CN116198748B - Synchronous vibration isolation and energy harvesting device suitable for on-orbit capture and on-orbit capture spacecraft - Google Patents
Synchronous vibration isolation and energy harvesting device suitable for on-orbit capture and on-orbit capture spacecraft Download PDFInfo
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- CN116198748B CN116198748B CN202310196047.9A CN202310196047A CN116198748B CN 116198748 B CN116198748 B CN 116198748B CN 202310196047 A CN202310196047 A CN 202310196047A CN 116198748 B CN116198748 B CN 116198748B
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- 238000002955 isolation Methods 0.000 title claims abstract description 115
- 238000003306 harvesting Methods 0.000 title claims abstract description 54
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- 239000011664 nicotinic acid Substances 0.000 claims description 16
- 230000003068 static effect Effects 0.000 claims description 4
- 230000006870 function Effects 0.000 abstract description 6
- 238000011161 development Methods 0.000 abstract description 2
- 230000007613 environmental effect Effects 0.000 abstract 1
- 230000033001 locomotion Effects 0.000 description 5
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- 230000009286 beneficial effect Effects 0.000 description 2
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- 229910052451 lead zirconate titanate Inorganic materials 0.000 description 2
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- HFGPZNIAWCZYJU-UHFFFAOYSA-N lead zirconate titanate Chemical compound [O-2].[O-2].[O-2].[O-2].[O-2].[Ti+4].[Zr+4].[Pb+2] HFGPZNIAWCZYJU-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G4/00—Tools specially adapted for use in space
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02N—ELECTRIC MACHINES NOT OTHERWISE PROVIDED FOR
- H02N2/00—Electric machines in general using piezoelectric effect, electrostriction or magnetostriction
- H02N2/18—Electric machines in general using piezoelectric effect, electrostriction or magnetostriction producing electrical output from mechanical input, e.g. generators
- H02N2/186—Vibration harvesters
- H02N2/188—Vibration harvesters adapted for resonant operation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G4/00—Tools specially adapted for use in space
- B64G2004/005—Robotic manipulator systems for use in space
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Abstract
The invention belongs to the field of aerospace technical equipment, and particularly relates to a synchronous vibration isolation and energy harvesting device suitable for on-orbit capture and an on-orbit capture spacecraft. The synchronous vibration isolation and energy harvesting device suitable for on-orbit capture comprises a capture structure, a vibration isolation structure and an energy harvesting structure. The capture structure is used to capture a moving object and generate vibrations. The vibration isolation structure is used for damping the capture structure, and the vibration damping structure comprises a vibration isolation platform connected with the capture structure and a vibration isolation assembly connected with the vibration isolation platform. The energy harvesting structure is connected with the vibration isolation platform and is arranged at intervals with the vibration isolation assembly so as to convert mechanical energy into electric energy. The invention can realize vibration isolation and energy collection of satellites. The invention has the functions of synchronous vibration isolation and energy harvesting, not only can effectively control low-frequency vibration, but also can collect vibration energy to supply power for wireless sensors with different functions, effectively reduces the harm to satellites caused by vibration, and meets the requirements of environmental protection and sustainable development.
Description
Technical Field
The invention belongs to the field of aerospace technical equipment, and particularly relates to a synchronous vibration isolation and energy harvesting device suitable for on-orbit capture and an on-orbit capture spacecraft.
Background
In recent years, with the rapid development of space technology, in-orbit satellites and spacecraft having functions of satellite assembly, maintenance, recovery, and removal of space debris have received a lot of attention. The acquisition structure plays an important role in the operation of these in-orbit satellites and spacecraft, and when the spacecraft actively acquires the target, a system consisting of the spacecraft, the target and the acquisition structure is called an in-orbit acquisition spacecraft.
Because some faulty satellites and space debris lack some or all of the movement information, the movement information includes velocity, acceleration, and rotational angular velocity. There is always a collision or vibration interaction between the capture structure and the target. This collision and vibration may cause the satellite or spacecraft to experience detrimental vibratory or drifting movements along its flight trajectory. Therefore, the efficient and rapid isolation technology of the harmful vibration is important for the safe and stable operation of the satellite. If the vibration energy can be converted into available electric energy, various low-power small-sized sensors (sensors such as sound, light, temperature, speed and the like) in satellites or spacecrafts can be powered, dependence on solar energy, nuclear energy and chemical energy systems is reduced, the types of aviation power generation systems are expanded, and the cost for integrating and packaging with electronic systems is reduced by utilizing the small-sized energy harvester.
Disclosure of Invention
The embodiment of the application aims to provide a synchronous vibration isolation and energy harvesting device suitable for on-orbit capture, which aims to solve the problem of how to reduce the vibration interference of a target object to a satellite and synchronously collect energy.
In order to achieve the above purpose, the application adopts the following technical scheme:
In a first aspect, a synchronous vibration isolation and energy harvesting device suitable for on-orbit capture is provided, comprising:
a capturing structure for capturing a moving object and generating vibration; and
The vibration isolation structure is used for damping the capturing structure and comprises a vibration isolation platform connected with the capturing structure, a vibration isolation assembly connected with the vibration isolation platform and an energy harvesting structure connected with the vibration isolation platform and arranged at intervals with the vibration isolation assembly;
The capture structure is used for transmitting mechanical vibration of the target object to the vibration isolation platform, the vibration isolation assembly is used for vibration reduction of the vibration isolation platform, and the energy harvesting structure vibrates along with the vibration isolation platform so as to convert mechanical energy into electric energy.
In some embodiments, the energy harvesting structure includes a piezoelectric beam, a first magnet, and a second magnet disposed opposite to the first magnet at intervals and repulsive to the first magnet, one end of the piezoelectric beam is fixedly connected with the vibration isolation platform, and the other end of the piezoelectric beam is disposed opposite to the vibration isolation platform in a suspended manner and is connected with the second magnet.
In some embodiments, the piezoelectric beam includes a base layer and a piezoelectric deformation layer disposed on the base layer for converting mechanical energy into electrical energy, and the second magnet is coupled to the base layer.
In some embodiments, the energy harvesting structure further comprises a piezoelectric box connected to the vibration isolation platform, the first magnet and the piezoelectric beam are both housed in the piezoelectric box, and the first magnet and the piezoelectric beam are both connected to an inner wall of the piezoelectric box.
In some embodiments, the first magnets are arranged in a spacing of two, both of the first magnets are repulsive to the second magnets, and the second magnets are located between the two first magnets.
In some embodiments, the second magnet is equidistant from the two first magnets.
In some embodiments, the vibration isolation assembly includes an articulated arm and two intersecting arms that are connected in a crossed and rotated manner, two articulated arms are respectively connected to two ends of any one of the intersecting arms, one end of any one of the intersecting arms is connected to the vibration isolation platform in a rotated manner through the articulated arm, and the other end of any one of the intersecting arms is connected to an external structural member in a rotated manner through the articulated arm.
In some embodiments, the vibration isolation assembly further includes a restoring member having an elastic restoring force, the two hinged arms and the two intersecting arms located on the same side of the switching point of the two intersecting arms form a bionic quadrilateral together, the restoring member is located in the bionic quadrilateral, and two ends of the restoring member are respectively connected with two sides of the bionic quadrilateral.
In some embodiments, the capturing structure includes two manipulators for gripping the target object, and one end of each manipulator is connected to the vibration isolation platform.
In a second aspect, an on-orbit capture spacecraft is provided, which comprises the synchronous vibration isolation and energy harvesting device suitable for on-orbit capture, the on-orbit capture spacecraft further comprises a satellite and a connecting arm, one end of the connecting arm is connected with the satellite, and the other end of the connecting arm is connected with the vibration isolation assembly.
The application has the beneficial effects that: the synchronous vibration isolation and energy harvesting device suitable for on-orbit capture comprises a capturing structure, a vibration isolation structure and an energy harvesting structure, wherein the capturing structure is used for capturing space debris in motion and inevitably generating harmful vibration. The vibration isolation structure is used for weakening vibration and converting mechanical energy into electric energy through the energy harvesting structure, so that synchronous vibration isolation and energy harvesting of the vibration are realized.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments or exemplary technical descriptions will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained according to these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 is a schematic perspective view of an on-orbit capture spacecraft provided by an embodiment of the application;
FIG. 2 is a schematic structural view of a synchronous vibration isolation and energy harvesting device suitable for on-orbit capture of the on-orbit capture spacecraft of FIG. 1;
FIG. 3 is a schematic cross-sectional view of the energy harvesting structure of FIG. 2;
FIG. 4 is a schematic cross-sectional view of the energy harvesting structure of the alternative embodiment of FIG. 2.
Wherein, each reference sign in the figure:
100. Capturing a spacecraft on orbit; 101. space debris; 102. a connecting arm; 300. a capture structure; 301. a manipulator; 200. a satellite; 400. a vibration isolation structure; 401. a vibration isolation platform; 402. a vibration isolation assembly; 403. a reset member; 404. an energy harvesting structure; 4021. a cross arm; 4022. an articulated arm; 4023. a bionic quadrilateral; 500. a piezoelectric beam; 502. a piezoelectric deformation layer; 501. a base layer; 4041. a first magnet; 4042. a second magnet; 4044. a piezoelectric cassette;
Detailed Description
The present application will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present application more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the application.
It will be understood that when an element is referred to as being "mounted" or "disposed" on another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly or indirectly connected to the other element. The orientation or positional relationship indicated by the terms "upper", "lower", "left", "right", etc. are based on the orientation or positional relationship shown in the drawings, are for convenience of description only, and are not intended to indicate or imply that the apparatus or element in question must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the application, and the specific meaning of the terms described above will be understood by those of ordinary skill in the art as appropriate. The terms "first," "second," and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features. The meaning of "a plurality of" is two or more, unless specifically defined otherwise.
Referring to fig. 1 to 3, an embodiment of the present application provides a synchronous vibration isolation and energy harvesting device suitable for in-orbit capture, which is connected to a satellite 200 or a spacecraft and is used for capturing a target object moving in space, namely space debris 101, and collecting energy. Space debris 101 includes debris from the detector, debris from the asteroid, and a wide variety of space debris, which have complex trajectories and velocities.
Referring to fig. 1 to 3, a synchronous vibration isolation and energy harvesting device suitable for on-orbit capture includes a capture structure 300 and a vibration isolation structure 400. The capture structure 300 is used to capture a moving object. It will be appreciated that the capture structure 300 actively picks up or grips the moving space debris 101, preventing the space debris 101 from damaging the satellite 200, while the capture structure 300 collides with the space debris 101 and vibrates. The vibration isolation structure 400 is used to damp vibration of the capture structure 300 to block conduction of the vibration. The vibration reduction structure comprises a vibration isolation platform 401 connected with the capturing structure 300, a vibration isolation assembly 402 connected with the vibration isolation platform 401, and an energy harvesting structure 404 connected with the vibration isolation platform 401 and arranged at intervals with the vibration isolation assembly 402. It will be appreciated that vibrations generated between the capture structure 300 and the space debris 101 are conducted to the vibration isolation platform 401, which in turn conducts the vibration isolation platform 401 to the vibration isolation assembly 402. The energy harvesting structure 404 is connected to the vibration isolation platform 401 and vibrates together with the vibration isolation platform 401 to convert mechanical energy into electrical energy, so as to supply power to low-power electronic devices on the satellite 200 or the spacecraft, where the low-power electronic devices may be sensors for sound, light, temperature, speed, and the like. One end of the vibration isolation assembly 402 is connected with the vibration isolation platform 401, the other end of the vibration isolation assembly 402 is connected with the satellite 200, and the generated vibration can be weakened through the vibration isolation platform 401 and the vibration isolation assembly 402, so that the interference of the vibration on the flight of the satellite 200 is reduced.
Referring to fig. 1 to 3, the synchronous vibration isolation and energy harvesting device suitable for on-orbit capturing according to the present embodiment includes a capturing structure 300, a vibration isolation structure 400, and an energy harvesting structure 404, where the capturing structure 300 is used for capturing the moving space debris 101 and inevitably generates harmful vibration. Vibration isolation structure 400 is used to attenuate vibrations and convert mechanical energy to electrical energy via energy harvesting structure 404, which provides a barrier to vibrations and energy harvesting.
It is appreciated that the converted and collected electric energy can supplement the self-energy of the satellite 200, so as to improve the disadvantages of short service life, frequent charge/discharge and frequent replacement of the satellite 200.
Referring to fig. 1 to 3, in some embodiments, the energy harvesting structure 404 includes a piezoelectric beam 500, a first magnet 4041, and a second magnet 4042 disposed opposite to the first magnet 4041 at a distance and repellent to the first magnet 4041, one end of the piezoelectric beam 500 is fixedly connected to the vibration isolation platform 401, and the other end of the piezoelectric beam 500 is disposed opposite to the vibration isolation platform 401 in a suspended manner and is connected to the second magnet 4042. The first magnet 4041 and the second magnet 4042 have a certain distance therebetween, and the line connecting the first magnet 4041 and the second magnet 4042 is parallel to the axial direction of the piezoelectric beam 500.
Referring to fig. 1 to 3, alternatively, the piezoelectric beam 500 generates electric energy using a positive piezoelectric effect, which is a phenomenon in which electric polarization is generated due to deformation. When a physical pressure is applied to the piezoelectric material, the electric dipole moment in the material body becomes shorter due to compression, and the piezoelectric material is resistant to the change, and an equal amount of positive and negative charges are generated on opposite surfaces of the material so as to keep the same. This phenomenon of electrical polarization due to deformation is called "positive piezoelectric effect". The positive piezoelectric effect is essentially the process of converting mechanical energy into electrical energy.
Referring to fig. 1 to 3, after the space debris 101 is captured by the capturing structure 300, the end of the piezoelectric beam 500 provided with the second magnet 4042 vibrates along with the vibration isolation platform 401 and deforms, so as to generate electric energy, and the magnetic field of the first magnet 4041 and the magnetic field of the second magnet 4042 on the piezoelectric beam 500 affect each other and form a nonlinear monostable system. Compared with the common spring-mass-damping vibration isolator and the quasi-zero rigid vibration isolator, the monostable system has lower resonant frequency, and the problems of structural instability caused by the chaotic behavior of the quasi-zero rigid vibration isolator, low load capacity when reaching negative rigidity and the like can be avoided. In addition, the monostable system can improve the vibration damping performance in a high excitation frequency area, and can further improve the broadband vibration damping performance. Compared with a device with an linear energy collection mechanism, the synchronous vibration isolation and energy harvesting device of the monostable system, which is suitable for on-orbit capture, can widen the bandwidth and improve the low-frequency energy output. Thereby realizing energy harvesting and vibration reduction at the same time.
In some embodiments, the piezoelectric beam 500 includes a base layer 501 and a piezoelectric deformation layer 502 disposed on the base layer 501 for converting mechanical energy into electrical energy, and the second magnet 4042 is coupled to the base layer 501. The piezoelectric deformation layer 502 vibrates with the base layer 501 and is elastically deformed, thereby converting mechanical energy into electrical energy. The piezoelectric deformation layer 502 includes two stacked layers of lead zirconate titanate (PZT, pbZrxTi1-xO 3).
Referring to fig. 1 to 3, alternatively, two surfaces of the substrate layer 501 opposite to each other are provided with piezoelectric deformation layers 502, and a plane defined by a vibration track of the substrate layer 501 is perpendicular to the surfaces of the two piezoelectric deformation layers 502.
Alternatively, the first magnet 4041 is a permanent magnet, a static magnet, or a constant magnet.
Alternatively, the second magnet 4042 is a permanent magnet, a static magnet, or a constant magnet.
In some embodiments, the energy harvesting structure 404 further comprises a piezoelectric box 4044 connected to the vibration isolation platform 401, the first magnet 4041 and the piezoelectric beam 500 are both contained in the piezoelectric box 4044, and the first magnet 4041 and the piezoelectric beam 500 are both connected to an inner wall of the piezoelectric box 4044. The first magnet 4041, the second magnet 4042, and the piezoelectric beam 500 may be shielded by a piezoelectric capsule 4044.
Referring to fig. 4, in some embodiments, two first magnets 4041 are arranged at intervals, the two first magnets 4041 repel the second magnets 4042, and the second magnets 4042 are located between the two first magnets 4041, that is, the connection line of the two first magnets 4041 is perpendicular to the axial direction of the piezoelectric beam 500. The two first magnets 4041 and the second magnets 4042 repel each other, so that a multistable system is formed, and the repulsive forces of the two first magnets 4041 and the second magnets 4042 cancel each other, so that the piezoelectric beam 500 can be restored to a balanced static state as soon as possible, and the influence of vibration of the piezoelectric beam 500 on the flight of the satellite 200 is reduced.
Referring to fig. 4, in some embodiments, the second magnet 4042 is equidistant from the two first magnets 4041, thereby maximizing power generation and timely resetting the piezoelectric beam 500.
Referring to fig. 1 to 3, in some embodiments, the vibration isolation assembly 402 includes an articulated arm 4022 and two intersecting arms 4021 that are connected by intersecting and rotating, two intersecting arms 4022 are respectively connected to two ends of each intersecting arm 4021 in an adapting manner, one end of each intersecting arm 4021 is rotatably connected to the vibration isolation platform 401 through the articulated arm 4022, and the other end of each intersecting arm 4021 is rotatably connected to an external structural member through the articulated arm 4022. By the cooperation of the cross arm 4021 and the hinge arm 4022, the influence of vibration on the satellite 200 can be reduced. It will be appreciated that the two cross arms 4021 are open, the vibration isolation platform 401 is proximate to the satellite 200, the two cross arms 4021 are closed, and the vibration isolation platform 401 is distal to the satellite 200, such that the energy harvesting structure 404 converts mechanical energy to electrical energy.
In some embodiments, the vibration isolation assembly 402 further includes a restoring member 403 having an elastic restoring force, where the two articulated arms 4022 and the two intersecting arms 4021 that are located on the same side of the switching point of the two intersecting arms together form a bionic quadrilateral 4023, it is understood that two bionic quadrilaterals 4023 are formed together, the restoring member 403 is located in one of the bionic quadrilaterals 4023, and two ends of the restoring member 403 are respectively connected to two sides of the bionic quadrilateral 4023. It can be appreciated that the restoring member 403 is elastically deformed according to the shape of the bionic quadrilateral 4023. Two ends of the reset element 403 are respectively connected with two articulated arms 4022, or two ends of the reset element 403 are respectively connected with two cross arms 4021, or one end of the reset element 403 is connected with one cross arm 4021, and the other end of the reset element 403 is connected with one articulated arm 4022.
Optionally, a reset element 403 is disposed in each bionic quadrilateral 4023.
Optionally, the bionic quadrilateral 4023 is a quadrilateral structure with nonlinear rigidity and damping, which is inspired by the body motion and body structure of birds and is designed through calculation of geometric relations.
Referring to fig. 1 to 3, alternatively, the reset element 403 is a tube spring, one end of the tube spring is connected to the junction between one of the cross arms 4021 and one of the hinge arms 4022, and the other end of the tube spring is connected to the junction between the other cross arm 4021 and the other hinge arm 4022. When the vibration isolation platform 401 approaches the satellite 200, the tube spring is compressed and deformed; when the vibration isolation platform 401 is far away from the satellite 200, the tube springs are stretched and deformed, and the vibration isolation platform 401 can reciprocate relative to the satellite 200 through the tube springs, so that vibration isolation is realized, transmission of vibration to the satellite 200 is reduced, and the energy harvesting structure 404 is enabled to continuously convert mechanical energy into electric energy.
Referring to fig. 1 to 3, in some embodiments, the capturing structure 300 includes two manipulators 301 for gripping the target object, and one end of each manipulator 301 is connected to the vibration isolation platform 401. The manipulator 301 is controlled by a controller and is capable of capturing the moving space debris 101.
Alternatively, the two cross arms 4021 may be rotationally coupled by a screw and nut fit, or the articulating arm 4022 may be rotationally coupled to the cross arm 4021, or the articulating arm 4022 may be rotationally coupled to an external structure.
Referring to fig. 1 to 3, the present invention further provides an on-orbit capturing spacecraft 100, where the on-orbit capturing spacecraft 100 includes a synchronous vibration isolation and energy harvesting device suitable for on-orbit capturing, and the specific structure of the synchronous vibration isolation and energy harvesting device suitable for on-orbit capturing refers to the above embodiment, and since the on-orbit capturing spacecraft 100 adopts all the technical solutions of all the embodiments, all the beneficial effects brought by the technical solutions of all the embodiments are also provided, and are not repeated herein.
In some embodiments, the on-orbit capture spacecraft 100 further comprises a satellite 200 and a connection arm 102, one end of the connection arm 102 is connected to the satellite 200, and the other end of the connection arm 102 is connected to the vibration isolation assembly 402.
Alternatively, two articulated arms 4022 are pivotally connected to one end of the connecting arm 102.
Referring to fig. 1 to 3, the on-orbit capture spacecraft 100 provided in the present embodiment has a synchronous vibration isolation and energy harvesting function, and the synchronous vibration isolation and energy harvesting device suitable for on-orbit capture includes a vibration isolation assembly 402 having a bionic quadrilateral 4023 and an energy harvesting structure 404 having a nonlinear monostable system. Therefore, the low-frequency vibration can be effectively controlled, vibration energy is collected to supply power for wireless sensors with different functions, the damage to the satellite 200 caused by the vibration is effectively reduced, and the satellite is environment-friendly and sustainable. The vibration isolation structure of the bionic quadrilateral 4023 is used for further improving the broadband vibration reduction performance under low-frequency periodic excitation, the vibration reduction capability under pulse amplitude can be improved under pulse excitation, broadband energy capture can be realized while vibration isolation is performed, two functions are realized at the same time node, and the efficiency is high.
The foregoing is merely an alternative embodiment of the present application and is not intended to limit the present application. Various modifications and variations of the present application will be apparent to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.
Claims (8)
1. A synchronous vibration isolation and energy harvesting device suitable for on-orbit capture, comprising:
a capturing structure for capturing a moving object and generating vibration;
The vibration isolation structure is used for damping the capture structure and comprises a vibration isolation platform connected with the capture structure and a vibration isolation assembly connected with the vibration isolation platform; and
The energy harvesting structure is connected with the vibration isolation platform and is arranged at intervals with the vibration isolation assembly;
The capture structure is used for transmitting mechanical vibration of the target object to the vibration isolation platform, the vibration isolation assembly is used for damping vibration of the vibration isolation platform, and the energy harvesting structure vibrates together with the vibration isolation platform so as to convert mechanical energy into electric energy;
the energy harvesting structure comprises a piezoelectric beam, a first magnet and a second magnet which is arranged opposite to the first magnet at intervals and is repulsed with the first magnet, one end of the piezoelectric beam is fixedly connected with the vibration isolation platform, and the other end of the piezoelectric beam is arranged in a suspending manner opposite to the vibration isolation platform and is connected with the second magnet;
The first magnets are arranged at intervals, the two first magnets repel the second magnets, the second magnets are arranged between the two first magnets, the repulsive force of the two first magnets and the repulsive force of the second magnets counteract each other, and the piezoelectric beam is restored to a balanced static state, so that the influence of vibration of the piezoelectric beam on satellites is reduced.
2. The synchronous vibration isolation and energy harvesting device suitable for on-orbit capture of claim 1, wherein: the piezoelectric beam comprises a basal layer and a piezoelectric deformation layer, wherein the piezoelectric deformation layer is arranged on the basal layer and used for converting mechanical energy into electric energy, and the second magnet is connected with the basal layer.
3. The synchronous vibration isolation and energy harvesting device suitable for on-orbit capture of claim 1, wherein: the energy harvesting structure further comprises a piezoelectric box connected with the vibration isolation platform, the first magnet and the piezoelectric beam are contained in the piezoelectric box, and the first magnet and the piezoelectric beam are connected with the inner wall of the piezoelectric box.
4. A synchronous vibration isolation and energy harvesting device suitable for on-orbit capture as claimed in any one of claims 1 to 3, wherein: the distances from the second magnet to the two first magnets are equal.
5. A synchronous vibration isolation and energy harvesting device suitable for on-orbit capture as claimed in any one of claims 1 to 3, wherein: the vibration isolation assembly comprises an articulated arm and two crossed arms which are arranged in a crossing mode and are rotationally connected, two articulated arms are respectively connected to two ends of each crossed arm in a switching mode, one end of each crossed arm is rotationally connected with the vibration isolation platform through the articulated arm, and the other end of each crossed arm is rotationally connected with an external structural member through the articulated arm.
6. The synchronous vibration isolation and energy harvesting device suitable for on-orbit capture of claim 5, wherein: the vibration isolation assembly further comprises a reset piece with elastic restoring force, wherein the two hinge arms and the two cross arms are located on the same side of the switching point of the two cross arms to form a bionic quadrilateral together, the reset piece is located in the bionic quadrilateral, and two ends of the reset piece are respectively connected with two sides of the bionic quadrilateral.
7. A synchronous vibration isolation and energy harvesting device suitable for on-orbit capture as claimed in any one of claims 1 to 3, wherein: the capture structure comprises two manipulators for clamping the target object, and one ends of the two manipulators are connected with the vibration isolation platform.
8. An on-orbit capture spacecraft comprising a synchronous vibration isolation and energy harvesting device according to any of claims 1-7, said on-orbit capture spacecraft further comprising a satellite and a connecting arm, one end of said connecting arm being connected to said satellite and the other end of said connecting arm being connected to said vibration isolation assembly.
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Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001301699A (en) * | 2000-04-20 | 2001-10-31 | Natl Space Development Agency Of Japan | Near flight type space robot and space maneuver operating system using the same |
| KR101301695B1 (en) * | 2012-07-27 | 2013-08-30 | 대구가톨릭대학교산학협력단 | Energy harvester |
| CN103354434A (en) * | 2013-07-02 | 2013-10-16 | 天津大学 | Bistable piezoelectric cantilever beam vibration energy collector |
| CN104836478A (en) * | 2015-05-19 | 2015-08-12 | 北京理工大学 | Piezoelectric-electromagnetic composite low-frequency broadband energy harvester |
| CN108183626A (en) * | 2018-01-08 | 2018-06-19 | 中北大学 | Power generation screw based on magnetoelectricity-Piezoelectric anisotropy formula structure |
| CN108372941A (en) * | 2018-02-05 | 2018-08-07 | 西北工业大学深圳研究院 | A kind of space junk break catching apparatus with energy absorption function |
| CN111015720A (en) * | 2019-11-29 | 2020-04-17 | 中国空间技术研究院 | Super-large flexible capturing device for capturing and clearing space debris |
| CN210693802U (en) * | 2019-12-05 | 2020-06-05 | 广州大学 | Highway vibration piezoelectricity, magnetoelectricity composite power generation device |
| CN111814277A (en) * | 2020-08-24 | 2020-10-23 | 西北工业大学 | Vibration isolation platform and dynamic model construction method thereof |
| CN113044249A (en) * | 2021-04-19 | 2021-06-29 | 北京理工大学 | Space debris capturing and despinning system based on damper |
| CN113060308A (en) * | 2021-02-25 | 2021-07-02 | 北京科技大学 | Space capturing vibration damper for starship mechanical arm |
| CN215420129U (en) * | 2021-04-16 | 2022-01-04 | 苏州市职业大学 | Vibrating mechanical energy power generation device |
| WO2022090774A1 (en) * | 2020-10-29 | 2022-05-05 | Clearspace Sa | Capture system adapted to capture space objects, in particular for recovery or deorbiting purposes |
| CN115057003A (en) * | 2022-05-27 | 2022-09-16 | 北京空间飞行器总体设计部 | Robot satellite |
-
2023
- 2023-02-24 CN CN202310196047.9A patent/CN116198748B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001301699A (en) * | 2000-04-20 | 2001-10-31 | Natl Space Development Agency Of Japan | Near flight type space robot and space maneuver operating system using the same |
| KR101301695B1 (en) * | 2012-07-27 | 2013-08-30 | 대구가톨릭대학교산학협력단 | Energy harvester |
| CN103354434A (en) * | 2013-07-02 | 2013-10-16 | 天津大学 | Bistable piezoelectric cantilever beam vibration energy collector |
| CN104836478A (en) * | 2015-05-19 | 2015-08-12 | 北京理工大学 | Piezoelectric-electromagnetic composite low-frequency broadband energy harvester |
| CN108183626A (en) * | 2018-01-08 | 2018-06-19 | 中北大学 | Power generation screw based on magnetoelectricity-Piezoelectric anisotropy formula structure |
| CN108372941A (en) * | 2018-02-05 | 2018-08-07 | 西北工业大学深圳研究院 | A kind of space junk break catching apparatus with energy absorption function |
| CN111015720A (en) * | 2019-11-29 | 2020-04-17 | 中国空间技术研究院 | Super-large flexible capturing device for capturing and clearing space debris |
| CN210693802U (en) * | 2019-12-05 | 2020-06-05 | 广州大学 | Highway vibration piezoelectricity, magnetoelectricity composite power generation device |
| CN111814277A (en) * | 2020-08-24 | 2020-10-23 | 西北工业大学 | Vibration isolation platform and dynamic model construction method thereof |
| WO2022090774A1 (en) * | 2020-10-29 | 2022-05-05 | Clearspace Sa | Capture system adapted to capture space objects, in particular for recovery or deorbiting purposes |
| CN113060308A (en) * | 2021-02-25 | 2021-07-02 | 北京科技大学 | Space capturing vibration damper for starship mechanical arm |
| CN215420129U (en) * | 2021-04-16 | 2022-01-04 | 苏州市职业大学 | Vibrating mechanical energy power generation device |
| CN113044249A (en) * | 2021-04-19 | 2021-06-29 | 北京理工大学 | Space debris capturing and despinning system based on damper |
| CN115057003A (en) * | 2022-05-27 | 2022-09-16 | 北京空间飞行器总体设计部 | Robot satellite |
Non-Patent Citations (2)
| Title |
|---|
| 压电俘能器结构及其力/电耦合作用分析;胡元太;蒋树农;薛欢;;固体力学学报(05);第451-467页 * |
| 胡元太 ; 蒋树农 ; 薛欢 ; .压电俘能器结构及其力/电耦合作用分析.固体力学学报.2010,(05),第451-467页. * |
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