CN115432209A - Vibration reduction and energy acquisition integrated device for whole-satellite system - Google Patents
Vibration reduction and energy acquisition integrated device for whole-satellite system Download PDFInfo
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Abstract
The invention relates to the technical field of aerospace engineering, in particular to an integral satellite system vibration reduction and energy acquisition integrated device. A guide rod is arranged in a conical shell type satellite adapter shell of the integrated device, a track is arranged on the guide rod, a mass block can move up and down along the track, linear energy acquisition assemblies arranged on two sides of the mass block are connected with the side wall of the shell through a revolute pair, a linear energy acquisition assembly is further arranged below the mass block, a nonlinear energy acquisition assembly is arranged above the mass block, and the nonlinear energy acquisition assembly is connected with the upper bottom surface of the shell through the guide rod; the capacitors of the linear energy acquisition assembly and the nonlinear energy acquisition assembly are electrically connected with the sensor; and in a stable state, under the combined action of the linear energy acquisition assembly and the nonlinear energy acquisition assembly, the mass block is arranged at the central position of the shell of the conical shell type satellite adapter. The invention increases the stability of the spacecraft, thereby reducing the influence of harmful vibration isolation on the spacecraft.
Description
Technical Field
The invention relates to the technical field of aerospace engineering, in particular to an integral satellite system vibration reduction and energy acquisition integrated device.
Background
In the field of aerospace engineering, spacecraft are subjected to different types of loading during operation, including periodic, random, and transient excitations. The prior art is based on the whole-satellite vibration isolation technology, and the damage of the load to the structure can be reduced to a certain extent by adding the vibration isolation device in the spacecraft. The whole satellite vibration isolator is arranged between the rocket and the satellite adapter, and vibration isolation is achieved by using elasticity and damping effect of the whole satellite vibration isolator, so that vibration transmission from the rocket to the satellite is reduced in an active flight section of satellite launching. At low frequency resonance, damping acts to suppress the peak response, and at mid and high frequencies the transmission of vibrations is reduced by the use of a relatively compliant isolator. The design of the vibration isolator needs to be comprehensively considered from the aspects of restraining response peaks and isolating medium-high frequency vibration.
In recent years, a technology for realizing mechanism vibration control by utilizing a Nonlinear Energy Sink (NES) is researched by a wide range of scholars at home and abroad. The NES mainly comprises cubic nonlinear stiffness, damping materials and magnetic blocks, and can realize unidirectional and irreversible transmission of vibration energy from a main system to a nonlinear part so as to achieve the aim of effective vibration reduction. The energy transferred to the non-linear vibration absorber is eventually dissipated by the damping material and the magnetic material of the non-linear part. The nonlinear energy sink can realize broadband vibration reduction, but the influence on the natural frequency of the system is relatively small, and due to the introduction of the nonlinearity, the system has strong hardening characteristics, so that a hopping phenomenon in a broadband range occurs, the effective vibration isolation bandwidth is seriously influenced, and the whole satellite system using the vibration reduction device is damaged.
Disclosure of Invention
In view of this, the present invention provides a novel integrated device for vibration reduction and energy collection of a whole satellite system, which can effectively suppress vibration generated by broadband vibration to ensure a better service environment for a payload on a spacecraft.
In order to achieve the above purpose, the present invention mainly provides the following technical solutions:
the utility model provides a whole star system damping and energy acquisition integrated device, includes awl shell type satellite adapter shell, be equipped with in the awl shell type satellite adapter shell:
the guide rod is vertically arranged above the lower bottom surface of the conical shell type satellite adapter shell, and a track is arranged on the guide rod;
the mass block is arranged on the guide rod and can move up and down along the track;
the linear energy acquisition assemblies are respectively arranged on two sides of the mass block, the two linear energy acquisition assemblies are symmetrically arranged on two sides of the mass block and are connected with the side wall of the conical shell type satellite adapter shell through a revolute pair, a linear energy acquisition assembly is arranged below the mass block and comprises a linear spring and a giant magnetostrictive material which are arranged in parallel, and a capacitor is connected in parallel on the giant magnetostrictive material;
the nonlinear energy acquisition assembly is arranged above the mass block and comprises a nonlinear spring, a linear damping structure and a giant magnetostrictive material which are arranged in parallel, and a capacitor is connected in parallel on the giant magnetostrictive material through a lead;
the support rod is vertically arranged below the upper bottom surface of the conical shell type satellite adapter shell, a connecting plate is arranged at the lower end of the support rod, and the nonlinear energy acquisition assembly and the guide rod are fixedly arranged below the connecting plate;
the capacitors of the linear energy acquisition assembly and the nonlinear energy acquisition assembly are electrically connected with the sensor;
and is configured to:
and in a stable state, under the combined action of the linear energy acquisition assembly and the nonlinear energy acquisition assembly, the mass block is arranged at the central position of the conical shell type satellite adapter shell.
In the integral star system vibration reduction and energy collection integrated device, the three linear energy collection assemblies form a quasi-zero stiffness system;
in the device integrating vibration reduction and energy collection of the whole satellite system, in a stable state, the included angle between the linear springs of the three linear energy collection assemblies is 120 0 The linear spring is parallel to the rotating pair connected with the linear spring.
In the integrated device for vibration reduction and energy collection of the whole satellite system, the mass block is made of metal or alloy material, and the weight of the mass block is 0.3Kg-3Kg.
In the device integrating vibration reduction and energy collection of the whole satellite system, two ends of the linear energy collection assembly are respectively provided with the connecting sheet, two ends of the linear spring are respectively connected with the connecting sheet, and two ends of the giant magnetostrictive material are respectively connected with the connecting sheet.
In the device integrating vibration reduction and energy collection of the whole satellite system, one end of a nonlinear spring in the nonlinear energy collection assembly is connected with the lower end connecting plate of the supporting rod, and the other end of the nonlinear spring is connected with the mass block;
in the device integrating vibration reduction and energy collection of the whole satellite system, one end of a linear damping structure in the nonlinear energy collection assembly is connected with the connecting plate, and the other end of the linear damping structure is connected with the mass block;
in the device integrating vibration reduction and energy collection of the whole satellite system, one end of the giant magnetostrictive material in the nonlinear energy collection assembly is connected with the connecting plate, and the other end of the giant magnetostrictive material is connected with the mass block.
In the device integrating vibration reduction and energy collection of the whole satellite system, the linear damping structure in the nonlinear energy collection assembly is made of high-damping alloy.
In the integrated device for vibration reduction and energy collection of the whole satellite system, the high damping alloy is a copper-zinc-aluminum alloy, an iron-chromium-molybdenum alloy or a manganese-copper alloy.
In the device integrating vibration reduction and energy collection of the whole satellite system, the rail of the guide rod is linear, and the mass block is provided with a rail matching structure;
in the device integrating vibration reduction and energy collection of the whole satellite system, the rail is a convex strip, and the rail matching structure is a groove; or the rail is a groove, and the rail matching structure is a convex strip; the shapes of the convex strips and the grooves are matched.
In the integrated device for vibration reduction and energy collection of the whole satellite system, the support rod is made of aluminum alloy;
in the device integrating vibration reduction and energy collection of the whole satellite system, the upper end of the supporting rod is fixedly connected with the center of the upper bottom surface of the conical shell type satellite adapter shell.
In the device integrating vibration reduction and energy collection for the whole satellite system, the linear energy collection assembly below the mass block is arranged at the central position of the lower bottom surface of the conical shell type satellite adapter shell
By means of the technical scheme, the vibration reduction and energy acquisition integrated device for the whole satellite system, provided by the invention, at least has the following advantages:
(1) By utilizing the excellent characteristics of high static and low dynamic of the quasi-zero stiffness system, the frequency response speed of the spacecraft vibration can be accelerated, the vibration isolation and absorption capacity can be improved, and the resonance peak value of the spacecraft system can be reduced. The nonlinear springs realize broadband vibration suppression, the linear springs on the two sides and below realize transverse vibration suppression, and compared with a classical structure, the passive vibration isolation system increases the stability of the spacecraft, thereby reducing the influence of harmful vibration isolation on the spacecraft.
(2) An energy acquisition device is built, and the conversion from vibration harmful to the spacecraft to a power supply device capable of supplying power is realized by utilizing the conductivity of the giant magnetostrictive material and the electromagnetic conversion technology. The energy collector collects electric energy, and the sensor is used for detecting feedback and monitoring feedback power supply of the device in the cone shell, so that the problem of energy limitation of the spacecraft is solved.
(3) Traditional passive vibration absorption and vibration isolation device dissipates the vibration through damping, is very big waste on the spacecraft under the limited condition of resource, and this device collects the energy and stores and rational utilization, can be used to satellite autonomous energy supply under the no illumination condition.
(4) The device is convenient to manufacture, has lower cost and can solve the practical problem in engineering.
The foregoing description is only an overview of the technical solutions of the present invention, and in order to make the technical solutions of the present invention more clearly understood and to implement them in accordance with the contents of the description, the following detailed description is given with reference to the preferred embodiments of the present invention and the accompanying drawings.
Drawings
FIG. 1 is a schematic structural diagram of an integrated whole-satellite system vibration reduction and energy collection device.
Detailed Description
To further illustrate the technical means and effects of the present invention adopted to achieve the predetermined objects, the following detailed description will be given to the embodiments, structures, features and effects of an integrated device for vibration damping and energy collection of a whole satellite system according to the present invention with reference to the accompanying drawings and preferred embodiments. In the following description, different "one embodiment" or "an embodiment" refers to not necessarily the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
The vibration reduction and energy collection integrated device for the whole satellite system shown in fig. 1 comprises a conical shell type satellite adapter shell 1, wherein a guide rod 2, a mass block 3, a linear energy collection assembly 5, a nonlinear energy collection assembly 6, a support rod and a sensor 8 are arranged in the conical shell type satellite adapter shell 1, the guide rod 2 is vertically arranged above the lower bottom surface of the conical shell type satellite adapter shell 1, and a track is arranged on the guide rod 2; a mass block 3 is arranged on the guide rod 2, and the mass block 3 can move up and down along the track; two linear energy collecting assemblies 5 are respectively arranged on two sides of the mass block 3, the two linear energy collecting assemblies 5 are symmetrically arranged on two sides of the mass block 3, the two linear energy collecting assemblies 5 are connected with the side wall of the conical shell type satellite adapter shell 1 through a revolute pair 7, a linear energy collecting assembly 5 is arranged below the mass block 3, each linear energy collecting assembly 5 comprises a linear spring 51 and a giant magnetostrictive material 52 which are arranged in parallel, and a capacitor 4 is connected in parallel on each giant magnetostrictive material 52; a nonlinear energy acquisition assembly 6 is arranged above the mass block 3, the nonlinear energy acquisition assembly 6 comprises a nonlinear spring 61, a linear damping structure 62 and a giant magnetostrictive material 52 which are arranged in parallel, and a capacitor 4 is connected in parallel on the giant magnetostrictive material 52 through a lead; the support rod is vertically arranged below the upper bottom surface of the conical shell type satellite adapter shell 1, a connecting plate is arranged at the lower end of the support rod, and the nonlinear energy acquisition assembly 6 and the guide rod 2 are fixedly arranged below the connecting plate; the capacitors 4 of the linear energy collection assembly 5 and the nonlinear energy collection assembly 6 are both electrically connected with the sensor 8; and is configured to: in a stable state, under the combined action of the linear energy collection assembly 5 and the nonlinear energy collection assembly 6, the mass block 3 is arranged at the central position of the conical shell type satellite adapter shell 1.
According to the invention, through the combined action of the linear energy acquisition assembly 5 and the nonlinear energy acquisition assembly 6, the single-frequency vibration of the spacecraft can be effectively inhibited, and the linear stiffness is ensured not to be introduced, so that the influence on the original system resonance area is hardly caused, the vibration inhibition effect is obvious, the stability of the spacecraft is increased, and the influence of harmful vibration isolation on the spacecraft is reduced.
The linear energy collecting assembly 5 of the present invention is connected to the rotating pair 7, so that the rotating pair 7 can be used as a rotating shaft of one end of the linear spring 51, that is, when the linear spring 51 vibrates up and down with the mass block 3, the linear spring 51 can rotate around the rotating pair 7. The rotating pair 7 is also called a revolute pair, and in one kind of kinematic pair, two rotating arms of the rotating pair 7 are connected through a rotating shaft, so that the linear energy collecting assembly 5 rotates in a manner of moving on a plane. The linear springs 51 on both sides of the mass 3 and below achieve lateral vibration suppression.
Therefore, when the mass block 3 moves up and down, the linear energy collecting assemblies 5 on two sides can be driven to stretch or contract. The revolute pair 7 comprises two revolute arms and a rotary shaft, the first ends of the two revolute arms are rotatably connected through the rotary shaft, the second ends of the two revolute arms are fixedly connected with the side wall and the linear energy collecting assembly 5 respectively, and the revolute pair 7 enables the linear energy collecting assembly 5 to move on only one plane.
Furthermore, in order to facilitate installation of the linear energy collection assembly 5, two ends of the linear energy collection assembly 5 are respectively provided with a connection piece, two ends of the linear spring 51 are respectively connected with the connection pieces, and two ends of the giant magnetostrictive material 52 are respectively connected with the connection pieces. The giant magnetostrictive material 52 can convert mechanical energy into electromagnetic energy when being stretched and shortened, namely, the targeted energy transfer of the integrated device for vibration reduction and energy collection of the whole satellite system can be effectively realized.
The guide rod 2 constrains the direction of motion of the linear energy harvesting assembly 5 and the nonlinear energy harvesting assembly 6 by constraining the direction of vibration of the mass 3.
When the vibration reduction and energy collection integrated device of the whole satellite system is excited by the outside world in a working environment, the mass block 3 is caused to vibrate up and down, and the vibration energy of the mass block 3 arranged in the conical shell type satellite adapter shell 1 is transferred to the linear energy collection assembly 5 and the nonlinear energy collection assembly 6 in a targeted mode. Wherein one part of the vibration energy is dissipated in the form of mechanical energy and the other part is dissipated by the damping material of the linear energy harvesting assembly 5 and the nonlinear energy harvesting assembly 6, thus realizing passive vibration control. The linear energy collecting assembly 5 forms quasi-zero stiffness by a three-spring structure, and the mass block 3 which vibrates up and down is restrained by the tension and compression of the three springs to restore the original balance position (namely, a stable state).
The whole-satellite system vibration reduction and energy collection integrated device forms quasi-zero stiffness through a three-spring structure, and the stability of the system is improved. As the effect of vibration suppression is obviously reduced once the excitation frequency of the linear energy acquisition component 5 is not equal to the natural frequency of the vibration absorber, the whole star system vibration attenuation and energy acquisition integrated device can have high stability and reliability, wide vibration attenuation frequency band and strong robustness by adding the linear energy acquisition component 6 of the nonlinear vibration absorber (as the spring has no linear stiffness, the linear energy acquisition component can be excited by any vibration frequency as long as the excitation energy reaches the required threshold value).
The three-spring quasi-zero stiffness vibration isolation only reduces the total linear stiffness of the spacecraft by generating negative linear stiffness, thereby reducing the natural frequency of the system and realizing the purpose of high-frequency vibration isolation. The high static low dynamic quasi-zero stiffness condition is realized by offsetting the positive stiffness of the vertical spring by the negative stiffness generated by the two oblique linear springs 51 in the vertical direction, and the frequency response speed of the spacecraft vibration can be accelerated by utilizing the excellent characteristics of high static low dynamic of the quasi-zero stiffness system, so that the vibration isolation and absorption capacity is improved, and the resonance peak value of the spacecraft is reduced. The quasi-zero stiffness design can reduce the natural frequency of the system, thereby achieving effective vibration isolation.
The invention dissipates partial energy in the form of mechanical energy, and realizes energy conversion while realizing passive vibration control by taking the giant magnetostrictive material 52 as an energy collector.
The energy collected by the linear energy collecting assembly 5 and the nonlinear energy collecting assembly 6 is used as the energy of the sensor 8, and specifically, the electric energy collected by the capacitor 4 is transmitted to the sensor 8 through a lead connected with the sensor to supply power to the sensor 8, so that the vibration reduction and energy collection integrated device of the whole satellite system does not need external energy. The invention can collect, store and reasonably utilize energy, and can be used for satellite autonomous energy supply under the condition of no illumination.
The sensor 8 is used for health detection of the whole-satellite system vibration reduction and energy acquisition integrated device, and the vibration strength of the whole-satellite system vibration reduction and energy acquisition integrated device is judged mainly by identifying the magnitude of an electric signal.
According to the invention, the linear energy collecting assemblies 5 are respectively arranged on the two sides and the lower part of the mass block 3, and the nonlinear energy collecting assembly 6 is arranged on the upper part of the mass block, so that the vibration in different directions can be collected by the device, and the vibration absorption and vibration isolation can be realized.
Further, in order to improve the frequency response speed of the vibration reduction and energy collection integrated device of the whole satellite system, the three linear energy collection assemblies 5 form a three-spring quasi-zero stiffness structure, and in a stable state, an included angle between linear springs 51 of the three linear energy collection assemblies 5 is 120 degrees, and the linear springs 51 are parallel to the revolute pairs 7 connected with the linear springs 51. By utilizing the excellent characteristics of high static and low dynamic of the quasi-zero stiffness system, the frequency response speed of the spacecraft vibration can be accelerated, the vibration isolation and absorption capacity can be improved, and the resonance peak value of the spacecraft system can be reduced, so that the stability problem of low-frequency vibration can be effectively solved, and the device has good broadband vibration elimination characteristics. Because a large machine often has broadband characteristics in a complex dynamic environment, a precision instrument has extremely strict requirements on a vibration environment in the process of an on-orbit operation stage of a spacecraft, even tiny vibration can also have extremely adverse influence on the measurement or indication precision of the spacecraft, an active and passive integrated vibration isolation technology is mainly applied to the vibration control of a broadband structure in the past, however, the structure of a vibration control mechanism with the broadband characteristics has the characteristics of strong coupling, large scale, low rigidity, weak damping, extreme external environment and the like, so that the active and passive integrated vibration control technology is difficult to adapt to the working conditions.
The three-spring structure of the invention forms quasi-zero stiffness to reduce the natural frequency of the system and broadens the effective bandwidth of passive vibration control. The special quasi-zero stiffness system can realize lower frequency and higher stiffness, has higher response speed and effectively solves the stability problem of low-frequency vibration.
The three-spring quasi-zero stiffness structure formed by the three linear energy acquisition assemblies 5 has zero dynamic stiffness at a static balance position, so that the vibration isolator has lower stiffness on the premise of ensuring the bearing capacity, and shows excellent low-frequency vibration isolation performance. The negative linear stiffness is generated, so that the total linear stiffness of the system is reduced, and the natural frequency of the system is reduced, thereby achieving the purpose of high-frequency vibration isolation. The high static low dynamic quasi-zero stiffness condition is realized by offsetting the positive stiffness of the vertical spring through the negative stiffness generated by the two oblique springs in the vertical direction, and the high static low dynamic excellent characteristics of the quasi-zero stiffness system are utilized, so that the frequency response speed of the spacecraft vibration is accelerated, the vibration isolation and absorption capacity is improved, and the resonance peak value of the spacecraft system is reduced.
Through the synergistic effect of the linear energy acquisition assembly 5 and the nonlinear energy acquisition assembly 6, the vibration isolation frequency band of the vibration reduction and energy acquisition integrated device of the whole satellite system is wider, and efficient vibration suppression is realized. The problem that the deformation resistance of the system is reduced when the linear rigidity is reduced due to the fact that only the linear energy collecting assembly 5 is used is solved, the influence of the natural frequency on the vibration reduction and energy collection integrated device of the whole satellite system is relatively small, the advantages of the vibration reduction performance and the vibration isolation performance of the vibration reduction and energy collection integrated device of the whole satellite system are more obvious under large excitation, and the vibration reduction performance of displacement response is more prominent under small excitation.
The vibration reduction and energy collection integrated device of the whole-satellite system utilizes the excellent characteristics of high static and low dynamic of a quasi-zero stiffness system, so that the frequency response speed of the vibration of the spacecraft can be accelerated, the vibration isolation and absorption capacity can be improved, and the resonance peak value of the spacecraft system can be reduced.
The vibration reduction and energy collection integrated device of the whole-satellite system can realize broadband vibration suppression through the nonlinear spring 61, the linear springs 51 on the two sides of the mass block 3 and below the mass block 3 can realize transverse vibration suppression, and compared with a classical structure, the passive vibration isolation system increases the stability of a spacecraft, so that the influence of harmful vibration isolation on the spacecraft is reduced.
In addition, the nonlinear energy harvesting component 6 and the linear energy harvesting component 5 are both provided with energy harvesting devices, and by utilizing the conductivity and electromagnetic conversion characteristics of the giant magnetostrictive material 52, the giant magnetostrictive material can be repeatedly stretched and shortened, so that mechanical energy (or mechanical displacement and information) can be converted into electromagnetic energy (or electromagnetic information). Thereby, a conversion from vibrations harmful to the spacecraft into powerable power supply means is achieved.
Further, in order to increase the energy generated by the vibration, the present invention further defines the material and weight of the mass block 3. The mass block 3 is made of metal or alloy material, the mass block 3 is made of material with high density and small volume, and the metal is preferably made of materials such as iron and stainless steel. The weight of the mass block 3 is set according to the requirement of the satellite, and can be any value between 0.3Kg and 3Kg.
One end of a nonlinear spring 61 in the nonlinear energy acquisition assembly 6 is connected with a lower end connecting plate of the supporting rod, and the other end of the nonlinear spring 61 is connected with the mass block 3; specifically, in a steady state, the nonlinear spring 61 is parallel to the guide bar 2.
One end of a linear damping structure 62 in the nonlinear energy collection assembly 6 is connected with the connecting plate, and the other end of the linear damping structure 62 is connected with the mass block 3, specifically, in a stable state, the linear damping structure 62 is parallel to the guide rod 2;
one end of a giant magnetostrictive material 63 in the nonlinear energy acquisition assembly 6 is connected with the connecting plate, the other end of the giant magnetostrictive material 63 is connected with the mass block 3, and specifically, in a stable state, the giant magnetostrictive material 63 is parallel to the guide rod 2.
The linear damping structure 62 in the nonlinear energy harvesting assembly 6 is a structure that integrates a damping material, which is a high damping alloy, with a member to dissipate vibration energy.
The high damping alloy is a copper-zinc-aluminum alloy, an iron-chromium-molybdenum alloy or a manganese-copper alloy.
The track of the guide rod 2 is linear, and a track matching structure is arranged on the mass block 3; the mass 3 can slide up and down along the guide bar 2. The specific implementation forms include the following two types: one) the rail is a convex strip, and the rail matching structure is a groove; secondly) or the rail is a groove, and the rail matching structure is a convex strip; the shapes of the convex strips and the grooves are matched. Both forms allow the mass 3 to slide up and down the guide rods 2.
In order to reduce the weight of the support rod, the support rod is made of aluminum alloy; the upper end of the supporting rod is fixedly connected with the center of the upper bottom surface of the conical shell type satellite adapter shell 1.
In order to ensure that the mass block 3 is located at the center of the cone-shell type satellite adapter housing 1 in a stable state, the linear energy collection assembly 5 below the mass block 3 is arranged at the center of the lower bottom surface of the cone-shell type satellite adapter housing 1.
The invention solves the problem that the spacecraft is interfered by the actual environment to a great extent. Before the spacecraft enters the intended orbit, it needs to withstand itself a series of harsh vibration environments, such as cowling noise, explosive shock, random vibration loading, etc. These have a great impact on the delicate components of the spacecraft such as solar sailboards, antennas, etc. The aerospace vehicle can face a plurality of severe dynamic environments in the motion process, wherein vibration is an important reason causing the drift of the indexes of the internal precise structure, the reduction of precision and the damage of the structure. Therefore, effective vibration suppression is essential to ensure proper operation of the equipment. The vibration reduction and vibration isolation integrated device of the whole-satellite system is arranged in a spacecraft to realize vibration reduction and vibration isolation in a passive control mode, and the nonlinear energy sink can realize that vibration energy is transmitted to a nonlinear part from the aerospace craft in a one-way and irreversible mode, so that the aim of effective vibration reduction is fulfilled. The energy transferred to the nonlinear vibration absorber is eventually dissipated by the damping material and the magnetic material of the nonlinear part. By utilizing the excellent characteristics of high static and low dynamic of a quasi-zero stiffness system, the overall linear stiffness of the system is reduced by generating negative linear stiffness, so that the natural frequency of the system is reduced, and the aim of high-frequency vibration isolation is fulfilled. The system accelerates the frequency response speed of the vibration of the spacecraft, increases the vibration isolation and absorption capacity and reduces the resonance peak value of the spacecraft system. The electric energy is supplied to the sensor 8 through the capacitors 4 of the linear energy acquisition assembly 5 and the nonlinear energy acquisition assembly 6, and the sensor 8 can also be used for health detection of the whole satellite system so as to improve the self-power supply capability of the system. The sensor 8 is used for detecting feedback and monitoring feedback power supply of the device in the cone shell, so that the problem of energy limitation of the spacecraft is solved. The sensor 8 may comprise the following types: 1) The force-sensitive sensor 8 judges the vibration strength of the satellite adapter by identifying the vibration force of the system mass block 3; 2) The magnetic sensor 8 judges the vibration strength of the satellite adapter by identifying the change of the magnetic quantity of the system giant magnetostrictive material 52; 3) The current sensor 8 judges the vibration strength of the satellite adapter by identifying the magnitude of the transferred electric signal of the system.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and any simple modification, equivalent change and modification made to the above embodiment according to the technical spirit of the present invention are still within the scope of the technical solution of the present invention.
Claims (10)
1. The utility model provides a whole star system damping and energy acquisition integrated device which characterized in that, includes awl shell type satellite adapter shell be equipped with in the awl shell type satellite adapter shell:
the guide rod is vertically arranged above the lower bottom surface of the conical shell type satellite adapter shell, and a track is arranged on the guide rod;
the mass block is arranged on the guide rod and can move up and down along the track;
the two linear energy acquisition assemblies are symmetrically arranged on the two sides of the mass block and are connected with the side wall of the conical shell type satellite adapter shell through a revolute pair, the linear energy acquisition assembly is arranged below the mass block and comprises a linear spring and a giant magnetostrictive material which are arranged in parallel, and a capacitor is connected in parallel on the giant magnetostrictive material;
the nonlinear energy acquisition assembly is arranged above the mass block and comprises a nonlinear spring, a linear damping structure and a giant magnetostrictive material which are arranged in parallel, and a capacitor is connected in parallel on the giant magnetostrictive material through a lead;
the support rod is vertically arranged below the upper bottom surface of the conical shell type satellite adapter shell, a connecting plate is arranged at the lower end of the support rod, and the nonlinear energy acquisition assembly and the guide rod are fixedly arranged below the connecting plate;
the capacitors of the linear energy acquisition assembly and the nonlinear energy acquisition assembly are electrically connected with the sensor;
and is configured to:
and in a stable state, under the combined action of the linear energy acquisition assembly and the nonlinear energy acquisition assembly, the mass block is arranged at the central position of the conical shell type satellite adapter shell.
2. The integrated whole-satellite system vibration damping and energy harvesting device of claim 1,
the three linear energy acquisition assemblies form a quasi-zero stiffness system;
at steady state, the angle between the linear springs of the three linear energy harvesting assemblies is 120 0 And the linear spring is parallel to the rotating pair connected with the linear spring.
3. The integrated whole satellite system vibration attenuation and energy harvesting device according to claim 1,
the mass block is made of metal or alloy materials, and the weight of the mass block is 0.3Kg-3Kg.
4. The integrated whole-satellite system vibration damping and energy harvesting device of claim 1,
the two ends of the linear energy acquisition assembly are respectively provided with a connecting sheet, the two ends of the linear spring are respectively connected with the connecting sheets, and the two ends of the giant magnetostrictive material are respectively connected with the connecting sheets.
5. The integrated whole-satellite system vibration damping and energy harvesting device of claim 1,
one end of a nonlinear spring in the nonlinear energy acquisition assembly is connected with the lower end connecting plate of the supporting rod, and the other end of the nonlinear spring is connected with the mass block;
one end of a linear damping structure in the nonlinear energy acquisition assembly is connected with the connecting plate, and the other end of the linear damping structure is connected with the mass block;
one end of a giant magnetostrictive material in the nonlinear energy acquisition assembly is connected with the connecting plate, and the other end of the giant magnetostrictive material is connected with the mass block.
6. The integrated whole satellite system vibration attenuation and energy harvesting device according to claim 1,
the material of the linear damping structure in the nonlinear energy acquisition assembly is high-damping alloy.
7. The integrated whole satellite system vibration attenuation and energy harvesting device according to claim 6,
the high damping alloy is copper-zinc-aluminum alloy, iron-chromium-molybdenum alloy or manganese-copper alloy.
8. The integrated whole satellite system vibration attenuation and energy harvesting device according to claim 1,
the rail of the guide rod is linear, and a rail matching structure is arranged on the mass block;
the rail is a convex strip, and the rail matching structure is a groove; or the rail is a groove, and the rail matching structure is a convex strip; the shapes of the convex strips and the grooves are matched.
9. The integrated whole satellite system vibration attenuation and energy harvesting device according to claim 1,
the support rod is made of aluminum alloy;
the upper end of the supporting rod is fixedly connected with the center of the upper bottom surface of the conical shell type satellite adapter shell.
10. The integrated whole satellite system vibration attenuation and energy harvesting device according to claim 1,
the linear energy acquisition assembly below the mass block is arranged in the center of the lower bottom surface of the conical shell type satellite adapter shell.
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