Stacked satellite force-bearing column precision detection method

Abstract

This invention discloses a method for precision testing of stacked satellite support columns, comprising the following steps: The satellite is clamped and fixed on a machine tool to ensure that the satellite's support and stress are approximately the same as in the stacked state; the mounting surfaces of the main and secondary support columns are machined, and the upper and lower metal rings of the main and secondary support columns are integrated and assembled; the coaxiality of the upper and lower ring surfaces of the main and secondary support columns, the flatness of the plating end faces, and the radial fit clearance of the stacked support columns are machined, and the machined plating end faces are then plated; the main support columns, secondary support columns, and satellite are assembled with the mounting fixture; the main and secondary support columns are securely connected to the satellite; during precision testing, the secure connection between the main and secondary support columns and the mounting fixture is released, and the satellite is precisely measured. This invention can achieve small error ranges in the installation precision of different support columns for satellites stacked in the same batch, exhibiting good consistency.

Description

Technical Field

[0001] This invention relates to the field of spacecraft load-bearing column accuracy systems, specifically a method for detecting the accuracy of stacked satellite load-bearing columns. Background Technology

[0002] Satellite stacking launch technology significantly reduces satellite launch costs and thus saves on satellite development costs by fully utilizing the space in the launch fairing. The load-bearing column is one of the core components of a stacked satellite structure, and its installation accuracy affects the force transmission path and launch separation safety. Stacking launch technology is mature abroad and has been used in numerous Starlink satellite launches. In my country, however, this technology is still in its early stages, and there are no publicly available successful cases regarding methods for ensuring the installation accuracy of the load-bearing column, influencing factors, and testing methods. Summary of the Invention

[0003] To address the shortcomings of existing technologies, this invention provides a method for detecting the accuracy of stacked satellite load-bearing columns.

[0004] Compared to the absolute precision of installation, the installation of load-bearing columns offers consistent precision. This allows for a small range of installation precision errors between different load-bearing columns of satellites stacked in the same batch, resulting in good consistency.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A method for accuracy testing of stacked satellite load-bearing columns includes the following steps:

[0007] Step S1: The satellite is clamped and fixed on the machine tool to ensure that the satellite's support and stress are similar to the stacked state;

[0008] Step S2: Machining the mounting surfaces of the satellite's main and secondary load-bearing columns;

[0009] Step S3: Machining the main and secondary load-bearing columns, and assembling the upper and lower metal rings of the main and secondary load-bearing columns;

[0010] Step S4: Machin the coaxiality of the annular surfaces of the upper and lower end faces of the main load-bearing column and the annular surfaces of the upper and lower end faces of the secondary load-bearing column, the flatness of the coated end faces, and the radial fit clearance of the stacked load-bearing columns, and then coat the machined coated end faces.

[0011] Step S5: Assemble the main load-bearing column, secondary load-bearing column, satellite, and installation fixtures;

[0012] Step S6: Securely connect the main load-bearing column and the secondary load-bearing column to the satellite; during the precision measurement, release the main load-bearing column and the secondary load-bearing column from the installation fixture and perform precision measurement on the satellite.

[0013] As a further aspect of the present invention, satellite support points are reserved at the installation positions of the main load-bearing column and the secondary load-bearing column in step S1.

[0014] As a further aspect of the present invention, step S3 specifically includes:

[0015] Step S3.1: Perform precision machining on the flatness of the mounting surfaces of the two auxiliary load-bearing columns on the satellite, ensuring that the flatness of the coplanar mounting surfaces of the two load-bearing columns on the satellite is better than 0.05mm;

[0016] Step S3.2: Using the mounting surfaces of the two secondary load-bearing columns as a reference, process the mounting surfaces of the other secondary load-bearing columns.

[0017] As a further aspect of the present invention, step S4 further includes: a second overall machining after the coating is applied, with the coating end face as a reference, the parallelism between the uncoated end face and the coated end face of the overall machined load-bearing column is better than 0.05 mm, and the height is better than 0.08 mm.

[0018] As a further aspect of the present invention, step S5 includes:

[0019] Step S5.1: Insert the pins into the pin holes on the support column installation fixture, and the auxiliary support column will be positioned with the installation fixture through the pin holes reserved on the column;

[0020] Step S5.2: Place the cover plate fixture on the upper surface of the secondary load-bearing column, and use double-ended studs to clamp the cover plate fixture and the installation fixture to fix the secondary load-bearing column, and make the bottom surface of the secondary load-bearing column completely fit with the load-bearing column mounting surface of the installation fixture;

[0021] Step S5.3: Satellite and installation fixture contact each other via support base: Hoist the satellite onto the load-bearing column installation fixture and adjust the height of the support base so that it can be close to the bottom surface of the satellite.

[0022] As a further aspect of the present invention, step S6 includes:

[0023] Step S6.1: Pre-assemble the load-bearing column bracket with the main load-bearing column and the secondary load-bearing column;

[0024] Step S6.2: Insert the pin into the pin hole on the load-bearing column installation fixture, and position the main load-bearing column with the fixture through the pin hole reserved on the column;

[0025] Step S6.3: Place the cover plate fixture on the upper surface of the main load-bearing column, and use double-ended studs to clamp the cover plate fixture and the load-bearing column installation fixture to fix the main load-bearing column and make its bottom surface completely fit with the fixture.

[0026] As a further aspect of the present invention, the step of performing precise measurement on the satellite in step S6 includes: placing the satellite on a marble platform for precise measurement; using the points on the marble to form a reference plane, and aligning the points on the upper and lower outer cylindrical surfaces of the main and secondary load-bearing columns.

[0027] Projecting onto the marble surface and fitting the points obtained from the projection onto a circle yields three center points. Using the main load-bearing column as the origin of the coordinate axis and the two lines connecting the centers of the two auxiliary load-bearing columns as the X-axis, a measurement coordinate system is established through these three points. This yields the lateral and longitudinal distances of the three points within the reference plane. The measured distance tolerance is 0.087 mm, meeting the requirements. Establishing the distances from points on the upper annular surfaces of the main and auxiliary load-bearing columns to the reference plane yields the distribution of the height difference between the main and auxiliary load-bearing columns. The measured height error from points on the upper annular surfaces of the main and auxiliary load-bearing columns to the reference plane is distributed within the range of 0.024 mm to 0.069 mm, meeting the requirements.

[0028] The present invention has the following beneficial effects:

[0029] The main purpose of this invention is to measure the accuracy data of the stacked satellite support columns and check the consistency of the accuracy.

[0030] During precise measurement, the stability of the satellite's state and the measurement reference must be ensured. The satellite is measured in a single-satellite stacked state, i.e., the lower end face of the load-bearing column is freely supported. The measurement reference must be a reference surface with sufficient stiffness and flatness. Therefore, after the load-bearing column is assembled and adjusted, the constraint relationship between the load-bearing column and the tooling must be removed, and the load-bearing column is placed on a 00-grade marble plane in a stacked state. Using the marble plane as the reference surface, and the end face and axis of the load-bearing column as the measurement objects, the installation accuracy of the load-bearing column is evaluated. This invention can achieve a small error range in the installation accuracy of different load-bearing columns of satellites stacked in the same batch, exhibiting good consistency.

[0031] To more clearly illustrate the structural features and effects of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of the process for detecting the accuracy of stacked satellite load-bearing columns mentioned in this invention.

[0033] Figure 2 , Figure 3 This is a model diagram of the satellite, main load-bearing column, and secondary load-bearing column mentioned in this invention.

[0034] Figure 4 This is a partial schematic diagram of the installation of the secondary load-bearing column and the satellite mentioned in this invention.

[0035] Figure 5 , Figure 6 This is a schematic diagram of the structure of different sides of the satellite mentioned in this invention.

[0036] Figure 7 This is a schematic diagram of the installation fixture mentioned in this invention.

[0037] Figure 8 This is a partial structural diagram of the secondary load-bearing column and installation fixtures mentioned in this invention.

[0038] Figure 9 This is a schematic diagram illustrating the installation process of the main load-bearing column, secondary load-bearing column, satellite, and installation fixtures mentioned in this invention.

[0039] Figure 10 This is a schematic diagram illustrating the installation process of the main load-bearing column and installation fixtures mentioned in this invention.

[0040] Figure 11 This is a partial schematic diagram of the secondary load-bearing column mentioned in this invention.

[0041] The attached diagrams are labeled as follows: 1. Satellite (or celestial body); 2, 3, 4, 5, 6, and 7 are the mounting surfaces of the load-bearing columns; 8. Main load-bearing column; 9. Secondary load-bearing column; 10. Secondary load-bearing column; 11. Installation fixture; 12. Load-bearing column mounting surface; 13. Double-ended stud screw; 14. Installation pin; 15. Support base; 16. Cover plate fixture; 17. Upper end face of secondary load-bearing column; 18. Lower end face of secondary load-bearing column; 20. Upper end face of main load-bearing column; 21. Lower end face of main load-bearing column; 22. Upper mounting surface of secondary load-bearing column bracket; 23. Upper mounting surface of secondary load-bearing column bracket; 24. Lower mounting surface of secondary load-bearing column bracket; 26 and 29 are load-bearing column brackets; 27. Mounting surface of main load-bearing column mounting bracket; 28. Satellite support point; 30. Upper plating surface; 31. Detailed Implementation

[0042] The present invention will now be further described in conjunction with the accompanying drawings and relevant knowledge, and will be described clearly and completely. Obviously, the described applications are only some embodiments of the present invention, and not all embodiments.

[0043] Reference Figure 1 As shown, the present invention relates to a method for detecting the accuracy of stacked satellite load-bearing columns.

[0044] To achieve the following accuracy requirements during installation: the flatness of the end face of the load-bearing column, the height difference between the end faces, and the spacing between the load-bearing column axes.

[0045] For stacked satellites, the installation accuracy of the support columns is more important than the absolute accuracy of the installation itself. This means that the installation accuracy error range of different support columns for satellites from the same batch must be sufficiently small to ensure good consistency. Installation accuracy is mainly achieved through overall machining, assembly and adjustment, and precise measurement.

[0046] In this invention, integral machining involves coating the end faces of the load-bearing columns to increase the coefficient of friction and prevent cold welding. However, due to satellite envelope limitations and the need to reduce coating costs and improve efficiency, coating cannot be performed after assembly with the satellite structure. Therefore, the method of integrally machining the load-bearing columns after assembly with the satellite structure cannot guarantee assembly accuracy. In this invention, integral machining mainly refers to integral machining of the mounting surface of the satellite load-bearing columns and integral machining of individual load-bearing columns.

[0047] Machining of the satellite's load-bearing column mounting surface as a whole: To ensure machining accuracy, a suitable satellite configuration and clamping method must be selected before machining. To ensure that the combined weight and preload of the stacked satellites can be transmitted from top to bottom along the designed force transmission path of the load-bearing column after stacking, the accuracy and consistency of the load-bearing column under heavy-load and sealed conditions must be guaranteed. Therefore, the satellite is in a heavy-load and sealed state when machining the satellite's load-bearing column mounting surface as a whole. Considering the generation of excess material during machining, counterweights of equal weight to the prototype are installed at each individual mounting point of the satellite to ensure a satellite heavy-load and sealed state similar to the prototype. When clamping the satellite on the machine tool, to ensure that the force and force transmission method of the satellite are similar to those during stacking, and to ensure the deformation and accuracy of the satellite under heavy load, no additional forces or contact positions should be arbitrarily changed or added. Suitable connection points can be found at the load-bearing column mounting locations, and suitable fixtures can be made for clamping and fixing.

[0048] Machining a single load-bearing column: During machining, the main considerations are ensuring the coaxiality of the upper and lower annular surfaces, the flatness and height of the upper and lower end faces, and the fit between the upper and lower load-bearing columns when stacked. To ensure the accuracy of the load-bearing column and the integrity of the coating, machining is performed on the end faces that are not yet coated after the coating is applied. The manufacturing of the load-bearing column can be completed in two steps: Before coating, the coaxiality of the upper and lower annular surfaces, the flatness of the coating layer, and the fit between the upper and lower load-bearing columns when stacked are machined as a whole; after coating, using the coating layer as a reference, the parallelism of the end faces without coating and the height of the two end faces are machined as a whole.

[0049] Assembly and Adjustment: After overall machining, during assembly and adjustment of the satellite and the load-bearing column, the satellite's condition should be consistent with the heavy-load and support condition of the machining. Tooling can be used to first fix the load-bearing column, ensuring the flatness, height difference, and axial spacing of the load-bearing column end faces. Then, adjust the relative position between the satellite and the load-bearing column, filling any gaps with shims.

[0050] In the precision measurement process of this invention, the main purpose is to measure the accuracy data of the stacked satellite support columns and check the consistency of accuracy. During precision measurement, the stability of the satellite state and the measurement reference must be ensured. The satellite is measured in a single-satellite stacked state, i.e., the lower end face of the support column is freely supported. The measurement reference must be a reference surface with sufficient stiffness and flatness. Therefore, after the support columns are assembled and adjusted, the constraint relationship between the support columns and the tooling needs to be removed. The support columns are then placed in a stacked state on a 00-grade marble plane. Using the marble plane as the reference surface and the end face and axis of the support columns as the measurement objects, the installation accuracy of the support columns is evaluated.

[0051] Reference Figures 1-11 As shown, this invention provides a specific method for detecting the accuracy of stacked satellite load-bearing columns, specifically including:

[0052] Step 1: Satellite Machining Preparation: Following the satellite's mounting configuration, complete the installation of individual counterweight units to ensure the satellite meets the requirements for heavy-load, sealed-in configuration. To guarantee machining accuracy, a suitable satellite configuration and clamping method must be selected before machining. To ensure that the combined weight and preload of the stacked satellites are transmitted from top to bottom along the designed force transmission path of the support columns, the accuracy and consistency of the support columns under heavy-load, sealed-in configuration must be guaranteed. Therefore, the satellite is in a heavy-load, sealed-in configuration when the support column mounting surface is machined as a whole. Considering the generation of excess material during machining, counterweights of equal weight to the prototype are installed at each individual satellite mounting location to ensure a satellite heavy-load, sealed-in configuration similar to the prototype. When clamping the satellite on the machine tool, to ensure that the force and force transmission method of the satellite are similar to those during stacking, and to ensure the deformation and accuracy of the satellite under heavy load, no additional forces or contact positions should be arbitrarily changed or added. Suitable connection points can be found at the support column mounting locations, and suitable fixtures can be made for clamping and fixing.

[0053] Step 2: Mounting and securing the satellite on the machine tool: Refer to... Figures 2-3 As shown, the satellite support point 28 is reserved at the installation position of the load-bearing column, and M10 double-ended studs are used to tighten and fix the satellite to the clamp, ensuring that the satellite support and stress are similar to the stacking state.

[0054] Step 3: Overall machining of the load-bearing column mounting surfaces: According to the design requirements, using the astronomical reference surface 8 as the reference, the load-bearing column mounting surfaces 2, 3, 4, 6, and 7 of the astronomical column are machined.

[0055] Step 3.1: Refer to Figure 5 and Figure 6 As shown, in accordance with the design requirements, the flatness of the mounting surfaces 6 of the two secondary load-bearing columns is precision machined to ensure that the flatness of the coplanar mounting surfaces of the two load-bearing columns on the star is better than 0.05mm;

[0056] Step 3.2: Using the secondary load-bearing column mounting surface 6 as a reference, process the flatness of the two secondary load-bearing column mounting surfaces 2, the perpendicularity to the secondary load-bearing column mounting surface 6, and the distance between the mounting holes and the secondary load-bearing column mounting surface 6, so that the flatness is better than 0.02mm, the perpendicularity is better than 0.08mm, and the distance is better than 0.1mm;

[0057] Step 3.3: Using the secondary load-bearing column mounting surface 2 and the secondary load-bearing column mounting surface 6 as references, process the secondary load-bearing column mounting surface 3 and the secondary load-bearing column mounting surface 4, ensuring that the flatness of the secondary load-bearing column mounting surface 3 and the secondary load-bearing column mounting surface 4 is better than 0.02mm, the perpendicularity with the secondary load-bearing column mounting surface 2 is ≤0.05mm, and the perpendicularity with the secondary load-bearing column mounting surface 6 is ≤0.08mm;

[0058] Step 3.4: Using the secondary load-bearing column mounting surface 6 as a reference, process the main load-bearing column mounting surface 7 so that its flatness is better than 0.02mm and its parallelism with the secondary load-bearing column mounting surface 6 is better than 0.08mm.

[0059] Step 4: Prepare the main and secondary load-bearing columns for machining. According to the drawings, complete the integrated assembly of the main load-bearing column 9, secondary load-bearing column 10, and secondary load-bearing column 11 with the upper metal ring on the upper end face 18 of the secondary load-bearing column, the lower metal ring on the lower end face 19 of the secondary load-bearing column, the upper metal ring on the upper end face 20 of the main load-bearing column, and the lower metal ring on the lower end face 21 of the main load-bearing column. Leave a 2mm machining allowance on the end faces of the upper plating surface 30 and the lower plating surface 31 of the secondary load-bearing columns 10 and 11. In this invention, the machining of the load-bearing columns mainly ensures the coaxiality of the upper and lower ring surfaces, the flatness and height of the upper and lower end faces, and the fit relationship between the upper and lower load-bearing columns when stacked. To ensure the accuracy of the load-bearing columns and the integrity of the plating, machining is required on the end faces that are not yet coated after the plating is completed. The load-bearing column can be fabricated using a two-step integral machining process: Before coating, the coaxiality of the upper and lower annular surfaces of the load-bearing column, the flatness of the coating layer, and the fit between the upper and lower load-bearing columns during stacking are all addressed during integral machining. After coating, using the coating layer as a reference, the parallelism of the coating end faces and the height of the two end faces are not addressed during integral machining. Furthermore, during the assembly and adjustment of the satellite and load-bearing column after integral machining, the satellite's condition is consistent with the heavy-load and support condition established during machining. Tooling can be used to first fix the load-bearing column, ensuring the flatness of the end faces, height difference, and axial spacing. Then, the relative position between the satellite and the load-bearing column is adjusted, and shims are used to fill any gaps.

[0060] Step 5: First overall machining before coating: The coaxiality of the annular surfaces 20 and 21 on the upper and lower end faces of the main load-bearing column and the annular surfaces 18 and 19 on the upper and lower end faces of the secondary load-bearing column, the flatness of the end face of the lower coating layer 31, and the radial fit clearance of the stacked load-bearing columns are machined to ensure that the coaxiality is better than 0.1mm, the flatness is better than 0.03mm, and the clearance is better than 0.02mm.

[0061] Step 6: Apply the coating to the processed end face. To ensure that other surfaces are not damaged, a protective film must be applied to the remaining surfaces before application.

[0062] Step 7: Second overall machining after coating: Using the end face of the coating end face 31 as a reference, machine the end face of the coating surface 30 on the load-bearing column to make its parallelism with the reference better than 0.05mm and its height better than 0.08mm.

[0063] Step 8: Refer to Figures 7-9 As shown, the installation includes a load-bearing column mounting fixture 12; a load-bearing column mounting surface 13; mounting pins 15; a support base 16; and secondary load-bearing columns 10 and 11 positioned and installed with the mounting fixture 12. Specifically, it includes:

[0064] Step 8.1: Insert the mounting pin 15 into the pin hole on the support column mounting fixture 12. The secondary support columns 10 and 11 are positioned with the mounting fixture 12 through the pre-drilled pin holes on the columns (located on the lower end face 19 of the secondary support column) to ensure the distance accuracy of the secondary support columns 10 and 11.

[0065] Step 8.2: Place the cover plate fixture 17 on the upper end face 18 of the secondary load-bearing column, and use double-ended stud screws 14 to clamp the cover plate fixture and the load-bearing column mounting fixture 12 to fix the secondary load-bearing column 10 and the secondary load-bearing column 11, and make its bottom surface completely fit with the load-bearing column mounting surface 13 of the load-bearing column mounting fixture 12.

[0066] Step 9: The star body 1 contacts the support column installation fixture 12 by relying on the support base 16: hoist the star body 1 onto the support column installation fixture 12, and adjust the height of the support base 16 so that it can be close to the bottom surface of the star body 1 and can bear the weight of the star body.

[0067] Step 10: Position and install the main load-bearing column 9, secondary load-bearing column 10, and secondary load-bearing column 11 with the installation fixture 12; specifically including:

[0068] The load-bearing column brackets 26 and 29 are pre-assembled with the main load-bearing column 9, secondary load-bearing column 10, and secondary load-bearing column 11. The screws are not tightened, allowing for minor adjustments to their relative positions. The mounting pins 15 are inserted into the pin holes on the load-bearing column mounting fixture 12 (located on the lower end face 21 of the main load-bearing column). The main load-bearing column 9 is positioned with the fixture through the pre-drilled pin holes (located on the lower end face 19 of the secondary load-bearing column), ensuring the distance accuracy of the main load-bearing column 9. The cover plate fixture 17 is placed on the upper end face 20 of the main load-bearing column 9, and the cover plate fixture 17 is clamped to the load-bearing column mounting fixture 12 using double-ended stud screws 14 to fix the main load-bearing column 9, ensuring its bottom surface is completely flush with the fixture. The load-bearing column bracket 26 and the main load-bearing column mounting bracket mounting surface 27 are also present.

[0069] Step 11: Adjust the positional relationship between satellite 1 and auxiliary support column 10: Adjust the position of the satellite relative to the support column using the fine-tuning device on the tooling, so that there is an appropriate gap between the support column bracket 29 and the corresponding mounting surface of the satellite (in the design, the installation distance of the support column on the satellite has a negative tolerance, which can ensure the existence of gaps). Taking the auxiliary support column 10 as an example, fine-tuning the position of the satellite will create gaps between the mounting surfaces 2, 3, and 6 of the support column and the mounting surfaces 23 and 24 of the support column bracket 29. The gap size should be controlled within 0.1 to 0.3 mm.

[0070] Step 12: Measure and fill the gap between the support column and the satellite: Use a feeler gauge to measure the gap between the mounting surface of the support column bracket and the corresponding hole positions on the mounting surface of the satellite support column, and then insert copper shims of the appropriate thickness into the gap to fill it.

[0071] Step 13: Secure the connection between the load-bearing column and the satellite: Check the gap filling status and hole correspondence status between the load-bearing column bracket mounting surface and the load-bearing column mounting surface, and then tighten the connecting screws.

[0072] Step 14: Place the satellite on the marble platform for precise measurement; the main purpose is to measure the accuracy data of the stacked satellite load-bearing columns and check the consistency of accuracy. During precise measurement, the stability of the satellite's state and the measurement reference must be ensured. The satellite is measured in a single-satellite stacked state, i.e., the lower end face of the load-bearing column is freely supported. The measurement reference must be a reference surface with sufficient stiffness and flatness. Therefore, after the load-bearing columns are assembled and adjusted, the constraints between the load-bearing columns and the tooling must be removed. The load-bearing columns are then placed on a Grade 00 marble plane in a stacked state. Using the marble plane as the reference surface and the end face and axis of the load-bearing columns as the measurement objects, the installation accuracy of the load-bearing columns is evaluated.

[0073] Specifically, this includes: The satellite was hoisted onto the Grade 00 marble platform to allow the lower end face of the support column to freely contact the marble surface. After 24 hours of static contact, precise measurements were taken. A feeler gauge was used to measure the gaps between the main support column 9, secondary support column 10, and secondary support column 11 and the marble surface. The measured gap was 0.046 mm, meaning the coplanarity of the bottom surfaces of support columns 9, 10, and 11 was approximately 0.046 mm, meeting the requirements. A laser tracker was used with SA software to measure the relative positions of the main support column 9, secondary support column 10, and secondary support column 11. Points were taken on the marble surface, evenly distributed around the satellite. Points were also taken on the upper and lower outer cylindrical surfaces of the main support column 9, secondary support column 10, and secondary support column 11, distributed in a "W" shape along the cylindrical surface. Points were taken from the upper annular surfaces of the main load-bearing column 9, secondary load-bearing column 10, and secondary load-bearing column 11, with the points evenly distributed along the circumference. In SA software, a reference plane was fitted using these points on the marble surface. The points on the upper and lower outer cylindrical surfaces of the main load-bearing column 9, secondary load-bearing column 10, and secondary load-bearing column 11 were projected onto the marble surface, and the points obtained from the projection were fitted to the circumference, thus obtaining three center points. Using the main load-bearing column as the origin of the coordinate axis and the two lines connecting the centers of the two secondary load-bearing columns as the X-axis, a measurement coordinate system was established using these three points. The lateral and longitudinal distances of the three points within the reference plane were then obtained. The measured distance tolerance was 0.087 mm, which meets the requirements. By establishing the distances from points on the upper annular surfaces of the main load-bearing column 9, secondary load-bearing column 10, and secondary load-bearing column 11 to the reference plane, the distribution of height differences between the load-bearing columns can be obtained. The measured height errors from these points to the reference plane are within the range of 0.024 mm to 0.069 mm, meeting the requirements. To ensure the stacked assembly relationship and launch safety, the installation accuracy of the stacked satellite load-bearing columns under heavy-load sealing conditions, especially the consistency of installation accuracy among the stacked satellite load-bearing columns, must be strictly guaranteed. The method provided by this invention can achieve accuracy assurance and detection for stacked satellite load-bearing columns, and complete the accuracy consistency assessment of different satellite load-bearing columns involved in the stacking. Furthermore, examples demonstrate the effectiveness of this method.

[0074] The technical principles of the present invention have been described above with reference to specific embodiments, which are merely preferred embodiments of the present invention. The scope of protection of the present invention is not limited to the above embodiments; all technical solutions falling within the scope of the present invention's concept are within its protection scope. Those skilled in the art can conceive of other specific embodiments of the present invention without creative effort, and these embodiments will all fall within the protection scope of the present invention.

Claims

1. A method for detecting the accuracy of stacked satellite load-bearing columns, characterized in that, Includes the following steps: Step S1: The satellite is clamped and fixed on the machine tool to ensure that the satellite's support and stress are similar to the stacked state; Step S2: Machining the mounting surfaces of the satellite's main and secondary load-bearing columns; Step S3: Machining the main and secondary load-bearing columns, and assembling the upper and lower metal rings of the main and secondary load-bearing columns; Step S4: Machining the coaxiality of the annular surfaces of the upper and lower end faces of the main load-bearing column and the annular surfaces of the upper and lower end faces of the secondary load-bearing column, the flatness of the end face of the lower plating layer, and the radial fit clearance of the stacked load-bearing columns, and then plating the machined plating end face. Step S5: Assemble the main load-bearing column, secondary load-bearing column, satellite, and installation fixtures; Step S6: Securely connect the main load-bearing column and the secondary load-bearing column to the satellite; during the precision measurement, release the main load-bearing column and the secondary load-bearing column from the installation fixture and perform precision measurement on the satellite.

2. The method for detecting the accuracy of stacked satellite load-bearing columns as described in claim 1, characterized in that, The satellite support points reserved at the installation positions of the main load-bearing column and the secondary load-bearing column in step S1.

3. The method for detecting the accuracy of stacked satellite load-bearing columns as described in claim 1, characterized in that, Step S3 specifically includes: Step S3.1: Perform precision machining on the flatness of the mounting surfaces of the two auxiliary load-bearing columns on the satellite, ensuring that the flatness of the coplanar mounting surfaces of the two load-bearing columns on the satellite is better than 0.05mm; Step S3.2: Using the mounting surfaces of the two secondary load-bearing columns as a reference, process the mounting surfaces of the other secondary load-bearing columns.

4. The method for detecting the accuracy of stacked satellite load-bearing columns as described in claim 1, characterized in that, Step S4 further includes: a second overall machining after the coating is applied, using the end face of the lower coating surface as a reference, machining the load-bearing column as a whole, so that the parallelism between the uncoated end face and the coated end face is better than 0.05mm and the height is better than 0.08mm.

5. The method for detecting the accuracy of stacked satellite load-bearing columns as described in claim 1, characterized in that, Step S5 includes: Step S5.1: Insert the pins into the pin holes on the support column installation fixture, and the auxiliary support column will be positioned with the installation fixture through the pin holes reserved on the column; Step S5.2: Place the cover plate fixture on the upper surface of the secondary load-bearing column, and use double-ended studs to clamp the cover plate fixture and the installation fixture to fix the secondary load-bearing column, and make the bottom surface of the secondary load-bearing column completely fit with the load-bearing column mounting surface of the installation fixture. Step S5.3: Satellite and installation fixture contact each other via support base: Hoist the satellite onto the load-bearing column installation fixture and adjust the height of the support base so that it can be close to the bottom surface of the satellite.

6. The method for detecting the accuracy of stacked satellite load-bearing columns as described in claim 1, characterized in that, Step S6 includes: Step S6.1: Pre-assemble the load-bearing column bracket with the main load-bearing column and the secondary load-bearing column; Step S6.2: Insert the pin into the pin hole on the load-bearing column installation fixture, and position the main load-bearing column with the fixture through the pin hole reserved on the column; Step S6.3: Place the cover plate fixture on the upper surface of the main load-bearing column, and use double-ended studs to clamp the cover plate fixture and the load-bearing column installation fixture to fix the main load-bearing column and make its bottom surface completely fit with the fixture.

7. The method for accuracy testing of stacked satellite load-bearing columns as described in claim 1, characterized in that, The steps in step S6 for precise satellite measurement include: placing the satellite on a marble platform for precise measurement; fitting a reference plane using points on the marble; projecting points on the upper and lower outer cylindrical surfaces of the main and secondary load-bearing columns onto the marble surface, and fitting a circle using the projected points to obtain three center points; establishing a measurement coordinate system using the main load-bearing column as the origin of the coordinate axis and the two lines connecting the centers of the two secondary load-bearing columns as the X-axis, and obtaining the lateral and longitudinal distances of the three points in the reference plane. The measured distance tolerance is 0.087 mm, which meets the requirements; establishing the distances from points on the upper annular surfaces of the main and secondary load-bearing columns to the reference plane, thus obtaining the distances between the main and secondary load-bearing columns. The distribution of height differences between load-bearing columns shows that the measured height error from the upper annular surface of the main and secondary load-bearing columns to the reference surface is within the range of 0.024mm to 0.069mm, which meets the requirements.

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