.

[0014] Furthermore, the third heat pipe group is arranged along the Z-axis. When the satellite is in the first spatial attitude, both the first and third heat pipe groups are parallel to the horizontal plane, and the second heat pipe group is parallel to the vertical plane.

[0015] Furthermore, when the satellite is in the second spatial attitude, the second and third heat pipe groups are parallel to the horizontal plane, and the first heat pipe group is parallel to the vertical plane.

[0016] Furthermore, when the satellite is in the third spatial attitude, the first and second heat pipe groups are parallel to the horizontal plane, and the third heat pipe group is parallel to the vertical plane.

[0017] Furthermore, a first temperature difference is obtained through the first temperature data and the second temperature data, a second temperature difference is obtained through the second temperature data and the third temperature data, and a third temperature difference is obtained through the first temperature data and the third temperature data, so as to adjust the first heat pipe group, the second heat pipe group and the third heat pipe group according to the first temperature difference, the second temperature difference and the third temperature difference.

[0018] The beneficial effect of this invention lies in providing a thermal vacuum testing method for mass-produced communication satellites. The testing method includes obtaining first temperature data for a satellite with a first heat pipe group and a second heat pipe group in a first space attitude through a thermal balance test; obtaining second temperature data by placing the satellite in a second space attitude; and obtaining an evaluation result of the satellite's heat pipe layout based on the first and second temperature data. Based on the evaluation result, the satellite's heat pipe layout can be adjusted until the evaluation result is optimal, ensuring that the satellite's heat amplification and temperature equalization effects are best achieved. This testing method, by placing the satellite in different space attitudes, eliminates the influence of gravity during testing, thereby providing an effective reference for the satellite's heat pipe layout and thermal control design. Attached Figure Description

[0019] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0020] Figure 1 The diagram shows a flowchart of a thermal vacuum test method for mass-produced communication satellites in Example 1.

[0021] Figure 2 The diagram shows the structure of the satellite in the first spatial attitude in Embodiment 1.

[0022] Figure 3 The diagram shows the structure of the satellite in the second spatial attitude in Embodiment 1.

[0023] Figure 4 The diagram shows a flowchart of a thermal vacuum test method for mass-produced communication satellites in Example 2.

[0024] Figure 5 The diagram shows the structure of the satellite in the first spatial attitude in Embodiment 2.

[0025] Figure 6 The diagram shows the structure of the satellite in the second spatial attitude in Embodiment 2.

[0026] Figure 7 The diagram shows the structure of the satellite in the third spatial attitude in Embodiment 2.

[0027] In the figure, the following labels are used: 10, first heat pipe group; 20, second heat pipe group; 30, third heat pipe group. Detailed Implementation

[0028] To make the technical problem to be solved, the technical solution, and the beneficial effects of this invention clearer, the invention will now be described in detail with reference to the accompanying drawings. This drawing is a simplified schematic diagram, illustrating only the basic structure of the invention, and therefore only shows the components relevant to the invention. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0029] Communication satellites typically carry numerous payload units that generate significant heat during operation, and these units are mostly distributed across various modules. Therefore, a network of heat pipes needs to be embedded within each module to dissipate heat and ensure proper functioning. However, during ground-based thermal vacuum testing, it is difficult to ensure that all heat pipes in each module are placed horizontally. Due to gravity, heat pipes embedded in vertically or tilted modules may malfunction, causing significant deviations from design temperatures and hindering effective evaluation of the satellite's thermal design rationality.

[0030] Therefore, this application proposes a thermal vacuum testing method for mass-produced communication satellites. By placing two, three, or more satellites in different attitudes, it ensures that some heat pipes in each satellite can operate effectively. Cross-validation of the test data from each satellite allows for effective evaluation of the rationality of the satellite's thermal design. Furthermore, the actual usage of the pre-embedded heat pipes within a single module can be evaluated based on the temperature levels of that module under different attitudes. The thermal vacuum testing method for mass-produced communication satellites will be described in detail below with reference to specific embodiments.

[0031] Example 1

[0032] refer to Figure 1-3 As shown, the thermal vacuum test method for mass-produced communication satellites provided by the present invention includes the following steps.

[0033] In step S1, the first temperature data of the satellite with the first heat pipe group 10 and the second heat pipe group 20 installed, under the first space attitude, is obtained through a thermal balance test. It should be understood that... Figure 2-3 The arrangement of the first heat pipe group 10 and the second heat pipe group 20 in the satellite is merely an illustration for ease of understanding and does not represent the actual arrangement in the satellite.

[0034] In some implementations, the satellite is placed in a vacuum chamber during thermal balance testing. The vacuum chamber is then cooled with liquid nitrogen to ensure a cold, dark environment around the satellite. Heat generated by the electric current heating effect in functional units such as control and communication devices within the satellite is transferred through heat pipes. The first heat pipe group 10 and the second heat pipe group 20 in the satellite can transfer heat to the satellite's radiators via a heat-conducting medium, or to various surfaces of the satellite, ensuring that the temperature throughout the satellite remains within the target range, thereby guaranteeing the normal operation of all functional units. The satellite's radiators and various surfaces dissipate heat into the cold, dark environment through thermal radiation, thus achieving heat dissipation.

[0035] In some embodiments, both the first heat pipe group 10 and the second heat pipe group 20 include at least one heat pipe. The first heat pipe group 10 and the second heat pipe group 20 can be pre-embedded in the satellite's cabin or installed between various functional units of the satellite. The heat pipes in the first heat pipe group 10 and the second heat pipe group 20 can be powder sintered heat pipes, grooved heat pipes, fiber heat pipes, etc.

[0036] Combination Figure 2 As shown, in some embodiments, the first heat pipe assembly 10 is arranged along the X-axis, and the second heat pipe assembly 20 is arranged along the Y-axis. When the satellite is in a first space attitude, the first heat pipe assembly 10 is parallel to the horizontal plane, and the second heat pipe assembly 20 is parallel to the vertical plane. Since the first heat pipe assembly 10 is horizontal when the satellite is in the first space attitude, the flow of the heat-conducting medium in the first heat pipe assembly 10 is not affected by gravity. Since the second heat pipe assembly 20 is vertical when the satellite is in the first space attitude, the flow of the heat-conducting medium in the second heat pipe assembly 20 is affected by gravity.

[0037] In some implementations, the first temperature data is the temperature data of each monitoring point in the satellite and / or the temperature data of each functional unit.

[0038] In step S2, the satellite is placed in a second space attitude to obtain the second temperature data.

[0039] Combination Figure 3 As shown, in some embodiments, when the satellite is in the second space attitude, the first heat pipe assembly 10 is parallel to the vertical plane, and the second heat pipe assembly 20 is parallel to the horizontal plane. Since the first heat pipe assembly 10 is vertical when the satellite is in the second space attitude, the flow of the heat-conducting medium in the first heat pipe assembly 10 is affected by gravity. Since the second heat pipe assembly 20 is horizontal when the satellite is in the second space attitude, the flow of the heat-conducting medium in the second heat pipe assembly 20 is not affected by gravity.

[0040] Similarly, in some implementations, the second temperature data is the temperature data of each monitoring point in the satellite and / or the temperature data of each functional unit.

[0041] In step S3, the evaluation results of the satellite's heat pipe layout are obtained based on the first temperature data and the second temperature data.

[0042] In some implementations, because the heat generated by each functional unit during operation radiates and diffuses in all directions, the temperature of each monitoring point and / or functional unit in the satellite is affected by both the first heat pipe group 10 and the second heat pipe group 20, rather than by either the first heat pipe group 10 or the second heat pipe group 20 alone. When evaluating the rationality of the heat pipe layout, the temperature uniformity of the monitoring points and / or functional units in the satellite should be considered when the satellite is in its first and second space attitudes.

[0043] In some implementations, the first and second temperature data can be compared with computer simulation results to obtain the approximation of the temperature of the monitoring points or functional units when the satellite is in the first and second space attitudes. If the first and second temperature data deviate significantly from the simulation results, it indicates that the temperature uniformity of the monitoring points and / or functional units in the satellite is low when the satellite is in the first and second space attitudes. If the first and second temperature data deviate slightly from the simulation results, it indicates that the temperature uniformity of the monitoring points and / or functional units in the satellite is high when the satellite is in the first and second space attitudes.

[0044] In some implementations, the temperature difference between each monitoring point and / or functional unit when the satellite is in a first space attitude and a second space attitude is obtained through first temperature data and second temperature data.

[0045] In one specific implementation, for a particular monitoring point or functional unit, the greater the temperature difference between the satellite in its first and second space attitudes, the greater the deviation in temperature caused by the first heat pipe group 10 and the second heat pipe group 20. That is, the heat at the monitoring point or functional unit is mainly carried away by the first heat pipe group 10 or the second heat pipe group 20. Conversely, the smaller the temperature difference between the monitoring point or functional unit and the satellite in its first and second space attitudes, the smaller the deviation in temperature caused by the first heat pipe group 10 and the second heat pipe group 20.

[0046] In some implementations, as long as the temperature difference between the monitoring point or functional unit and the satellite in the first and second spatial attitudes is within a predetermined range, the temperature deviation of the monitoring point or functional unit due to the influence of the first heat pipe group 10 and the second heat pipe group 20 can be considered small. The predetermined range is determined by those skilled in the art as needed. Generally, the satellite's functional units can operate within a range of -20℃ to 50℃, and the predetermined range can be a subset of -20℃ to 50℃. Preferably, the predetermined range is -10℃ to 40℃. More preferably, the predetermined range is 0℃ to 30℃.

[0047] In some implementations, the more monitoring points or functional units whose temperature differences are within a predetermined range, the more reasonable the satellite's heat pipe layout can be considered. Conversely, the fewer monitoring points or functional units whose temperature differences are not within a predetermined range, the less reasonable the satellite's heat pipe layout can be considered.

[0048] In some embodiments, the temperature of the compartment with the first heat pipe group 10 and / or the second heat pipe group 20 embedded can also be obtained during the test under the first space attitude and the second space attitude, so as to evaluate the actual use of the first heat pipe group 10 and / or the second heat pipe group 20.

[0049] In step S4, the heat pipe layout of the satellite is adjusted based on the evaluation results, and steps S1 to S3 are repeated until the evaluation results are optimal.

[0050] In some implementations, the evaluation result is considered optimal when the temperature difference of all monitoring points and / or functional units is within the predetermined range; otherwise, the evaluation result is considered poor.

[0051] In some implementations, when the evaluation results are unsatisfactory, the number of heat pipes in the first heat pipe group 10 and the second heat pipe group 20, the spacing between each heat pipe, the length or diameter of a certain heat pipe, etc., can be adjusted.

[0052] In the above experimental method, the satellite only has a first heat pipe group 10 arranged along the X-axis and a second heat pipe group 20 arranged along the Y-axis. Therefore, the above experimental method can be applied to certain flat-panel satellite configurations, as well as satellites with other configurations that only have heat pipe groups arranged in two directional dimensions.

[0053] Example 2

[0054] For satellites with heat pipe arrays arranged in three directional dimensions, such as box-type satellites, the experimental method provided in this application includes the following steps.

[0055] refer to Figure 4-7As shown, in step S1, the first temperature data of the satellite with the first heat pipe group 10, the second heat pipe group 20, and the third heat pipe group 30 set up are obtained through a thermal balance test under the first space attitude. It should be understood that... Figure 5-7 The arrangement of the first heat pipe group 10, the second heat pipe group 20 and the third heat pipe group 30 in the satellite is merely an illustration for ease of understanding and does not represent the actual arrangement in the satellite.

[0056] In some embodiments, the first heat pipe assembly 10 is arranged along the X-axis, the second heat pipe assembly 20 is arranged along the Y-axis, and the third heat pipe assembly 30 is arranged along the Z-axis. For example... Figure 5 As shown, when the satellite is in the first space attitude, the first heat pipe group 10 and the third heat pipe group 30 are both parallel to the horizontal plane, and the second heat pipe group 20 is parallel to the vertical plane. The flow of the heat-conducting medium in the first heat pipe group 10 and the second heat pipe group 20 is not affected by gravity, while the flow of the heat-conducting medium in the third heat pipe group 30 is affected by gravity.

[0057] In step S2, the satellite is placed in a second spatial attitude to obtain second temperature data; the satellite is placed in a third spatial state to obtain third temperature data.

[0058] In some implementations, such as Figure 6 As shown, when the satellite is in the second space attitude, the second heat pipe group 20 and the third heat pipe group 30 are parallel to the horizontal plane, and the first heat pipe group 10 is parallel to the vertical plane. Figure 7 As shown, when the satellite is in the third space attitude, the first heat pipe group 10 and the second heat pipe group 20 are parallel to the horizontal plane, and the third heat pipe group 30 is parallel to the vertical plane.

[0059] In step S3, the evaluation results of the satellite's heat pipe layout are obtained based on the first temperature data, the second temperature data, and the third temperature data.

[0060] In some implementations, the first temperature data, the second temperature data, and the third temperature data can be compared with computer simulation results to determine the temperature uniformity of the monitoring point and / or functional unit when the satellite is in the first, second, and third spatial attitudes.

[0061] In some implementations, a first temperature difference between the monitoring point and / or functional unit when the satellite is in a first space attitude and a second space attitude is obtained using first temperature data and second temperature data. A second temperature difference between the monitoring point or functional unit when the satellite is in a second space attitude and a third space attitude is obtained using second temperature data and third temperature data. A third temperature difference between the monitoring point or functional unit when the satellite is in a first space attitude and a third space attitude is obtained using first temperature data and third temperature data.

[0062] In some embodiments, for a specific monitoring point or functional unit, a larger first temperature difference indicates a greater deviation in temperature caused by the influence of the first heat pipe group 10 and the second heat pipe group 20. A larger second temperature difference indicates a greater deviation in temperature caused by the influence of the first heat pipe group 10 and the third heat pipe group 30. A larger third temperature difference indicates a greater deviation in temperature caused by the influence of the second heat pipe group 20 and the third heat pipe group 30. As long as the first, second, and third temperature differences of the monitoring point or functional unit are within the predetermined range, it can be considered that the temperature deviation caused by the influence of the first heat pipe group 10, the second heat pipe group 20, and the third heat pipe group 30 is small. The predetermined range can be a subset of -20℃ to 50℃.

[0063] In some embodiments, the temperature of the compartment with the first heat pipe group 10, the second heat pipe group 20 and / or the third heat pipe group 30 embedded can also be obtained during the test in the first space attitude, the second space attitude and the third space attitude, in order to evaluate the actual use of the first heat pipe group 10, the second heat pipe group 20 and / or the third heat pipe group 30.

[0064] In step S4, the heat pipe layout of the satellite is adjusted based on the evaluation results, and steps S1 to S3 are repeated until the evaluation results are optimal.

[0065] In some implementations, the evaluation result is considered optimal when the first, second, and third temperature differences of all monitoring points or functional units are within the predetermined range; otherwise, the evaluation result is considered poor.

[0066] In some embodiments, when the evaluation results are unsatisfactory, the number of heat pipes, the spacing between heat pipes, and the length or diameter of a particular heat pipe in the first heat pipe group 10, the second heat pipe group 20, and the third heat pipe group 30 can be adjusted specifically based on the first temperature difference, the second temperature difference, and the third temperature difference. For example, when the first and second temperature differences are not within the predetermined range, but the third temperature difference is within the predetermined range, the first heat pipe group 10 can be adjusted specifically. When the second and third temperature differences are not within the predetermined range, but the first temperature difference is within the predetermined range, the third heat pipe group 30 can be adjusted specifically. When the first and third temperature differences are not within the predetermined range, but the second temperature difference is within the predetermined range, the second heat pipe group 20 can be adjusted specifically.

[0067] In some embodiments and implementations not shown, the heat pipes in the satellite are not limited to straight lines, but can also be configured as polygonal or curved lines.

[0068] Based on the above-described experimental method, this application also provides an experimental apparatus, including a vacuum chamber and an installation platform disposed within the vacuum chamber. After being cooled by liquid nitrogen, the vacuum chamber creates a cold, dark environment inside. The installation platform is used to mount at least two identical experimental satellites. The installation platform is configured to allow the two experimental satellites to be in a first spatial attitude and a second spatial attitude, respectively, so as to simultaneously obtain first and second temperature data. Preferably, a cold shield is also provided on the installation platform to separate the two experimental satellites. This prevents the external heat flow generated by the two experimental satellites during the experiment from affecting each other. The cold shield is well known to those skilled in the art and will not be described in detail in this application.

[0069] In some embodiments, the mounting platform is configured to position the three test satellites in a first spatial attitude, a second spatial attitude, and a third spatial attitude, respectively, when mounting the three test satellites, so as to simultaneously obtain first temperature data, second temperature data, and third temperature data.

[0070] In some embodiments, the mounting platform is also equipped with infrared heating cages surrounding each test satellite to apply thermal radiation to the test satellites from a specific orientation, thereby further verifying and evaluating the rationality of the satellite's heat pipe layout.

[0071] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0072] It should be understood that the terms "length", "width", "up", "down", "front and back", "left and right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention.

[0073] Although the invention has been described with reference to preferred embodiments, various modifications can be made and components can be replaced with equivalents without departing from the scope of the invention. In particular, the technical features mentioned in the various embodiments can be combined in any manner as long as there is no structural conflict. The invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A method for thermal vacuum testing of mass-produced communication satellites, comprising the following steps: Step S1: Obtain the first temperature data of the satellite in the first space attitude with the first heat pipe group (10) and the second heat pipe group (20) set through the thermal balance test; Step S2: Position the satellite in a second spatial attitude to obtain the second temperature data; Step S3: Based on the first temperature data and the second temperature data, obtain the evaluation results of the heat pipe layout of the satellite; In step S1, the first heat pipe group (10) is arranged along the X-axis direction, and the second heat pipe group (20) is arranged along the Y-axis direction. The first heat pipe group (10) and the second heat pipe group (20) are parallel to the horizontal plane and the vertical plane respectively when the satellite is in the first spatial attitude, and are parallel to the vertical plane and the horizontal plane respectively when the satellite is in the second spatial attitude.

2. The thermal vacuum test method for mass-produced communication satellites according to claim 1, characterized in that, The first temperature data and the second temperature data are the temperatures of each monitoring point and / or functional unit of the satellite when the satellite is in the first space attitude and the second space attitude, respectively.

3. The thermal vacuum test method for mass-produced communication satellites according to claim 2, characterized in that, The first temperature data and the second temperature data are compared with the simulation results to obtain the approximation of the temperature of the monitoring point and / or functional unit when the satellite is in the first space attitude and the second space attitude.

4. The thermal vacuum test method for mass-produced communication satellites according to claim 2, characterized in that, In step S3, the temperature difference between each monitoring point and / or functional unit when the satellite is in the first space attitude and the second space attitude is obtained through the first temperature data and the second temperature data, and it is determined whether the temperature difference is within a predetermined range in order to obtain the evaluation result.

5. The thermal vacuum test method for mass-produced communication satellites according to any one of claims 1-4, characterized in that, In step S1, the satellite is also equipped with a third heat pipe group (30) so as to obtain the first temperature data of the satellite with the first heat pipe group (10), the second heat pipe group (20) and the third heat pipe group (30) in the first space attitude; in step S2, the satellite is made to be in the third space attitude to obtain the third temperature data.

6. The thermal vacuum test method for mass-produced communication satellites according to claim 5, characterized in that, The third heat pipe group (30) is arranged along the Z-axis. When the satellite is in the first spatial attitude, the first heat pipe group (10) and the third heat pipe group (30) are both parallel to the horizontal plane, and the second heat pipe group (20) is parallel to the vertical plane.

7. The thermal vacuum test method for mass-produced communication satellites according to claim 6, characterized in that, When the satellite is in the second space attitude, the second heat pipe group (20) and the third heat pipe group (30) are parallel to the horizontal plane, and the first heat pipe group (10) is parallel to the vertical plane.

8. The thermal vacuum test method for mass-produced communication satellites according to claim 6, characterized in that, When the satellite is in the third spatial attitude, the first heat pipe group (10) and the second heat pipe group (20) are parallel to the horizontal plane, and the third heat pipe group (30) is parallel to the vertical plane.

9. The thermal vacuum test method for mass-produced communication satellites according to claim 5, characterized in that, A first temperature difference is obtained by using the first temperature data and the second temperature data, a second temperature difference is obtained by using the second temperature data and the third temperature data, and a third temperature difference is obtained by using the first temperature data and the third temperature data, so as to adjust the first heat pipe group (10), the second heat pipe group (20) and the third heat pipe group (30) according to the first temperature difference, the second temperature difference and the third temperature difference.

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