CN112993588A - Low-stress processing method for large-size high-precision antenna interface - Google Patents
Low-stress processing method for large-size high-precision antenna interface Download PDFInfo
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- CN112993588A CN112993588A CN202110209798.0A CN202110209798A CN112993588A CN 112993588 A CN112993588 A CN 112993588A CN 202110209798 A CN202110209798 A CN 202110209798A CN 112993588 A CN112993588 A CN 112993588A
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- reflector assembly
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/141—Apparatus or processes specially adapted for manufacturing reflecting surfaces
Abstract
A large-size high-precision antenna interface low-stress processing method adopts structural design to reduce the influence of stress on the profile precision in the processing process to the maximum extent, and by designing an interface part process allowance area and utilizing a surface area position to carry out marking and detection on a processing position marking point, the profile precision of a reflector assembly is effectively improved, the precision stability of a reflector is improved, the problem that the processing stress introduced in the processing process of the antenna interface position has great influence on the profile precision and the antenna stability is solved, and the processing method is simple to operate, controllable in parameter and easy to realize.
Description
Technical Field
The invention relates to a low-stress processing method for a large-size high-precision antenna interface, and belongs to the field of high-precision high-stability antenna reflecting surface development.
Background
With the rapid development of space information technology, space control and utilization is one of the important targets sought by the world military and the strong country. Under the promotion of the development of information technology and the requirements of related industries, the beam pointing direction of the satellite-borne antenna develops towards the directions of more flexibility, higher resolution and larger scene coverage. Therefore, the antenna with smaller size cannot meet the requirement of actual work, and the antenna with larger size and higher precision has special significance for clearly grasping the earth surface information and macroscopically grasping the earth motion target information, so that the research on the large-scale satellite-borne high-precision high-stability antenna technology becomes the trend requirement for future development of the earth observation field.
The key points of the development and forming of the large-size, high-precision and high-stability antenna are that the influence of stress on the precision and stability of the antenna is reduced, the processing stress is inevitably brought in the interface forming process of the large-size antenna assembly, the introduction of the stress has great influence on the maintenance of the profile precision and the antenna stability, a low-stress processing method is required to be adopted, the stress influence is reduced, and the stability of the profile precision and the application process precision of the large-size antenna is improved.
Disclosure of Invention
The technical problem solved by the invention is as follows: aiming at the problem that in the prior art, the processing stress introduced in the processing process of the antenna interface position has great influence on the shape precision and the antenna stability, the low-stress processing method of the large-size high-precision antenna interface is provided.
The technical scheme for solving the technical problems is as follows:
a large-size high-precision antenna interface low-stress processing method comprises the following steps:
(1) designing an interface part process allowance area according to the position of an antenna reflector assembly interface to be processed and the structure and the size of the antenna reflector assembly;
(2) an interface supporting tool is designed according to the structure and the size of the antenna reflector assembly;
(3) the interface position of the antenna reflector assembly faces upwards and is fixed with an external machining center platform;
(4) gluing and fixing the process allowance area in the step (1) and the interface supporting tool in the step (2);
(5) fixedly connecting the bottom of the interface supporting tool and an external machining center platform after the glue joint obtained in the step (4);
(6) confirming the surface area position on one surface of the interface position of the antenna reflector assembly, marking a mark point of a processing position, and recording the position and the size of the peripheral area of the interface position;
(7) performing trial machining according to the position and the size of a peripheral area of the interface position, detecting the coordinate change of a mark point of the machining position through a profile detector, and adjusting the trial machining until the influence of the trial machining on the coordinate change of the mark point is zero;
(8) processing the interface position, confirming the coordinate change of the mark point after processing one quadrant position on one surface of the interface position of the antenna reflector assembly, if the displacement change is less than 0.01mm, continuing processing, and if not, returning to the step (7) to perform trial processing adjustment;
(9) if the parameter abnormal condition occurs in the processing process, stopping processing, adjusting the gluing position of the interface supporting tool and the antenna reflector assembly and the connecting position of the antenna reflector assembly and the external processing center platform, returning to the step (6), and if the parameter abnormal condition does not exist, continuing processing the interface position;
(10) and after the processing is finished, detecting the profile precision and the interface size of the antenna reflector assembly, and finishing the processing if the detection standard is met.
The antenna reflector assembly is a solid surface reflector of a carbon fiber honeycomb sandwich structure, the external dimension of the solid surface reflector is that the projection diameter is larger than 1m, and the thickness of the sandwich structure is not smaller than 12 mm.
The profile accuracy RMS of the antenna reflector assembly is better than 0.08mm, and the RMS is root mean square error.
The profile precision change value of the antenna reflector assembly after thermal vacuum experiments and mechanical experiments is less than 0.05mm r.m.s.
In the step (10), the detection standard of the profile precision and the interface size of the antenna reflector assembly is specifically as follows:
the profile precision is less than 0.05mm r.m.s compared with the change value before processing, and the interface position precision is better than +/-0.1 mm.
Compared with the prior art, the invention has the advantages that:
according to the large-size high-precision antenna interface low-stress processing method provided by the invention, the influence of stress on the profile precision in the processing process is reduced to the maximum extent by adopting the structural design, the processing position mark point marking and detection are carried out by designing the interface part process allowance area and utilizing the surface area position, the profile precision of the reflector assembly is effectively improved, the precision stability of the reflector is improved, the development and development of a large-caliber high-precision high-temperature reflector are facilitated, the processing method is simple to operate, the parameters are controllable, and the realization is easy.
Drawings
FIG. 1 is a schematic diagram of the configuration of a high-precision reflector product provided by the invention;
FIG. 2 is a schematic view of a platform clamping of a low stress machining center according to the present invention;
Detailed Description
A large-size high-precision antenna interface low-stress processing method is used for reducing the risk of influencing the profile precision while solving the problem that the interface of a large-size reflector assembly requires to ensure the interface precision, is an antenna reflector assembly interface forming technology with large size, high precision and high stability, and is suitable for a satellite-borne carbon fiber honeycomb sandwich structure antenna reflector, and the specific flow of the processing method is as follows:
(1) designing an interface part process allowance area according to the position of an antenna reflector assembly interface to be processed and the structure and the size of the antenna reflector assembly;
(2) an interface supporting tool is designed according to the structure and the size of the antenna reflector assembly;
(3) the interface position of the antenna reflector assembly faces upwards and is fixed with an external machining center platform;
(4) gluing and fixing the process allowance area in the step (1) and the interface supporting tool in the step (2);
(5) fixedly connecting the bottom of the interface supporting tool and an external machining center platform after the glue joint obtained in the step (4);
(6) confirming the surface area position on one surface of the interface position of the antenna reflector assembly, marking a mark point of a processing position, and recording the position and the size of the peripheral area of the interface position;
(7) performing trial machining according to the position and the size of a peripheral area of the interface position, detecting the coordinate change of a mark point of the machining position through a profile detector, and adjusting the trial machining until the influence of the trial machining on the coordinate change of the mark point is zero;
(8) processing the interface position, confirming the coordinate change of the mark point after processing one quadrant position on one surface of the interface position of the antenna reflector assembly, if the displacement change is less than 0.01mm, continuing processing, and if not, returning to the step (7) to perform trial processing adjustment;
(9) if the parameter abnormal condition occurs in the processing process, stopping processing, adjusting the gluing position of the interface supporting tool and the antenna reflector assembly and the connecting position of the antenna reflector assembly and the external processing center platform, returning to the step (6), and if the parameter abnormal condition does not exist, continuing processing the interface position;
(10) after the processing is finished, detecting the profile precision and the interface size of the antenna reflector assembly, and if the detection standard is met, finishing the processing;
the detection standard of the profile precision and the interface size of the antenna reflector assembly is as follows:
the profile precision is less than 0.05mm r.m.s compared with the change value before processing, and the interface position precision is better than +/-0.1 mm.
The antenna reflector assembly is a solid surface reflector with a carbon fiber honeycomb sandwich structure, the external dimension of the solid surface reflector is that the projection diameter is larger than 1m, and the thickness of the sandwich structure is not smaller than 12 mm;
the profile accuracy RMS of the antenna reflector assembly is better than 0.08mm, and the RMS is root mean square error;
the profile precision change value of the antenna reflector assembly after the thermal vacuum experiment and the mechanical experiment is less than 0.05 mm.
The following is further illustrated with reference to specific examples:
in this embodiment, taking an interface molding process in which the accuracy of the external assembly interface of the antenna reflector assembly is better than ± 0.1mm as an example, a process margin area is designed on the interface part assembled with the reflection surface body of the antenna reflector assembly, and the process margin ensures that manual processing can be removed without affecting assembly bonding assembly. Secondly, after the assembly and the glue joint of the reflection assembly are finished, a supporting tool is designed at the assembly position of the reflector external interface part, and clamping and supporting in the machining process are guaranteed. Secondly, in the clamping process, the opening surface of the reflector is placed upwards, the supporting tool is placed between the reflecting surface and the external machining center platform, and the contact position of the supporting tool and the reflecting surface is in the interface part process area. Then, the contact surface of the supporting tool and the reflector component is glued by room-temperature normal-temperature glue, so that clamping and fixing are realized. And finally, finishing the interface size machining by adopting a five-axis machining center, and ensuring the machining precision.
The large-size reflecting surface refers to a fixed surface reflector of a carbon fiber honeycomb sandwich structure with the diameter of the outline projection area of the reflecting surface larger than 1m, and the thickness of the honeycomb sandwich structure is not smaller than 12 mm. The high-precision finger profile precision RMS is better than 0.08mm, the RMS refers to the root mean square error, and the high-stability finger reflector undergoes a thermal vacuum experiment and a mechanical experiment, and the profile precision change value is less than 0.05mm r.m.s.
The method comprises the following specific steps:
step 1: designing an interface part process allowance area according to the position of an antenna reflector assembly interface and the structural size of the assembly;
step 2: designing an interface supporting tool according to the size of the antenna reflector assembly;
and step 3: fixing the reflector assembly interface with the external machining center platform in a way that the interface is arranged to face upwards;
and 4, step 4: the supporting tool is connected with the process allowance area and is fixed by normal temperature glue;
and 5: fixedly connecting the bottom of the support tool glued in the step 4 with an external machining center platform;
step 6: confirming the position of the surface area at the central point and the periphery in the interface of the antenna reflector, determining by using marker marking points, and recording the position size;
and 7: trial-running a machining program according to the size position of the interface, performing trial machining according to quadrants one by one, and detecting the coordinate change of a mark point adjacent to a machining area by using a profile detector;
and 8: after the influence of the trial run sequence on the coordinate values of the mark points is confirmed to be zero, starting to run the machining program;
and step 9: confirming the coordinate change of the marking point every time a quadrant position is machined, and confirming that the displacement change is less than 0.01 mm;
step 10: if the parameters are abnormal, stopping processing, and adjusting the gluing position of the support tool and the component and the clamping position of the component and the platform;
step 11: under the condition of abnormal parameters, returning to the step 6 to finish the interface processing;
step 12: and detecting the profile precision and the interface size of the antenna reflector assembly, and confirming that the profile precision is smaller than 0.05mm r.m.s compared with the change value before processing, and the interface precision is better than +/-0.1 mm.
The method specifically comprises the following steps:
as shown in fig. 1, when a high-precision reflector assembly with an aperture of 1.2m and a profile accuracy requirement of not more than 0.05mm r.m.s after a thermal vacuum test is prepared, a machining allowance area is reserved at an interface position of the antenna reflector assembly, namely the end face of the switching angle box. The antenna reflector assembly is then clamped onto a bottom tooling of the tooling center table with the mouth facing up. Then designing a supporting tool; assembling and fixing the support tool and the reflector assembly, and confirming that the support tool is supported at the position of the transfer corner box and is not in contact with the molded surface of the reflector assembly; adhering the support tool and the transfer corner box by using AB glue at normal temperature; and then fixing the reflector assembly and the support tool on a five-axis machining platform by using a pressing plate, clamping the pressing plate on the support tool and the auxiliary tool, as shown in fig. 2, finally, monitoring and recording the profile of the reflecting surface by using a side instrument and a marker pen, running a program in a trial mode, confirming that the mark points have no displacement change, and performing combined machining. The precision of the molded surface after final machining is 0.04mm r.m.s, and the variation of the molded surface is 0.013mm r.m.s compared with the 0.027mm r.m.s before machining. The interface precision is +/-0.05 mm, and the requirement is met.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (5)
1. A large-size high-precision antenna interface low-stress processing method is characterized by comprising the following steps:
(1) designing an interface part process allowance area according to the position of an antenna reflector assembly interface to be processed and the structure and the size of the antenna reflector assembly;
(2) an interface supporting tool is designed according to the structure and the size of the antenna reflector assembly;
(3) the interface position of the antenna reflector assembly faces upwards and is fixed with an external machining center platform;
(4) gluing and fixing the process allowance area in the step (1) and the interface supporting tool in the step (2);
(5) fixedly connecting the bottom of the interface supporting tool and an external machining center platform after the glue joint obtained in the step (4);
(6) confirming the surface area position on one surface of the interface position of the antenna reflector assembly, marking a mark point of a processing position, and recording the position and the size of the peripheral area of the interface position;
(7) performing trial machining according to the position and the size of a peripheral area of the interface position, detecting the coordinate change of a mark point of the machining position through a profile detector, and adjusting the trial machining until the influence of the trial machining on the coordinate change of the mark point is zero;
(8) processing the interface position, confirming the coordinate change of the mark point after processing one quadrant position on one surface of the interface position of the antenna reflector assembly, if the displacement change is less than 0.01mm, continuing processing, and if not, returning to the step (7) to perform trial processing adjustment;
(9) if the parameter abnormal condition occurs in the processing process, stopping processing, adjusting the gluing position of the interface supporting tool and the antenna reflector assembly and the connecting position of the antenna reflector assembly and the external processing center platform, returning to the step (6), and if the parameter abnormal condition does not exist, continuing processing the interface position;
(10) and after the processing is finished, detecting the profile precision and the interface size of the antenna reflector assembly, and finishing the processing if the detection standard is met.
2. The method for processing the interface of the large-size high-precision antenna with low stress as claimed in claim 1, wherein the method comprises the following steps:
the antenna reflector assembly is a solid surface reflector of a carbon fiber honeycomb sandwich structure, the external dimension of the solid surface reflector is that the projection diameter is larger than 1m, and the thickness of the sandwich structure is not smaller than 12 mm.
3. The method for processing the interface of the large-size high-precision antenna with low stress as claimed in claim 1, wherein the method comprises the following steps:
the profile accuracy RMS of the antenna reflector assembly is better than 0.08mm, and the RMS is root mean square error.
4. The method for processing the interface of the large-size high-precision antenna with low stress as claimed in claim 1, wherein the method comprises the following steps:
the profile precision change value of the antenna reflector assembly after thermal vacuum experiments and mechanical experiments is less than 0.05mm r.m.s.
5. The method for processing the interface of the large-size high-precision antenna with low stress as claimed in claim 1, wherein the method comprises the following steps:
in the step (10), the detection standard of the profile precision and the interface size of the antenna reflector assembly is specifically as follows:
the profile precision is less than 0.05mm r.m.s compared with the change value before processing, and the interface position precision is better than +/-0.1 mm.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110209798.0A CN112993588B (en) | 2021-02-24 | 2021-02-24 | Low-stress processing method for large-size high-precision antenna interface |
| PCT/CN2021/131373 WO2022179202A1 (en) | 2021-02-24 | 2021-11-18 | Low-stress processing method for large-size and high-precision antenna interface |
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| CN202110209798.0A CN112993588B (en) | 2021-02-24 | 2021-02-24 | Low-stress processing method for large-size high-precision antenna interface |
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| CN112993588A true CN112993588A (en) | 2021-06-18 |
| CN112993588B CN112993588B (en) | 2022-09-06 |
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| WO2022179202A1 (en) * | 2021-02-24 | 2022-09-01 | 北京卫星制造厂有限公司 | Low-stress processing method for large-size and high-precision antenna interface |
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- 2021-11-18 WO PCT/CN2021/131373 patent/WO2022179202A1/en active Application Filing
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| CN112993588B (en) | 2022-09-06 |
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