CN105129112A - Active and passive integrated vibration isolation device and vibration isolation platform - Google Patents
Active and passive integrated vibration isolation device and vibration isolation platform Download PDFInfo
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- CN105129112A CN105129112A CN201510434273.1A CN201510434273A CN105129112A CN 105129112 A CN105129112 A CN 105129112A CN 201510434273 A CN201510434273 A CN 201510434273A CN 105129112 A CN105129112 A CN 105129112A
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Abstract
The invention discloses an active and passive integrated vibration isolation device and a vibration isolation platform. The vibration isolation device comprises an elastic plane net structure, an active electromagnetic dynamic vibration absorber, and a piezoelectric stack actuator. The elastic plane net structure is formed by weaving steel wires in a tensioning and crossed manner. The active electromagnetic dynamic vibration absorber is arranged on the intersection of a central region of the elastic plane net structure. The piezoelectric stack actuator is arranged on the edge position of the elastic plane net structure. The vibration isolation platform comprises the vibration isolation device, a bearing cylinder, an intermediate support, and a control system. A satellite attitude control device assembly is arranged on the intermediate support. The intermediate support is installed on the vibration isolation device. The vibration isolation device is installed on the inner side of the bearing cylinder. The control system is used to control the active electromagnetic dynamic vibration absorber according to vibration acceleration information of the intermediate support, and control the piezoelectric stack actuator according to the vibration acceleration information of the bearing cylinder. The vibration isolation device and the vibration isolation platform are effective for low-frequency line spectrum, and have good control effect on broadband random excitation.
Description
Technical field
The present invention relates to vibration damping field, be specifically related to a kind of for the attitude control of satellite control equipment active-passive integrated isolation mounting of micro-vibration control and vibration-isolating platform in-orbit.
Background technology
Along with the Project of the satellite projects such as large quantities of civilian or military mapping, scouting, deep space scouting, celestial observation, laser communication, these projects are to satellite pointing stability and the continuous upgrading observing resolution requirement, and the scientific research personnel of related research institutes finds that satellite attitude vibration, star upper rotary or the micro-obstacle of vibration of reciprocating member to satellite platform become the bottleneck of restriction high sensitive capacity weight use just gradually.For the precision instrument and equipment being operated in space environment, excessive obstacle of vibration will affect the normal performance of its performance, and as earth observation camera, under the influence of vibrations, its imaging effect will worsen, and image resolution ratio reduces.Therefore, requirement must take appropriate measures, under ensureing the vibration level environment that responsive capacity weight is in " super quiet ", to realize high-accuracy high-resolution imaging.
Research shows, in the interference of numerous carrying equipments of spacecraft, the disturbance produced during the gesture stability component workings such as momentum wheel, flywheel, control moment gyroscope is the major disturbances source affecting capacity weight image quality.Reduce the major measure of soruce of vibration to capacity weight disturbance such as momentum wheel, flywheel, control moment gyroscope to have:
One is that the vibration reducing vibration source exports energy, but current manufacture level and technological level only can reach current Minimum Static overbalance and unbalancing value; In order to meet the demand of high precision and very high precision capacity weight, various vibration control measure must be taked.
Two is control the framing member in micro-vibration passing approach and optimize, as utilize local stiffness optimization to mounting bracket or satellite bearing cylinder structure carry out dynam correction and optimization or structural strain comparatively large regions lay restriction damping layer, but as first natural frequency (more than 100Hz) far below structural slab of the frequency of disturbing source, the more difficult performance of vibration damping advantage of restriction damping layer.
Three is additional subtract vibration isolation, absorbing braking measure by increasing, and reduces the energy and the level of response that are delivered to responsive capacity weight place.
From the running environment of controlled system, although developed in ground system many routines or performance-oriented vibration control technology (as structural dynamic characteristics optimization, damping energy dissipation, absorbing, vibration isolation etc.), but because there is particular/special requirement the aspect such as complexity, reliability, stability, life-span, volume and weight of space environment for use to vibration control apparatus, surface control techniques can not be grafted directly in the micro-vibration control of spacecraft simply.Control for soruce of vibration on spacecraft must consider the particularity of its environment for use, and research and development is novel subtracts isolation mounting.
At present for high frequency components force and moment, the measure subtracting vibration isolation can be adopted to process, according to the difference of installation interface, can carry out subtracting vibration isolation process for sensitive load, also can carry out subtracting vibration isolation process for vibration sources such as momentum wheel, flywheel, control moment gyroscopes.For the disturbance force characteristic of momentum wheel, flywheel and control moment gyroscope, simultaneously in order to meet its functional requirement, the isolation mounting demand fulfillment taked has six to vibration isolation capability, and the minimum natural frequency in six direction should be greater than a certain frequency values (being generally at least 12Hz-15Hz).
Vibration isolation treatment measures common at present have many bars vibration-isolating platform [E.H.Anderson, J.P.Fumo, R.S.Erwin.Satelliteultraquietisolationtechnologyexperime nt (SUITE) .AerospaceConferenceProceedings, IEEE.2000, 4:299-313.] [M.B.McMickell, T.Kreider, E.Hansen, T.Davis, M.Gonzalez.Opticalpayloadisolationusingtheminiaturevibra tionisolationsystem (MVIS-II) .ProceedingsofSPIE, 2007, 6527:03-1-03-13.] [A.Preumont, M.Horodinca, I.Romanescu, B.deMarneffe, M.Avraam, A.Deraemaeker, F.Bossens, A.AbuHanieh.Asix-axissingle-stageactivevibrationisolator basedonStewartplatform.JournalofSoundandVibration, 2007, 300 (3): 644-661.] and flexible isolation mounting [W.Y.Zhou, D.X.Li.Designandanalysisofanintelligentvibrationisolatio nplatformforreaction/momentumwheelassemblies, JournalofSoundandVibration, 2012, 331 (13): 2984-3005.] [W.Y.Zhou, D.X.Li.Experimentalresearchonavibrationisolationplatform formomentumwheelassembly.JournalofSoundandVibration, 2013, 332 (5): 1157 – 1171.] [D.Kamesh, R.Pandiyan, A.Ghosal.Passivevibrationisolationofreactionwheeldisturb ancesusingalowfrequencyflexiblespaceplatform.JournalofSo undandVibration, 2012, 331:1310-1330.] [D.Kamesh, R.Pandiyan, A.Ghosal.Modeling, designandanalysisoflowfrequencyplatformforattenuatingmic ro-vibrationinspacecraft.JournalofSoundandVibration, 2010, 329:3431-3450.].
Disturb for low frequency spectrum lines, because spacecraft is to the requirement of momentum wheel appearance control characteristic and directional property, the demand of spacecraft being impacted in lift-off process to suppression, should not adopt the isolation mounting that isolation frequency is lower, the following several method of general employing suppresses at present:
One is adopt impedance bundary to increase system damping, and damping can suppress the response at natural frequency place, adopts the damper of three parameters can not worsen the inhibition of high frequency response simultaneously;
Two is adopt active control technology, as VISS, many bars isolation mounting of active-passive integratedization such as SUITE and MIVE has good low frequency vibration isolation performance [W.Y.Zhou, D.X.Li.Designandanalysisofanintelligentvibrationisolatio nplatformforreaction/momentumwheelassemblies, JournalofSoundandVibration, 2012,, or on elastic vibration isolation device, paste piezoelectric patches and adopt velocity feedback effectively can improve damping 331 (13): 2984-3005.];
Three is adopt dynamic absorber technology, the output of momentum wheel is vibrated by source and transfers on dynamic absorber and dissipate, but requires that absorbing can from the rotation speed change of motion tracking appearance control equipment.
Can obtain as drawn a conclusion from above analysis:
(1) vibration control of space vehicle needs to adopt compact, failure-free Vibration Absorption Designing as far as possible, and the disturbance of the translation that isolation mounting can effectively suppress vibration source to cause simultaneously and rotational freedom is the gordian technique of carrying out multi-freedom-degree vibration control.Therefore proposed novel isolation mounting should have vibration-isolating platform character, effectively can control multidirectional vibration simultaneously.
(2) in micro-vibration control of space structure, the various ways such as Passive Control, ACTIVE CONTROL and main passive Hybrid mode can be adopted effectively to control the obstacle of vibration of high frequency, low frequency and full frequency band.Need the General Principle of vibration control to be applied to Natural vibration source in the bang path of capacity weight, carry out vibration damping by single-stage, multistage mode that is passive or active and passive associating, realize high-precision position, point to control.
(3) advantage of active damping to obtain significantly vibration damping (particularly low frequency), be applicable to high precision control, but its shortcoming is also obvious, as system complex, consume the energy, the effective weight taking aircraft and space etc. on star, when using ACTIVE CONTROL, need to adopt the controllable force sources such as light and handy high precision driving, Electromagnetic Drive (voice coil motor, inertia actuator) and intellectual material driving, to produce incentive equilibrium interference source excitation a little according to given control law.
Summary of the invention
The present invention, in order to overcome above technical matters, proposes a kind of active-passive integrated isolation mounting and vibration-isolating platform, for the micro-vibration control in-orbit of attitude control of satellite control equipment.
Technical scheme of the present invention is as follows:
The invention discloses a kind of active-passive integrated isolation mounting, comprise elastic linear web frame, initiatively electromagnetism dynamic vibration absorber and piezoelectric pile actuator, wherein,
Described elastic linear web frame is formed by steel wire netting twine tensioning interlacing;
Described active electromagnetism dynamic vibration absorber is arranged on the point of crossing of described elastic linear web frame central area;
Described piezoelectric pile actuator is arranged at the boundary position of described elastic linear web frame.
The present invention separately discloses a kind of active-passive integrated vibration-isolating platform, for the micro-vibration control in-orbit of satellite gravity anomaly apparatus assembly, comprises isolation mounting described above, loaded cylinder, central support and control system, wherein,
Described satellite gravity anomaly apparatus assembly is located on described central support, and described central support is installed on described isolation mounting;
Described isolation mounting is installed on inside described loaded cylinder;
Described control system in order to:
Vibration acceleration information according to described central support controls described active electromagnetism dynamic vibration absorber;
Vibration acceleration information according to described loaded cylinder controls described piezoelectric pile actuator.
Preferably, described control system comprises the first acceleration pick-up and the second acceleration pick-up, wherein,
Described first acceleration pick-up is arranged on the loaded cylinder near described elastic linear web frame, in order to detect the first vibration acceleration on described elastic linear web frame;
Described second acceleration pick-up is arranged on described central support, in order to detect second vibration acceleration at described central support place.
Preferably, described control system also comprises signal analysis and control module, described signal analysis and control module to be gone forward side by side line frequency analysis of spectrum and feature signal extraction in order to be received described first vibration acceleration and the second vibration acceleration signal by wire, tracking filter is carried out to the line spectrum of low frequency, and by the second low-frequency control signal of the first low-frequency control signal and described active electromagnetism dynamic vibration absorber that provide described piezoelectric pile actuator based on the adaptive control algorithm of mode filtering and.
Preferably, comprise the first power amplifier and the second power amplifier, wherein,
Second low-frequency control signal described in described first power amplifier accepts also amplifies, and then exports described active electromagnetism dynamic vibration absorber to;
First low-frequency control signal described in described second power amplifier accepts also amplifies, and then exports described piezoelectric pile actuator to.
Preferably, described signal analysis and control module comprise central support acceleration analysis submodule, loaded cylinder acceleration analysis submodule and control signal generation submodule, wherein,
Described central support acceleration analysis submodule comprises the second low-pass filter and the 2nd FFT Fourler transform module, described second low-pass filter receives the second vibration acceleration signal that described second acceleration pick-up transmits, signal after LPF is transferred to described control signal generation submodule after described 2nd FFT Fourler transform resume module, forms the second filtering signal;
Described loaded cylinder acceleration analysis submodule comprises the first low-pass filter and a FFT Fourler transform module, described first low-pass filter receives the first vibration acceleration signal that described first acceleration pick-up transmits, signal after LPF is transferred to described control signal generation submodule after a described FFT Fourler transform resume module, forms the first filtering signal;
Described control signal generation submodule comprises mode filtering self-adaptive control module, a D/A modular converter and the 2nd D/A modular converter, wherein,
Described first filtering signal forms the first low-frequency control signal after described mode filtering self-adaptive control module calculates, and described first low-frequency control signal is sent to described second power amplifier after a described D/A modular converter carries out digital to analogy conversion;
Described second filtering signal forms the second low-frequency control signal after described mode filtering self-adaptive control module calculates, and described second low-frequency control signal is sent to described first power amplifier after described 2nd D/A modular converter carries out digital to analogy conversion.
Preferably, described active electromagnetism dynamic vibration absorber exports the transverse force putting on elastic linear web frame Nodes, and described piezoelectric pile actuator exports the longitudinal force put on elastic linear web frame steel wire netting twine.
Preferably, also comprise erection joint and mounting seat, described central support is installed on described elastic linear web frame by mounting seat, and described steel wire netting twine is arranged on described loaded cylinder by described erection joint.
Preferably, screw and the draw-in groove with described wire net lines matching is offered bottom described mounting seat, described mounting seat embeds in described steel wire netting twine by described draw-in groove, is also fixed by bolt and described screw between described mounting seat and elastic linear web frame.
Preferably, described satellite gravity anomaly assembly is momentum wheel, flywheel or control moment gyroscope.
Compared with prior art, beneficial effect of the present invention is as follows:
1. the elasticity that the present invention utilizes lightweight steel wire netting twine to provide when micro-vibration carries out passive vibration isolation to reduce the transmission of attitude control device (momentum wheel, flywheel or control moment gyroscope) disturbance to satellite health structure (loaded cylinder or service module etc.), and is converted into only along the longitudinal force of lightweight steel wire netting twine by six of attitude control device to transmitting force; Because vibration is only transmitted along lightweight steel wire netting twine, the piezoelectric pile active-control vibration offset at plane net structure boundary place is utilized to be delivered to the dynamic force (not affecting the static attitude control effort needing to transmit) of satellite health structure (loaded cylinder or service module etc.); By border ACTIVE CONTROL, energy can be reflected back toward plane net structure centre, the vibration of plane net structure centre is exaggerated, overcome micro-vibration amplitude less, be difficult to directly utilize dynamic vibration absorber to carry out the difficult point of absorbing, utilize the active electromagnetism dynamic vibration absorber being arranged in plane net structure centre place to absorb the energy returned from edge reflection, the vibration of whole vibration-isolating platform and transferring energy are controlled.
2. the present invention can realize the vibration isolation of six degree of freedom, adjustment by the construction parameter such as modulus, the predetermincd tension of steel wire netting twine, the density degree of plane net structure of steel wire netting twine provides the rigidity met the demands, ensure the transmission of static attitude control torque on the one hand, provide suitable isolation frequency on the other hand;
3. the present invention can realize low frequency and wide bandly to control simultaneously, utilizes the rigidity of plane net structure to carry out passive vibration isolation; The piezoelectric pile ACTIVE CONTROL of boundary is utilized to provide the control of low frequency spectrum lines vibration passing; Initiatively Electromagnet absorber is utilized to absorb the energy at low frequency spectrum lines place.
4. can to realize being delivered to the vibrational energy of satellite health structure (loaded cylinder or service module etc.) little in the present invention, ensure that the vibration of vibration-isolating platform self is very little simultaneously, be conducive to the vibration severity reducing attitude control device (momentum wheel, flywheel or control moment gyroscope) attachment point place, extend its life-span.
5. The present invention gives the connection mode of the passive integrated isolation mounting of described elastic linear host and satellite health structure (loaded cylinder or service module etc.), attitude control of satellite control equipment (momentum wheel, flywheel or control moment gyroscope) central support, show that it has the good advantage of suitable dress property.
6. the plane net structure that the present invention proposes is a kind of vibration-isolating platform that can realize multidirectional vibration isolation, plane net structure carries itself by tension force, simultaneously in the vertical ability (being equivalent to low-pass filter) with passive high-frequency vibration isolation, and transmission characteristic regulates by tension force.In addition, plane net structure compact conformation, lightweight, can organically combine with active member.Distributed ACTIVE CONTROL is taked at the boundary of plane net structure, to take the initiative absorbing at the Nodes of plane net structure, form active-passive integrated vibration-isolating platform, be applicable to the first order vibration isolation of appearance control equipment, realize low frequency and narrow bandwidth and the wide band vibration damping of high frequency.
Accompanying drawing explanation
Fig. 1 is the active-passive integrated isolation mounting of vibration isolation of the present invention and vibration-isolating platform schematic diagram;
Fig. 2 is the enlarged diagram of vibration-isolating platform mounting seat A of the present invention;
Fig. 3 is signal analysis of the present invention and control module schematic diagram;
Fig. 4 is erection joint schematic diagram of the present invention;
Fig. 5 is the jointing of steel wire netting twine of the present invention and piezoelectric pile actuator.
[nomenclature]
1-Satellite Attitude control apparatus assembly, 2-central support, 3-mounting seat, 4-plane net structure, 5-is electromagnetism dynamic vibration absorber initiatively, 6-piezoelectric pile actuator, 7-loaded cylinder, 8-first acceleration pick-up, 9-central support acceleration analysis submodule, 10-loaded cylinder acceleration analysis submodule, 11-control signal generation submodule, 12-first power amplifier, 13-second power amplifier, 14-second acceleration pick-up, 15-erection joint, 16-steel wire netting twine, 17-jointing.
Detailed description of the invention
Below with reference to accompanying drawing of the present invention; clear, complete description and discussion are carried out to the technical scheme in the embodiment of the present invention; obviously; as described herein is only a part of example of the present invention; it is not whole examples; based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under the prerequisite not making creative work, all belongs to protection scope of the present invention.
In the present embodiment, the structural representation of a kind of active-passive integrated isolation mounting and vibration-isolating platform as shown in Figure 1, be mainly used in micro-in-orbit vibration control of satellite gravity anomaly apparatus assembly 1, described satellite gravity anomaly apparatus assembly 1 can be momentum wheel, flywheel or control moment gyroscope.
Wherein, described isolation mounting comprises elastic linear web frame 4, initiatively electromagnetism dynamic vibration absorber 5 and piezoelectric pile actuator 6, and described elastic linear web frame 4 is formed by steel wire netting twine 16 tensioning interlacing; Described active electromagnetism dynamic vibration absorber 5 is arranged on the point of crossing of described elastic linear web frame 4 central area; Described piezoelectric pile actuator 6 is arranged at the boundary position of described elastic linear web frame 4.
Described vibration-isolating platform comprises isolation mounting described above, Satellite Attitude control control convenience assembly 1, loaded cylinder 7, central support 2, erection joint 15, mounting seat 3 and control system, wherein, described satellite gravity anomaly apparatus assembly 1 is located on described central support 2, and described central support 2 is installed on described isolation mounting; Described isolation mounting is installed on inside described loaded cylinder 7; Described control system in order to:
Vibration acceleration information according to described central support 2 controls described active electromagnetism dynamic vibration absorber 5;
Vibration acceleration information according to described loaded cylinder 7 controls described piezoelectric pile actuator 6.
Described central support 2 is installed on described elastic linear web frame 4 by mounting seat 3, and described steel wire netting twine 16 is arranged on described loaded cylinder 7 by described erection joint 15.
Described mounting seat 3 is between described central support 2 and elastic linear web frame 4, the enlarged drawing of mounting seat 3 is see Fig. 2, mounting seat 3 is box structures, the draw-in groove that bottom offers screw and mates with the described steel wire netting twine 16 intersected, described mounting seat 3 embeds in described steel wire netting twine 16 by described draw-in groove, and then bolt-locking is passed through in the screw of mounting seat 3 bottom, make to be achieved a fixed connection by bolt and screw between described mounting seat 3 and elastic linear web frame 4, ensure that mounting seat 3 can not be takeoff disengagement netting twine.
The steel wire netting twine 16 of described active-passive integrated elastic linear web frame 4 is installed in satellite health structure (loaded cylinder or service module etc.) by the erection joint 15 shown in Fig. 4.Insert steel wire netting twine 16 in one end circular hole of erection joint 15, then will insert erection joint 15 pier at steel wire netting twine 16 position slightly by the mode that pier is thick, compression steel wire netting twine 16, realizes reliably connecting.
The steel wire netting twine 16 of described active-passive integrated elastic linear web frame 4 is connected with piezoelectric pile actuator 6 by the jointing 17 shown in Fig. 5.One end of jointing 17 is circular hole, inserts steel wire netting twine 16, and then will insert erection joint 15 pier at steel wire netting twine 16 position slightly by the mode that pier is thick, compression steel wire netting twine 16, realizes reliably connecting; The other end of jointing 17 is tapped bore, is connected with the thread end of piezoelectric pile actuator 6.The other end of piezoelectric pile actuator 6 is connected with satellite health structure (loaded cylinder or service module etc.) by erection joint 15.
When Satellite Attitude control control convenience assembly 1 operates, the axle frequency, its head bearing assembly centre bearer ball etc. of appearance control equipment can produce six to low frequency spectrum lines and the wide band micro-vibration exciting force of high frequency and excitation moment.
Micro-vibrational excitation force and moment is when central support 2 is passed to mounting seat 3, the each of mounting seat 3 is passed to satellite health structure (loaded cylinder or service module etc.) to exciting force and excitation moment by the steel wire netting twine 16 in elastic linear web frame 4, affects the upper capacity weight carried of satellite health structure (loaded cylinder or service module etc.) and normally works.
In order to the micro-vibrational excitation force and moment produced satellite gravity anomaly apparatus assembly 1 controls, the present invention carries out passive vibration isolation by steel wire netting twine 16 elasticity of providing when micro-vibration and transmits to the high frequency wide frequency band of satellite health structure (loaded cylinder or service module etc.) to reduce attitude control device (momentum wheel, flywheel or control moment gyroscope) disturbance, and is converted into six of attitude control of satellite control equipment only along the longitudinal force of lightweight steel wire netting twine 16 to transmitting force.
In preferred embodiment, described control system comprises the first acceleration pick-up 8 and the second acceleration pick-up 14, wherein, described first acceleration pick-up 8 is arranged on the loaded cylinder 7 near described elastic linear web frame 4, in order to detect the first vibration acceleration on described elastic linear web frame 4; Described second acceleration pick-up 14 is arranged on described central support 2, in order to detect second vibration acceleration at described central support 2 place.
Preferably, described control system also comprises signal analysis and control module, described signal analysis and control module to be gone forward side by side line frequency analysis of spectrum and feature signal extraction in order to be received described first vibration acceleration and the second vibration acceleration signal by wire, tracking filter is carried out to the line spectrum of low frequency, and by the second low-frequency control signal of the first low-frequency control signal and described active electromagnetism dynamic vibration absorber 5 that provide described piezoelectric pile actuator 6 based on the adaptive control algorithm of mode filtering.
Described vibration-isolating platform comprises the first power amplifier 12 and the second power amplifier 13 further, and wherein, described first power amplifier 12 receives described second low-frequency control signal and amplifies, and then exports described active electromagnetism dynamic vibration absorber 5 to; Described second power amplifier 13 receives described first low-frequency control signal and amplifies, and then exports described piezoelectric pile actuator 6 to.Wherein, described active electromagnetism dynamic vibration absorber 5 exports the transverse force putting on elastic linear web frame 4 Nodes, and described piezoelectric pile actuator 6 exports the longitudinal force put on elastic linear web frame 4 steel wire netting twine 16.
In preferred embodiment, described signal analysis and control module comprise central support acceleration analysis submodule 9, loaded cylinder acceleration analysis submodule 10 and control signal generation submodule 11, wherein,
Described central support acceleration analysis submodule 9 comprises the second low-pass filter and the 2nd FFT Fourler transform module, described second low-pass filter receives the second vibration acceleration signal that described second acceleration pick-up 14 transmits, signal after LPF is transferred to described control signal generation submodule 11 after described 2nd FFT Fourler transform resume module, forms the second filtering signal;
Described loaded cylinder acceleration analysis submodule 10 comprises the first low-pass filter and a FFT Fourler transform module, described first low-pass filter receives the first vibration acceleration signal that described first acceleration pick-up 8 transmits, signal after LPF is transferred to described control signal generation submodule 11 after a described FFT Fourler transform resume module, forms the first filtering signal;
Described control signal generation submodule 11 comprises mode filtering self-adaptive control module, a D/A modular converter and the 2nd D/A modular converter, wherein,
Described first filtering signal forms the first low-frequency control signal after described mode filtering self-adaptive control module calculates, and described first low-frequency control signal is sent to described second power amplifier 13 after a described D/A modular converter carries out digital to analogy conversion;
Described second filtering signal forms the second low-frequency control signal after described mode filtering self-adaptive control module calculates, and described second low-frequency control signal is sent to described first power amplifier 12 after described 2nd D/A modular converter carries out digital to analogy conversion.
Specific works process:
The first vibration acceleration is recorded and real-time monitor Vibration Condition by the first acceleration pick-up 8 being arranged in the satellite health structure (loaded cylinder or service module etc.) near elastic linear web frame 4, using the first vibration acceleration signal of recording as feedback signal, the first vibration acceleration signal recorded is exported to signal analysis and control module by wire, signal analysis and control module receive the first vibration acceleration signal and to go forward side by side line frequency analysis of spectrum and feature signal extraction, tracking filter is carried out to the line spectrum of low frequency, by providing the first low-frequency control signal of piezoelectric pile actuator 6 based on the adaptive control algorithm of mode filtering, this control signal amplifies at the second power amplifier 13, then export to and be positioned at elastic linear web frame 4 boundary and be connected on piezoelectric pile actuator 6 on steel wire netting twine 16, piezoelectric pile actuator 6 is made to export the longitudinal force put on elastic linear web frame 4 steel wire netting twine 16, this longitudinal force is contrary with the longitudinal transmitting force do not applied when controlling, counteracting is delivered to the dynamic force of satellite health structure (loaded cylinder or service module etc.), thus realize the control of low frequency transmitting force.
Second vibration acceleration at central support 2 place is recorded and real-time monitor Vibration Condition by vibration second acceleration pick-up 14 be arranged on central support 2, using the second vibration acceleration signal of recording as feedback signal, the second vibration acceleration signal recorded is exported to signal analysis and control module by wire, signal analysis and control module receive the second vibration acceleration signal and to go forward side by side line frequency analysis of spectrum and feature signal extraction, tracking filter is carried out to the line spectrum of low frequency, by providing the second low-frequency control signal of initiatively electromagnetism dynamic vibration absorber 5 based on the adaptive control algorithm of mode filtering, this control signal amplifies at the first power amplifier 12, then the active electromagnetism dynamic vibration absorber 5 being positioned at elastic linear web frame 4 center is exported to, initiatively electromagnetism dynamic vibration absorber 5 is made to export the transverse force putting on elastic linear web frame 4 Nodes, realize the vibration control of the web frame near center.
The disclosed preferred embodiment of the present invention just sets forth the present invention for helping above.Preferred embodiment does not have all details of detailed descriptionthe, does not limit the detailed description of the invention that this invention is only described yet.Obviously, according to the content of this specification sheets, can make many modifications and variations.This specification sheets is chosen and is specifically described these embodiments, is to explain principle of the present invention and practical application better, thus makes art technical personnel understand well and to utilize the present invention.The present invention is only subject to the restriction of claims and four corner and equivalent.
Claims (10)
1. an active-passive integrated isolation mounting, is characterized in that, comprises elastic linear web frame, initiatively electromagnetism dynamic vibration absorber and piezoelectric pile actuator, wherein,
Described elastic linear web frame is formed by steel wire netting twine tensioning interlacing;
Described active electromagnetism dynamic vibration absorber is arranged on the point of crossing of described elastic linear web frame central area;
Described piezoelectric pile actuator is arranged at the boundary position of described elastic linear web frame.
2. an active-passive integrated vibration-isolating platform, for the micro-vibration control in-orbit of satellite gravity anomaly apparatus assembly, is characterized in that, comprise isolation mounting as claimed in claim 1, loaded cylinder, central support and control system, wherein,
Described satellite gravity anomaly apparatus assembly is located on described central support, and described central support is installed on described isolation mounting;
Described isolation mounting is installed on inside described loaded cylinder;
Described control system in order to:
Vibration acceleration information according to described central support controls described active electromagnetism dynamic vibration absorber;
Vibration acceleration information according to described loaded cylinder controls described piezoelectric pile actuator.
3. a kind of active-passive integrated vibration-isolating platform as claimed in claim 2, is characterized in that, described control system comprises the first acceleration pick-up and the second acceleration pick-up, wherein,
Described first acceleration pick-up is arranged on the loaded cylinder near described elastic linear web frame, in order to detect the first vibration acceleration on described elastic linear web frame;
Described second acceleration pick-up is arranged on described central support, in order to detect second vibration acceleration at described central support place.
4. a kind of active-passive integrated vibration-isolating platform as claimed in claim 2, it is characterized in that, described control system also comprises signal analysis and control module, described signal analysis and control module to be gone forward side by side line frequency analysis of spectrum and feature signal extraction in order to be received described first vibration acceleration and the second vibration acceleration signal by wire, tracking filter is carried out to the line spectrum of low frequency, and by the second low-frequency control signal of the first low-frequency control signal and described active electromagnetism dynamic vibration absorber that provide described piezoelectric pile actuator based on the adaptive control algorithm of mode filtering.
5. a kind of active-passive integrated vibration-isolating platform as claimed in claim 4, is characterized in that, comprises the first power amplifier and the second power amplifier, wherein,
Second low-frequency control signal described in described first power amplifier accepts also amplifies, and then exports described active electromagnetism dynamic vibration absorber to;
First low-frequency control signal described in described second power amplifier accepts also amplifies, and then exports described piezoelectric pile actuator to.
6. a kind of active-passive integrated vibration-isolating platform as claimed in claim 5, is characterized in that, described signal analysis and control module comprise central support acceleration analysis submodule, loaded cylinder acceleration analysis submodule and control signal generation submodule, wherein,
Described central support acceleration analysis submodule comprises the second low-pass filter and the 2nd FFT Fourler transform module, described second low-pass filter receives the second vibration acceleration signal that described second acceleration pick-up transmits, signal after LPF is transferred to described control signal generation submodule after described 2nd FFT Fourler transform resume module, forms the second filtering signal;
Described loaded cylinder acceleration analysis submodule comprises the first low-pass filter and a FFT Fourler transform module, described first low-pass filter receives the first vibration acceleration signal that described first acceleration pick-up transmits, signal after LPF is transferred to described control signal generation submodule after a described FFT Fourler transform resume module, forms the first filtering signal;
Described control signal generation submodule comprises mode filtering self-adaptive control module, a D/A modular converter and the 2nd D/A modular converter, wherein,
Described first filtering signal forms the first low-frequency control signal after described mode filtering self-adaptive control module calculates, and described first low-frequency control signal is sent to described second power amplifier after a described D/A modular converter carries out digital to analogy conversion;
Described second filtering signal forms the second low-frequency control signal after described mode filtering self-adaptive control module calculates, and described second low-frequency control signal is sent to described first power amplifier after described 2nd D/A modular converter carries out digital to analogy conversion.
7. a kind of active-passive integrated vibration-isolating platform as claimed in claim 6, it is characterized in that, described active electromagnetism dynamic vibration absorber exports the transverse force putting on elastic linear web frame Nodes, and described piezoelectric pile actuator exports the longitudinal force put on elastic linear web frame steel wire netting twine.
8. a kind of active-passive integrated vibration-isolating platform as claimed in claim 2, it is characterized in that, also comprise erection joint and mounting seat, described central support is installed on described elastic linear web frame by mounting seat, and described steel wire netting twine is arranged on described loaded cylinder by described erection joint.
9. a kind of active-passive integrated vibration-isolating platform as claimed in claim 8, it is characterized in that, screw and the draw-in groove with described wire net lines matching is offered bottom described mounting seat, described mounting seat embeds in described steel wire netting twine by described draw-in groove, is also fixed by bolt and described screw between described mounting seat and elastic linear web frame.
10. a kind of active-passive integrated vibration-isolating platform as claimed in claim 2, is characterized in that, described satellite gravity anomaly assembly is momentum wheel, flywheel or control moment gyroscope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510434273.1A CN105129112B (en) | 2015-07-22 | 2015-07-22 | Active and passive integrated vibration isolation device and vibration isolation platform |
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| CN106059392A (en) * | 2016-07-08 | 2016-10-26 | 上海大学 | Apparatus for realizing whole-satellite self-energy-supply active and passive integrated nonlinear vibration control |
| CN107089348A (en) * | 2017-04-01 | 2017-08-25 | 中国空间技术研究院 | On-orbit fault game method based on many flexible accessory satellite dynamics optimized Control Modes |
| CN107291988A (en) * | 2017-05-25 | 2017-10-24 | 北京空间飞行器总体设计部 | A kind of momenttum wheel installation interface equivalent excitation power acquisition methods |
| CN108195571A (en) * | 2016-12-08 | 2018-06-22 | 中国船舶工业***工程研究院 | A kind of actuator testboard active vibration isolation system based on piezoelectric ceramics |
| CN108897239A (en) * | 2018-06-29 | 2018-11-27 | 北京控制工程研究所 | A kind of spacecraft two-stage gesture stability simulation system |
| CN112198911A (en) * | 2020-09-29 | 2021-01-08 | 上海大学 | Method and system for eliminating random line spectrum self-adaptive tracking |
| CN113883353A (en) * | 2021-09-18 | 2022-01-04 | 苏州东菱智能减振降噪技术有限公司 | Six-degree-of-freedom pipeline shock absorber and shock absorption method |
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| CN106059392A (en) * | 2016-07-08 | 2016-10-26 | 上海大学 | Apparatus for realizing whole-satellite self-energy-supply active and passive integrated nonlinear vibration control |
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| CN108195571A (en) * | 2016-12-08 | 2018-06-22 | 中国船舶工业***工程研究院 | A kind of actuator testboard active vibration isolation system based on piezoelectric ceramics |
| CN107089348A (en) * | 2017-04-01 | 2017-08-25 | 中国空间技术研究院 | On-orbit fault game method based on many flexible accessory satellite dynamics optimized Control Modes |
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| CN108897239A (en) * | 2018-06-29 | 2018-11-27 | 北京控制工程研究所 | A kind of spacecraft two-stage gesture stability simulation system |
| CN112198911A (en) * | 2020-09-29 | 2021-01-08 | 上海大学 | Method and system for eliminating random line spectrum self-adaptive tracking |
| CN112198911B (en) * | 2020-09-29 | 2021-07-27 | 上海大学 | Method and system for eliminating random line spectrum self-adaptive tracking |
| CN113883353A (en) * | 2021-09-18 | 2022-01-04 | 苏州东菱智能减振降噪技术有限公司 | Six-degree-of-freedom pipeline shock absorber and shock absorption method |
| CN113883353B (en) * | 2021-09-18 | 2023-11-03 | 苏州东菱智能减振降噪技术有限公司 | Six-degree-of-freedom pipeline vibration damper and vibration damping method |
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