Force-thermal coupling verification test method suitable for thruster support

Abstract

The invention discloses a force-heat coupling verification test method suitable for a thruster support, and the method comprises the steps: determining test piece parameters according to a product design state and a verification purpose; determining test loads including a force load and a temperature load according to force and thermal simulation results and a test purpose; designing a test fixing clamp; determining a loading mode and a control mode of the force load and the temperature load according to the test load; a thruster support is fixed on a test fixing clamp, and according to a loading mode and a control mode of a load, a force-heat coupling loading method is adopted to carry out force-heat coupling verification. The method has the advantages of flexible application of coupling and decoupling working conditions, simple operation, wide application range, accurate and reliable result and the like.

Description

A force-thermal coupling verification test method suitable for thruster supports Technical Field

[0001] This invention relates to a force-thermal coupling verification test method applicable to thruster supports, belonging to the field of thruster technology. Background Technology

[0002] The thruster support is subjected to continuously changing loads and temperatures during launch and orbital maneuvers. Verifying its compliance with space mission requirements necessitates confirming that its stiffness, strength, and thermal stability meet requirements under combined extreme loads and temperatures, necessitating force-thermal coupling verification tests. Existing component-level force-thermal coupling tests typically utilize environmental chambers, which, besides being limited by chamber size, cannot achieve distributed temperature loading. Large-scale force-thermal coupling distributed loading systems are often extremely complex, making their application to thruster supports both cumbersome and resource-intensive, and hindering flexible switching between decoupling and coupling conditions. Therefore, there is an urgent need to propose a force-thermal coupling verification design and implementation method suitable for thruster supports, capable of easily implementing distributed thermal loading and flexibly switching between force-thermal decoupling and coupling conditions. Summary of the Invention

[0003] The technical problem solved by the present invention is to overcome the shortcomings of the prior art and provide a force-thermal coupling verification test method suitable for thruster supports, which allows for flexible application of coupling and decoupling conditions and is easy to operate.

[0004] The technical solution of this invention is as follows: This invention discloses a force-thermal coupling verification test method suitable for thruster brackets, comprising: determining the test piece parameters according to the product design status and verification purpose; determining the test load, including force load and temperature load, according to the force and thermal simulation results and the test purpose; designing the test fixture; determining the loading method and control method of the force load and temperature load according to the test load; fixing the thruster bracket on the test fixture; and performing force-thermal coupling verification by adopting the force-thermal coupling loading method according to the loading method and control method of the load.

[0005] Furthermore, in the above method, determining the test specimen specifically means that the test specimen configuration, structural parameters, material type, molding process and quality control are the same as the actual product being tested, and the stiffness, strength, stability and thermal stability characteristics are the same as the product being tested, and the interface is the same as the real product.

[0006] Furthermore, in the above method, determining the test load specifically involves: determining the test conditions, including force conditions, temperature conditions, and force-thermal coupling conditions; wherein, the force-thermal coupling condition includes the starting point of force or heat, the loading and unloading levels corresponding to force or heat at the same level, the control point location, measurement time, holding time, and measurement timing of force-thermal coupling; determining the maximum magnitude, grading method, loading method, and loading requirements of the test conditions; determining the loads, including mechanical loads and temperature loads; the mechanical loads include thrust loads and thrust vibration loads; wherein, the vibration loads are determined based on the measured acceleration results in the thruster ground ignition test; the temperature loads are expanded by at least 10°C based on the thermal analysis results.

[0007] Furthermore, in the above method, the test fixture and the thruster bracket are fixed to the test fixture by connecting angle boxes, ensuring that the parallelism between the flange normal direction of the thruster bracket and the longitudinal loading direction is less than 0.5mm, and the parallelism between the X-direction and the transverse loading direction is less than 0.5mm.

[0008] Furthermore, in the above method, the temperature load loading and control methods are as follows: the temperature load is applied by wrapping with heating tape; at least one temperature measuring point is set on each connecting rod of the thruster bracket; each connecting rod is wrapped with thermal insulation; and the temperature deviation of each measuring point is controlled within the range of [0, +3]℃.

[0009] Furthermore, in the above method, the loading and control methods of the force load are as follows: a multi-directional loading fixture is used to achieve simultaneous lateral and axial loading; the force load is connected to the thruster support flange through the loading fixture and loaded onto the thruster support; the axial load is applied to the flange surface of the flange to ensure that the line of action of the force is parallel to the axis; the lateral load is applied to the horizontal plane of the thruster's center of mass, and the loading fixture is connected to the support flange by screws; the center of mass of the loading fixture is coaxial with the center of mass of the thruster support.

[0010] Furthermore, in the above method, the force-thermal coupling loading method specifically involves: loading to the qualification level load at room temperature and recording strain and displacement; calculating the skew angle and lateral offset of the flange face based on the strain and displacement; correcting the loading fixture based on the skew angle and lateral offset until the skew angle and lateral offset meet the requirements; dividing into different temperature gradients according to the temperature field requirements and performing graded heating, monitoring the displacement and connecting rod temperature after reaching each temperature gradient; if the displacement does not change, maintaining the temperature and load for at least 5 minutes, and continuing to heat and measure the next temperature gradient until all temperature gradients are loaded; performing temperature load unloading and graded force load unloading, measuring strain and displacement when unloading each temperature gradient.

[0011] Furthermore, in the above method, the force-thermal coupling verification specifically involves: installing loading fixtures and control equipment for force and temperature loads; attaching displacement, strain, and temperature measurement sensors to the test piece and loading fixtures; adopting a force-thermal coupling loading method according to the test loading requirements, and measuring displacement, strain, and temperature values ​​in real time at different stages; calculating the skew angle and lateral offset of the flange face based on the displacement, strain, and temperature values; determining the deformation of the test piece under force-thermal coupling based on the skew angle and lateral offset of the flange face; and performing non-destructive testing and accuracy retesting after the test to confirm whether the thruster bracket has any new defects after the test and whether the accuracy meets the requirements.

[0012] Furthermore, in the above method, the non-destructive testing and precision inspection to confirm whether there are any new defects in the thruster bracket after the test and whether the precision meets the requirements specifically involves: using the tapping method to perform non-destructive testing on the adhesive joints of the test piece's connectors, flanges, and upper joints; and performing defect inspection on the bonding quality of the carbon fiber structure and metal joint bonding joints; and re-testing the precision of the thruster bracket after the test, ensuring that the testing conditions, methods, and equipment are consistent with those before the test, and determining whether the change in the precision of the thruster bracket before and after the test is within the required range.

[0013] The beneficial effects of this invention compared to the prior art are as follows: (1) This invention provides a force-thermal coupling verification method suitable for thruster supports, addressing the experimental requirements of complex alternating force-thermal coupling conditions in the launch and orbit-changing phases. This method overcomes the shortcomings of existing coupling test systems, such as complexity, difficulty in realizing distributed temperature fields, and difficulty in switching between decoupling and coupling conditions. It has the advantages of flexible application of coupling and decoupling conditions, simple operation, wide applicability, and accurate and reliable results.

[0014] (2) This method overcomes the limitations of traditional force-thermal coupling test systems, such as complexity, difficulty in applying decoupling and coupling conditions together, and inability to distribute the uniform application of temperature field. It is flexible in switching between decoupling and coupling conditions, easy to operate, and realizes distributed and graded loading of temperature field and force load field.

[0015] (3) This method combines simulation and experimentation to provide the thermal load distribution field and force load distribution field of the product, as well as the coupling field between the two. This allows for accurate distributed temperature field loading and longitudinal and transverse force loading, enabling precise design of the distributed load in the experiment and avoiding over- or under-testing of the product. (4) This method has a wide range of applications. The temperature distributed loading coupled with the longitudinal and transverse force loading method has no special requirements for the test piece or connection state, and is widely applicable to force-thermal coupling tests at non-low temperatures. The method is reliable and easy to operate. Attached Figure Description

[0016] Figure 1 is a schematic diagram of the thruster support of the present invention; Figure 2 is a schematic diagram of the placement of the test piece of the present invention. Detailed Implementation

[0017] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0018] This invention discloses a force-thermal coupling verification method suitable for thruster supports, comprising: determining test specimen parameters according to product design status and verification purpose; determining test loads, including force loads and temperature loads, according to force and thermal simulation results and test purpose; designing test fixtures; determining the loading and control methods of force loads and temperature loads according to the test loads; fixing the thruster support on the test fixtures; and performing force-thermal coupling verification by using a force-thermal coupling loading method according to the loading and control methods of the loads.

[0019] Preferably, the test specimen is determined in the following ways: the configuration, structural parameters, material type, molding process and quality control of the test specimen are the same as those of the actual product being tested, and the stiffness, strength, stability and thermal stability characteristics of the test specimen are the same as those of the actual product, and the interface is the same as that of the actual product.

[0020] Preferably, the test load is determined by: determining the test conditions, including force conditions, temperature conditions, and force-thermal coupling conditions; wherein, the force-thermal coupling conditions include the starting points of force or heat, the loading and unloading levels of force or heat at the same level, the control point location, measurement time, holding time, and measurement timing of force-thermal coupling; determining the maximum magnitude, grading method, loading method, and loading requirements of the test conditions; determining the loads, including mechanical loads and temperature loads; the mechanical loads include thrust loads and thrust vibration loads; wherein, the vibration loads are determined based on the measured acceleration results in the thruster ground ignition test; the temperature loads are expanded by at least 10°C based on the thermal analysis results.

[0021] Preferably, the thruster bracket is fixed to the test fixture via a connecting angle box, ensuring that the parallelism between the flange normal direction and the longitudinal loading direction of the thruster bracket is less than 0.5 mm, and the parallelism between the X-direction and the transverse loading direction is less than 0.5 mm.

[0022] Preferably, the temperature load loading and control method are as follows: the temperature load is applied by wrapping with heating tape; at least one temperature measuring point is set on each connecting rod of the thruster bracket; each connecting rod is wrapped with thermal insulation; and the temperature deviation of each measuring point is controlled within the range of [0, +3]℃.

[0023] Preferably, the loading and control methods of the force load are as follows: a multi-directional loading fixture is used to achieve simultaneous lateral and axial loading; the force load is connected to the thruster support flange through the loading fixture and loaded onto the thruster support; the axial load is applied to the flange surface of the flange to ensure that the line of action of the force is parallel to the axis; the lateral load is applied to the horizontal plane of the thruster's center of mass, and the loading fixture is connected to the support flange by screws; the center of mass of the loading fixture is coaxial with the center of mass of the thruster support.

[0024] Preferably, the force-thermal coupling loading method specifically involves: loading to the qualification level load at room temperature and recording strain and displacement; calculating the skew angle and lateral offset of the flange face based on the strain and displacement; correcting the loading fixture based on the skew angle and lateral offset until the skew angle and lateral offset meet the requirements; dividing into different temperature gradients according to the temperature field requirements and performing graded heating, monitoring the displacement and connecting rod temperature after reaching each temperature gradient; if the displacement does not change, maintaining the temperature and load for at least 5 minutes, and continuing to heat and measure the next temperature gradient until all temperature gradients are loaded; performing temperature load unloading and graded force load unloading, measuring strain and displacement when unloading each temperature gradient.

[0025] Preferably, force-thermal coupling verification is performed, specifically as follows: installing loading fixtures and control equipment for force and temperature loads; attaching displacement, strain, and temperature measurement sensors to the test piece and loading fixtures; adopting a force-thermal coupling loading method according to the test loading requirements, and measuring displacement, strain, and temperature values ​​in real time at different stages; calculating the skew angle and lateral offset of the flange face based on the displacement, strain, and temperature values; judging the deformation of the test piece under force-thermal coupling based on the skew angle and lateral offset of the flange face; after the test, performing non-destructive testing and accuracy retesting to confirm whether the thruster bracket has any new defects after the test and whether the accuracy meets the requirements.

[0026] Preferably, non-destructive testing and precision inspection are performed to confirm whether there are any new defects in the thruster bracket after the test and whether the precision meets the requirements. Specifically, the bonding of the connectors, flanges, and upper joints of the test piece is performed using the tapping method, and the bonding quality of the bonding between the carbon fiber structure and the metal joint is inspected for defects. The precision of the thruster bracket after the test is re-tested, and the testing status, methods, and equipment are kept consistent with those before the test to determine whether the change in the precision of the thruster bracket before and after the test is within the required range.

[0027] As shown in Figures 1 and 2, this embodiment provides a force-thermal coupling verification test method suitable for thruster brackets, which includes the following steps: 1. Establishing a test system The test system consists of: a test piece, a temperature loading / measurement / control system, a force loading / measurement / control system, and a test fixing and clamping boundary; wherein, the test piece includes a flange 1, a connecting angle box 2, a connecting rod 3, an upper connector 4, and a temperature control connecting piece 5.

[0028] 1) Determine the test specimen parameters based on the product design status and verification purpose, and design a test specimen that can represent the product qualification status or directly use the qualification specimen; 2) Determine the test load based on the force and thermal simulation results and the test purpose, including the force and thermal load coupling loading method, and clarify the working condition type, maximum level, graded loading method, load control method, etc.

[0029] 3) Design of test fixtures, including clamping and fixing boundaries, determining clamping interfaces and fixing boundary interfaces, and determining the implementation method of fixing boundaries according to fixing requirements.

[0030] 4) Test load design: Based on the test load, determine the loading interface, loading fixture and loading method, and clarify the loading control method according to the loading accuracy requirements.

[0031] 5) Test temperature load design: Based on the test temperature load requirements, determine the temperature load loading method and heating position, and clarify the measurement points and control methods according to the accuracy requirements.

[0032] 6) Determine the observation area and observations in the test according to the test objectives, and formulate test procedures and safety control measures; 2 Test piece design 1) The test piece is a thruster support qualification piece or a test piece with the same parameters that can represent its qualification status.

[0033] 2) The configuration, structural parameters, material type, molding process, and quality control of the test specimen must be identical to the actual product being evaluated. It must accurately reflect the stiffness, strength, stability, and thermal stability characteristics of the product being evaluated. The interfaces must be identical to those of the actual product.

[0034] 3. Test Load Design 1) The test load should include the working conditions and combinations thereof, including force and temperature. The maximum load level, grading method, loading method, and loading requirements of the working conditions should be clearly defined.

[0035] 2) The mechanical load of the test comes from the force exerted on the support when the thruster is ignited, including the thruster thrust and the thruster vibration load, wherein the vibration load is determined based on the acceleration results measured in the ground ignition test of the thruster.

[0036] 3) The temperature load in the test is derived from the thermal analysis results and is extended by at least 10°C.

[0037] 4) In force-thermal coupling conditions, the starting point of force / thermal load and the corresponding loading / unloading levels of force / thermal load under the same level should be clearly defined; the location of coupling control point, measurement time, load holding time and measurement timing should be clearly defined.

[0038] 4. Coupled Loading Design 1) Temperature Loading: Distributed temperature field loading needs to be implemented based on thermal analysis results. Since environmental chamber loading is not feasible, a heating belt wrapping method is used to apply the temperature load. The specifications of the heating belt are determined based on the required temperature.

[0039] 2) Based on the temperature field distribution and the implementation method of the heating belt, determine the temperature control points. At least one temperature measuring point should be installed on each rod of the thruster support. Additionally, the six connecting rods need to be insulated.

[0040] 3) Force load application: Mechanical loads require combined axial and lateral loading, achieved using specialized multi-directional loading fixtures. The application is carried out according to the multi-directional graded loading table.

[0041] 4) The force load is connected to the thruster support flange via a loading fixture and applied to the thruster support. Axial loads are applied to the flange surface, ensuring the force line of action is parallel to the axis; lateral loads are applied at the thruster's center of mass. The loading fixture is connected to the support flange via bolts.

[0042] 5) When loading, the weight of the loading fixture should be taken into account and deducted from the approved loading table, and the load can be evenly transferred to the three installation points; the center of mass of the fixture is coaxial with the center of mass of the bracket.

[0043] 6) For the thruster support, the heating points are heated simultaneously, and the temperature deviation of each measuring point is controlled within the range of [0, +3]℃.

[0044] 7) Coupled loading method: First, load to the qualification level at room temperature, record strain and displacement, and analyze the flange face skew angle and lateral offset. Then, according to the temperature field requirements, perform graded heating at three temperature gradients. After reaching each temperature gradient, monitor the displacement gauge reading and the temperature of the connecting rod (the connecting rod temperature should be between the joint and temperature control connecting plate temperatures). If there is no change in the displacement gauge reading, maintain the temperature and load for at least 5 minutes before continuing to the next temperature gradient and measuring. Then, unload the temperature load and force load in reverse order, measuring strain and displacement at each stage.

[0045] 5. Design of test fixtures 1) The design of test fixtures must ensure sufficient rigidity and interface accuracy, and must not cause additional deformation of the support test piece during assembly and testing.

[0046] 2) The thruster bracket is fixed to the fixture via a connecting angle box. The connection between the connecting angle box and the fixture is a screw connection using M5 titanium nails (QJ2580-93, 1100MPa), with a tightening torque of 4.5 N·m. After installation, the test piece must meet the following requirements: the parallelism between the flange normal direction and the longitudinal loading direction is less than 0.5 mm, and the parallelism between the X-direction and the transverse loading direction is less than 0.5 mm.

[0047] 6 Test Procedure 1) Install the test piece into the test fixture, and secure the test fixture to the fixed fixture; 2) Install the force load and temperature load loading fixture and control equipment.

[0048] 3) Attach displacement, strain, and temperature measurement sensors to the test specimens and tooling.

[0049] 4) Conduct graded loading of force-thermal coupling according to the test loading requirements, and measure displacement, strain and temperature values ​​in real time at each stage to determine the deformation and temperature state of the test piece after loading, and determine whether an abnormal state occurs that requires pausing, stopping or adjusting the test; 5) Conduct data analysis based on the test data and the on-site phenomena of the test piece to determine its deformation and stability under force-thermal coupling.

[0050] 6) After the test, non-destructive testing and accuracy retesting are carried out to confirm whether there are any new defects in the thruster support after the test and whether the accuracy meets the requirements.

[0051] 7 Test Results and Evaluation 1) Strain, displacement and temperature measurements should be recorded for each load level during the test.

[0052] 2) Based on stress, displacement, and temperature data, determine the stress and deformation state of the product under given temperature and loading process, and determine whether plastic deformation or failure has occurred.

[0053] 3) Based on the displacement measurement results of each loading and unloading process, the axial deviation angle and lateral displacement of the thruster support flange during each loading stage are calculated. The lateral displacement change of the flange axis is calculated by fitting the measured values ​​from three radial displacement measuring points to the deformed flange axis position. The axial deviation angle of the mounting surface is calculated by fitting the deformed flange mounting surface with three longitudinal displacement measurements.

[0054] 4) After the test, the bonding of the product pipe fittings to the flange and the upper joint was carried out by non-destructive testing using the tapping method, and the bonding quality of the bonding between the carbon fiber composite structure and the metal joint was tested.

[0055] After the test, the thruster support needs to be inspected for accuracy. The inspection status, method and equipment should be kept the same as before the test to determine whether there is a significant change in the accuracy of the 490N thruster support before and after the test.

[0056] In this embodiment, the steps for the force-thermal coupling verification test applicable to the thruster support are as follows: 1. Test piece design: The test piece is a thruster support qualification piece or a test piece with the same parameters that can represent its qualification status.

[0057] 2. Test Load Design: Mechanical simulation and thermal analysis were conducted on the product. The mechanical loads needed to cover the force exerted on the support during thruster ignition, including thruster thrust and thruster vibration loads, as well as the thruster response and loads. The temperature loads were derived from the thermal analysis results after launch and on-orbit operation, and were expanded by 10°C based on their evaluation results. Based on the analysis results, the mechanical-thermal coupling load condition design was completed.

[0058] Table 1. Typical loading and unloading conditions under force-thermal coupling.

[0059] After each temperature condition stabilizes, the temperature is maintained for 5 minutes before the next temperature gradient is applied.

[0060] 3. Coupled loading tests need to achieve longitudinal and transverse combined loading of force loads and distributed coupled loading of thermal loads. The two are designed separately, and coupling or decoupling is achieved through working condition design and graded control points.

[0061] 4. Test Data Measurement and Analysis: During the test, record the strain, stress, and temperature under each load level. Determine whether the product undergoes plastic deformation or failure at the given temperature and during loading, whether the thermal stability meets the requirements, whether the accuracy changes before and after the test, and whether new defects are generated.

[0062] Although the present invention has been described in detail through the preferred embodiments above, it should be understood that the above description should not be considered as a limitation of the present invention. Various modifications and substitutions to the present invention will be apparent to those skilled in the art after reading the above description. Therefore, the scope of protection of the present invention should be defined by the appended claims.

[0063] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A force-thermal coupling verification test method suitable for thruster supports, characterized in that, include: Determine the test specimen parameters based on the product design status and verification objectives; Based on the force and thermal simulation results and the purpose of the experiment, the test loads, including force loads and temperature loads, are determined. Design of test fixtures; Based on the test load, determine the loading and control methods for the force load and temperature load; fix the thruster bracket on the test fixture, and verify the force-thermal coupling by using the force-thermal coupling loading method according to the load loading and control method.

2. The force-thermal coupling verification test method for a thruster support according to claim 1, characterized in that, The specific determination of the test specimen is as follows: the configuration, structural parameters, material type, molding process and quality control of the test specimen are the same as those of the actual product being tested, and the stiffness, strength, stability and thermal stability characteristics of the test specimen are the same as those of the actual product, and the interface is the same as that of the actual product.

3. The force-thermal coupling verification test method for a thruster support according to claim 1, characterized in that, The determination of the test load specifically includes: determining the test conditions, including force conditions, temperature conditions, and force-thermal coupling conditions; wherein, the force-thermal coupling conditions include the starting points of force or heat, the corresponding loading and unloading levels of force or heat at the same level, the control point location, measurement time, holding time, and measurement timing of force-thermal coupling; determining the maximum magnitude, grading method, loading method, and loading requirements of the test conditions; determining the loads, including mechanical loads and temperature loads; the mechanical loads include thrust loads and thrust vibration loads; wherein, the vibration loads are determined based on the measured acceleration results in the thruster ground ignition test; the temperature loads are expanded by at least 10°C based on the thermal analysis results.

4. The force-thermal coupling verification test method for a thruster support according to claim 1, characterized in that, The test fixture is fixed to the thruster bracket via a connecting angle box, ensuring that the parallelism between the flange normal direction and the longitudinal loading direction of the thruster bracket is less than 0.5 mm, and the parallelism between the X-direction and the transverse loading direction is less than 0.5 mm.

5. The force-thermal coupling verification test method for a thruster support according to claim 1, characterized in that: The temperature load loading and control methods are as follows: temperature load is applied by wrapping with heating tape; at least one temperature measuring point is set on each connecting rod of the thruster bracket; each connecting rod is wrapped with thermal insulation; and the temperature deviation of each measuring point is controlled within the range of [0, +3]℃.

6. The force-thermal coupling verification test method for a thruster support according to claim 1, characterized in that: The loading and control methods of the force load are as follows: a multi-directional loading fixture is used to achieve simultaneous lateral and axial loading; the force load is connected to the thruster support flange through the loading fixture and loaded onto the thruster support; the axial load is applied to the flange surface of the flange to ensure that the line of action of the force is parallel to the axis; the lateral load is applied to the horizontal plane of the thruster's center of mass, and the loading fixture is connected to the support flange by screws; the center of mass of the loading fixture is coaxial with the center of mass of the thruster support.

7. The force-thermal coupling verification test method for a thruster support according to claim 1, characterized in that: The force-thermal coupling loading method is as follows: At room temperature, apply the load to the qualification level and record the strain and displacement; calculate the skew angle and lateral offset of the flange face based on the strain and displacement; adjust the loading fixture according to the skew angle and lateral offset until they meet the requirements; according to the temperature field requirements, perform graded heating at different temperature gradients, monitoring the displacement and connecting rod temperature after each temperature gradient is reached; if the displacement does not change, maintain the temperature and load for at least 5 minutes, and continue heating and measuring the next temperature gradient until all temperature gradients are loaded; perform temperature load unloading and graded force load unloading, measuring strain and displacement during the unloading of each temperature gradient.

8. The force-thermal coupling verification test method for a thruster support according to claim 7, characterized in that, The force-thermal coupling verification specifically involves: installing loading fixtures and control equipment for force and temperature loads; attaching displacement, strain, and temperature measurement sensors to the test piece and loading fixtures; adopting a force-thermal coupling loading method according to the test loading requirements, and measuring displacement, strain, and temperature values ​​in real time at different stages; and calculating the skew angle and lateral offset of the flange face based on the displacement, strain, and temperature values. Based on the skew angle and lateral offset of the flange face, the deformation of the test piece under the action of force-thermal coupling is determined; after the test, non-destructive testing and accuracy retesting are carried out to confirm whether there are any new defects in the thruster bracket after the test and whether the accuracy meets the requirements.

9. The force-thermal coupling verification test method for a thruster support according to claim 8, characterized in that: The non-destructive testing and precision inspection are conducted to confirm whether there are any new defects in the thruster bracket after the test and whether the precision meets the requirements. Specifically, the non-destructive testing of the adhesive joints of the connectors, flanges, and upper joints of the test piece is carried out using the tapping method, and the bonding quality of the bonding joints between the carbon fiber structure and the metal joints is inspected for defects. The precision of the thruster bracket after the test is re-tested, and the testing status, methods, and equipment are kept consistent with those before the test to determine whether the change in the precision of the thruster bracket before and after the test is within the required range.

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