Rapid alignment device and method for missile-borne antenna far-field phasing

Abstract

The present disclosure relates to a kind of quick alignment device and method for missile-borne antenna far field matching, the device includes: first support, second support;First fine adjustment mechanism and second fine adjustment mechanism;First rotating mechanism includes: first fixed plate, first rotating bearing, first limit structure and rotating shaft;Second rotating mechanism includes: second fixed plate, second rotating bearing and second limit structure.This application adapts to the far field matching of multiple small missile-borne antennas, does not depend on specialized test darkroom place, reduces cost;Can quickly, efficiently realize the alignment work of missile-borne antenna and horn antenna;While it can also reduce the matching error caused by antenna turning, avoid secondary disassembly.

Description

Technical Field

[0001] The embodiments of the present disclosure relate to the field of antenna alignment technology, and more particularly to a rapid alignment device and method for far-field phase matching of missile-borne antennas. Background Art

[0002] Missile-borne antennas are an indispensable part of guided weapons. With the increasing precision and intelligence of combat, the demand for missile-borne antennas in all aspects is gradually increasing.

[0003] Currently, mass-produced missile-borne antennas often utilize small, customized darkrooms (boxes) for far-field phase matching. However, for experimental antennas or small batches of antennas, customized darkrooms are relatively expensive and lack universality. Due to the high-frequency nature of missile-borne antennas, far-field phase matching requires very high accuracy. The coaxiality between the antenna and the horn significantly impacts the matching results. Simple phase matching methods, however, struggle to ensure accurate phase matching for high-frequency antennas due to the long alignment time and significant external interference, making it difficult to meet the matching requirements.

[0004] Therefore, it is necessary to improve one or more problems existing in the above-mentioned related technical solutions.

[0005] It should be noted that this section is intended to provide background or context for the technical solutions of the present disclosure stated in the claims. The description herein is not admitted to be prior art by virtue of being included in this section. Summary of the Invention

[0006] The purpose of the embodiments of the present disclosure is to provide a rapid alignment device and method for far-field phase matching of missile-borne antennas, thereby overcoming one or more problems caused by the limitations and defects of related technologies to at least a certain extent.

[0007] The present disclosure first provides a rapid alignment device for missile-borne antenna far-field phase matching, comprising:

[0008] a first bracket and a second bracket, wherein the first bracket and the second bracket are arranged facing each other;

[0009] a first fine-adjustment mechanism and a second fine-adjustment mechanism, wherein the first fine-adjustment mechanism is disposed on the first bracket, and the second fine-adjustment mechanism is disposed on the second bracket;

[0010] a turntable, the turntable being arranged on the second fine-tuning mechanism;

[0011] a first rotating mechanism and a second rotating mechanism, wherein the first rotating mechanism and the second rotating mechanism are both arranged vertically, the first rotating mechanism is arranged on the first fine-tuning mechanism, and the second rotating mechanism is arranged on the turntable, and the turntable is used to adjust the rotation angle of the second rotating mechanism;

[0012] The first rotating mechanism includes: a first fixed plate, a first rotating bearing, a first limiting structure and a rotating shaft; the first fixed plate is provided with two first limiting blocks, a first through hole and three targets, the two first limiting blocks are on the same horizontal line, the three targets are all set on the surface of the first fixed plate, and the three targets are not set collinearly; the outer ring of the first rotating bearing is fixedly set at the first through hole, the first limiting structure is provided with a second through hole and a first protrusion, the rotating shaft passes through the second through hole and is fixedly connected to the inner ring of the first rotating bearing, the first limiting structure is fixedly connected to the rotating shaft, and the first limiting block is used to limit the first protrusion; the end of the rotating shaft away from the first rotating bearing is provided with a mounting plate, and the mounting plate is used to install a horn antenna; the first fixed plate and the first limiting structure are both provided with pin holes, and the pin holes are used to penetrate positioning pins;

[0013] The second rotating mechanism includes: a second fixed plate, a second rotating bearing and a second limiting structure; two second limiting blocks, a third through hole and three groups of light beam emitting devices are provided on the second fixed plate, the two second limiting blocks are on the same horizontal line, the three groups of light beam emitting devices are arranged in a one-to-one correspondence with the three targets, and each group of light beam emitting devices includes at least two light beam emitting devices; the outer ring of the second rotating bearing is fixedly provided at the third through hole, the inner ring of the second rotating bearing is fixedly connected to the second limiting structure, the second limiting structure is provided with a second protrusion, and the second limiting block is used to limit the second protrusion; the end of the second limiting structure away from the second rotating bearing is used to install a missile-borne antenna; pin holes are provided on the second fixed plate and the second limiting structure, and the pin holes are used to penetrate positioning pins.

[0014] In one embodiment of the present disclosure, the first fine-adjustment mechanism and the second fine-adjustment mechanism are respectively connected to the first bracket and the second bracket through a plurality of threaded rods, and the height and level of the first fine-adjustment mechanism and the second fine-adjustment mechanism are adjusted by rotating the plurality of threaded rods.

[0015] In one embodiment of the present disclosure, a heat dissipation mechanism is provided on the turntable.

[0016] In one embodiment of the present disclosure, the pin hole on the first limiting structure is provided on the first protrusion, and the pin hole on the second limiting structure is provided on the second protrusion.

[0017] In one embodiment of the present disclosure, the light beam emitting device is a laser light source.

[0018] In one embodiment of the present disclosure, each group of light beam emitting devices is installed with two laser light sources, and the angle between the light beam emitting directions of the two laser light sources is an acute angle.

[0019] In one embodiment of the present disclosure, the target is a cross target.

[0020] The present disclosure also provides a method for rapid alignment of missile-borne antennas in the far field, wherein the alignment device described in any one of the above items is used to align a horn antenna with the missile-borne antenna. The method includes:

[0021] Coarsely adjust the first fine-adjustment mechanism to a horizontal level, and fine-adjust the second fine-adjustment mechanism to a horizontal level;

[0022] Using positioning pins to fix the missile-borne antenna and the horn antenna in their respective first positions;

[0023] Determining the angle formed by the emission directions of the light beams in each group of the light beam emitting devices based on the high frequency requirements of the missile-borne antenna and the distance between the missile-borne antenna and the horn antenna, turning on the first group of the light beam emitting devices so that the emission directions of the light beams in the group are adjusted according to the angle, and the light beams in the group intersect at a first point;

[0024] adjusting the position of the horn antenna so that the first point is located at the first target of the first fixing plate;

[0025] Turning on the second group of light beam emitting devices to adjust the emission directions of the light beams in the group according to the included angle and to make the light beams in the group intersect at a second point; adjusting the position of the horn antenna so that the second point is located at the second target of the first fixing plate;

[0026] Turning on the third group of light beam emitting devices to adjust the emission directions of the light beams in the group according to the included angle and to make the light beams in the group intersect at a third point; adjusting the position of the horn antenna so that the third point is located at the third target of the first fixing plate;

[0027] Fine-tune the first fine-tuning mechanism so that the first point, the second point, and the third point coincide with the centers of the first target, the second target, and the third target, respectively, so that the axes of the missile-borne antenna and the horn antenna are aligned.

[0028] In one embodiment of the present disclosure, the method further includes:

[0029] Fixing the missile-borne antenna and the horn antenna at their respective second positions, wherein the second position is the position of the two antennas after rotating the missile-borne antenna and the horn antenna by 90°;

[0030] The missile-borne antenna and the horn antenna are matched.

[0031] In one embodiment of the present disclosure, when in the second position, the missile-borne antenna and the horn antenna are in their respective H-planes or E-planes.

[0032] The technical solutions provided by the embodiments of the present disclosure may have the following beneficial effects:

[0033] The rapid alignment device and method for far-field phase matching of missile-borne antennas disclosed in the embodiments of the present invention utilizes the cooperation of a first fixing plate and a first limiting structure to enable the horn antenna to rotate in the vertical direction, and utilizes the cooperation of a second fixing plate and a second limiting structure to enable the missile-borne antenna to rotate in the vertical direction. Alignment of the two antennas is then accomplished using the correspondence between the light beam emitting device and the target; phase matching can also be performed by rotating the two antennas. This application is suitable for far-field phase matching of various small missile-borne antennas, does not rely on specialized test chambers, and reduces costs. It can quickly and efficiently achieve alignment between the missile-borne antenna and the horn antenna. It can also reduce phase matching errors caused by flipping the antenna, avoiding secondary disassembly and assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The accompanying drawings are incorporated into and constitute a part of the specification, illustrate embodiments consistent with the present disclosure, and together with the specification, are used to explain the principles of the present disclosure. Obviously, the drawings described below are only some embodiments of the present disclosure, and those skilled in the art can derive other drawings based on these drawings without inventive effort.

[0035] Figure 1 A schematic diagram showing the overall structure of a rapid alignment device for missile-borne antenna far-field phase matching in an exemplary embodiment of the present disclosure is shown;

[0036] Figure 2 A schematic structural diagram of a horn antenna end in an exemplary embodiment of the present disclosure is shown;

[0037] Figure 3 A schematic diagram showing an exploded structure of a horn antenna end in an exemplary embodiment of the present disclosure is shown;

[0038] Figure 4 A schematic structural diagram of a missile-borne antenna terminal in an exemplary embodiment of the present disclosure is shown;

[0039] Figure 5 A schematic diagram showing the explosion structure of a missile-borne antenna end in an exemplary embodiment of the present disclosure is shown;

[0040] Figure 6 A schematic diagram of the optical path structure between two antennas in an exemplary embodiment of the present disclosure is shown.

[0041] Reference numerals:

[0042] 10. Horn antenna; 20. Missile-borne antenna;

[0043] 100, first bracket; 200, second bracket; 300, first fine-tuning mechanism; 400, second fine-tuning mechanism; 500, turntable; 501, heat dissipation mechanism;

[0044] 600, first rotating mechanism; 601, first fixing plate; 6011, first limiting block; 6012, first through hole; 6013, target; 602, first rotating bearing; 603, first limiting structure; 6031, second through hole; 6032, first protrusion; 604, rotating shaft; 605, mounting plate;

[0045] 700, second rotating mechanism; 701, second fixing plate; 7011, second limiting block; 7012, third through hole; 7013, light beam emitting device; 702, second rotating bearing; 703, second limiting structure; 7031, second protrusion;

[0046] 800, pin hole; 801, positioning pin;

[0047] 900, threaded rod. DETAILED DESCRIPTION

[0048] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete and will fully convey the concepts of the example embodiments to those skilled in the art. The described features, mechanisms, or characteristics may be combined in any suitable manner in one or more embodiments.

[0049] In addition, the accompanying drawings are merely schematic illustrations of embodiments of the present disclosure and are not necessarily drawn to scale. Like reference numerals in the figures represent like or similar parts, and thus repeated descriptions thereof will be omitted. Some of the blocks shown in the accompanying drawings are functional entities and do not necessarily correspond to physically or logically separate entities.

[0050] In this exemplary embodiment, a rapid alignment device for far-field phase matching of a missile-borne antenna 20 is first provided. Figures 1 to 6 , including: a first bracket 100 and a second bracket 200, a first fine-tuning mechanism 300 and a second fine-tuning mechanism 400, a turntable 500, a first rotating mechanism 600 and a second rotating mechanism 700.

[0051] Specifically, the first bracket 100 and the second bracket 200 are arranged facing each other, and the first bracket 100 and the second bracket 200 are respectively used to carry other components, and the first bracket 100 and the second bracket 200 are at the same height and can be moved horizontally to adjust the distance between the horn antenna 10 and the missile-borne antenna 20. Figure 2 and Figure 4 The first bracket 100 and the second bracket 200 are respectively provided with a first fine-tuning mechanism 300 and a second fine-tuning mechanism 400, which are used to adjust the horizontality and height of their respective antennas. The second fine-tuning mechanism 400 is provided with a turntable 500 for adjusting the angle of the second rotating mechanism 700 and the missile-borne antenna 20.

[0052] The first rotating mechanism 600 and the second rotating mechanism 700 are both vertically arranged. The first rotating mechanism 600 is arranged on the first fine-tuning mechanism 300 , and the second rotating mechanism 700 is arranged on the turntable 500 .

[0053] The specific structures of the first rotating mechanism 600 and the second rotating mechanism 700 are described below.

[0054] Please refer to Figure 2 and Figure 3 The first rotating mechanism 600 includes: a first fixed plate 601, a first rotating bearing 602, a first limiting structure 603 and a rotating shaft 604.

[0055] The first fixing plate 601 is provided with two first stoppers 6011, a first through-hole 6012, and three targets 6013. The two first stoppers 6011 are located on the same horizontal line and are used to define the position of the horn antenna 10. The three targets 6013 are disposed on the surface of the first fixing plate 601, and the three targets 6013 are not collinearly arranged. For example, the line connecting the three targets 6013 can form an equilateral triangle, but this is not limited to this.

[0056] In order to rotate the horn antenna 10 vertically, the following settings are performed:

[0057] The outer ring of the first rotating bearing 602 is fixedly mounted on the first through-hole 6012. The first retaining structure 603 is provided with a second through-hole 6031 and a first protrusion 6032. The rotating shaft 604 passes through the second through-hole 6031 and is fixedly connected to the inner ring of the first rotating bearing 602. The first retaining structure 603 is fixedly connected to the rotating shaft 604. The first retaining block 6011 is used to limit the position of the first protrusion 6032. The end of the rotating shaft 604 away from the first rotating bearing 602 is provided with a mounting plate 605 for mounting the horn antenna 10. The specific structure of the mounting plate 605 is not limited herein.

[0058] The first fixing plate 601 and the first limiting structure 603 are both provided with a pin hole 800 for inserting a positioning pin 801. Once the positioning pin 801 is inserted into the pin hole 800, the first fixing plate 601 and the first limiting structure 603 cannot rotate, thereby preventing the position of the horn antenna 10 from changing.

[0059] It can be understood from the above embodiments that the process of the horn antenna 10 rotating vertically is as follows:

[0060] Rotate the first limiting structure 603 (or directly rotate the mounting plate 605). Since the first limiting structure 603 is fixedly connected to the inner ring of the first rotating bearing 602 via the rotating shaft 604, the horn antenna 10 is fixedly connected relative to the first limiting structure 603. Therefore, the first limiting structure 603 drives the horn antenna 10 to rotate. When the first limiting structure 603 rotates, the first protrusion 6032 on it is blocked by the first limiting block 6011. At this point, the horn antenna 10 is in the first position. Then, insert the positioning pin 801 into the pin hole 800 to fix the position of the horn antenna 10. After removing the positioning pin 801, the position of the horn antenna 10 can be further adjusted, rotating 90° clockwise or counterclockwise.

[0061] In order to rotate the missile-borne antenna 20 vertically, the following settings are performed:

[0062] Please refer to Figure 4 and Figure 5 The second rotating mechanism 700 includes: a second fixing plate 701 , a second rotating bearing 702 and a second limiting structure 703 .

[0063] The second fixing plate 701 is provided with two second limiting blocks 7011, a third through hole 7012 and three groups of light beam emitting devices 7013. The two second limiting blocks 7011 are on the same horizontal line and are used to limit the position of the missile-borne antenna 20.

[0064] Three groups of beam emitting devices 7013 are arranged in a one-to-one correspondence with the three targets 6013, and each group of beam emitting devices 7013 includes at least two beam emitting devices 7013. The outer ring of the second rotating bearing 702 is fixedly mounted on the third through hole 7012, and the inner ring of the second rotating bearing 702 is fixedly connected to the second limiting structure 703. The second limiting structure 703 is provided with a second protrusion 7031, and the second limiting block 7011 is used to limit the second protrusion 7031. The end of the second limiting structure 703 away from the second rotating bearing 702 is used to mount the missile-borne antenna 20. The second fixing plate 701 and the second limiting structure 703 are both provided with a pin hole 800, which is used to penetrate the positioning pin 801.

[0065] By rotating the second stopper structure 703, the missile-borne antenna 20 rotates. When the second stopper 7011 is reached, the positioning pin 801 is inserted into the pin hole 800, positioning the missile-borne antenna 20 in the first position. After removing the positioning pin 801, the missile-borne antenna 20 can be rotated 90° clockwise or counterclockwise, and the positioning pin 801 is still used for positioning after the rotation.

[0066] In this embodiment, the horn antenna 10 can be rotated vertically by cooperating with the first fixing plate 601 and the first limiting structure 603, and the missile-borne antenna 20 can be rotated vertically by cooperating with the second fixing plate 701 and the second limiting structure 703. The two antennas are then aligned using the correspondence between the beam emitting device 7013 and the target 6013. Phase matching can also be performed by rotating the two antennas. This application is suitable for far-field phase matching of various small missile-borne antennas 20, does not rely on specialized test chambers, and reduces costs. It can quickly and efficiently achieve alignment between the missile-borne antenna 20 and the horn antenna 10. It can also reduce phase matching errors caused by flipping the antenna, avoiding secondary disassembly and assembly.

[0067] Based on the above embodiments, the fine-tuning process of the fine-tuning mechanism of the present application is described.

[0068] The first fine-tuning mechanism 300 and the second fine-tuning mechanism 400 are connected to the first bracket 100 and the second bracket 200 respectively via a plurality of threaded rods 900. The height and level of the first fine-tuning mechanism 300 and the second fine-tuning mechanism 400 can be adjusted by rotating the threaded rods 900. The threaded rods 900 can be fine-threaded to improve the adjustment accuracy.

[0069] Optionally, in some embodiments, the pin hole 800 on the first retaining structure 603 is disposed on the first protrusion 6032, and the pin hole 800 on the second retaining structure 703 is disposed on the second protrusion 7031. By inserting the positioning pin 801 through the pin hole 800, the antenna is positioned, preventing antenna deflection. The first protrusion 6032 and the second protrusion 7031 can be arc-shaped, for example, with a central angle of 90°, or any other shape, without limitation.

[0070] Typically, the beam emitting device 7013 is a laser light source. Laser beams have good directionality and high brightness, making them suitable for calibration. Furthermore, each set of beam emitting devices 7013 is equipped with two laser light sources. The angle α between the beam emission directions of the two laser light sources is acute, allowing the two laser beams to overlap. It should be noted that this angle is determined by the distance between the horn antenna 10 and the missile-borne antenna 20.

[0071] In addition, please refer to Figure 4The turntable 500 is provided with a heat dissipation mechanism 501 , which can be a heat dissipation module composed of a fan, for cooling the missile-borne antenna 20 .

[0072] This embodiment further provides a rapid alignment method for far-field phase matching of a missile-borne antenna 20. The alignment of the horn antenna 10 and the missile-borne antenna 20 is performed using any of the above-mentioned alignment devices. The method specifically includes the following steps:

[0073] S101: Coarsely adjust the first fine-adjustment mechanism 300 to a horizontal position, and fine-adjust the second fine-adjustment mechanism 400 to a horizontal position. Specifically, the adjustment can be performed by utilizing the height of the threaded rod 900 on each fine-adjustment mechanism.

[0074] S102: Fix the missile-borne antenna 20 and the horn antenna 10 at their respective first positions using the positioning pins 801. When the antennas are at the first positions, they are located on a working surface that needs to be aligned.

[0075] S103: Based on the high frequency requirements of the missile-borne antenna 20 and the distance between the missile-borne antenna 20 and the horn antenna 10, the angle formed by the emission directions of the light beams in each group of light beam emitting devices 7013 is determined. The first group of light beam emitting devices 7013 is turned on, and the emission directions of the light beams in the group are adjusted according to the angle, so that the light beams in the group intersect at the first point.

[0076] S104 , adjusting the position of the horn antenna 10 so that the first point is located at the first target 6013 of the first fixing plate 601 . That is, by adjusting the position of the horn antenna 10 , the intersection point of each light beam of the first group is located at the target 6013 .

[0077] S105, turn on the second group of light beam emitting devices 7013, adjust the emission direction of each light beam in the group according to the included angle, and make the light beams in the group intersect at the second point; adjust the position of the horn antenna 10 so that the second point is located at the second target 6013 of the first fixed plate 601.

[0078] S106, turn on the third group of light beam emitting devices 7013, adjust the emission direction of each light beam in the group according to the included angle, and make the light beams in the group intersect at the third point; adjust the position of the horn antenna 10 so that the third point is located at the third target 6013 of the first fixed plate 601.

[0079] S107, fine-tune the first fine-tuning mechanism 300 so that the first point, the second point and the third point coincide with the centers of the first target 6013, the second target 6013 and the third target 6013 respectively, so that the axes of the missile-borne antenna 20 and the horn antenna 10 are aligned.

[0080] In this embodiment, a fine-tuning mechanism is used to keep the antenna horizontal, the intersection of the light beams emitted by the light beam emitting device 7013 is aligned one by one with the three targets 6013, and the principle of three points forming a plane is used to make the end face of the horn antenna 10 and the antenna array surface of the missile-borne antenna 20 parallel; the fine-tuning mechanism is used to align the height of the light beam intersection with the target 6013 to ensure the coaxiality of the two antennas.

[0081] In some embodiments, after the coaxiality adjustment is completed, the positioning pins 801 can be removed to rotate the two antennas 90° so that the two antennas are located at the second position, and the positioning pins 801 can be inserted to align the H and E surfaces of the antennas.

[0082] In this embodiment, during the phase matching process of the antenna, the antenna does not need to be disassembled a second time, which saves steps and reduces errors caused by external interference on the antenna.

[0083] To sum up, in order to solve the problem of low cost and fast alignment of the far-field phase matching of missile-borne antennas 20, this application proposes a far-field phase matching device suitable for a variety of missile-borne antennas 20. The use of light beam alignment is intuitive and convenient to improve the convenience of operation, save preliminary preparation time, and improve the phase matching efficiency. The use of a rotating mechanism avoids phase matching errors and improves the phase matching accuracy. The whole set of equipment has a simple structure, low cost, and is suitable for a wide range of occasions and is suitable for most missile-borne far-field phase matching.

[0084] This application has low cost, simple parts and small investment; it has strong compatibility, and the system can work in an existing large microwave darkroom or be used in an open area; it has a fast response speed, the missile-borne antenna 20 end is fixed, and the horn antenna 10 end is adjustable, and the three-group light beam positioning is more efficient, intuitive and faster than other measurement methods such as ranging; it has little impact on the external environment, avoids secondary disassembly and assembly, and the use of a rotating mechanism can ensure that the missile-borne antenna 20 and the horn antenna 10 are not touched, reducing errors caused by external interference.

[0085] It should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like in the above description indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present disclosure and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the embodiments of the present disclosure.

[0086] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly indicate the number of the technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the embodiments of the present disclosure, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0087] In the embodiments of the present disclosure, unless otherwise expressly specified or limited, the terms "installed," "connected," "connected," "fixed," and the like should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integration; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and they may refer to internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present disclosure based on specific circumstances.

[0088] In the embodiments of the present disclosure, unless otherwise expressly specified and limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature includes the first feature being directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0089] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" means that the specific features, mechanisms, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present disclosure. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, mechanisms, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification.

[0090] Those skilled in the art will readily appreciate other embodiments of the present disclosure after considering the specification and practicing the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the present disclosure that follow the general principles of the present disclosure and include common knowledge or customary techniques in the art not disclosed herein. The description and examples are to be considered as exemplary only, with the true scope and spirit of the present disclosure being indicated by the appended claims.

Claims

1. A rapid alignment device for missile-borne antenna far-field phase matching, characterized in that: include: a first bracket and a second bracket, wherein the first bracket and the second bracket are arranged facing each other; a first fine-adjustment mechanism and a second fine-adjustment mechanism, wherein the first fine-adjustment mechanism is disposed on the first bracket, and the second fine-adjustment mechanism is disposed on the second bracket; a turntable, the turntable being arranged on the second fine-tuning mechanism; a first rotating mechanism and a second rotating mechanism, wherein the first rotating mechanism and the second rotating mechanism are both arranged vertically, the first rotating mechanism is arranged on the first fine-tuning mechanism, and the second rotating mechanism is arranged on the turntable, and the turntable is used to adjust the rotation angle of the second rotating mechanism; The first rotating mechanism includes: a first fixed plate, a first rotating bearing, a first limiting structure and a rotating shaft; the first fixed plate is provided with two first limiting blocks, a first through hole and three targets, the two first limiting blocks are on the same horizontal line, the three targets are all set on the surface of the first fixed plate, and the three targets are not set collinearly; the outer ring of the first rotating bearing is fixedly set at the first through hole, the first limiting structure is provided with a second through hole and a first protrusion, the rotating shaft passes through the second through hole and is fixedly connected to the inner ring of the first rotating bearing, the first limiting structure is fixedly connected to the rotating shaft, and the first limiting block is used to limit the first protrusion; the end of the rotating shaft away from the first rotating bearing is provided with a mounting plate, and the mounting plate is used to install a horn antenna; the first fixed plate and the first limiting structure are both provided with pin holes, and the pin holes are used to penetrate positioning pins; The second rotating mechanism includes: a second fixed plate, a second rotating bearing and a second limiting structure; two second limiting blocks, a third through hole and three groups of light beam emitting devices are provided on the second fixed plate, the two second limiting blocks are on the same horizontal line, the three groups of light beam emitting devices are arranged in a one-to-one correspondence with the three targets, and each group of light beam emitting devices includes at least two light beam emitting devices; the outer ring of the second rotating bearing is fixedly provided at the third through hole, the inner ring of the second rotating bearing is fixedly connected to the second limiting structure, the second limiting structure is provided with a second protrusion, and the second limiting block is used to limit the second protrusion; the end of the second limiting structure away from the second rotating bearing is used to install a missile-borne antenna; pin holes are provided on the second fixed plate and the second limiting structure, and the pin holes are used to penetrate positioning pins.

2. The rapid alignment device for missile-borne antenna far-field phase matching according to claim 1, characterized in that: The first fine-adjustment mechanism and the second fine-adjustment mechanism are respectively connected to the first bracket and the second bracket through a plurality of threaded rods, and the height and level of the first fine-adjustment mechanism and the second fine-adjustment mechanism are adjusted by rotating the plurality of threaded rods.

3. The rapid alignment device for missile-borne antenna far-field phase matching according to claim 1, characterized in that: The turntable is provided with a heat dissipation mechanism.

4. The rapid alignment device for missile-borne antenna far-field phase matching according to claim 1, characterized in that: The pin hole on the first limiting structure is arranged on the first protrusion, and the pin hole on the second limiting structure is arranged on the second protrusion.

5. The rapid alignment device for missile-borne antenna far-field phase matching according to claim 1, characterized in that: The light beam emitting device is a laser light source.

6. The rapid alignment device for missile-borne antenna far-field phase matching according to claim 5, characterized in that: Each group of light beam emitting devices is equipped with two laser light sources, and the angle between the light beam emitting directions of the two laser light sources is an acute angle.

7. The rapid alignment device for missile-borne antenna far-field phase matching according to any one of claims 1 to 6, characterized in that: The target is a cross target.

8. A rapid alignment method for missile-borne antenna far-field phase matching, characterized in that: The alignment device according to any one of claims 1 to 7 is used to align a horn antenna and a missile-borne antenna, the method comprising: Coarsely adjust the first fine-adjustment mechanism to a horizontal level, and fine-adjust the second fine-adjustment mechanism to a horizontal level; Using positioning pins to fix the missile-borne antenna and the horn antenna in their respective first positions; Determining the angle formed by the emission directions of the light beams in each group of the light beam emitting devices based on the high frequency requirements of the missile-borne antenna and the distance between the missile-borne antenna and the horn antenna, turning on the first group of the light beam emitting devices so that the emission directions of the light beams in the group are adjusted according to the angle, and the light beams in the group intersect at a first point; adjusting the position of the horn antenna so that the first point is located at the first target of the first fixing plate; Turning on the second group of light beam emitting devices to adjust the emission directions of the light beams in the group according to the included angle and to make the light beams in the group intersect at a second point; adjusting the position of the horn antenna so that the second point is located at the second target of the first fixing plate; Turning on the third group of light beam emitting devices to adjust the emission directions of the light beams in the group according to the included angle and to make the light beams in the group intersect at a third point; adjusting the position of the horn antenna so that the third point is located at the third target of the first fixing plate; Fine-tune the first fine-tuning mechanism so that the first point, the second point, and the third point coincide with the centers of the first target, the second target, and the third target, respectively, so that the axes of the missile-borne antenna and the horn antenna are aligned.

9. The rapid alignment method for missile-borne antenna far-field phase matching according to claim 8, characterized in that: The method further comprises: Fixing the missile-borne antenna and the horn antenna at their respective second positions, wherein the second position is the position of the two antennas after rotating the missile-borne antenna and the horn antenna by 90°; The missile-borne antenna and the horn antenna are matched.

10. The rapid alignment method for missile-borne antenna far-field phase matching according to claim 9, characterized in that: When in the second position, the missile-borne antenna and the horn antenna are in their respective H-planes or E-planes.

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