CN114017457B - Quasi-zero stiffness vibration isolation device for spacecraft flywheel based on bistable beam - Google Patents
Quasi-zero stiffness vibration isolation device for spacecraft flywheel based on bistable beam Download PDFInfo
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- CN114017457B CN114017457B CN202111189221.4A CN202111189221A CN114017457B CN 114017457 B CN114017457 B CN 114017457B CN 202111189221 A CN202111189221 A CN 202111189221A CN 114017457 B CN114017457 B CN 114017457B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2228/00—Functional characteristics, e.g. variability, frequency-dependence
- F16F2228/06—Stiffness
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2230/00—Purpose; Design features
- F16F2230/14—Ball joints; Spherical support elements
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention provides a quasi-zero stiffness vibration isolation device for a spacecraft flywheel based on a bistable beam, which comprises a plurality of quasi-zero stiffness vibration isolation units, an upper platform and a lower platform, wherein the upper supporting end of each quasi-zero stiffness vibration isolation unit is flexibly hinged with an upper spherical hinge arranged on the circumferential direction of the upper platform, the lower supporting end of each quasi-zero stiffness vibration isolation unit is flexibly hinged with a lower spherical hinge arranged on the circumferential direction of the lower platform, the hinged supporting points of the upper spherical hinge and the lower spherical hinge are alternately arranged along the upper platform and the lower platform in a staggered way, and the spacecraft flywheel is arranged on the upper platform. When the external force acts on the vibration isolation device, the acting force can be distributed to a plurality of quasi-zero stiffness vibration isolation units arranged in the vibration isolation device, unidirectional axial force is transmitted inside the quasi-zero stiffness vibration isolation units, the quasi-zero stiffness vibration isolation units are in a balanced state, and overall stable low-frequency vibration isolation of the vibration isolation device is achieved.
Description
Technical Field
The invention relates to the technical field of vibration isolation, in particular to a micro-vibration quasi-zero stiffness vibration isolation device for a spacecraft flywheel based on a bistable beam.
Background
With the high-speed development of aerospace technology, the requirements of aerospace engineering on the attitude stability and pointing accuracy of a spacecraft are continuously improved. The micro-vibration of the flywheel of the spacecraft has become a bottleneck problem restricting the development of high-performance spacecraft in China. In order to prevent the high-precision load of the spacecraft from being influenced by the micro-vibration environment, a vibration isolation device needs to be designed for a rotating source such as a flywheel. The passive vibration isolation device has the advantages of high reliability, no need of energy input and the like, and is suitable for complex environments such as space and the like.
Some domestic scholars also put forward various flywheel passive vibration isolation schemes and have achieved good effects. Guan Xin and the like provide a composite vibration isolation scheme consisting of a passive vibration isolation rod unit and a tuned mass damper, and achieve good vibration isolation effects (Guan Xin, wang Guangyuan, liang Lu, chen Xiang, tang Shaofan, wang Weigang, cao Dongjing, tu Yonggang, guo Gaofeng, zhang Guobin, zheng steel, space camera low-frequency vibration isolation system and experimental verification [ J ] aerospace return and remote sensing, 2011,32 (06): 53-61.).
However, the method is based on a linear vibration isolation theory, and theoretically and practically, the problems that the low-frequency vibration isolation is difficult due to overlarge static deformation and instability and the vibration isolation is unstable due to the unstable loading direction of a vibration isolation unit exist.
Disclosure of Invention
The invention provides a spacecraft flywheel quasi-zero stiffness vibration isolation device based on bistable beams, aiming at overcoming the defects of unstable vibration isolation and difficult low-frequency vibration isolation in the prior art.
In order to solve the technical problems, the technical scheme of the invention is as follows:
the invention provides a quasi-zero stiffness vibration isolation device for a spacecraft flywheel based on a bistable beam, which is characterized by comprising a plurality of quasi-zero stiffness vibration isolation units, an upper platform and a lower platform, wherein the upper supporting end of each quasi-zero stiffness vibration isolation unit is flexibly hinged with an upper spherical hinge arranged on the circumferential direction of the upper platform, the lower supporting end of each quasi-zero stiffness vibration isolation unit is flexibly hinged with a lower spherical hinge arranged on the circumferential direction of the lower platform, the hinge pivots of the upper spherical hinge and the lower spherical hinge are alternately arranged along the upper platform and the lower platform in a staggered mode, and the spacecraft flywheel is arranged on the upper platform.
In the technical scheme, when the external force acts on the vibration isolation device, the acting force can be distributed to a plurality of quasi-zero stiffness vibration isolation units arranged in the vibration isolation device, unidirectional axial force is transmitted in the quasi-zero stiffness vibration isolation units, and overall stable low-frequency vibration isolation of the vibration isolation device is realized.
Preferably, the device is provided with M quasi-zero stiffness vibration isolation units, wherein M is an even number, M/2 upper flexible hinge bosses are arranged on the upper platform, M/2 lower flexible hinge bosses are arranged on the lower platform, two upper spherical hinges and two lower spherical hinges are respectively arranged on each upper flexible hinge boss and each lower flexible hinge boss, and the upper bearing end and the lower bearing end of each two quasi-zero stiffness vibration isolation units are respectively flexibly hinged with two upper spherical hinges and two lower spherical hinges respectively arranged on each upper flexible hinge boss and each lower flexible hinge boss.
Preferably, the device is provided with 6 quasi-zero rigidity vibration isolation units, 3 upper flexible hinged bosses are arranged on the upper platform, 3 lower flexible hinged bosses are arranged on the lower platform, the 3 upper flexible hinged bosses are uniformly distributed along the circumferential direction of the upper platform, and the lower flexible hinged bosses are uniformly distributed along the circumferential direction of the lower platform. The upper flexible hinge boss and the lower flexible hinge boss are at least provided with two inclined planes, the two upper spherical hinges are arranged on the two inclined planes of the upper flexible hinge boss, the two lower spherical hinges are arranged on the two inclined planes of the lower flexible hinge boss, a connecting line of a hinge fulcrum of the upper spherical hinge and a hinge fulcrum of the lower spherical hinge forms a certain angle with a horizontal plane, the two lower spherical hinges can share one hinge fulcrum, and the two lower spherical hinges can share one hinge fulcrum.
Preferably, the quasi-zero stiffness vibration isolation unit comprises a first bearing, a second bearing, a dowel bar, a first transmission piece, a second transmission piece, a plurality of bistable beams and a shell; the shell is sleeved on the peripheries of the first bearing and the second bearing; two ends of the dowel bar are respectively connected with the inner rings of the first bearing and the second bearing through a first transmission piece; the bistable state roof beam sets up inside the shell, bistable state roof beam middle part is established at the dowel bar periphery through the second driving medium cover, just bistable state roof beam both ends and shell fixed connection.
Preferably, the housing comprises an upper end cover, a lower end cover and a fixer; the upper end cover, the fixer and the lower end cover are sequentially connected, and two ends of the bistable beam are connected with the fixer.
Preferably, the first bearing and the second bearing outer ring are provided with first screw holes, the middle parts of the upper end cover and the lower end cover are provided with hollow holes, the periphery of each hollow hole is provided with a second screw hole matched with the first screw hole, the first bearing is connected with the upper end cover through the first screw holes and the second screw holes, and the second bearing is connected with the lower end cover through the first screw holes and the second screw holes.
Preferably, the fixer is provided with a plurality of pillars along the vertical direction, and the pillars are positioned on the same horizontal line; the end surface of the strut is provided with a screw hole; the middle part of the bistable beam is connected with the dowel bar through a threaded sleeve, and the two ends of the bistable beam are connected with screw holes formed in the end face of the support through screws.
Preferably, the bistable beams are connected with the dowel bars in a parallel mode, and the bistable beams are uniformly distributed by taking the dowel bars as central axes.
Preferably, a connecting hole used for being connected with a spacecraft flywheel is formed in the middle of the upper portion of the upper platform.
Preferably, the top of the first bearing and the top of the second bearing are respectively provided with an adapter for externally connecting an upper spherical hinge and a lower spherical hinge.
In a second aspect, the present invention further provides a method for using a bistable beam-based spacecraft flywheel quasi-zero stiffness vibration isolation device, which is applied to any one of the above schemes, and includes: the spacecraft flywheel is connected to the upper platform, when an external acting force acts on the vibration isolation device, the acting force can be distributed to a plurality of quasi-zero rigidity vibration isolation units connected with the vibration isolation platform, unidirectional axial force is transmitted inside the quasi-zero rigidity vibration isolation units, low-frequency vibration isolation of the vibration isolation device is achieved, and the acting force is effectively prevented from vibrating the spacecraft flywheel.
Compared with the prior art, the technical scheme of the invention has the beneficial effects that: the adoption is by a plurality of quasi-zero rigidity vibration isolation units to and the quasi-zero rigidity vibration isolation device of the spacecraft flywheel based on bistable beam that the vibration isolation platform is constituteed, when external acting force was used in the vibration isolation device, the acting force can be distributed to a plurality of quasi-zero rigidity vibration isolation unit be connected with the vibration isolation platform, the inside transmission folk prescription of quasi-zero rigidity vibration isolation unit is to axial power, and quasi-zero rigidity vibration isolation unit is balanced state, realizes the low frequency vibration isolation to the vibration isolation device overall stability.
Drawings
Fig. 1 is a schematic diagram of a quasi-zero stiffness vibration isolation device of a spacecraft flywheel with bistable beams.
Fig. 2 is a schematic view of a vibration isolation platform.
FIG. 3 is a schematic three-dimensional coordinate diagram of a spacecraft flywheel quasi-zero stiffness vibration isolation device with bistable beams
Fig. 4 is a schematic top coordinate view of a quasi-zero stiffness vibration isolation device for a spacecraft flywheel with bistable beams.
Figure 5 is a perspective view of a quasi-zero stiffness strut.
Figure 6 is a cross-sectional view of a quasi-zero stiffness strut.
Fig. 7 is a schematic diagram of a negative stiffness unit of a bistable beam.
Fig. 8 is a schematic structural view of a bistable beam.
Fig. 9 is a schematic view of the upper end cap.
Fig. 10 is a schematic view of a holder.
FIG. 11 is a schematic view of the lower end cap.
Fig. 12 is a schematic view of a bearing.
The vibration isolation device comprises a 1-quasi-zero stiffness vibration isolation unit, a 101-upper end cover, a 102-fixer, a 1021-strut, a 103-lower end cover, a 104-bistable beam, a 105-first bearing, a 106-second bearing, a 107-first transmission piece, a 108-second transmission piece, a 109-dowel bar, a 2-upper platform, a 3-lower platform, a 4-flywheel connecting hole, a 51-upper flexible hinge boss, a 52-lower flexible hinge boss, a 511-upper spherical hinge, a 521-lower spherical hinge and a 6-adapter.
Detailed Description
The drawings are for illustrative purposes only and are not to be construed as limiting the patent;
for the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product;
it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.
The technical solution of the present invention is further described below with reference to the accompanying drawings and examples.
Example 1
Referring to fig. 1-4, the present embodiment provides a quasi-zero stiffness vibration isolation device for a spacecraft flywheel based on a bistable beam, including a plurality of quasi-zero stiffness vibration isolation units 1, an upper platform 2 and a lower platform 3, an upper support end of the quasi-zero stiffness vibration isolation unit 1 is flexibly hinged to an upper spherical hinge 511 disposed on the circumferential direction of the upper platform 2, a lower support end of the quasi-zero stiffness vibration isolation unit 1 is flexibly hinged to a lower spherical hinge 521 disposed on the circumferential direction of the lower platform 3, and hinge pivots of the upper spherical hinge 511 and the lower spherical hinge 521 are alternately disposed along the upper platform 2 and the lower platform 3, and the spacecraft flywheel is mounted on the upper platform 2.
In this embodiment, the apparatus is provided with 6 quasi-zero stiffness vibration isolation units 1, wherein 6 is an even number, 3 upper flexible hinge bosses 51 are provided on the upper platform 2, 3 lower flexible hinge bosses 52 are provided on the lower platform 3, two upper spherical hinges 511 and two lower spherical hinges 521 are respectively provided on each of the upper flexible hinge bosses 51 and the lower flexible hinge bosses 52, and the upper support end and the lower support end of each of the two quasi-zero stiffness vibration isolation units 1 are respectively flexibly hinged to the two upper spherical hinges 511 and the two lower spherical hinges 521 respectively provided on each of the upper flexible hinge bosses 51 and the lower flexible hinge bosses 52. The 3 upper flexible hinge bosses 51 are evenly distributed along the circumferential direction of the upper platform 2, and the lower flexible hinge bosses 52 are evenly distributed along the circumferential direction of the lower platform 3. The upper flexible hinge boss 51 and the lower flexible hinge boss 52 are at least provided with two inclined planes, the two upper spherical hinges 5 are arranged on the two inclined planes of the upper flexible hinge boss 51, the two lower spherical hinges 511 are arranged on the two inclined planes of the lower flexible hinge boss 52, a certain angle is formed between a connecting line of a hinge fulcrum of the upper spherical hinge 5 and a hinge fulcrum of the lower spherical hinge 511 and a horizontal plane, the two lower spherical hinges 511 can share one hinge fulcrum, and the two lower spherical hinges 511 can share one hinge fulcrum.
In the embodiment, a plurality of quasi-zero stiffness vibration isolation units 1 are connected with a multi-degree-of-freedom vibration isolation platform consisting of an upper platform 2 and a lower platform 3 to form a multi-degree-of-freedom vibration isolation device, so that an effective and stable vibration isolation effect is obtained.
In this embodiment, a connecting hole for connecting with a spacecraft flywheel is formed in the middle above the upper platform 2.
In the specific implementation process, the spacecraft flywheel is connected to the upper platform 2, when external acting force acts on the vibration isolation device, the acting force can be distributed to the multiple quasi-zero stiffness vibration isolation units 1 connected with the multi-degree-of-freedom vibration isolation platform, and unidirectional axial force is transmitted inside the quasi-zero stiffness vibration isolation units 1, so that vibration isolation of multiple degrees of freedom is achieved, and low-frequency vibration isolation of the vibration isolation device is stable integrally.
The upper platform 2, the lower platform 3 and the 6 quasi-zero stiffness vibration isolation units 1 form a six-degree-of-freedom vibration isolation platform; as shown in figure 1, 6 quasi-zero stiffness vibration isolation unitsThe vibration isolation unit 1, the upper platform 2 and the lower platform 3 are connected together through 3 upper flexible connection bosses 51, 3 lower flexible hinge bosses 52, 6 upper spherical hinges 511 and 6 lower spherical hinges 521, and every two quasi-zero stiffness vibration isolation units 1 share one intersection point. As shown in fig. 3, fig. 3 is a schematic three-dimensional coordinate diagram of a quasi-zero stiffness vibration isolation device for a spacecraft flywheel with bistable beams, where a circle radius of an upper platform 2 is R, a circle radius of a lower platform 3 is R, and a height difference between the upper platform 2 and the lower platform 3 is H. Establishing a coordinate system O by taking the mass center of the platform as an origin P x p y p z p As shown in fig. 10. The quasi-zero rigidity vibration isolation unit 1 has the length of
When +>
The relative positions of the six quasi-zero stiffness vibration isolation units 1 of the six-degree-of-freedom vibration isolation platform can be determined accordingly.
The six-degree-of-freedom vibration isolation platform is structurally designed to reduce the overall weight and pursue better stability, and when external acting force acts on the vibration isolation device, the acting force can be distributed to six quasi-zero rigidity vibration isolation units connected with the six-degree-of-freedom vibration isolation platform, so that vibration isolation of multiple degrees of freedom is achieved, and low-frequency vibration isolation stable for the whole vibration isolation device is achieved. Through a series of simplified designs, the weight of the vibration isolation device can be greatly reduced. Four through holes are formed in the center of the upper platform 2 and are used for being connected with a spacecraft flywheel, so that vibration isolation of the flywheel is achieved.
The six-degree-of-freedom vibration isolation platform based on the quasi-zero stiffness vibration isolation unit 1 can eliminate the disturbance amplification phenomenon, improve the low-frequency vibration isolation performance, realize the full-speed vibration isolation of the flywheel, and the radial angular displacement response amplitude can meet the requirement of the pointing accuracy of the moment vector of the momentum of the flywheel.
Example 2
Referring to fig. 5 to 12, the present embodiment provides a quasi-zero stiffness vibration isolation device for a spacecraft flywheel with bistable beams, including a plurality of quasi-zero stiffness vibration isolation units, where the quasi-zero stiffness vibration isolation unit 1 includes a first bearing 105, a second bearing 106, a dowel bar 109, a first transmission member 107, a second transmission member, a plurality of bistable beams 104, and a housing; the outer shell is sleeved on the peripheries of the first bearing 105 and the second bearing 106; two ends of the dowel bar 109 are respectively connected with the inner rings of the first bearing 105 and the second bearing 106 through a first transmission piece 107; the bistable beam 104 is arranged inside the shell, the middle part of the bistable beam 104 is sleeved on the periphery of the dowel bar 109 through a second transmission piece 108, and two ends of the bistable beam 104 are fixedly connected with the shell and form a certain initial angle alpha on the inner wall of the shell.
In this embodiment, a screw is used as the transmission rod 109, and a screw sleeve is used as the transmission member 107.
In this embodiment, the housing includes an upper end cap 101, a lower end cap 103, and a holder 102; the upper end cover 101, the fixer 102 and the lower end cover 103 are connected in sequence, and two ends of the bistable beam 104 are connected with the fixer 102. The upper cap 101, the holder 102 and the lower cap 103 are made of an aluminum alloy material and processed to have a surface roughness of 1.6R.
In this embodiment, the outer rings of the first bearing 105 and the second bearing 106 are provided with first screw holes, the middle parts of the upper end cover 101 and the lower end cover 103 are provided with hollow holes, the periphery of each hollow hole is provided with a second screw hole matched with the first screw hole, the first bearing 105 is connected with the upper end cover 101 through the first screw hole and the second screw hole, and the second bearing 106 is connected with the lower end cover 103 through the first screw hole and the second screw hole.
In this embodiment, 2 support columns 1021 are arranged on the fixer 102 along the vertical direction, and the 2 support columns 1021 are located on the same horizontal line; a screw hole is formed in the end face of the support 1021; the middle part of the bistable beam 104 is connected with the dowel bar 109 through a threaded sleeve, and two ends of the bistable beam 104 are connected with screw holes arranged on the end surface of the support 1021 through screws.
In this embodiment, the top of the first bearing 105 and the top of the second bearing 106 are respectively provided with an adapter 6 for externally connecting and separating the upper spherical hinge 511 and the lower spherical hinge 521. Through the adapter interface 6, the quasi-zero stiffness vibration isolation unit 1 can be connected to a vibration isolation platform with multiple degrees of freedom to realize a vibration isolation system with multiple degrees of freedom, so that vibration isolation with multiple degrees of freedom is realized.
In this embodiment, the bistable beams 104 are connected with the dowel bars 109 in parallel, and the bistable beams 104 are uniformly distributed by using the dowel bars 109 as central axes, so as to improve the stability of the vibration isolation system.
In a specific implementation process, when the quasi-zero stiffness vibration isolation unit bears a vibration-isolated object, the vibration isolation device distributes an acting force to the quasi-zero stiffness vibration isolation unit, the first bearing 105 and the second bearing 106 transmit a unidirectional axial force to the bistable beam 104 through the dowel bar, the bistable beam 104 is stressed to deform, and meanwhile, the first transmission piece 107 and the second transmission piece 108 move relatively along the first bearing 105 or the first transmission piece 107 and the second transmission piece 108 move relatively along the center of the second bearing 106; the first transmission piece 107, the second transmission piece 108 and the bistable beam 104 reach balance at the position of the bistable beam 104 with the maximum negative rigidity value, and the quasi-zero rigidity vibration isolation unit 1 is in a balance state and isolates low-frequency vibration interference.
Aiming at the low-frequency vibration isolation requirement of micro-vibration of a spacecraft, the invention designs a novel bistable beam 104 type quasi-zero stiffness vibration isolation unit 1 by analyzing the negative stiffness characteristic of the bistable beam 104. Under the conditions of small amplitude of vibration exciting force and proper damping ratio, the effective vibration isolation frequency and the resonance peak value of the novel quasi-zero stiffness vibration isolation unit 1 are far lower than those of an equivalent linear vibration isolation system, and the low-frequency vibration isolation unit is very suitable for solving the problem of low-frequency vibration isolation of micro-vibration.
The same or similar reference numerals correspond to the same or similar parts;
the terms describing positional relationships in the drawings are for illustrative purposes only and are not to be construed as limiting the patent;
it should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (6)
1. A spacecraft flywheel quasi-zero stiffness vibration isolation device based on bistable beams is characterized by comprising a plurality of quasi-zero stiffness vibration isolation units (1), an upper platform (2) and a lower platform (3), wherein the upper supporting ends of the quasi-zero stiffness vibration isolation units (1) are flexibly hinged with upper spherical hinges (511) arranged on the periphery of the upper platform (2), the lower supporting ends of the quasi-zero stiffness vibration isolation units (1) are flexibly hinged with lower spherical hinges (521) arranged on the periphery of the lower platform (3), the hinging fulcrums of the upper spherical hinges (511) and the lower spherical hinges (521) are arranged alternately along the upper platform (2) and the lower platform (3), and a spacecraft flywheel is arranged on the upper platform (2);
the quasi-zero stiffness vibration isolation unit (1) comprises a first bearing (105), a second bearing (106), a dowel bar (109), a first transmission piece (107), a second transmission piece (108), a plurality of bistable beams (104) and a shell; the outer shell is sleeved on the peripheries of the first bearing (105) and the second bearing (106); two ends of the dowel bar (109) are respectively connected with the inner rings of the first bearing (105) and the second bearing (106) through a first transmission piece (107); the bistable beam (104) is arranged inside the shell, the middle part of the bistable beam (104) is sleeved on the periphery of the dowel bar (109) through a second transmission piece (108), and two ends of the bistable beam (104) are fixedly connected with the shell; the bistable beam (104) is connected with a dowel bar (109) in a parallel mode, and the bistable beam (104) is uniformly distributed by taking the dowel bar (109) as a central axis;
the shell comprises an upper end cover (101), a lower end cover (103) and a fixer (102); the upper end cover (101), the fixer (102) and the lower end cover (103) are sequentially connected, and two ends of the bistable beam (104) are connected with the fixer (102);
2 supporting columns (1021) are arranged on the fixer (102) along the vertical direction, and the 2 supporting columns (1021) are positioned on the same horizontal line; the end surface of the strut (1021) is provided with a screw hole; the middle part of the bistable beam (104) is connected with the dowel bar (109) through a threaded sleeve, and the two ends of the bistable beam (104) are connected with screw holes arranged on the end surface of the support (1021) through screws.
2. The quasi-zero stiffness vibration isolation device of the bistable beam-based spacecraft flywheel, according to claim 1, is provided with M quasi-zero stiffness vibration isolation units (1), wherein M is an even number, M/2 upper flexible hinge bosses (51) are provided on the upper platform (2), M/2 lower flexible hinge bosses (52) are provided on the lower platform (3), two upper spherical hinges (511) and two lower spherical hinges (521) are respectively provided on each upper flexible hinge boss (51) and each lower flexible hinge boss (52), and the upper bearing ends and the lower bearing ends of every two quasi-zero stiffness vibration isolation units (1) are flexibly hinged to two upper spherical hinges (511) and two lower spherical hinges (521) respectively provided on each upper flexible hinge boss (51) and each lower flexible hinge boss (52).
3. The quasi-zero stiffness vibration isolation device for the spacecraft flywheel based on the bistable beam according to claim 2, wherein the device is provided with 6 quasi-zero stiffness vibration isolation units (1), the upper platform (2) is provided with 3 upper flexible hinge bosses (51), the lower platform (3) is provided with 3 lower flexible hinge bosses (52), the 3 upper flexible hinge bosses (51) are uniformly distributed along the circumferential direction of the upper platform (2), and the lower flexible hinge bosses (52) are uniformly distributed along the circumferential direction of the lower platform (3).
4. The quasi-zero stiffness vibration isolation device of the bistable beam-based spacecraft flywheel, according to claim 3, wherein first screw holes are formed in outer rings of the first bearing (105) and the second bearing (106), hollow holes are formed in the middle parts of the upper end cover (101) and the lower end cover (103), second screw holes matched with the first screw holes are formed in the periphery of the hollow holes, the first bearing (105) is connected with the upper end cover (101) through the first screw holes and the second screw holes, and the second bearing (106) is connected with the lower end cover (103) through the first screw holes and the second screw holes.
5. The quasi-zero stiffness vibration isolation device for the spacecraft flywheel based on the bistable beam as claimed in claim 1, wherein a connecting hole for connecting with the spacecraft flywheel is formed in the middle above the upper platform (2).
6. The quasi-zero stiffness vibration isolation device for the bistable beam-based spacecraft flywheel of claim 2, wherein the top of the first bearing (105) and the top of the second bearing (106) are respectively provided with an adapter port (6) for externally connecting an upper spherical hinge (511) and a lower spherical hinge (521).
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| CN105041961B (en) * | 2015-07-08 | 2017-01-25 | 西安交通大学 | Six-degree-of-freedom quasi-zero-rigidity vibration isolation system based on Stewart platform |
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