Three-degree-of-freedom angular displacement-free vibration damping device

Abstract

The application discloses a three-degree-of-freedom angular displacement-free damping device, which comprises a damping unit (01), a universal joint mechanism (02), an airplane mounting base (1), a translation bar (2), a roll support (3), a photoelectric mounting support (4), the damping unit (01) is arranged between the airplane mounting base (1) and the photoelectric mounting support (4), the upper ball bearing of the universal joint mechanism (02) is fixedly connected with the photoelectric mounting support (4), the lower ball bearing is fixedly connected with the roll support (3), the roll support (3) is provided with two roll supports (3) which are arranged in parallel, the two ends of each roll support (3) are respectively mounted on the airplane mounting base (1) through deep groove ball bearings I (5), and a degree of freedom is formed between the airplane mounting base (1) and the roll support (3), and the two ends of the roll support (3) are respectively connected with a translation bar (2) through deep groove ball bearings II (6). The application improves the system stability, improves the system stability precision and guarantees the image quality of the photoelectric system.

Description

Technical Field

[0001] This invention belongs to the field of airborne optoelectronic equipment with relatively small vibration displacement values, and relates to a three-degree-of-freedom vibration reduction device without angular displacement. Background Technology

[0002] With the development of modern technology, the demands on weapon systems in warfare are becoming increasingly higher. Long-range detection, accurate aiming, strong survivability, and high combat effectiveness have become basic requirements for modern weapon systems. Airborne stabilization systems, as an important component of airborne weapon systems, also face the same challenges.

[0003] An optoelectronic turret is an optoelectronic system that uses optoelectronic loads to achieve target detection and monitoring. Vibration severely affects the performance and reliability of optoelectronic stabilization platforms, especially high-precision stabilization platforms. Various vibrations are transmitted through elastic components to the platform base, causing vibrations in the platform frame and body. While traditional vibration reduction methods can reduce external vibration interference and ensure the installation and reliability of the equipment, angular vibration significantly reduces the image quality of the optoelectronic system, affecting the system's target detection and identification. Therefore, eliminating angular vibration can achieve good vibration isolation. The function of a non-angular displacement vibration reduction device is to ensure that the optoelectronic turret only has translational motion relative to the carrier, without any relative rotational degree of freedom, thereby improving the system's image quality and effectively enhancing the system's performance. Summary of the Invention

[0004] (I) Purpose of the Invention

[0005] The purpose of this invention is to provide a three-degree-of-freedom vibration damping device without angular displacement, which can effectively isolate the photoelectric turret in three directions, effectively isolate it from external impacts and vibrations, greatly attenuate mid-to-high frequency vibrations, keep the natural frequency away from external interference frequencies, avoid resonance, enable the system to achieve the best vibration damping effect, improve the stability of various functions of the photoelectric turret, improve the performance of the photoelectric turret, and ensure the reliability of the photoelectric turret.

[0006] (II) Technical Solution

[0007] To solve the above-mentioned technical problems, the present invention provides a three-degree-of-freedom vibration damping device without angular displacement, including a vibration damping unit 01, a universal joint mechanism 02, an aircraft mounting base 1, a translation rod 2, a roll support 3, and a photoelectric mounting bracket 4; the vibration damping unit 01 is arranged between the aircraft mounting base 1 and the photoelectric mounting bracket 4, and effectively attenuates the transmission of vibration source from the aircraft mounting base 1; the upper ball bearing of the universal joint mechanism 02 is fixedly connected to the photoelectric mounting bracket 4, and the lower ball bearing is fixedly connected to the roll support 3, forming a gap between the photoelectric mounting bracket 4 and the roll support 3. There are two relative degrees of freedom; there are two roll supports 3 arranged in parallel, and the two ends of each roll support 3 are respectively mounted on the aircraft mounting base 1 through deep groove ball bearings I5. The aircraft mounting base 1 and the roll support 3 form one degree of freedom; the two ends of the roll support 3 are respectively connected to a translation rod 2 through deep groove ball bearings II6. The arrangement of translation rod 2 and deep groove ball bearings II6 ensures the synchronicity of the up and down movement of the two roll supports 3; furthermore, the arrangement of the roll support 3 and the universal joint mechanism 02 effectively constrains the three degrees of freedom of the photoelectric mounting bracket.

[0008] (III) Beneficial Effects

[0009] The three-degree-of-freedom, angular displacement-free vibration damping device provided by the above technical solution uses a six-degree-of-freedom universal joint mechanism to restrict the three angular degrees of freedom of the system through the constraints of the upper and lower mounting platforms. The photoelectric system only has linear vibration degree of freedom, which greatly improves the system's stability and accuracy, and ensures the image quality of the photoelectric system. By selecting appropriate parameters for the vibration damper, the system can attenuate mid-to-high frequency vibrations to a great extent, keeping the natural frequency away from external interference frequencies and avoiding resonance, thus achieving the best vibration damping effect. The universal joint mechanism effectively solves the coupling effect caused by centrifugal force in airborne photoelectric equipment, avoids image blurring caused by angular disturbances, and makes full use of buffer blocks to effectively solve collisions and increase reliability. The design is simple, low-cost, and adaptable to various centrifugal airborne photoelectric equipment, making it highly versatile. Attached Figure Description

[0010] Figure 1 This is a schematic diagram of the three-degree-of-freedom vibration damping device without angular displacement of the present invention;

[0011] Figure 2 for Figure 1 Schematic diagram of the vibration damping device in the middle;

[0012] Figure 3 for Figure 1 A schematic diagram of the universal joint mechanism in the middle;

[0013] Figure 4 and 5 They are respectively Figure 1 Front and top views of the base platform;

[0014] Figure 6 This is a schematic diagram of an integrated photoelectric turret and a vibration damping device without angular displacement. Detailed Implementation

[0015] To make the objectives, contents, and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples.

[0016] like Figures 1 to 5 As shown, the three-degree-of-freedom vibration damping device in this embodiment includes a damping unit 01, a universal joint mechanism 02, an aircraft mounting base 1, a translation rod 2, a roll support 3, and a photoelectric mounting bracket 4. The damping unit 01 is arranged between the aircraft mounting base 1 and the photoelectric mounting bracket 4, effectively attenuating the transmission of vibration from the aircraft mounting base 1. The upper ball bearing of the universal joint mechanism 02 is fixedly connected to the photoelectric mounting bracket 4, and the lower ball bearing is fixedly connected to the roll support 3, so that two degrees of freedom are formed between the photoelectric mounting bracket 4 and the roll support 3. Regarding the motion; there are two roll supports 3, arranged in parallel. The two ends of each roll support 3 are respectively mounted on the aircraft mounting base 1 through deep groove ball bearings I5, forming one degree of freedom between the aircraft mounting base 1 and the roll support 3; the two ends of the roll support 3 are respectively connected to a translation rod 2 through deep groove ball bearings II6. The arrangement of translation rod 2 and deep groove ball bearings II6 ensures the synchronicity of the up and down movement of the two roll supports 3; furthermore, the arrangement of the roll support 3 and the universal joint mechanism 02 effectively constrains the three degrees of freedom of the photoelectric mounting bracket.

[0017] like Figure 2 As shown, the vibration damping unit 01 includes: an inner damper sleeve 01-1, a spring damper I01-2, a spring damper II01-3, a damper spacer 01-4, a damper outer sleeve 01-5, a damper inner pressure ring 01-6, and a limiting buffer block 01-7. The inner damper sleeve 01-1 is coaxially arranged inside the damper outer sleeve 01-5. Two spring dampers I01-2 are fitted from top to bottom on the outer wall of the inner damper sleeve 01-1. An annular groove is opened on the inner wall of the damper outer sleeve 01-5, and the damper spacer is arranged in the annular groove. 01-4, the damper spacer 01-4 separates the spring damper I01-2 and the spring damper II01-3. The two spring dampers I01-2 are located above and below the damper spacer 01-4, respectively. The spring damper II01-3 is arranged on the outer wall of the upper part of the damper outer sleeve 01-5. The upper end of the damper inner sleeve 01-1 and the spring damper II01-3 are fixed to the photoelectric mounting bracket 4. The lower end of the damper outer sleeve 01-5 is fixed to the aircraft mounting base 1, and the damping is performed in the vertical Z direction.

[0018] There are four spring dampers II01-3, which are installed on the outer wall of the damper jacket 01-5 in a circumferentially distributed manner, and respectively damping the system in the horizontal and perpendicular X and Y directions.

[0019] The inner pressure ring 01-6 of the vibration damper is installed at the bottom of the inner sleeve 01-1 of the vibration damper to restrict the position of the vibration damper. A limiting buffer block 01-7 is installed at the bottom of the inner pressure ring 01-6 of the vibration damper to restrict the position of the structure and provide a buffering effect under conditions of excessive impact or deformation.

[0020] Each vibration damping unit 01 has a vibration damping effect in two directions. Four vibration damping units 01 are installed in a circular arrangement with two sets of units 01 arranged perpendicularly to each other, so that the horizontal vibration damping direction is perpendicular to each other. In this way, the vibration damping unit 01 has a vibration damping effect in three vertical directions.

[0021] like Figure 3 As shown, the universal joint mechanism 02 includes two ball bearings 02-1 and a connecting rod 02-2 connecting the two ball bearings 02-1. The axial angle between the upper and lower ball bearings 02-1 is 60°. The universal joint mechanism 02 has the characteristics of high rigidity, strong load-bearing capacity, and non-cumulative positional error. By designing four universal joint mechanisms, the structural parameters of the system are determined, ensuring that the system has good motion control performance within its normal operating range.

[0022] like Figure 4 So and Figure 5 As shown, a deep groove ball bearing I5 is mounted on the aircraft mounting base 1. The inner bore of the deep groove ball bearing I5 is connected to the roll support 3. The two ends of the roll support 3 are mounted in the inner bore of the deep groove ball bearing II6. The deep groove ball bearing II6 is connected to the translation rod 2. The deep groove ball bearing I5 gives the roll support 3 only one degree of freedom. By installing the translation rod 2, the four mounting end faces of the roll support 3 can rotate synchronously.

[0023] like Figure 6 As shown, in this embodiment, the vibration damping unit 01 effectively isolates the photoelectric turret in three directions. The two ball bearings 02-1 of the universal joint mechanism 02 are connected to the photoelectric mounting bracket 4 and the roll bracket 3 respectively. Through the constraint of the deep groove ball bearing's degree of freedom and the high consistency of the four universal joint mechanisms 02, the photoelectric mounting bracket 4 has only three translational degrees of freedom and no rotational degrees of freedom, preventing angular disturbances in the system. A limit buffer block 01-7 is installed on the lower side of the photoelectric mounting bracket 4. This limit buffer block restricts the movement displacement of the photoelectric turret, ensuring that the photoelectric system will not experience impacts or collisions, thus improving the system's reliability.

[0024] As can be seen from the above technical solution, the present invention has the following significant features:

[0025] When applied, this invention employs four vibration damping units to effectively isolate external vibration interference; the universal joint mechanism eliminates the coupling effect caused by the ordinary arrangement of vibration dampers, and the vibration damping units effectively avoid collisions caused by various impacts and excessive displacement vibrations of the system; and the three degrees of freedom of the system's three corner disturbance directions are restricted.

[0026] Airborne optoelectronic equipment can significantly improve the quality of optoelectronic images and ensure system reliability under effective vibration reduction conditions. The present invention utilizes a three-degree-of-freedom non-angular displacement vibration reduction device to effectively combine vibration reduction technology and a three-degree-of-freedom motion restriction mechanism. This effectively restricts the three degrees of freedom of angular vibration, avoiding the coupling of angular disturbances caused by linear vibration of centrifugal airborne optoelectronic equipment. It also achieves effective isolation of linear vibration in three directions, keeps the natural frequency away from external interference frequencies, effectively decouples the system, and enables it to achieve the best vibration reduction effect.

[0027] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A three-degree-of-freedom vibration damping device without angular displacement, characterized in that, include: Vibration damping unit (01), universal joint mechanism (02), aircraft mounting base (1), translation rod (2), roll support (3), photoelectric mounting bracket (4); the vibration damping unit (01) is arranged between the aircraft mounting base (1) and the photoelectric mounting bracket (4), and the vibration damping unit (01) attenuates the transmission of vibration source of the aircraft mounting base (1); the upper ball bearing of the universal joint mechanism (02) is fixed to the photoelectric mounting bracket (4), and the lower ball bearing is fixed to the roll support (3), so that the photoelectric mounting bracket (4) and the roll support (3) form two degrees of freedom relative motion; the roll support There are two roller brackets (3) arranged in parallel. The two ends of each roller bracket (3) are respectively mounted on the aircraft mounting base (1) through deep groove ball bearing I (5). The aircraft mounting base (1) and the roller bracket (3) form one degree of freedom. The two ends of the roller bracket (3) are respectively connected to a translation rod (2) through deep groove ball bearing II (6). Through the arrangement of translation rod (2) and deep groove ball bearing II (6), the synchronicity of the up and down movement of the two roller brackets (3) is realized. Through the arrangement of roller bracket (3) and universal joint mechanism (02), the three degrees of freedom of the photoelectric mounting bracket are constrained. The vibration damping unit (01) includes: an inner damper sleeve (01-1), spring damper I (01-2), spring damper II (01-3), a damper spacer (01-4), and a damper outer sleeve (01-5). The inner damper sleeve (01-1) is coaxially arranged inside the outer damper sleeve (01-5). Two spring dampers I (01-2) are fitted from top to bottom on the outer wall of the inner damper sleeve (01-1). An annular groove is opened on the inner wall of the outer damper sleeve (01-5), and the damper spacer (01-4) is arranged in the annular groove. The damper spacer (01-4) separates the spring damper I (01-2) and the spring damper II (01-3). The two spring dampers I (01-2) are located above and below the damper spacer (01-4) respectively. The spring damper II (01-3) is arranged on the outer wall of the upper part of the damper outer sleeve (01-5). The upper end of the damper inner sleeve (01-1) and the spring damper II (01-3) are fixed to the photoelectric mounting bracket (4). The lower end of the damper outer sleeve (01-5) is fixed to the aircraft mounting base (1).

2. The three-degree-of-freedom vibration damping device without angular displacement as described in claim 1, characterized in that, There are four spring dampers II (01-3), which are installed on the outer wall of the damper jacket (01-5) in a circumferentially distributed manner.

3. The three-degree-of-freedom vibration damping device without angular displacement as described in claim 2, characterized in that, The vibration damping unit (01) further includes: an inner pressure ring (01-6) for the vibration damper, which is installed at the bottom of the inner sleeve (01-1) of the vibration damper to restrict the position of the vibration damper.

4. The three-degree-of-freedom vibration damping device without angular displacement as described in claim 3, characterized in that, The bottom of the inner pressure ring (01-6) of the shock absorber is equipped with a limiting buffer block (01-7).

5. The three-degree-of-freedom vibration damping device without angular displacement as described in claim 4, characterized in that, The universal joint mechanism (02) includes two ball bearings (02-1) and a connecting rod (02-2) connecting the two ball bearings (02-1).

6. The three-degree-of-freedom vibration damping device without angular displacement as described in claim 5, characterized in that, In the universal joint mechanism (02), the axial included angle between the upper and lower ball bearings (02-1) is 60°.

7. The three-degree-of-freedom vibration damping device without angular displacement as described in claim 6, characterized in that, The aircraft mounting base (1) is equipped with a deep groove ball bearing I (5). The inner hole of the deep groove ball bearing I (5) is connected to the roll bracket (3). The two ends of the roll bracket (3) are installed in the inner hole of the deep groove ball bearing II (6). The deep groove ball bearing II (6) is connected to the translation rod (2). The deep groove ball bearing I (5) makes the roll bracket (3) have only one degree of freedom. By installing the translation rod (2), the four mounting end faces of the roll bracket (3) rotate synchronously.

8. The three-degree-of-freedom vibration damping device without angular displacement as described in claim 7, characterized in that, The vibration damping unit (01) is arranged in four evenly distributed circles. The four vibration damping units (01) form two groups. The two groups of vibration damping units (01) are arranged relatively vertically, so that the horizontal vibration damping direction is perpendicular to each other, forming a vibration damping effect in three vertical directions.

9. The application of a three-degree-of-freedom non-angular displacement vibration damping device based on any one of claims 1-8 in the field of airborne optoelectronic equipment.

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