Integrated Card-Type Satellite Laser Communication Antenna

Abstract

This utility model discloses an integrated card-type satellite laser communication antenna, comprising a primary mirror, a secondary mirror, and a secondary mirror support, all made of the same material with the same coefficient of thermal expansion. The secondary mirror support is a conical support, with its base detachably connected to the primary mirror via fasteners. An adjustment shim is provided between the primary mirror and the secondary mirror support. The apex of the conical support is nested with the secondary mirror, with the reflective surface of the secondary mirror facing the reflective surface of the primary mirror. This utility model features a compact structure, convenient installation and debugging, and high reliability. Because the primary mirror, secondary mirror, and secondary mirror support have the same coefficient of thermal expansion, it fundamentally eliminates the deformation risks caused by differences in thermal expansion between different materials in traditional antennas. Through the self-compensation effect of material thermal expansion, it eliminates the need for traditional thermal control systems while improving environmental adaptability, ensuring stable operation of the antenna in extreme temperature environments.

Description

Technical Field

[0001] This utility model relates to the field of laser communication technology, specifically to an integrated card-type satellite laser communication antenna. Background Technology

[0002] With the continuous development of modern communication technology, satellite laser communication has developed rapidly. Modern communication technology has put forward extremely stringent requirements for antenna systems. Lightweight, miniaturization, high precision, high sensitivity and high environmental adaptability have become key indicators for industry development. In particular, thermal control is also required when dealing with complex environments. Traditional parabolic antennas mainly have three major technical constraints: (1) Traditional schemes use optical glass + Invar support frame. On-orbit temperature difference leads to interface stress accumulation, resulting in surface shape error; (2) Thermal control energy consumption contradiction: In order to ensure stable performance under high and low temperature environments, thermal control modules are usually required, which increases the difficulty of the system and also increases the volume and weight; (3) Assembly accuracy decay: Multi-material assembly leads to residual stress, especially when the temperature changes, the system performance will fluctuate.

[0003] Traditional Cassegrain satellite communication antennas typically consist of multiple modules, with the optical component being particularly susceptible to the drastic temperature variations in space, requiring separate thermal control. This complex structure also makes them prone to assembly and adjustment errors. Furthermore, traditional manufacturing processes struggle to ensure the continuity of the reflector's curvature and optical quality, making them more susceptible to deformation or surface deviation in temperature-changing environments. Additionally, while some traditional antenna systems utilize lightweight materials, their overall structural rigidity is insufficient to withstand dynamic loads or deformation caused by temperature changes, severely limiting their reliability in high-dynamic, high-precision applications. Given the current industry technological demands, designing an integrated, thermally control-free Cassegrain satellite laser communication antenna is of paramount importance for technological breakthroughs. Utility Model Content

[0004] The technical problem to be solved by this utility model is to provide an integrated card-type satellite laser communication antenna that is compact, easy to install and debug, and highly adaptable to the environment, in order to overcome the shortcomings of the existing technology.

[0005] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is as follows:

[0006] An integrated card-type satellite laser communication antenna includes a primary mirror, a secondary mirror, and a secondary mirror support, all made of the same material with the same coefficient of thermal expansion. The secondary mirror support is a conical support, with the base of the conical support detachably connected to the primary mirror via fasteners. An adjustment shim is provided between the primary mirror and the secondary mirror support. The apex of the conical support is nested with the secondary mirror, and the reflecting surface of the secondary mirror faces the reflecting surface of the primary mirror.

[0007] As a further improvement of this utility model, the primary mirror, secondary mirror, and secondary mirror support are all made of aerospace-grade aluminum alloy.

[0008] As a further improvement of this utility model, the main mirror includes a reflector body and a first flexible joint; one end face of the reflector body is the main mirror reflecting surface, and the other end face of the reflector body is the back face; the first flexible joint is a circular main structure, and the reflector body is embedded in the first flexible joint; the secondary mirror bracket is detachably connected to the first flexible joint.

[0009] As a further improvement of this utility model, there is a preset gap between the outer circle of the reflector body and the inner wall of the first flexible joint, and multiple connectors are evenly distributed in the preset gap. The reflector body and the first flexible joint are connected as one unit by the connectors.

[0010] As a further improvement of this utility model, the first flexible joint is provided with a plurality of crescent grooves, and the crescent grooves correspond one-to-one with the connecting body.

[0011] As a further improvement of this utility model, a plurality of second flexible joints are evenly distributed on the outer circumference of the first flexible joint, and the second flexible joints are used to realize the installation and fixation of the satellite laser communication antenna.

[0012] As a further improvement of this utility model, the first flexible joint is also provided with a plurality of protrusions, the second flexible joint corresponds one-to-one with the protrusions, the connecting body and the protrusions are arranged alternately, and the protrusions are provided with threaded holes on both sides for connecting the secondary mirror bracket.

[0013] As a further improvement of this utility model, the secondary mirror support includes a primary mirror mounting cylinder, a secondary mirror mounting cylinder, and multiple pull rods; one end of each pull rod is connected to the primary mirror mounting cylinder, and the other end of each pull rod is connected to the secondary mirror mounting cylinder; the primary mirror mounting cylinder is detachably connected to the first flexible joint, and the secondary mirror mounting cylinder is nested with the secondary mirror.

[0014] As a further improvement of this utility model, the secondary mirror is a two-section cylindrical structure, including a large cylinder and a small cylinder. The small cylinder is nested in the secondary mirror mounting hole of the secondary mirror mounting cylinder. The end face of the large cylinder away from the small cylinder is the secondary mirror reflecting surface, and the secondary mirror reflecting surface faces the primary mirror reflecting surface of the reflector body.

[0015] As a further improvement of this utility model, the primary mirror reflecting surface of the reflector body is a concave parabolic surface, and the secondary mirror reflecting surface is a convex parabolic surface.

[0016] Compared with the prior art, the advantages of this utility model are:

[0017] This utility model's integrated card-type satellite laser communication antenna is made by using the same material and thermal expansion coefficient for the primary mirror, secondary mirror, and secondary mirror support. This ensures that the thermal expansion coefficients of the primary mirror, secondary mirror, and secondary mirror support are uniform, fundamentally eliminating the deformation risks caused by the thermal expansion differences of different materials in traditional antennas. Through the self-compensation effect of material thermal expansion, it eliminates the need for traditional thermal control systems while improving environmental adaptability, ensuring that the antenna can operate stably in extreme temperature environments. Attached Figure Description

[0018] Figure 1 This is an isometric schematic diagram of the integrated card-type satellite laser communication antenna in a specific embodiment of this utility model;

[0019] Figure 2 This is a schematic diagram of the front structure of the main mirror in a specific embodiment of this utility model;

[0020] Figure 3 This is a left view of the integrated card-type satellite laser communication antenna in a specific embodiment of this utility model;

[0021] Figure 4 for Figure 2 Schematic diagram of the structural principle of the cross-section along the AA direction;

[0022] Figure 5 This is a schematic diagram of the back structure of the primary mirror in a specific embodiment of this utility model;

[0023] Figure 6 This is a schematic diagram of the optical path test of the integrated card-type satellite laser communication antenna in a specific embodiment of this utility model;

[0024] Legend: 1. Primary mirror; 2. Secondary mirror; 3. Secondary mirror bracket; 4. Adjustment shim; 5. Fastener; 6. Plane mirror; 7. Test fixture; 8. Laser interferometer; 9. Five-dimensional adjustment stage; 11. Mirror body; 102. First flexible joint; 103. Second flexible joint; 104. Connector; 105. Preset gap; 106. Crescent groove; 21. Large cylinder; 22. Small cylinder; 23. Secondary mirror reflecting surface; 24. Stepped surface; 31. Primary mirror mounting cylinder; 32. Secondary mirror mounting cylinder; 33. Pull rod; 111. Primary mirror reflecting surface; 122. Boss; 123. Threaded hole; 131. Connecting through hole; 132. First groove; 132. Second groove; 321. Secondary mirror mounting hole; 322. Secondary mirror positioning surface. Detailed Implementation

[0025] The present invention will be further described below with reference to the accompanying drawings and specific preferred embodiments, but this does not limit the scope of protection of the present invention.

[0026] In the description of this utility model, it should be understood that the terms "side", "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0027] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "multiple" means two or more, unless otherwise explicitly specified.

[0028] Example

[0029] like Figure 1 As shown, the integrated card-type satellite laser communication antenna of this utility model includes a primary mirror 1, a secondary mirror 2, and a secondary mirror support 3 made of aerospace-grade aluminum alloy. The secondary mirror support 3 is a conical support, and the bottom of the conical support is detachably connected to the primary mirror 1 by screw fasteners 5. A fan-shaped adjustment shim 4 is provided between the primary mirror 1 and the secondary mirror support 3 to facilitate adjustment of the connection between the primary mirror 1 and the secondary mirror support 3. The top of the conical support is nested and connected to the secondary mirror 2, and the reflecting surface of the secondary mirror 2 faces the reflecting surface of the primary mirror 1.

[0030] In this embodiment, by using aerospace-grade aluminum alloy to fabricate the primary mirror 1, secondary mirror 2, and secondary mirror support 3, the thermal expansion coefficients of the primary mirror 1, secondary mirror 2, and secondary mirror support 3 are made uniform, fundamentally eliminating the deformation risks caused by the thermal expansion differences of different materials in traditional antennas. Through the self-compensation effect of material thermal expansion, the traditional thermal control system is eliminated while improving environmental adaptability, ensuring that the antenna can operate stably in extreme temperature environments.

[0031] like Figure 2 and Figure 4 As shown, the primary mirror 1 includes a reflector body 11 and a first flexible joint 102. One end face of the reflector body 11 is the primary mirror reflecting surface 111, which is designed as a concave parabolic surface. The other end face of the reflector body 11 is a flat back surface. The first flexible joint 102 is a ring-shaped main structure, and the reflector body 11 is embedded in the first flexible joint 102. The secondary mirror support 3 is detachably connected to the first flexible joint 102.

[0032] like Figure 2 As shown, there is a pre-set gap 105 of about 1 mm between the outer circle of the reflector body 11 and the inner wall of the first flexible joint 102, and three connectors 104 are evenly distributed in the pre-set gap 105. The reflector body 11 and the first flexible joint 102 are connected as a whole by the connectors 104. Furthermore, three crescent-shaped grooves 106 are evenly distributed on the first flexible joint 102, and each crescent-shaped groove 106 corresponds to one of the connectors 104. The pre-set gap 105 between the first flexible joint 102 and the reflector body 101 can reduce the installation stress of the main mirror 1, thereby reducing the impact of installation stress on the surface accuracy of the main mirror 1. At the same time, the crescent-shaped grooves 106 provided on the first flexible joint 102 can further release the installation stress.

[0033] like Figure 2 As shown, three second flexible joints 103 are evenly distributed around the outer circumference of the first flexible joint 102. The second flexible joints 103 are used to mount and fix the satellite laser communication antenna. Furthermore, each second flexible joint 103 has a connecting through-hole 131 for connecting to an external structure, and a first groove 132 and a second groove 133, each 0.5 mm wide, are provided on the front and back sides of the area between the connecting through-hole 131 and the first flexible joint 102. Since the primary mirror 1 needs to be connected to an external structure, which can easily generate stress, three second flexible joints 103 are provided on the primary mirror 1, and two grooves are provided between the connecting through-hole 131 and the first flexible joint 102 on the second flexible joint 103 to relieve stress, thus reducing the impact of external installation on the surface accuracy of the primary mirror 1.

[0034] like Figure 2 and Figure 5 As shown, the first flexible joint 102 is also evenly distributed with multiple bosses 122, and the second flexible joint 103 corresponds one-to-one with the bosses 122. The connecting body 104 and the bosses 122 are arranged alternately at a 60° angle. Threaded holes 123 are provided on both sides of the bosses 122 for connecting the secondary mirror bracket 3. The three bosses 122 provided on the surface of the primary mirror 1 can effectively reduce the mounting surface area and make it easier to ensure the accuracy of the mounting surface during precision machining.

[0035] like Figure 3 and Figure 4As shown, the secondary mirror support 3 includes a primary mirror mounting cylinder 31, a secondary mirror mounting cylinder 32, and three tie rods 33. The primary mirror mounting cylinder 31, the secondary mirror mounting cylinder 32, and the tie rods 33 are all made of high-strength aluminum alloy. The secondary mirror mounting cylinder 32 has a secondary mirror mounting hole 322 at its center, and the primary mirror mounting cylinder 31 has a through hole at its center. One end of the tie rod 33 is connected to the primary mirror mounting cylinder 31, and the other end of the tie rod 33 is connected to the secondary mirror mounting cylinder 32, together forming a conical secondary mirror support 3. The primary mirror mounting cylinder 31 is detachably connected to the first flexible joint 102, and the secondary mirror mounting cylinder 32 is nested with the secondary mirror 2. Furthermore, the end face of the primary mirror mounting cylinder 31 has three sets of evenly distributed through holes in pairs, and the two through holes in each set are respectively located on both sides of the tie rod 33, corresponding to the threaded holes 123 on both sides of the boss 122.

[0036] It is understandable that, in order to avoid the influence of stray light, all structures in the communication antenna except for the reflective surface and the mounting surface must be black anodized. However, the primary mirror 1 cannot be black anodized. Therefore, in order to eliminate the influence of the reflection from the non-reflective surface of the primary mirror 1 on the entire antenna system, the outer circle of the primary mirror mounting cylinder 31 of the secondary mirror bracket 3 and the outer circle of the first flexible joint 102 of the primary mirror 1 are set to have the same diameter to achieve the effect of blocking light.

[0037] like Figure 4 As shown, the secondary mirror 2 is a two-section cylindrical structure, comprising a large cylinder 21 and a small cylinder 22, both integrally formed. The small cylinder 22 is nested within the secondary mirror mounting hole 321 of the secondary mirror mounting cylinder 32, with a gap of approximately 0.2 mm maintained between the stepped surface 24 and the secondary mirror mounting hole 321 for adhesive injection, thus bonding and fixing the secondary mirror 2 to the secondary mirror bracket 3 for stress-free installation. The end face of the large cylinder 21 away from the small cylinder 22 is the secondary mirror reflecting surface 23, which faces the primary mirror reflecting surface 111 of the reflector body 11. The secondary mirror reflecting surface 23 is designed as a convex parabolic surface.

[0038] In this embodiment, the debugging process of the integrated card-type satellite laser communication antenna is as follows:

[0039] Step S1: First, apply silicone rubber evenly to the secondary mirror mounting hole 321 of the secondary mirror bracket 3. Then, insert one end of the small cylinder 22 of the secondary mirror 2 into the secondary mirror mounting hole 321 of the secondary mirror bracket 3. Leave a gap of about 0.2mm between the stepped surface 24 formed by the large cylinder 21 and the small cylinder 22 of the secondary mirror 2 and the secondary mirror positioning surface 322.

[0040] Step S2: After the glue has hardened, place fastener 5 as shown. Figure 3As shown, the fastener 5 is tightened with a torque wrench by passing through the threaded holes 123 of the main mirror mounting cylinder 31, the adjusting shim 4 and the first flexible joint 12 from left to right. At this time, the main mirror 1 is also fixed on the secondary mirror bracket 3.

[0041] Step S3, as follows Figure 6 As shown, align the plane mirror 6 with the laser interferometer 8 and adjust the interference fringes to zero; then install the communication antenna onto the test fixture 7 through the pre-reserved connection through hole 131 on the main mirror 1 to form a test assembly. At this time, the test optical route consists of the plane mirror 6, the laser interferometer 8 and the test assembly.

[0042] Step S4: Adjust the position of the entire test system using the five-dimensional adjustment stage 9, align the communication antenna with the test optical path, observe the interference fringes in the interferometer measurement software, acquire images, analyze the image data to adjust the grinding amount of the shim 4, remove the adjustment shim 4 for grinding, and after the grinding is completed, integrate the entire device and place it in the test optical path for testing. Repeat the iteration until the data meets the requirements.

[0043] The above description is merely a preferred embodiment of this utility model. The protection scope of this utility model is not limited to the above embodiments. All technical solutions falling within the scope of this utility model's concept are protected by this utility model. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principle of this utility model should also be considered within the protection scope of this utility model.

Claims

1. An integrated card satellite laser communication antenna, characterized by, It includes a primary mirror (1), a secondary mirror (2), and a secondary mirror support (3) made of the same material and the same coefficient of thermal expansion. The secondary mirror support (3) is a conical support. The bottom of the conical support is detachably connected to the primary mirror (1) by fasteners (5). An adjustment shim (4) is provided between the primary mirror (1) and the secondary mirror support (3). The top of the conical support is nested with the secondary mirror (2), and the reflecting surface of the secondary mirror (2) faces the reflecting surface of the primary mirror (1).

2. The integrated card satellite laser communication antenna according to claim 1, wherein, The primary mirror (1), secondary mirror (2) and secondary mirror support (3) are all made of aerospace-grade aluminum alloy.

3. The integrated card satellite laser communication antenna according to claim 1, wherein, The primary mirror (1) includes a reflector body (11) and a first flexible joint (102); one end face of the reflector body (11) is the primary mirror reflector surface (111), and the other end face of the reflector body (11) is the back face; the first flexible joint (102) is a circular main structure, and the reflector body (11) is embedded in the first flexible joint (102); the secondary mirror support (3) is detachably connected to the first flexible joint (102).

4. The integrated card satellite laser communication antenna according to claim 3, wherein, There is a preset gap (105) between the outer circle of the reflector body (11) and the inner wall of the first flexible joint (102), and multiple connectors (104) are evenly distributed in the preset gap (105). The reflector body (11) and the first flexible joint (102) are connected as one unit through the connectors (104).

5. The integrated card satellite laser communication antenna according to claim 4, wherein, The first flexible joint (102) has multiple crescent-shaped grooves (106) evenly distributed on it, and each crescent-shaped groove (106) corresponds to a connector (104).

6. The integrated card satellite laser communication antenna according to claim 4, wherein, The outer circumference of the first flexible joint (102) is evenly distributed with a plurality of second flexible joints (103), which are used to realize the installation and fixation of the satellite laser communication antenna.

7. The integrated card satellite laser communication antenna according to claim 6, wherein, The first flexible joint (102) is also evenly distributed with multiple bosses (122), the second flexible joint (103) corresponds one-to-one with the bosses (122), the connecting body (104) is arranged alternately with the bosses (122), and the bosses (122) are provided with threaded holes (123) on both sides for connecting the secondary mirror bracket (3).

8. The integrated card satellite laser communication antenna according to any one of claims 3 to 7, characterized in that, The secondary mirror support (3) includes a primary mirror mounting cylinder (31), a secondary mirror mounting cylinder (32), and multiple pull rods (33); one end of the pull rod (33) is connected to the primary mirror mounting cylinder (31), and the other end of the pull rod (33) is connected to the secondary mirror mounting cylinder (32); the primary mirror mounting cylinder (31) is detachably connected to the first flexible joint (102), and the secondary mirror mounting cylinder (32) is nested with the secondary mirror (2).

9. The integrated card satellite laser communication antenna according to claim 8, wherein, The secondary mirror (2) is a two-section cylindrical structure, including a large cylinder (21) and a small cylinder (22). The small cylinder (22) is nested in the secondary mirror mounting hole (321) of the secondary mirror mounting cylinder (32). The end face of the large cylinder (21) away from the small cylinder (22) is the secondary mirror reflecting surface (23). The secondary mirror reflecting surface (23) faces the primary mirror reflecting surface (111) of the reflector body (11).

10. The integrated card satellite laser communication antenna according to claim 9, wherein, The primary mirror reflecting surface (111) of the reflector body (11) is a concave parabolic surface, and the secondary mirror reflecting surface (23) is a convex parabolic surface.

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