CN116923703A - Three-degree-of-freedom angular displacement free vibration damper - Google Patents
Three-degree-of-freedom angular displacement free vibration damper Download PDFInfo
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- CN116923703A CN116923703A CN202310756293.5A CN202310756293A CN116923703A CN 116923703 A CN116923703 A CN 116923703A CN 202310756293 A CN202310756293 A CN 202310756293A CN 116923703 A CN116923703 A CN 116923703A
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- 238000006073 displacement reaction Methods 0.000 title claims abstract description 23
- 238000005096 rolling process Methods 0.000 claims abstract description 41
- 230000007246 mechanism Effects 0.000 claims abstract description 23
- 238000013519 translation Methods 0.000 claims abstract description 15
- 230000009467 reduction Effects 0.000 claims abstract description 14
- 239000006096 absorbing agent Substances 0.000 claims description 27
- 238000013016 damping Methods 0.000 claims description 22
- 230000033001 locomotion Effects 0.000 claims description 9
- 230000035939 shock Effects 0.000 claims description 9
- 230000000694 effects Effects 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000005693 optoelectronics Effects 0.000 claims description 2
- 238000009827 uniform distribution Methods 0.000 claims description 2
- 238000002955 isolation Methods 0.000 description 4
- 230000008878 coupling Effects 0.000 description 2
- 230000001808 coupling effect Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005119 centrifugation Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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Abstract
The invention discloses a three-degree-of-freedom angular displacement free vibration damper, which comprises: the vibration reduction device comprises a vibration reduction unit (01), a universal joint mechanism (02), an aircraft mounting base (1), a translation rod (2), a transverse rolling support (3) and a photoelectric mounting support (4), wherein the vibration reduction unit (01) is arranged between the aircraft 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 bracket (4), and the lower ball bearing is fixedly connected with the transverse rolling bracket (3); two transverse rolling brackets (3) are arranged in parallel, two ends of each transverse rolling bracket (3) are respectively arranged on an aircraft mounting base (1) through deep groove ball bearings I (5), and one degree of freedom is formed between the aircraft mounting base (1) and the transverse rolling brackets (3); two ends of the transverse rolling support (3) are respectively connected with a translation rod (2) through deep groove ball bearings II (6). The invention improves the stability of the system, improves the stability precision of the system and ensures the image quality of the photoelectric system.
Description
Technical Field
The invention belongs to the field of airborne photoelectric equipment with relatively small vibration displacement value, and relates to a three-degree-of-freedom angular displacement-free vibration damper.
Background
With the development of modern technology, warfare is increasingly demanding on weapon systems. The far reaching, accurate, high survivability and high operational efficiency become the basic requirements of the present weapon systems. The same challenges are faced by an on-board stabilized sight system that is an important component of an on-board weapon system.
The photoelectric turret is a photoelectric system for realizing target detection and monitoring by utilizing photoelectric load, the vibration seriously affects the performance and reliability of a photoelectric stabilized sighting platform, and particularly for the high-precision stabilized sighting platform, various vibrations are transmitted to a platform base through an elastic member, so that the platform ring frame and the platform body vibrate. The traditional vibration reduction mode can reduce external vibration interference, ensure the installability and reliability of equipment, greatly reduce the image quality of a photoelectric system by angular vibration, influence the detection and identification of a system to a target, and therefore, good vibration isolation effect can be obtained by eliminating the angular vibration. The vibration damper without angular displacement has the function of enabling the photoelectric turret to only move in a translational mode relative to the carrier, and has no relative rotational freedom degree, so that the image quality of the system is improved, and the performance of the system is effectively improved.
Disclosure of Invention
Object of the invention
The purpose of the invention is that: the three-degree-of-freedom angular displacement-free vibration damper is capable of effectively isolating vibration of the photoelectric turret in three directions, effectively isolating external impact and vibration, attenuating middle-high frequency vibration to a great extent, enabling natural frequency to be far away from external interference frequency, avoiding resonance, enabling a system to achieve the optimal vibration damping effect, improving stability of various functions of the photoelectric turret, improving performance of the photoelectric turret and guaranteeing reliability of the photoelectric turret.
(II) technical scheme
In order to solve the technical problems, the invention provides a three-degree-of-freedom angular displacement free vibration damper which comprises a vibration damper unit 01, a universal joint mechanism 02, an aircraft mounting base 1, a translation rod 2, a roll bracket 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 the transmission of vibration sources of the aircraft mounting base 1 is effectively damped through the vibration damping unit 01; the upper ball bearing of the universal joint mechanism 02 is fixedly connected with the photoelectric mounting bracket 4, and the lower ball bearing is fixedly connected with the transverse rolling bracket 3, so that two degrees of freedom relative motion are formed between the photoelectric mounting bracket 4 and the transverse rolling bracket 3; the two transverse rolling brackets 3 are arranged in parallel, two ends of each transverse rolling bracket 3 are respectively arranged on the aircraft mounting base 1 through deep groove ball bearings I5, and one degree of freedom is formed between the aircraft mounting base 1 and the transverse rolling brackets 3; two ends of the transverse rolling support 3 are respectively connected with a translation rod 2 through a deep groove ball bearing II6, and the synchronism of up-and-down movement of the two transverse rolling supports 3 is ensured through the arrangement of the translation rod 2 and the deep groove ball bearing II 6; further, through the arrangement of the transverse rolling support 3 and the universal joint mechanism 02, three degrees of freedom of the photoelectric mounting support are effectively restrained.
(III) beneficial effects
According to the three-degree-of-freedom angular displacement free vibration damper provided by the technical scheme, the six-freedom universal joint mechanism limits three angular degrees of freedom of the system through the constraint of the upper and lower mounting platform devices, and the photoelectric system only has linear vibration degrees of freedom, so that the stability performance of the system is improved to a great extent, the stability precision of the system is improved, and the image quality of the photoelectric system is ensured; through the selection of proper parameters of the vibration absorber, the medium-high frequency vibration is attenuated to a great extent, and the natural frequency is far away from the external interference frequency, so that resonance is avoided, and the system achieves the optimal vibration absorption effect; the universal joint mechanism is utilized, so that the coupling effect of the airborne photoelectric equipment caused by centrifugation is effectively solved, the image blurring caused by angular disturbance is avoided, the buffer blocks are fully utilized, the collision is effectively solved, and the reliability is improved; the rolling bearing, the deep groove ball bearing and the spring damper are utilized, the design is simple, the cost is low, the centrifugal machine is suitable for various centrifugal machine-mounted photoelectric equipment, and the universality is strong.
Drawings
FIG. 1 is a schematic diagram of a three degree of freedom angular displacement free vibration damping device according to the present invention;
FIG. 2 is a schematic view of the vibration damping device of FIG. 1;
FIG. 3 is a schematic view of the gimbal mechanism of FIG. 1;
figures 4 and 5 are front and top views, respectively, of the base platform of figure 1;
FIG. 6 is a schematic diagram of an optoelectronic turret and a non-angular displacement damper.
Detailed Description
To make the objects, contents and advantages of the present invention more apparent, the following detailed description of the present invention will be given with reference to the accompanying drawings and examples.
As shown in fig. 1 to 5, the three-degree-of-freedom angular displacement free vibration damping device of the present embodiment includes a vibration damping unit 01, a universal joint mechanism 02, an aircraft mounting base 1, a translation rod 2, a roll bracket 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 the transmission of vibration sources of the aircraft mounting base 1 is effectively damped through the vibration damping unit 01; the upper ball bearing of the universal joint mechanism 02 is fixedly connected with the photoelectric mounting bracket 4, and the lower ball bearing is fixedly connected with the transverse rolling bracket 3, so that two degrees of freedom relative motion are formed between the photoelectric mounting bracket 4 and the transverse rolling bracket 3; the two transverse rolling brackets 3 are arranged in parallel, two ends of each transverse rolling bracket 3 are respectively arranged on the aircraft mounting base 1 through deep groove ball bearings I5, and one degree of freedom is formed between the aircraft mounting base 1 and the transverse rolling brackets 3; two ends of the transverse rolling support 3 are respectively connected with a translation rod 2 through a deep groove ball bearing II6, and the synchronism of up-and-down movement of the two transverse rolling supports 3 is ensured through the arrangement of the translation rod 2 and the deep groove ball bearing II 6; further, through the arrangement of the transverse rolling support 3 and the universal joint mechanism 02, three degrees of freedom of the photoelectric mounting support are effectively restrained.
As shown in fig. 2, the vibration damping unit 01 includes: the vibration absorber comprises a vibration absorber inner sleeve 01-1, a spring vibration absorber I01-2, a spring vibration absorber II01-3, a vibration absorber spacer ring 01-4, a vibration absorber outer sleeve 01-5, a vibration absorber inner pressing ring 01-6 and a limiting buffer block 01-7; the inner damper sleeve 01-1 is coaxially arranged in the outer damper sleeve 01-5, the outer wall of the inner damper sleeve 01-1 is sleeved with two spring dampers I01-2 from top to bottom, the inner wall of the outer damper sleeve 01-5 is provided with annular grooves, damper space rings 01-4 are arranged in the annular grooves, the damper space rings 01-4 separate the spring dampers I01-2 and II01-3, and the two spring dampers I01-2 are respectively positioned above and below the damper space rings 01-4; 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 fixedly connected with the photoelectric mounting bracket 4, and the lower end of the damper outer sleeve 01-5 is fixedly connected with the aircraft mounting base 1 to damp vibration in the vertical direction Z.
The four spring vibration dampers II01-3 are arranged on the outer wall of the vibration damper jacket 01-5 in a circumferentially uniform distribution mode, and respectively damp vibration in the horizontal and vertical X, Y directions of the system.
The inner pressing ring 01-6 of the shock absorber is arranged at the bottom of the inner sleeve 01-1 of the shock absorber to limit the position of the shock absorber. The bottom of the inner pressing ring 01-6 of the shock absorber is provided with a limiting buffer block 01-7, and the structure position is limited and the buffer effect is achieved under the condition of overlarge impact or deformation.
Each vibration damping unit 01 has two-directional vibration damping effects. Four vibration reduction units 01 in two groups are uniformly distributed on the circumference, and the vibration reduction units 01 in two groups are vertically arranged relatively, so that the horizontal vibration reduction directions are mutually vertical, and the vibration reduction units 01 have vibration reduction effects in 3 vertical directions.
As shown in fig. 3, the universal joint mechanism 02 includes two ball bearings 02-1 and a connecting rod 02-2 connecting the two ball bearings 02-1, and the upper and lower ball bearings 02-1 have an axial angle of 60 °. The universal joint mechanism 02 has the characteristics of high rigidity, high bearing capacity, no accumulation of position errors and the like, and the structural parameters of the system are determined by designing four universal joint mechanisms, so that the system can have good motion control performance within a normal working range.
As shown in fig. 4 and 5, a deep groove ball bearing I5 is installed on the aircraft installation base 1, an inner hole of the deep groove ball bearing I5 is connected with a transverse rolling support 3, two ends of the transverse rolling support 3 are installed at an inner hole of a deep groove ball bearing II6, and the deep groove ball bearing II6 is connected with a translation rod 2. The deep groove ball bearing I5 enables the rolling support 3 to have only one degree of freedom, and the four installation end faces of the rolling support 3 are synchronously rotated through the installation of the translation rod 2.
As shown in fig. 6, in the present embodiment, the vibration damping unit 01 effectively isolates vibration in three directions of the optical turret; the two ball bearings 02-1 of the universal joint mechanism 02 are respectively connected with the photoelectric mounting bracket 4 and the transverse rolling bracket 3, and the photoelectric mounting bracket 4 has three translational degrees of freedom without rotational degrees of freedom and the system cannot generate angular disturbance by limiting the degree of freedom of the deep groove ball bearings and the height consistency of the 4 universal joint mechanisms 02. The limiting buffer blocks 01-7 are arranged on the lower side of the photoelectric mounting support 4, and the limiting buffer blocks are used for limiting the movement displacement of the photoelectric turret so as to ensure that the photoelectric system cannot be impacted and collided. The reliability of the system is improved.
As can be seen from the technical scheme, the invention has the following remarkable characteristics:
when the vibration isolation device is applied, four vibration isolation units are adopted to effectively isolate external vibration interference; the coupling effect caused by the common arrangement mode of the shock absorber is relieved through the universal joint mechanism, and the shock absorbing unit effectively avoids collision between various impacts of the system and excessive displacement vibration; and the degrees of freedom of the three angular disturbance directions of the system are limited.
The airborne photoelectric equipment can greatly improve the quality of photoelectric images under the effective vibration reduction condition, and ensure the reliability of the system; according to the scheme, a vibration reduction technology and a three-degree-of-freedom limited motion mechanism are effectively combined by using the three-degree-of-freedom angular displacement free vibration reduction device, so that three angular vibration degrees of freedom can be effectively limited, and the coupling of angular disturbance caused by linear vibration of centrifugal airborne photoelectric equipment is avoided; and the effective isolation of the linear vibration in three directions is completed, the natural frequency is far away from the external interference frequency, and the coupling is effectively released, so that the system achieves the optimal vibration reduction effect.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications and variations could be made by those skilled in the art without departing from the technical principles of the present invention, and such modifications and variations should also be regarded as being within the scope of the invention.
Claims (10)
1. A three degree of freedom angular displacement free vibration damping device comprising: the device comprises a vibration reduction unit (01), a universal joint mechanism (02), an aircraft mounting base (1), a translation rod (2), a transverse rolling bracket (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 the transmission of a vibration source of the aircraft mounting base (1) is damped through the vibration damping unit (01); the upper ball bearing of the universal joint mechanism (02) is fixedly connected with the photoelectric mounting bracket (4), and the lower ball bearing is fixedly connected with the transverse rolling bracket (3), so that two degrees of freedom relative motion are formed between the photoelectric mounting bracket (4) and the transverse rolling bracket (3); two transverse rolling brackets (3) are arranged in parallel, two ends of each transverse rolling bracket (3) are respectively arranged on an aircraft mounting base (1) through deep groove ball bearings I (5), and one degree of freedom is formed between the aircraft mounting base (1) and the transverse rolling brackets (3); two ends of the transverse rolling support (3) are respectively connected with a translation rod (2) through a deep groove ball bearing II (6), and the synchronism of the up-and-down movement of the two transverse rolling supports (3) is realized through the arrangement of the translation rod (2) and the deep groove ball bearing II (6); three degrees of freedom of the photoelectric mounting support are restrained through the arrangement of the transverse rolling support (3) and the universal joint mechanism (02).
2. The three degree of freedom angular displacement free vibration damping device of claim 1 wherein the vibration damping unit (01) comprises: a damper inner sleeve (01-1), a spring damper I (01-2), a spring damper II (01-3), a damper space ring (01-4) and a damper outer sleeve (01-5); the vibration absorber inner sleeve (01-1) is coaxially arranged in the vibration absorber outer sleeve (01-5), two spring vibration absorbers I (01-2) are sleeved on the outer wall of the vibration absorber inner sleeve (01-1) from top to bottom, open-loop grooves are formed in the inner wall of the vibration absorber outer sleeve (01-5), vibration absorber space rings (01-4) are arranged in the annular grooves, the vibration absorber space rings (01-4) separate the spring vibration absorbers I (01-2) from the spring vibration absorbers II (01-3), and the two spring vibration absorbers I (01-2) are respectively positioned above and below the vibration absorber space rings (01-4); 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 fixedly connected with the photoelectric mounting bracket (4), and the lower end of the damper outer sleeve (01-5) is fixedly connected with the aircraft mounting base (1).
3. The three-degree-of-freedom angular displacement free vibration damper according to claim 2, wherein the number of the spring vibration dampers II (01-3) is four, and the spring vibration dampers II are arranged on the outer wall of the damper outer sleeve (01-5) in a circumferentially uniform distribution manner.
4. A three degree of freedom angular displacement free vibration damping device according to claim 3 wherein the vibration damping unit (01) further comprises: the inner ring (01-6) of the shock absorber is arranged at the bottom of the inner sleeve (01-1) of the shock absorber to limit the position of the shock absorber.
5. The three-degree-of-freedom angular displacement free vibration damper according to claim 4, wherein a limit buffer block (01-7) is installed at the bottom of the inner ring (01-6) of the vibration damper.
6. The three degree of freedom angular displacement vibration damping device of claim 5 wherein the gimbal mechanism (02) includes two ball bearings (02-1) and a connecting rod (02-2) connecting the two ball bearings (02-1).
7. The three-degree-of-freedom angular displacement vibration damper according to claim 6, wherein the axial angle between the upper and lower ball bearings (02-1) in the gimbal mechanism (02) is 60 °.
8. The three-degree-of-freedom angular displacement vibration damper according to claim 7, wherein the aircraft mounting base (1) is provided with a deep groove ball bearing I (5), an inner hole of the deep groove ball bearing I (5) is connected with a transverse rolling bracket (3), two ends of the transverse rolling bracket (3) are arranged at an inner hole of a deep groove ball bearing II (6), and the deep groove ball bearing II (6) is connected with a translation rod (2); the deep groove ball bearing I (5) enables the transverse rolling support (3) to have only one degree of freedom, and the four installation end faces of the transverse rolling support (3) are synchronously rotated through the installation of the translation rod (2).
9. The three-degree-of-freedom angular displacement vibration damper according to claim 8, wherein the vibration damper units (01) are arranged in four, circumferentially and uniformly distributed, the four vibration damper units (01) form two groups, and the two groups of vibration damper units (01) are vertically arranged relative to each other, so that the horizontal vibration damper directions are mutually perpendicular, and the vibration damper effects in 3 vertical directions are formed.
10. Use of a three degree of freedom angular displacement free vibration damping device according to any one of claims 1-9 in the field of airborne optoelectronic devices.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310756293.5A CN116923703A (en) | 2023-06-26 | 2023-06-26 | Three-degree-of-freedom angular displacement free vibration damper |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310756293.5A CN116923703A (en) | 2023-06-26 | 2023-06-26 | Three-degree-of-freedom angular displacement free vibration damper |
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| Publication Number | Publication Date |
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| CN116923703A true CN116923703A (en) | 2023-10-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310756293.5A Pending CN116923703A (en) | 2023-06-26 | 2023-06-26 | Three-degree-of-freedom angular displacement free vibration damper |
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| Country | Link |
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| CN (1) | CN116923703A (en) |
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- 2023-06-26 CN CN202310756293.5A patent/CN116923703A/en active Pending
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