Small-eccentricity radar antenna array plane pitching mechanism and eccentricity optimization method thereof

Abstract

The invention discloses a small-eccentricity radar antenna array plane pitching mechanism and an eccentricity optimization method thereof, belongs to the technical field of radar equipment, and solves the problem that the existing pitching mechanism has contradiction between storage height and motion stability and is difficult to reduce eccentric torque. The device comprises a crank sliding block assembly and a driving assembly, the crank sliding block assembly takes a connecting line between two second hinge shafts of a radar antenna array plane as a crank, a pulling and pressing rod assembly as a connecting rod and a sliding guide rod and a sliding assembly as sliding blocks, and the driving assembly provides power through lead screw transmission. Through an eccentric optimization method, related parameters are defined, a gravity center offset calculation formula is deduced, and a mechanism parameter combination is optimized with the purpose of minimizing mass center offset in the pitching process. According to the invention, the complete lodging of the radar antenna array surface is realized, and the mass center offset is effectively controlled while the storage height is reduced.

Description

Technical Field

[0001] This invention belongs to the field of radar equipment technology, and particularly relates to a small-eccentric radar antenna array elevation mechanism and its eccentricity optimization method. Background Technology

[0002] As indispensable electronic equipment in modern warfare, the performance and mobility of radar or antenna arrays directly affect their operational effectiveness. With the increasing demands for mobility in modern applications, various radar products typically require servo motion systems to achieve functions such as azimuth rotation and elevation, meeting operational and transportation requirements. Currently, azimuth rotation is mostly achieved through vertical azimuth turntables, while elevation is often achieved using U-shaped frame-supported elevation turntables, or through electric cylinder-driven crank-rocker mechanisms, four-bar linkages, etc. However, because radar antenna arrays are usually large, U-shaped frame-supported elevation turntables are quite tall when folded, making it difficult to meet space constraints during transportation and limiting their applicability on mobile platforms.

[0003] On the other hand, while crank-rocker mechanisms or four-bar linkages using electric cylinders can reduce the retracted height, the antenna array's center of mass will shift significantly during the entire process from the retracted to the deployed state. This shift will cause a large eccentric moment during the pitch motion of the entire device, placing higher demands on the stress performance of the support structure and mounting platform (such as the lifting mast or high-speed azimuth turntable). Especially under high-speed motion or complex operating conditions, the eccentric force or centrifugal force will increase significantly, potentially leading to equipment instability or even malfunction, severely restricting the application of radar systems on highly mobile platforms.

[0004] In summary, existing radar antenna array elevation mechanisms present a contradiction between structural compactness and motion stability. There is an urgent need for a new type of elevation mechanism that can effectively control the center of gravity shift and reduce the eccentric moment while meeting transportation size constraints, so as to improve the adaptability and reliability of radar systems on mobile platforms. Summary of the Invention

[0005] Based on the above analysis, the present invention aims to provide a radar antenna array elevation mechanism with small eccentricity and its eccentricity optimization method to solve the problem of the contradiction between the storage height and motion stability of the existing elevation mechanism and the difficulty in reducing the eccentric torque.

[0006] The objective of this invention is mainly achieved through the following technical solutions:

[0007] A small-eccentric radar antenna array elevation mechanism includes a crank-slider assembly and a drive assembly. The crank-slider assembly is used to realize the elevation action and control the center of mass offset, and the drive assembly is used to provide power to the radar antenna array elevation mechanism.

[0008] The crank-slider assembly includes a first hinge shaft, a tension / compression rod assembly, a radar antenna array, a second hinge shaft, a sliding guide rod, a third hinge shaft, and a sliding assembly;

[0009] The drive assembly includes a drive motor, a reducer, and a lead screw.

[0010] Furthermore, the tension / compression rod assembly includes a connecting rod, a first hinge bearing seat, and a second hinge bearing seat; the connecting rod has threads with opposite directions of rotation at both ends.

[0011] Furthermore, the tension / compression rod assembly also includes a first hinge bearing and a second hinge bearing; the first hinge bearing is installed in the first hinge bearing housing, and the second hinge bearing is installed in the second hinge bearing housing.

[0012] Furthermore, the sliding assembly includes a first sliding bearing seat, a synchronous connecting rod, a lead screw nut, a second sliding bearing seat, and a sliding bearing.

[0013] Furthermore, the lead screw and the lead screw nut in the sliding assembly form a helical pair.

[0014] Furthermore, the radar antenna array includes a structural frame and two bottom hinge seats located at its bottom.

[0015] Furthermore, it also includes an auxiliary structure, which includes a cable chain and an angle measuring device located at the third hinge axis.

[0016] Furthermore, the auxiliary structure also includes a mechanical limiting component disposed at the end of the sliding guide rod.

[0017] Furthermore, the crank-slider assembly uses the line connecting the two second hinge axes as the crank, the tension rod assembly as the connecting rod, and the sliding guide rod and the sliding assembly as the slider.

[0018] Furthermore, an eccentricity optimization method is also provided, employing the aforementioned small-eccentric radar antenna array elevation mechanism, comprising the following steps:

[0019] S1: Define the eccentricity optimization parameters;

[0020] S2: Derive the formula for calculating the center of gravity offset;

[0021] S3: Determine the optimization objective and parameters;

[0022] S4: Solve for the optimal parameter combination.

[0023] Furthermore, the radar antenna array elevation mechanism also includes an elevation base, a U-shaped frame support hinge seat, and a first drive component mounting seat.

[0024] Furthermore, the elevation base serves as the basic mounting platform for the radar antenna array elevation mechanism; the U-shaped frame support hinge seat is fixedly installed on the elevation base and is rotatably connected to the tension / compression rod assembly through the first hinge shaft; the first drive assembly mounting seat is fixedly installed on the elevation base, and the first drive assembly is used to support and fix the drive assembly.

[0025] Furthermore, the connecting rod has threads with opposite directions of rotation at both ends.

[0026] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0027] (1) This invention utilizes an optimized crank-slider mechanism, where the line connecting the hinge axes on the two sides of the radar antenna array serves as the crank, the tension / compression rod assembly as the connecting rod, and the sliding guide rod and sliding assembly as the slider. This design effectively controls the center of gravity shift during pitch motion. This not only reduces the overall height in the stowed state, meeting the space constraints of mobile platform transportation, but also reduces eccentric torque through geometric optimization, thereby lessening the load requirements on the support structure and installation platform and improving the radar system's adaptability under complex operating conditions.

[0028] (2) This invention adopts an adjustable structure of tension-compression rod assembly. The two ends of the connecting rod are provided with threads of opposite directions, which, together with the locking nut, enable precise adjustment and fixation of the hinge spacing, ensuring the stability of the mechanism during debugging, transportation and operation. This design allows for flexible adjustment of parameters according to actual needs, avoiding performance degradation caused by loose parts, while enabling the mechanism to adapt to antenna arrays of different sizes and weights, enhancing versatility and ease of maintenance.

[0029] (3) This invention utilizes an eccentric optimization method to minimize the center of gravity offset, optimizing key parameters such as the distance between the first and second hinges to achieve a small eccentric design while meeting constraints. Through geometric analysis and iterative verification, this method ensures that the change in the center of gravity is minimized throughout the pitch process, thereby significantly reducing the impact of eccentric or centrifugal forces on the system. This improves the stability and reliability of the radar antenna array during high-speed motion, providing an effective solution for high-mobility platform applications.

[0030] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained from what is particularly pointed out in the description and drawings. Attached Figure Description

[0031] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0032] Figure 1 This is a schematic diagram of the radar antenna array elevation mechanism in specific embodiment 1;

[0033] Figure 2 This is a schematic diagram of the tension / compression rod assembly of the radar antenna array elevation mechanism in specific embodiment 1;

[0034] Figure 3 This is a schematic diagram of the sliding component of the radar antenna array elevation mechanism in specific embodiment 1;

[0035] Figure 4 This is a schematic diagram of the radar antenna array structure of the radar antenna array elevation mechanism in specific embodiment 1.

[0036] Figure 5 This is a schematic diagram of the eccentricity optimization method in specific embodiment 2.

[0037] Figure label:

[0038] 1-Drive motor; 2-Reducer; 3-Pitch base; 4-First drive assembly mounting base; 5-U-shaped frame support hinge base; 6-First hinge shaft;

[0039] 7-Pull-Press rod assembly; 71-First hinge bearing; 72-First hinge bearing housing; 73-First lock nut; 74-Connecting rod; 75-Second lock nut; 76-Second hinge bearing housing; 77-Second hinge bearing;

[0040] 8-Radar antenna array; 81-Bottom hinge base; 82-Structural frame;

[0041] 9-Second hinge shaft; 10-Second drive assembly mounting base; 11-Sliding guide rod; 12-Drag chain; 13-Angle measuring device; 14-Third hinge shaft;

[0042] 15-Sliding assembly; 151-First sliding bearing housing; 152-Synchronous connecting rod; 153-Lead screw nut; 154-Second sliding bearing housing; 155-Sliding bearing;

[0043] 16-Mechanical limit assembly; 17-Lead screw. Detailed Implementation

[0044] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0045] Example 1

[0046] A specific embodiment of the present invention, such as Figure 1 As shown, a small-eccentric radar antenna array elevation mechanism is disclosed, including a crank-slider assembly and a drive assembly. The crank-slider assembly is used to realize the elevation action and control the center of mass offset, and the drive assembly is used to provide power for the radar antenna array elevation mechanism. Specifically, the crank-slider assembly includes a first hinge shaft 6, a tension / compression rod assembly 7, a radar antenna array 8, a second hinge shaft 9, a sliding guide rod 11, a third hinge shaft 14, and a sliding assembly 15; the drive assembly includes a drive motor 1, a reducer 2, and a lead screw 17.

[0047] The crank-slider assembly is based on the principle of a crank-slider mechanism. Specifically, the crank-slider mechanism mainly consists of three parts: a crank, a connecting rod, and a slider. The crank, connecting rod, and slider are interconnected to achieve the conversion of motion modes. The crank is a rotating component, usually connected to a power source, and generates motion through rotation. The motion of the crank can drive the slider to perform linear motion. The connecting rod connects the crank and the slider, and plays the role of transmitting motion. The length and angle of the connecting rod affect the motion trajectory and speed of the slider. The slider is a component that performs linear motion on a guide rail, usually connected to the frame. The motion of the slider is a direct result of the crank rotation and can achieve reciprocating linear motion.

[0048] In this embodiment, the crank-slider assembly uses the line connecting the two second hinge shafts 9 as the crank, the tension rod assembly 7 as the connecting rod, and the sliding pair composed of the sliding guide rod 11 and the sliding assembly 15 as the slider, together forming a complete crank-slider mechanism.

[0049] Furthermore, the radar antenna array elevation mechanism also includes an elevation base 3, which serves as a basic mounting platform and provides stable support for the radar antenna array elevation mechanism.

[0050] Furthermore, such as Figure 4As shown, the second hinge shaft 9 is an axial structure, and there are two of them. The second hinge shaft 9 is fixed on the radar antenna array 8 and is connected to the second hinge bearing 77 of the tension / compression rod assembly 7. The third hinge shaft 14 is an axial structure, and there are two of them. The third hinge shaft 14 is connected to the first sliding bearing seat 151 and the second sliding bearing seat 154 of the sliding assembly 15 and the bottom hinge seat 81 of the radar antenna array 8. The sliding bearing 155 of the sliding assembly 15 cooperates with the sliding guide rod 11 to form a sliding pair. The sliding guide rod 11 is fixedly installed on the elevation base 3 through the second drive assembly mounting seat 10 to provide guidance for the sliding assembly 15. When the drive assembly drives the sliding assembly 15 to move along the sliding guide rod 11, the sliding assembly 15 pushes the second hinge shaft 9 connected to the radar antenna array 8 to rotate around the second hinge bearing 77 through the third hinge shaft 14. When the sliding component 15 moves, the second hinge shaft 9 connected to the radar antenna array 8 rotates around the second hinge bearing 77 to achieve pitching action, while the third hinge shaft 14 moves only along the axis of the sliding guide rod 11.

[0051] Furthermore, such as Figure 4 As shown, the radar antenna array 8 includes a bottom hinge seat 81 and a structural frame 82. The structural frame 82 is the main load-bearing structure, used to mount and support the antenna. Two bottom hinge seats 81 are fixedly mounted at the bottom of the structural frame 82, and are used to connect with the sliding assembly 15. The radar antenna array 8 forms hinges with the sliding assembly 15 and the tension / compression rod assembly 7 via the bottom hinge seats 81 and the second hinge shaft 9, respectively, achieving stable transmission during pitch movement. The structural layout of the radar antenna array 8 minimizes the change in the center of gravity during pitch, which helps reduce eccentric moments.

[0052] Furthermore, such as Figure 2 As shown, the tension / compression rod assembly 7 includes a first hinge bearing 71, a first hinge bearing seat 72, a first locking nut 73, a connecting rod 74, a second locking nut 75, a second hinge bearing seat 76, and a second hinge bearing 77.

[0053] Specifically, the connecting rod 74 is a rod-shaped structure with threaded holes at both ends and a square structure in the middle. The two ends of the connecting rod 74 are connected to the first hinge bearing seat 72 and the second hinge bearing seat 76, respectively. The threaded hole connecting the connecting rod 74 to the first hinge bearing seat 72 is a left-hand thread, and the threaded hole connecting the connecting rod 74 to the second hinge bearing seat 76 is a right-hand thread. The square structure in the middle of the connecting rod 74 can be adjusted by using a wrench. The connecting rod 74, as the main component of the tension / compression rod assembly, is used to transmit tension and pressure and to achieve precise adjustment of the spacing between the tension / compression rod assemblies 7.

[0054] Specifically, both the first hinge bearing seat 72 and the second hinge bearing seat 76 are seat structures. The interior of both seats has bearing mounting positions, and their outer surfaces have threaded structures. The thread of the first hinge bearing seat 72 is a left-hand thread, and the thread of the second hinge bearing seat 76 is a right-hand thread. The first hinge bearing seat 72 and the second hinge bearing seat 76 are respectively connected to both ends of the connecting rod 74 via threads for mounting and fixing the hinge bearing.

[0055] Specifically, the first locking nut 73 is a left-hand threaded nut, and the second locking nut 75 is a right-hand threaded nut. The first locking nut 73 and the second locking nut 75 are used in conjunction with the first hinge bearing seat 72 and the second hinge bearing seat 76, respectively. After the hinge bearing seat and the connecting rod 74 are adjusted to their positions, reliable fixing is achieved by tightening the first locking nut 73 and the second locking nut 75. The first locking nut 73 and the second locking nut 75 are used to prevent changes in the hinge spacing due to component rotation during debugging, transportation, and operation of the radar antenna array elevation mechanism, ensuring the stability of the mechanism.

[0056] The first hinge bearing 71 and the second hinge bearing 77 have the same structure and are both standard bearing components. The first hinge bearing 71 and the second hinge bearing 77 are respectively installed in the first hinge bearing seat 72 and the second hinge bearing seat 76. The first hinge bearing 71 is connected to the U-shaped frame support hinge seat 5 via the first hinge shaft 6, forming a hinge connection. The first hinge bearing 71 and the second hinge bearing 77 are used to realize the rotational connection between the tension / compression rod assembly 7 and other components, ensuring the flexibility of the mechanism's movement.

[0057] During the pitching motion, when the center of gravity of the radar antenna array 8 is located between the first hinge axis 6 and the third hinge axis 14, the tension / compression rod assembly 7 bears pressure; when the center of gravity is located outside the first hinge axis 6 and the third hinge axis 14, the tension / compression rod assembly 7 bears tension. Through its adjustable and lockable structure, the tension / compression rod assembly 7 can provide stable support for the radar antenna array 8 under different operating conditions, while ensuring the accuracy of the mechanism's movement.

[0058] like Figure 3 As shown, the sliding assembly 15 includes a first sliding bearing seat 151, a synchronous connecting rod 152, a second sliding bearing seat 154, and a sliding bearing 155. The first and second sliding bearing seats 151 and 154 are bearing seat structures, and each contains a sliding bearing 155. The synchronous connecting rod 152 is a rod-shaped structure that connects the first and second sliding bearing seats 151 and 154 as a whole. The sliding bearing 155 cooperates with the sliding guide rod 11 to form a sliding pair.

[0059] Furthermore, the drive assembly includes a drive motor 1, a reducer 2, and a lead screw 17. The rotation of the drive motor 1 drives the lead screw 17 to rotate after the torque is increased by the reducer 2, providing the original power for the pitching action of the radar antenna array 8. The lead screw 17 and the lead screw nut 153 of the sliding assembly 15 form a screw pair. The screw pair converts the rotational torque of the drive motor 1 into the moving push-pull force of the sliding assembly 15, thereby driving the sliding assembly 15 to move.

[0060] The above description of a helical pair is a description of existing technology. A helical pair is a transmission pair based on a helix, mainly used to convert rotational motion into linear motion or vice versa. The core of a helical pair consists of a screw and a nut, which achieve force transmission and motion conversion through helical meshing.

[0061] The radar antenna array elevation mechanism also includes auxiliary structures, including a cable chain 12, an angle measuring device 13, and a mechanical limiting assembly 16. Specifically, the cable chain 12 is installed on the side of the elevation base 3. The cable chain 12 is used to fix and protect the cables and pipes connecting the radar antenna array 8 to the outside world, and guides the cables and pipes to bend and fold when the radar antenna array elevation mechanism is in operation, preventing damage to the cables and pipes. The angle measuring device 13 is installed at the third hinge axis 14 and is used to measure the elevation angle of the radar antenna array 8 in real time. The angle measuring device 13 provides angle feedback to the control system to ensure that the elevation angle is accurate and controllable.

[0062] Furthermore, the mechanical limiting component 16 is installed at the end of the sliding guide rod 11 to limit the travel of the sliding component 15. The mechanical limiting component 16 provides auxiliary support when the radar antenna array 8 is retracted, and prevents the mechanism from being damaged by overtravel when the radar antenna array 8 is in a fully collapsed retracted state. The retracted state is the state where the radar antenna array 8 is parallel to the contact surface of the mechanical limiting component 16. Specifically, the fully collapsed retracted state is as follows: the drive component drives the sliding component 15 to move along the sliding guide rod 11 towards the drive motor 1, and the radar antenna array 8 rotates around the second hinge axis 9 until its plane is parallel to the upper surface of the elevation base 3, that is, the fully collapsed retracted state.

[0063] The radar antenna array elevation mechanism features a compact and rational structural layout with clearly defined connections between components. Optimized design of the crank-slider mechanism minimizes the center of gravity shift during the elevation process of the radar antenna array 8, improving the transmission efficiency and response speed of the drive components. The adjustable design of the tension / compression rod assembly 7 provides the mechanism with good adaptability. The configuration of auxiliary components enhances the mechanism's functionality and improves the system's reliability and safety. While meeting the elevation requirements of the radar antenna array 8, the radar antenna array elevation mechanism effectively controls the center of gravity shift and reduces the impact of eccentric torque on the mounting platform.

[0064] Example 2

[0065] Another specific embodiment of the present invention discloses a method for optimizing the eccentricity of a radar antenna array elevation mechanism, employing the radar antenna array elevation mechanism of Embodiment 1, the steps of which include:

[0066] Step S1: Define the relevant parameters for eccentricity optimization

[0067] like Figure 5 As shown in the figure, A is the location of the first hinge axis 6; B0 is the location of the second hinge axis 9 when the radar antenna array 8 is in the retracted state; B i C0 represents the position of the second hinge axis 9 at a certain moment during the elevation movement of the radar antenna array 8; C0 represents the position of the third hinge axis 14 when the radar antenna array 8 is in the retracted state; C i G0 represents the position of the third hinge axis 14 at a certain moment during the elevation movement of the radar antenna array 8; G0 represents the position of the center of gravity of the radar antenna array 8 when it is in the retracted state; G i This refers to the position of the center of gravity of radar antenna array 8 at a certain moment during its pitching motion.

[0068] Furthermore, such as Figure 5 As shown, l1 is defined as the distance between the first hinge axis 6 and the second hinge axis 9; l2 is the distance between the second hinge axis 9 and the third hinge axis 14; l3 is the distance between the first hinge axis 6 and the third hinge axis 14 in the vertical direction; l4 is the distance between the centroid of the radar antenna array 8 and the third hinge axis 14; l5 is the distance between the centroid of the radar antenna array 8 and the second hinge axis 9; α i α is the elevation angle of the radar antenna array 8; α0 is the initial angle between the line connecting the second hinge axis 9 and the third hinge axis 14 and the axis of the sliding pair when the radar antenna array 8 is in the retracted state.

[0069] Furthermore, e is defined as the offset of the center of gravity of the radar antenna array 8 relative to the retracted state during the entire pitch process.

[0070] Step S2: Derive the formula for calculating the center of gravity offset

[0071] As shown in step S1, the offset of the center of gravity of the radar antenna array 8 relative to the retracted state during the entire elevation process is e, which can be further calculated using the following formula: In the above formula, l3 and l4 are limited by the structure and installation requirements of the radar antenna array 8, resulting in a small optimization space; it can be seen from the geometric relationship that α0 is a fixed value, therefore the centroid offset e of the radar antenna array 8 is related to l1, l5 and α iIt is related to the operation requirements of the radar antenna array 8; αi is related to the operation requirements of the radar antenna array 8 and cannot be used as an optimization parameter; at the same time, in order to ensure that no dead points occur during the operation of the mechanism, the constraint condition l1+l3>l2 must be satisfied.

[0072] Step S3: Determine the optimization objective and parameters

[0073] The maximum value of the centroid offset e of the radar antenna array 8 is taken as the optimization objective, that is, the maximum value of e is minimized by adjusting the parameters; the optimization parameters are determined to be l1 and l5; during the optimization process, the constraint condition l1+l3>l2 must be met, and the installation requirements of the radar antenna array 8 must also be met.

[0074] Step S4: Solve for the optimal parameters

[0075] Based on the above optimization objectives, optimization parameters and constraints, through geometric analysis and parameter iteration verification, the values ​​of l1 and l5 that minimize the maximum value of the center of gravity offset e are determined, and the parameter combination of the small eccentric radar antenna array elevation mechanism with the smallest eccentricity is obtained. This parameter combination ensures that it meets the requirements of l1+l3>l2 and installation requirements, thereby realizing the small eccentricity design.

[0076] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A small-eccentricity radar antenna array elevation mechanism, characterized by, The crank slider assembly is used to realize the pitching action and control the mass center deviation, and the driving assembly is used to provide power for the radar antenna array pitching mechanism. The crank slider assembly comprises a first hinge shaft (6), a tension-compression rod assembly (7), a radar antenna array (8), a second hinge shaft (9), a sliding guide rod (11), a third hinge shaft (14) and a sliding assembly (15). The driving assembly comprises a driving motor (1), a speed reducer (2) and a lead screw (17).

2. A small-eccentricity radar antenna array elevation mechanism according to claim 1, characterized in that The tension-compression rod assembly (7) comprises a connecting rod (74), a first hinge bearing seat (72) and a second hinge bearing seat (76).

3. A small-eccentricity radar antenna array elevation mechanism according to claim 2, characterized in that The tension-compression rod assembly (7) further comprises a first hinge bearing (71) and a second hinge bearing (77).

4. A small-eccentricity radar antenna array elevation mechanism according to claim 3, characterized in that The first hinge bearing (71) is installed in the first hinge bearing seat (72), and the second hinge bearing (77) is installed in the second hinge bearing seat (76).

5. The small-eccentricity radar antenna array elevation mechanism of claim 1, wherein, The lead screw (17) and a lead screw nut (153) in the sliding assembly (15) constitute a screw pair.

6. A small-eccentricity radar antenna array elevation mechanism according to claim 1, wherein, The radar antenna array (8) comprises a structural frame (82) and two bottom hinge seats (81) arranged at the bottom thereof.

7. A small-eccentricity radar antenna array elevation mechanism according to claim 1, wherein, The auxiliary structure further comprises a mechanical limiting assembly (16) arranged at the end of the sliding guide rod (11).

8. A small-eccentricity radar antenna array elevation mechanism according to claim 7, characterized in that The crank slider assembly takes the line between the two second hinge shafts (9) as a crank, takes the tension-compression rod assembly (7) as a connecting rod, and takes the sliding guide rod (11) and the sliding assembly (15) as a slider.

9. A small-eccentricity radar antenna array elevation mechanism according to claim 1, wherein, The method comprises the following steps:

10. An eccentricity optimization method using the small eccentric radar antenna array elevation mechanism according to any one of claims 1-9, characterized by, S1: defining eccentricity optimization parameters; S2: deriving a formula for calculating the mass center deviation; S3: determining optimization targets and parameters; S4: solving the optimal parameter combination. ​

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