阅读说明：本技术 卫星大口径可展开天线定位安装方法 (Satellite large-caliber deployable antenna positioning and mounting method ) 是由 孙伟 张国强 陈双全 崔国刚 潘瑞雪 刘政 曹岸杰 李金亮 扈宗鑫 张伟夫 于 2020-05-27 设计创作，主要内容包括：本发明提供了一种卫星大口径可展开天线定位安装方法,包括以下步骤：S1、根据天线馈源与天线反射面相对关系完成卫星正式侧板和卫星模拟侧板的高精度加工；S2、利用卫星模拟侧板及天线馈源,完成卫星舱内外与天线馈源相关的波导调整；S3、拆除卫星模拟侧板及天线馈源,然后安装卫星正式侧板及天线馈源；将卫星置于两轴转台上,通过两轴转台调整好卫星姿态,完成天线反射面压紧释放机构安装及天线反射面展开机构安装。本发明定位安装方法取消了大口径天线馈源与反射面之间的附属连接结构,节省了卫星宝贵的设计资源；减少了波导调整的难度；操作简单、适应性强,可应用于通信、侦察等卫星。(The invention provides a positioning and mounting method of a satellite large-caliber deployable antenna, which comprises the following steps: s1, finishing high-precision processing of the formal satellite side plate and the simulated satellite side plate according to the relative relation between the antenna feed source and the antenna reflecting surface; s2, utilizing the satellite simulation side plate and the antenna feed source to complete waveguide adjustment related to the antenna feed source inside and outside the satellite cabin; s3, removing the satellite simulation side plate and the antenna feed source, and then installing the satellite formal side plate and the antenna feed source; and (3) placing the satellite on the two-axis rotary table, and adjusting the posture of the satellite through the two-axis rotary table to complete the installation of the antenna reflecting surface pressing and releasing mechanism and the installation of the antenna reflecting surface unfolding mechanism. The positioning installation method cancels an auxiliary connection structure between the large-aperture antenna feed source and the reflecting surface, and saves precious design resources of the satellite; the difficulty of waveguide adjustment is reduced; the method is simple to operate and high in adaptability, and can be applied to satellites for communication, reconnaissance and the like.)

1. A satellite large-caliber deployable antenna positioning and mounting method is characterized by comprising the following steps:

s1, finishing high-precision processing of the formal satellite side plate and the simulated satellite side plate according to the relative relation between the antenna feed source and the antenna reflecting surface;

s2, utilizing the satellite simulation side plate and the antenna feed source to complete waveguide adjustment related to the antenna feed source inside and outside the satellite cabin;

step S3, removing the satellite simulation side plate and the antenna feed source, and then installing the satellite formal side plate and the antenna feed source; and (3) placing the satellite on the two-axis rotary table, and adjusting the posture of the satellite through the two-axis rotary table to complete the installation of the antenna reflecting surface pressing and releasing mechanism and the installation of the antenna reflecting surface unfolding mechanism.

2. The method for positioning and installing the satellite large-caliber deployable antenna according to claim 1, wherein in the step S1, the high-precision machining of the satellite main side plate and the satellite simulation side plate comprises the following steps:

s11, completing the assembly of the satellite shell;

s12, processing an antenna feed source positioning pin hole, an antenna reflecting surface pressing and releasing mechanism positioning pin hole and an antenna reflecting surface unfolding mechanism positioning pin hole on a formal side plate of the satellite;

s13, processing the satellite simulation side plate according to the size of the formal side plate of the satellite, wherein the satellite simulation side plate has no operation blind area, and installation and adjustment of the waveguide related to the antenna feed source in the satellite cabin are facilitated after the satellite simulation side plate is installed.

3. The method for positioning and installing the satellite large-caliber deployable antenna according to claim 2, wherein in step S12, finish machining positioning of the antenna feed source positioning pin hole and the antenna reflecting surface pressing and releasing mechanism positioning pin hole is completed by taking the positioning pin hole of the antenna reflecting surface deploying mechanism as an installation reference, and the antenna reflecting surface pressing and releasing mechanism is connected with the antenna reflecting surface deploying mechanism.

4. The positioning and mounting method for the large-caliber deployable antenna of the satellite according to claim 2 or 3, wherein the antenna feed source positioning pin hole and the positioning pin hole of the antenna reflector deployment mechanism are respectively located in the middle of two opposite sides of the side plate, and the positioning pin hole of the antenna reflector pressing and releasing mechanism is located on the side plate between the antenna feed source positioning pin hole and the positioning pin hole of the antenna reflector deployment mechanism.

5. The positioning and installation method for a large-aperture deployable antenna of a satellite according to claim 4, wherein the number of the positioning pin holes of the antenna reflector pressing and releasing mechanism is four, and the four positioning pin holes correspond to four pressing points of the antenna reflector pressing and releasing mechanism respectively.

6. The method for positioning and installing the satellite large-caliber deployable antenna according to claim 2 or 3, wherein in the step S12, the machining errors of the three positioning pin holes are controlled to be 0.05-0.1 mm.

7. The positioning and mounting method for the large-caliber deployable antenna of the satellite according to claim 6, wherein the machining error of the antenna feed source positioning pin hole is 0.05 mm.

8. The positioning and mounting method for the satellite large-caliber deployable antenna according to claim 1 or 2, wherein the satellite formal side plate and the satellite simulation side plate are processed with high precision according to the standard that the planeness is 0.2mm, the parallelism is not more than 0.2mm and the perpendicularity is not more than 0.2 mm.

9. The method for positioning and installing the satellite large-caliber deployable antenna according to claim 1, wherein a formal side plate of the satellite for installing the antenna feed source, the antenna reflecting surface pressing and releasing mechanism and the antenna reflecting surface deploying mechanism is a whole plate; the whole flatness of the installation surface of the different antenna reflecting surface pressing and releasing mechanism is controlled to be 0.20 mm.

10. The method for positioning and installing the satellite large-caliber deployable antenna according to claim 1, wherein in step S3, the satellite attitude is adjusted by a two-axis turntable, so that a formal side plate of the satellite for installing the antenna feed source, the antenna reflector pressing and releasing mechanism and the antenna reflector deploying mechanism is horizontally placed, and the levelness is not more than 2 mm.

Technical Field

The invention relates to the technical field of satellite processing and assembling, in particular to a positioning and mounting method of a large-caliber deployable antenna of a satellite.

Background

When a general satellite carries out the assembly of a large-caliber deployable antenna, three problems need to be solved. The method comprises the steps of solving the problem of high-precision positioning of an antenna feed source and a reflecting surface, wherein the traditional design is to ensure the high-precision positioning of the feed source and the reflecting surface, and the feed source and the reflecting surface are generally connected together by adopting a supporting structure, so that more useless structures are caused, and precious satellite design resources are wasted; and secondly, the problem that the waveguide related to the antenna feed source is installed is solved, when the number of waveguides connected with the feed source is large, the waveguide outside the cabin generally adopts a soft waveguide or waveguide gasket mode to correct the installation error of the waveguide, the installation error of the waveguide inside the cabin is reduced, and the transmission loss is avoided to be large. And thirdly, the problem that the antenna reflecting surface compresses the releasing mechanism to be installed is solved, and the problem that the antenna reflecting surface cannot be normally unfolded and cannot be normally used due to improper installation of the antenna reflecting surface compressing the releasing mechanism is solved.

Through to prior art's retrieval, utility model patent that application number is 201220702932.7 provides a navigation satellite receiving antenna installation device, including tubulose installation base, elasticity centering rod subassembly and connecting piece, the ring flange and the antenna carrier of tubulose installation base are connected, the hollow tube of tubulose installation base is used for assembling elasticity centering rod subassembly, elasticity centering rod subassembly carries out multiple spot elasticity centering with clearance fit's mode and connects in inserting the hollow tube of tubulose installation base, the connecting piece is used for connecting navigation satellite receiving antenna and elasticity centering rod subassembly. But does not relate to the positioning and mounting method associated with the aerospace in-orbit antenna.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a positioning and mounting method for a large-caliber deployable antenna of a satellite.

The purpose of the invention is realized by the following scheme:

a satellite large-caliber deployable antenna positioning and mounting method comprises the following steps:

s1, finishing high-precision processing of the formal satellite side plate and the simulated satellite side plate according to the relative relation between the antenna feed source and the antenna reflecting surface;

s2, utilizing the satellite simulation side plate and the antenna feed source to complete waveguide adjustment related to the antenna feed source inside and outside the satellite cabin;

step S3, removing the satellite simulation side plate and the antenna feed source, and then installing the satellite formal side plate and the antenna feed source; and (3) placing the satellite on the two-axis rotary table, and adjusting the posture of the satellite through the two-axis rotary table to complete the installation of the antenna reflecting surface pressing and releasing mechanism and the installation of the antenna reflecting surface unfolding mechanism.

Preferably, in step S1, the high-precision machining of the satellite main side plate and the satellite simulation side plate includes the following steps:

s11, completing satellite shell assembly (including satellite formal side plates);

s12, processing an antenna feed source positioning pin hole, an antenna reflecting surface pressing and releasing mechanism positioning pin hole and an antenna reflecting surface unfolding mechanism positioning pin hole on a formal side plate of the satellite;

s13, processing the satellite simulation side plate according to the size of the formal side plate of the satellite, wherein the satellite simulation side plate has no operation blind area, and installation and adjustment of the waveguide related to the antenna feed source in the satellite cabin are facilitated after the satellite simulation side plate is installed.

Preferably, in step S12, finish machining and positioning of the antenna feed source positioning pin hole and the antenna reflecting surface pressing and releasing mechanism positioning pin hole are completed by using the positioning pin hole of the antenna reflecting surface unfolding mechanism as an installation reference, and the antenna reflecting surface pressing and releasing mechanism is connected with the antenna reflecting surface unfolding mechanism.

Preferably, the antenna feed source positioning pin hole and the positioning pin hole of the antenna reflecting surface unfolding mechanism are respectively located in the middle of two opposite sides of the side plate, and the positioning pin hole of the antenna reflecting surface pressing and releasing mechanism is located on the side plate between the antenna feed source positioning pin hole and the positioning pin hole of the antenna reflecting surface unfolding mechanism.

Preferably, there are four positioning pin holes of the antenna reflecting surface pressing and releasing mechanism, which correspond to four pressing points of the antenna reflecting surface pressing and releasing mechanism respectively.

Preferably, in step S12, the machining errors of the three types of dowel holes are controlled to be 0.05-0.1 mm.

Preferably, the machining error of the antenna feed source positioning pin hole is 0.05 mm.

Preferably, the satellite formal side plate and the satellite simulation side plate are processed with high precision according to the standard that the planeness is 0.2mm, the parallelism is not more than 0.2mm, and the verticality is not more than 0.2 mm.

Preferably, the formal side plate of the satellite for installing the antenna feed source, the antenna reflecting surface pressing and releasing mechanism and the antenna reflecting surface unfolding mechanism is a whole plate; the whole flatness of the installation surface of the different antenna reflecting surface pressing and releasing mechanisms is controlled to be 0.20 mm.

Preferably, in step S3, the satellite attitude is adjusted by the two-axis turntable, so that a formal side plate of the satellite for mounting the antenna feed source, the antenna reflecting surface pressing and releasing mechanism, and the antenna reflecting surface unfolding mechanism is placed horizontally, and the levelness is not greater than 2 mm.

Compared with the prior art, the invention has the following beneficial effects: 1. according to the positioning and mounting method for the large-caliber deployable antenna of the satellite, the antenna feed source and the reflecting surface are positioned on the whole side plate of the satellite through the pin holes, so that an auxiliary connection structure between the antenna feed source and the reflecting surface is saved, precious design resources of the satellite are saved, and high-precision resetting and mounting of the antenna feed source and the reflecting surface can be guaranteed. 2. According to the positioning and mounting method for the satellite large-caliber deployable antenna, a feed source simulation side plate mounting mode is adopted, so that a better mounting reference is provided for the waveguide adjustment in the cabin to adjust the waveguide in place, the difficulty of the waveguide adjustment is reduced, the error of the antenna feed source after formal mounting is small, and the phenomenon that the transmission loss is large due to the large waveguide mounting error is avoided. 3. According to the positioning and mounting method for the large-aperture deployable antenna of the satellite, the side plate processes the relevant interface of the compression release mechanism in place, then the satellite side plate is horizontally upwards by adopting a two-axis turntable mode, and the levelness is adjusted to 2mm, so that the compression release mechanism can be mounted, the operation is simple, the adaptability is strong, and the positioning and mounting method can be applied to satellites such as communication, reconnaissance and the like.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic view of a satellite side plate for high-precision processing of an antenna feed source and a reflector pressing mechanism mounting interface;

FIG. 2 is a schematic diagram of the satellite side plate according to the present invention for processing precision requirements of the mounting interfaces of the antenna feed source and the reflector pressing mechanism;

FIG. 3 is a schematic diagram of the method of the present invention for adjusting the waveguide of a satellite by using a satellite simulation side plate;

FIG. 4 is a schematic diagram of the installation of the antenna reflection surface by the satellite in the two-axis turntable with the attitude adjusted according to the method of the present invention.

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

The problem that a large-caliber deployable antenna is difficult to position and install in the existing general assembly technology of the satellite is solved; the invention aims to provide a method for positioning a feed source and a reflecting surface, installing and adjusting a waveguide and installing an antenna reflecting surface, which is simple and easy in the whole process, greatly saves the installation time of a satellite antenna and is successfully applied to a rail type number.

As shown in fig. 1 to 4, the present invention will be described in further detail with reference to specific embodiments.