阅读说明：本技术 一种镁合金卫星天线反射面 (Magnesium alloy satellite antenna reflecting surface ) 是由 杨海林 董亮 邵炫 苏广明 吴国清 吴超章 王金良 于 2019-11-20 设计创作，主要内容包括：本发明提供一种镁合金卫星天线反射面,属于卫星天线技术领域。所述卫星天线反射面采用一体化成型结构,天线整体呈箱式结构；所述卫星天线反射面包括一个中间体和多个扇面,所述中间体位于中心位置,呈圆筒形箱体结构；所述扇面分布在中间体的周向,形成投影为圆形的反射面；所述扇面的前表面为光滑弧形面,后表面为支撑结构；所述支撑结构包括径向加强筋、轴向加强筋和方形加强筋。本发明具有精度高、信号接收稳定、重量轻、抗老化性能好和不易变形的优点。(The invention provides a magnesium alloy satellite antenna reflecting surface, and belongs to the technical field of satellite antennas. The reflecting surface of the satellite antenna adopts an integrated molding structure, and the whole antenna is of a box-type structure; the satellite antenna reflection surface comprises an intermediate body and a plurality of sectors, wherein the intermediate body is positioned at the center and is of a cylindrical box structure; the fan surface is distributed in the circumferential direction of the intermediate body to form a reflecting surface with a circular projection; the front surface of the sector is a smooth arc-shaped surface, and the rear surface of the sector is a supporting structure; the supporting structure comprises radial reinforcing ribs, axial reinforcing ribs and square reinforcing ribs. The invention has the advantages of high precision, stable signal receiving, light weight, good ageing resistance and difficult deformation.)

1. A magnesium alloy satellite antenna reflecting surface is characterized in that: the magnesium alloy satellite antenna is of a box-type structure as a whole; the satellite antenna reflection surface comprises an intermediate body and a plurality of sectors, wherein the intermediate body is positioned at the center and is of a cylindrical box structure; the fan surface is distributed in the circumferential direction of the intermediate body to form a reflecting surface with a circular projection; the front surface of the sector is a smooth arc-shaped surface, the rear surface of the sector is a supporting structure, and the sector is integrated with the supporting structure by adopting a main reflecting surface; the supporting structure comprises radial reinforcing ribs, axial reinforcing ribs and square reinforcing ribs.

2. The magnesium alloy satellite antenna reflector according to claim 1, wherein: each sector is connected with the intermediate body through a bolt, and two adjacent sectors are connected through bolts.

3. The magnesium alloy satellite antenna reflector according to claim 1, wherein: the whole intermediate body is of a box body structure formed by sleeving a plurality of concentric cylinders, and the cylinders are connected through intermediate reinforcing ribs distributed in a fan shape; in the multiple cylinders, the diameter difference of two adjacent cylinders is the same, the heights of the multiple cylinders are the same, the middle cylinder is a through hole, and the reflecting surface is arranged on one side of the other cylinders.

4. The magnesium alloy satellite antenna reflector of claim 3, wherein: the height of the middle reinforcing rib is equal to the height of the plurality of cylinders; the middle body reinforcing rib is provided with a first lightening hole.

5. The magnesium alloy satellite antenna reflector according to claim 1, wherein: the radial reinforcing ribs arranged on the rear surface of each sector are uniformly distributed in the sector, and the trend of the radial reinforcing ribs is along the radial direction of the sector; wherein, two radial reinforcing ribs on the edge are shared with two adjacent sectors; the two radial reinforcing ribs at the edge and the middle radial reinforcing rib are consistent with the three adjacent intermediate reinforcing ribs at the corresponding positions on the intermediate in direction; the radial reinforcing ribs are thin-walled structures with gradually-changed heights, the root part connected with the intermediate body is the highest, the tip part at the outer edge part of the sector is the lowest, the root part is connected with the top end of the tip part in a straight mode, and the bottoms of the radial reinforcing ribs are in contact with the rear surface of the sector to form the radial reinforcing ribs similar to trapezoids.

6. The magnesium alloy satellite antenna reflector according to claim 5, wherein: and the radial reinforcing ribs are provided with second lightening holes.

7. The magnesium alloy satellite antenna reflector of claim 6, wherein: the second lightening holes are distributed on the radial reinforcing ribs between the square reinforcing ribs and the middle body.

8. The magnesium alloy satellite antenna reflector according to claim 1, wherein: the axial reinforcing ribs form a plurality of concentric cylinders coaxial with the intermediate body at the rear part of the whole satellite antenna reflecting surface, the top view is a plurality of concentric circles, and the height of the axial reinforcing ribs is the same as that of the positions of the crossed radial reinforcing ribs.

9. The magnesium alloy satellite antenna reflector according to claim 1, wherein: the square reinforcing ribs are two, the two square reinforcing ribs are eight vertexes in total and are respectively positioned at the outer edge vertexes of each sector, the bottom surfaces of the square reinforcing ribs are in contact with the rear surfaces of the sectors, the tops of the square reinforcing ribs are straight, and the heights of the square reinforcing ribs are the same as the heights of the positions of the crossed radial reinforcing ribs, so that a thin-wall square reinforcing rib structure with variable heights is formed.

10. The magnesium alloy satellite antenna reflector according to claim 1, wherein: the whole wall thickness of the reflecting surface of the magnesium alloy satellite antenna is not more than 5 mm.

Technical Field

The invention belongs to the technical field of satellite antennas, and particularly relates to a magnesium alloy satellite antenna reflecting surface.

Background

The antenna reflecting surface is a conductive curved surface or plane used for intensively reflecting electromagnetic waves emitted by a feed source to a certain direction according to a certain requirement in a planar antenna so as to enhance the emission effect. Most satellite antennas have a parabolic body, but some multi-focus antennas are formed by combining a spherical surface and a parabolic surface, and the received satellite signals are concentrated to the focus point through the reflection of the parabolic antenna. At present, the commonly used reflecting surface is made of materials such as glass fiber reinforced plastics, carbon fiber, steel plate pre-drawing forming and aluminum alloy. Although the parabolic satellite receiving antenna using the cold-rolled steel plate is sprayed with paint and various coatings on the reflecting surface, the parabolic satellite receiving antenna is frequently scratched in the installation and transportation process, and the protective layer is easily damaged under the condition of outdoor exposure to rain, so that the cold-rolled steel plate is exposed to generate a corrosion phenomenon, and the service life is greatly shortened; the paraboloidal receiver body is made of pure aluminum or aluminum alloy, so that the paraboloidal receiver is high in price and manufacturing cost, and meanwhile, the pure aluminum and the aluminum alloy are soft, are easy to deform in use and are difficult to adapt to weather with strong wind and snow; the cast aluminum has high price and high brittleness, and is easy to crack and break in the using process. The traditional carbon fiber satellite antenna reflector body adopts a carbon fiber composite material sandwich structure, the back rib adopts an aluminum alloy material, and the back rib and the reflector body are connected by adopting glue joint or a metal embedded part screw. Due to mismatching of material performance, the focus of the reflecting surface is obviously changed along with fluctuation of environmental temperature, and the electrical performance is influenced; moreover, the connecting part of the aluminum alloy back rib and the reflecting surface is easy to generate structural damage when facing low temperature or high temperature; the glass fiber reinforced plastic antenna adopts a film pressing technology under high temperature and high pressure, the material characteristics and the processing technology thereof determine that the glass fiber reinforced plastic antenna has incomparable consistency with other antennas and has the characteristic of no deformation, so the service life is generally more than ten years, but the oscillator and the radio frequency coaxial cable of the existing glass fiber reinforced plastic antenna cannot be ensured to be in a straightening state for a long time, and the deformation of the glass fiber reinforced plastic antenna can bring adverse effects to a satellite receiving system in the signal transportation process.

In order to meet the requirements of vehicle-mounted and ground dual-purpose antennas, the new requirements on the reflecting surface of the antenna are large size, high precision, light weight and portability, and magnesium alloy is the lightest type of the current metal structural materials, and is characterized by small density (1.8 g/cm 3), namely 1/5 of steel, 1/4 of zinc and 2/3 of aluminum, and has very high specific strength, for example, the specific strength of AZ91D can reach 154, which is far higher than that of alloy steel (100).

The rigidity of the common cast magnesium alloy and the cast aluminum alloy is the same, so the specific strength of the alloy is obviously higher than that of the aluminum alloy, and the magnesium alloy is more used for designing integral components. The magnesium alloy has good heat dissipation performance, the heat dissipation time of the magnesium alloy is less than half of that of the aluminum alloy at the same temperature, and the heat can be quickly dissipated in the casting process. The magnesium alloy has higher specific elastic modulus, and can consume larger deformation work under the same stress condition, so the magnesium alloy has good vibration damping performance and can bear larger impact and vibration load. Magnesium alloys have good machinability, which is also incomparable with other metals.

Disclosure of Invention

The invention aims to provide a magnesium alloy satellite antenna reflecting surface to solve the problem of optimization between light weight and strength of the conventional satellite antenna.

In order to solve the technical problem, the invention provides a magnesium alloy satellite antenna reflecting surface which is formed by combining a reflecting surface and a supporting structure into a whole and has a box-type structure.

A magnesium alloy satellite antenna reflecting surface comprises an intermediate body and a plurality of sectors, wherein the intermediate body is positioned at the central position and is of a cylindrical box structure; the fan surface is distributed in the circumferential direction of the intermediate body to form a reflecting surface with a circular projection; the front surface of the sector is a smooth arc-shaped surface, and the rear surface of the sector is a supporting structure; the supporting structure comprises radial reinforcing ribs, axial reinforcing ribs and square reinforcing ribs.

Preferably, each sector is connected with the intermediate body through a bolt, and two adjacent sectors are connected through a bolt.

Preferably, the whole intermediate body is a box body structure formed by sleeving a plurality of concentric cylinders, and the cylinders are connected through intermediate reinforcing ribs distributed in a fan shape; the diameter difference of two adjacent cylinders is the same, the heights of the cylinders are the same, the middle cylinder is a through hole, and the reflecting surfaces are arranged on the single sides of the rest cylinders.

Preferably, the height of the intermediate reinforcing bar is equal to the height of the plurality of cylinders; the middle body reinforcing rib is provided with a first lightening hole.

Preferably, the radial reinforcing ribs arranged on the rear surface of each sector are uniformly distributed in the sector, and the trend of the radial reinforcing ribs is along the radial direction of the sector; wherein, two radial reinforcing ribs on the edge are shared with two adjacent sectors; the two radial reinforcing ribs at the edge and the middle radial reinforcing rib are consistent with the three adjacent intermediate reinforcing ribs at the corresponding positions on the intermediate in direction; the radial reinforcing ribs are thin-walled structures with gradually-changed heights, the root part connected with the intermediate body is the highest, the tip part at the outer edge part of the sector is the lowest, the root part is connected with the top end of the tip part in a straight mode, and the bottoms of the radial reinforcing ribs are in contact with the rear surface of the sector to form the radial reinforcing ribs similar to trapezoids.

Preferably, the radial reinforcing rib is provided with a second lightening hole.

Preferably, the second lightening holes are distributed on the radial reinforcing ribs between the square reinforcing ribs and the middle body.

Preferably, the axial ribs are formed in a plurality of concentric cylindrical shapes coaxial with the intermediate body at the rear portion of the entire satellite antenna reflection surface, the plurality of concentric circles are formed in a plan view, and the height of the plurality of axial ribs is the same as the height of the positions of the intersecting radial ribs.

Preferably, the number of the square reinforcing ribs is two, the two square reinforcing ribs have eight vertexes in total and are respectively located at the vertexes of the outer edge of each sector, the bottom surfaces of the square reinforcing ribs are in contact with the rear surface of each sector, the tops of the square reinforcing ribs are straight, and the heights of the square reinforcing ribs are the same as the heights of the positions of the crossed radial reinforcing ribs, so that the thin-wall square reinforcing rib structure with the variable heights is formed.

The invention has the advantages that:

(1) high precision, stable signal reception: the magnesium alloy satellite antenna reflection surface provided by the invention is of a box-type structure as a whole, and the rear surfaces of the intermediate body and the sector are of annular reinforcing rib structures, so that the minimum deformation of the reflection surface in the casting forming and subsequent machining processes is ensured, and the space geometric dimension and the plane geometric dimension precision of the antenna are ensured.

(2) The weight is light: the whole reflection surface of the satellite antenna is cast by magnesium alloy, is lighter than aluminum alloy 1/3, and the reinforcing ribs on the back of the antenna are calculated by mechanical properties and highly optimally designed, so that the purpose of dual weight reduction is achieved by height change and weight reduction holes under the condition of ensuring that the stress requirement is met.

(3) The ageing resistance and the fatigue resistance are good: the antenna is prepared by adopting magnesium alloy materials with glass fiber reinforced plastics and carbon fibers, so that the aging problem is solved; meanwhile, the antenna has good fatigue resistance and is not easily influenced by weather.

(4) Is not easy to deform: the magnesium alloy has high specific elastic modulus, can consume larger deformation work under the same stress condition, is not easy to deform when being impacted by external force such as sand stone and the like, has the defects of difficult pit generation and the like on the surface, and is suitable for field operation.

Drawings

Fig. 1 is a front view of a reflection surface of a magnesium alloy satellite antenna according to an embodiment of the present invention.

Fig. 2 is a rear view of a reflection surface of a magnesium alloy satellite antenna provided in an embodiment of the present invention.

Fig. 3 is a schematic view of a supporting structure of a reflection surface of a magnesium alloy satellite antenna provided in an embodiment of the present invention.

Fig. 4 is a schematic structural diagram of the intermediate body in the reflection surface of the magnesium alloy satellite antenna provided in the embodiment of the present invention.

Fig. 5 is a schematic rear view of a single sector in a reflection surface of a magnesium alloy satellite antenna provided in an embodiment of the present invention.

In the figure:

1. an intermediate; 2, sector; 101. a cylinder; 102, an intermediate reinforcing rib;

103. a first lightening hole; a radial reinforcing rib; 202, axial reinforcing ribs; 203, square reinforcing ribs;

204. and a second lightening hole.

Detailed Description

The present invention will be described in detail below with reference to the accompanying drawings and examples.

The invention firstly provides a magnesium alloy satellite antenna reflecting surface, which adopts a structure that a main reflecting surface and a supporting structure are combined into a whole, and the whole antenna is of a box-type structure. As shown in fig. 1 to fig. 3, the satellite antenna reflection surface provided by the embodiment of the present invention includes an intermediate body 1 and a plurality of sectors 2, where the intermediate body 1 is located at a central position and has a cylindrical structure, also called a box structure; the fan surfaces 2 are distributed in the circumferential direction of the intermediate body 1 to form a reflecting surface with a circular projection. The intermediate body and each sector 2 can be integrally formed by casting.

The embodiment provides a reflecting surface structure with 8 sectors 2, and the number of the specific sectors 2 can be adjusted according to requirements. Each sector 2 is connected with the intermediate body 1 through a bolt, two adjacent sectors 2 are connected through a bolt, all the sectors 2 are installed on the intermediate body 1 to form a complete satellite antenna reflection surface, the front surface of each sector 2 is a smooth arc-shaped surface (shown in figure 1), and the rear surface of each sector 2 is a supporting structure (shown in figure 2).

As shown in fig. 4, the whole intermediate body 1 is a box structure formed by sleeving three concentric cylinders 101, and the three cylinders 101 are connected by intermediate reinforcing ribs 102 distributed in a fan shape. Among the three cylinders 101, the diameter difference between two adjacent cylinders 101 is the same, the heights of the three cylinders 101 are the same, the middle cylinder 101 is a through hole, and the reflecting surface is arranged on one side of the other two cylinders 101.

The height of the intermediate reinforcing ribs 102 is equal to the height of the three cylinders 101. The middle body reinforcing rib 102 is provided with a first lightening hole 103.

As shown in fig. 2 and 3, the support structure of the rear surfaces of the eight sectors 2 comprises radial ribs 201, axial ribs 202 and square ribs 203. The radial reinforcing ribs 201 arranged on the rear surface of each sector 2 are the same, taking one sector 2 as an example, as shown in fig. 2 and 3, the area a is an area of the sector 2, as shown in fig. 5, five radial reinforcing ribs 201 are arranged on the rear surface of the sector 2, as shown in fig. 5, the radial reinforcing ribs 201 are uniformly distributed in the sector 2, and the radial reinforcing ribs 201 run along the radial direction of the sector. Wherein, two radial reinforcing ribs 201 at the edge are shared with two adjacent sectors 2, so as to play a role in connecting the adjacent sectors 2; the two radial reinforcing ribs 201 at the edge and the middle radial reinforcing rib 201 are in the same direction with the three adjacent middle reinforcing ribs 102 at corresponding positions on the middle body 1. The radial reinforcing ribs 201 are thin-walled structures with gradually-changed heights, the root part connected with the intermediate body 1 is the highest, the tip part at the outer edge part of the sector 2 is the lowest, the root part is connected with the top end of the tip part in a straight mode, and the bottoms of the radial reinforcing ribs 201 are in contact with the rear surface of the sector 2 to form the radial reinforcing ribs 201 similar to trapezoids.

The radial reinforcing rib 201 is provided with a second lightening hole 204.

Further preferably, the second lightening holes 204 are distributed on the radial reinforcing rib 201 between the square reinforcing rib 203 and the middle body 1.

Three of the axial reinforcing ribs 202 are formed, and three concentric cylindrical shapes coaxial with the intermediate body 1 are formed at the rear part of the whole satellite antenna reflection surface, and the top view is three concentric circles, as shown in fig. 2. The heights of the three axial reinforcing ribs 202 are the same as the heights of the positions of the crossed radial reinforcing ribs 201, and the positions of the three axial reinforcing ribs 202 are calculated according to an actual stress model.

The number of the square reinforcing ribs 203 is two, the two square reinforcing ribs 203 with square openings have eight vertexes, and the eight vertexes are respectively positioned at the outer edge vertexes of each sector 2, the bottom surfaces of the square reinforcing ribs 203 are in contact with the rear surfaces of the sectors 2, the tops of the square reinforcing ribs are straight, and the heights of the square reinforcing ribs are the same as the heights of the positions of the crossed radial reinforcing ribs 201, so that the thin-wall square reinforcing rib 203 structure with variable heights is formed.

In the satellite antenna reflecting surface provided by the embodiment of the invention, the supporting structure of each sector 2 and the rear surface thereof is a casting single body, and the total number of the casting single bodies is 8, and the radial dimension of each casting single body in the radius direction is controlled within 1.5 m, so that the casting is convenient. The casting monomer is suitable for a satellite antenna of 2-7 meters.

As shown in fig. 2, the radial reinforcing ribs and the axial reinforcing ribs on the back surface of the sector 2 form a "well" type reinforcing structure, the sector 2 is divided into a plurality of micro units, the embodiment provides 16 micro units, the structural design of each micro unit is controlled in a box body of 250mm × 250mm, and the thickness of the box body is set according to the strength requirement. Therefore, the whole combination of all the fan surfaces 2 is also of a box structure, and the structure ensures that the wall thickness of the antenna reflecting surface is 3-5 mm.

The well-type reinforcing structure can prevent the sector from being machined and deformed after casting and molding, and the whole assembled antenna reflecting surface is more favorable for transportation and has good shock absorption. The magnesium alloy antenna reflecting surface with the thin-wall structure has high profile precision and good stability. The integrated design is easier to adopt casting molding, the manufacturing period is short, and the mass production is facilitated.