CN106956785B - The in-orbit micro-vibration low frequency vibration isolation device of spacecraft - Google Patents
The in-orbit micro-vibration low frequency vibration isolation device of spacecraft Download PDFInfo
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- CN106956785B CN106956785B CN201510417377.1A CN201510417377A CN106956785B CN 106956785 B CN106956785 B CN 106956785B CN 201510417377 A CN201510417377 A CN 201510417377A CN 106956785 B CN106956785 B CN 106956785B
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Abstract
The invention discloses a kind of micro-vibration low frequency vibration isolation devices that spacecraft is in-orbit, it mainly include vibration isolation object support plate, isolation spring, damper, inner hinge, spring elongation quantity regulating device, outer hinge and pedestal, the side of the vibration isolation unit of isolation spring composition in parallel with damper is separately connected around vibration isolation object support plate by several inner hinges, the other side of vibration isolation unit passes through several outer hinges respectively and connect with spring elongation quantity regulating device, vibration isolation unit is whole free to rotate around inside and outside hinge, when vibration isolation vibrating objects generate displacement, inside and outside hinge provides rotational freedom for vibration isolation unit, guarantee that spring generates stretcher strain and carries out vibration isolation.The present invention realizes the vibration isolation of the in-orbit micro-vibration of spacecraft, improves the in-orbit disturbance component vibration isolation technique level of satellite, meets demand of the satellite especially high-precision earth observation satellite to in-orbit micro-vibration environment.
Description
Technical field
The invention belongs to the vibration control technology fields of spacecraft product, and in particular to a kind of in-orbit micro-vibration of spacecraft is low
Frequency vibration isolating method and device.
Background technique
The precision for improving spacecraft product aerial mission is an important trend of present satellites development, such as earth observation
The fields such as remote sensing, laser communication, space science experiment, deep space exploration.Payload with the raising of task precision, on satellite
Increasingly harsher requirement is proposed, to the micro-vibration environment of satellite in-orbit period to reach the task index of design.However, being
Guarantee the conventional function such as satellite gravity anomaly, thermal control, solar wing Direct to the sun, many machines of installation and operation on satellite
The vibration that electric equipment can cause satellite structure small deteriorates the vibration environment during satellite task executes, once micro-vibration environment
It is not able to satisfy high-precision mission requirements, it is necessary to take micro-vibration vibration isolation measure.
Micro-vibration vibration isolation technique refers to increasing in Vibration propagation path actively or passively component (vibration isolator), subtracts
Small vibration source is transmitted to the energy of load.Vibration isolator can be divided into passive vibration isolation, semi-active vibration-isolating, active vibration isolation and mixing every
Vibration.It is passive vibration isolation high reliablity, at low cost, extra power is not consumed, has good inhibition to high-frequency vibration, reduces passive vibration isolation
Device intrinsic frequency is to improve the effective ways of anti-vibration performance.In addition, resonance can effectively be inhibited by increasing damping, but decay simultaneously
Inhibition to high-frequency vibration, single-degree-of-freedom and two degrees of freedom passive vibration isolation have been widely used, for example are made using viscous material
Vibration suppression is carried out for passive damping.But passive vibration isolation is not suitable for inhibiting random and low-frequency vibration, is also not suitable for same
When inhibit resonance and high frequency response.Semi-active vibration-isolating can be further improved anti-vibration performance, it is logical according to different environmental conditions
Change damping and rigidity are crossed, anti-vibration performance, such as the semi-active vibration-isolating obtained by change rigidity and damping are improved.But it is passive
The theoretical limitation of vibration isolation still has, such as the contradiction that resonance amplification and high-frequency vibration inhibit, and changes rigidity and need again
Miscellaneous equipment, semi-active vibration-isolating substantially nevertheless suffer from the limitation of passive vibration isolation.
With the progress of modern control technology and smart actuators technology, active vibration isolation by increasing attention, it
Theoretically relatively passive and semi-active vibration-isolating is with more superior performance.In order to which the reliability for improving active vibration isolation is simultaneously sufficiently sharp
With the advantage of passive vibration isolation, active vibration isolation can be used on the basis of passive vibration isolation, constituted hybrid vibration isolation system, reached high-precision
Spend highly reliable vibration isolating effect.Therefore, it is necessary to provide a kind of in-orbit micro-vibration low frequency vibration isolation method and apparatus of spacecraft.
Summary of the invention
Based on this, the purpose of the present invention is to provide a kind of micro-vibration low frequency vibration isolation devices that spacecraft is in-orbit, for defending
The isolation of the in-orbit micro-vibration of high-precision scientific instruments equipment on magnitude spacecraft.
Technical scheme is as follows:
A kind of micro-vibration low frequency vibration isolation device that spacecraft is in-orbit mainly includes vibration isolation object support plate, isolation spring, resistance
Buddhist nun's device, inner hinge, spring elongation quantity regulating device, outer hinge and pedestal, the vibration isolation object support plate have setting vibration isolation
The installation interface of object；Isolation spring structure in parallel with damper is separately connected by several inner hinges around vibration isolation object support plate
At vibration isolation unit side, the other side of vibration isolation unit passes through several outer hinges and spring elongation quantity regulating device respectively and connects
It connects, vibration isolation unit is whole free to rotate around inside and outside hinge, and isolation spring is drawing spring, provides vibration isolation institute for vibration isolation object
The rigidity needed；Wherein, when vibration isolation vibrating objects generate displacement, inside and outside hinge provides rotational freedom for vibration isolation unit, guarantees
Spring generates stretcher strain, and the side wall of spring elongation quantity regulating device and concave base is attached, by regulating device to every
The initial tensile amount of vibration spring is adjusted, and vibration isolator rigidity is arranged, and pedestal has the installation interface fixed with extraneous structure.
Wherein, multiple vibration isolation units are arranged relative to vibration isolation object at axial symmetry.
Wherein, vibration isolation unit totally four and vibration isolation object support plate it is circumferential be arranged to every 90 ° it is symmetrical two-by-two.
Wherein, the spring in vibration isolation unit is the mode of multiple parallel connections.
Wherein, spring elongation quantity regulating device is the fit structure of the screw rod being threaded through on pedestal side wall and nut fastening.
Wherein, screw rod is fastenedly connected as spring elongation quantity regulating device, one end of screw rod by nut and pedestal, works as pine
When opening nut, screw rod is mobile, and the other end is connect with the hinge of spring outwards root；By unclamping nut, mobile screw changes bullet
The initial tensile amount of spring after adjusting in place, is fastened screw rod and pedestal by nut.
Wherein, vibration isolation object support plate uses the tower structure or aluminum honeycomb covering plank frame of aluminium alloy production.
Wherein, damper is fluid damper, MR damper or electromagnetic damper.
Further, the number of damper is identical as isolation spring number.
The present invention establishes a kind of low frequency vibration isolation device of in-orbit micro-vibration of spacecraft, realize the in-orbit micro-vibration of spacecraft every
Vibration, it is horizontal to improve the in-orbit disturbance component vibration isolation technique of satellite, meet satellite especially high-precision earth observation satellite to
The demand of rail micro-vibration environment.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the in-orbit micro-vibration low frequency vibration isolation device of spacecraft of the invention；
Wherein, 1-vibration isolation object support plate；2-inner hinges；3-isolation springs；4-dampers；5-outer hinges；6—
Spring elongation quantity regulating device；7-pedestals.
Fig. 2 is the spring elongation quantity regulating device structure in the in-orbit micro-vibration low frequency vibration isolation device of spacecraft of the invention
Figure.
Wherein, 21 be screw rod；22 be nut；7 be pedestal.
Specific embodiment
The structure of the in-orbit micro-vibration low frequency vibration isolation device of spacecraft of the invention is carried out furtherly with reference to the accompanying drawing
Bright, which is only exemplary, it is no intended to limit the scope of the invention.
Fig. 1 is the structural schematic diagram of the in-orbit micro-vibration low frequency vibration isolation device of spacecraft of the invention.Wherein, dress of the invention
It sets including vibration isolation object support plate 1, isolation spring 3, spring elongation quantity regulating device 6, inner hinge 2, outer hinge 5,4 and of damper
Pedestal 7, the vibration isolation object support plate 1 have the installation interface of setting vibration isolation object；Pass through around vibration isolation object support plate 1
Several inner hinges 2 are separately connected the side of the vibration isolation unit of the composition in parallel with damper 4 of isolation spring 3, vibration isolation unit it is another
Side passes through several outer hinges 5 respectively and connect with spring elongation quantity regulating device 6, and vibration isolation unit is whole can be certainly around inside and outside hinge 2,5
By rotating, isolation spring 3 is drawing spring, rigidity needed for providing vibration isolation for vibration isolation object；Wherein, when vibration isolation vibrating objects
When generating displacement, inside and outside hinge 2,5 provides rotational freedom for vibration isolation unit, guarantees that spring generates stretcher strain, spring elongation
Quantity regulating device 6 and the side wall of concave base 7 are attached, by spring elongation quantity regulating device 6 to the initial of isolation spring 3
Amount of tension is adjusted, and vibration isolator rigidity is arranged, and pedestal 7 has the installation interface fixed with extraneous structure.Specifically:
(1) vibration isolation object support plate
The main function of vibration isolation object support plate 1 is that the interface of installation is provided for vibration isolation object, the shape and ruler of support plate
It is very little to be designed according to vibration isolation object mechanical interface, the tower structure or aluminum honeycomb covering plank frame of aluminium alloy production can be used.
(2) isolation spring
Isolation spring uses drawing spring, multiple springs with parallel way by with pedestal and vibration isolation object support plate
Connection forms rock-steady structure, carries out vibration isolation to vibration isolation object.After supporting vibration isolation object, vibration isolation object is with what isolation mounting formed
System has lower intrinsic frequency, realizes the low frequency vibration isolation of vibration isolation object.Mechanical extension spring can be used in isolation spring, implements
Mode is total in three steps:
The first step chooses spring number, generally according to circumferential every 90 ° of settings, one spring in vibration isolation object support plate,
Spring number is chosen for 4.
Second step determines the rigidity of isolation mounting.It is dynamic according to structure according to the quality of vibration isolation object and isolation frequency requirement
Mechanics principle, the rigidity upper limit value of isolation mounting according to the following formula:
K in formulasys_maxFor the rigidity upper limit value of isolation mounting, fisoFor isolation frequency, M is vibration isolation object quality.
For example, vibration isolation object quality 5kg, isolation frequency 1Hz, then the rigidity upper limit value of isolation mounting is Ksys_max=2 π2×
12× 5=98.7N/m.
Third step determines spring rate and initial tensile amount.According to isolation mounting theory of constitution, when isolation mounting initial bit
The rigidity set is Ksys_maxWhen, the rigidity of single spring is
N is spring number in formula, and α is spring initial tensile amount, i.e., length and spring after applying initial tensile to spring
The ratio of drift when being not applied to initial tensile.
According to above-mentioned formula, after isolation mounting rigidity, spring number determine, the rigidity and initial tensile amount of single spring
With certain functional relation, different initial tensile amounts corresponds to different spring rates.To guarantee spring works state rigidity
Stability of characteristics, it is 1.2~1.5 that general initial tensile, which measures, and then can determine the rigidity of single spring.
For example, vibration isolator stiffness Ksys_max=98.7N/m, spring number n=4, initial tensile amount α=1.2, then single bullet
The rigidity of spring is
(3) damper
Damper is mainly used for inhibiting vibration isolator resonance, and fluid damper, MR damper or electromagnetic damping can be used
Device.Damper number is identical as isolation spring, is installed in parallel with isolation spring.
(4) spring elongation quantity regulating device
Spring elongation quantity regulating device is used for the requirement according to isolation frequency, adjusts setting initial tensile amount to spring.
Most basic embodiment is that spring elongation quantity regulating device is used as using screw rod, one end of screw rod by nut and
Pedestal is fastenedly connected, and when unclamping nut, screw rod can be moved, and the other end is connect with the hinge of spring outwards root.Pass through pine
Nut is opened, mobile screw changes the initial tensile amount of spring.After adjusting in place, screw rod and pedestal are fastened by nut.
Above embodiment is most basic method, and the mechanical devices such as flower basket bolt can be used and realize same function.
(5) hinge
The effect of hinge is to guarantee that spring is in stretching shape always when vibration isolator object support plate opposite base vibrates
State.Embodiment be using ball-type kinematic pair hinge, hinge setting in both ends of the spring, wherein the hinge connecting spring of one end and every
The object support plate that shakes connects, the hinge connecting spring and spring elongation quantity regulating device of the other end.Hinge can be at the angle of restriction
It is rotated freely in degree.When vibration isolation vibrating objects, the vibration displacement for driving support plate to be translatable and reverse therewith is connected by hinge
It connects, guarantees that extension spring is in tensional state always.Above embodiment is most basic method, and flexible hinge etc. can be used
Realize same function.
(6) pedestal
The interface that the main function of pedestal is to provide vibration isolator and extraneous structure is fixed, provides spring elongation quantity regulating device
Installation interface, keeping vibration isolator is complete as a result, frame-type mechanical structure can be used, and mainly uses stainless steel or aluminium alloy
For material, the composite materials such as aluminum honeycomb covering can also be used to mitigate weight.
Although the detailed description and description of the specific embodiments of the present invention are given above, it should be noted that
We can carry out various equivalent changes and modification to above embodiment according to the concept of the present invention, and generated function is made
It, should all be within protection scope of the present invention when with the spirit still covered without departing from specification and attached drawing.
Claims (9)
1. the in-orbit micro-vibration low frequency vibration isolation device of spacecraft, mainly include vibration isolation object support plate, isolation spring, damper,
Inner hinge, spring elongation quantity regulating device, outer hinge and pedestal, the vibration isolation object support plate have setting vibration isolation object
Interface is installed；Around vibration isolation object support plate by several inner hinges be separately connected isolation spring it is in parallel with damper constitute every
The side of vibration unit, the other side of vibration isolation unit pass through several outer hinges respectively and connect with spring elongation quantity regulating device, vibration isolation
Unit is whole free to rotate around inside and outside hinge, and isolation spring is drawing spring, provides for vibration isolation object rigid needed for vibration isolation
Degree；Wherein, when vibration isolation vibrating objects generate displacement, inside and outside hinge provides rotational freedom for vibration isolation unit, guarantees that spring produces
The side wall of raw stretcher strain, spring elongation quantity regulating device and concave base is attached, by regulating device to isolation spring
Initial tensile amount be adjusted to be arranged the rigidity of vibration isolation unit, pedestal has the installation interface fixed with extraneous structure.
2. micro-vibration low frequency vibration isolation device as described in claim 1, wherein multiple vibration isolation units are relative to vibration isolation object at axis pair
Claim setting.
3. micro-vibration low frequency vibration isolation device as described in claim 1, wherein vibration isolation unit totally four and in vibration isolation object support
Plate is circumferentially arranged to every 90 ° symmetrical two-by-two.
4. micro-vibration low frequency vibration isolation device as described in claim 1, wherein the spring in vibration isolation unit is the side of multiple parallel connections
Formula.
5. micro-vibration low frequency vibration isolation device as described in claim 1, wherein spring elongation quantity regulating device is to be threaded through pedestal
The fit structure of screw rod and nut fastening on side wall.
6. micro-vibration low frequency vibration isolation device as claimed in claim 5, wherein screw rod is as spring elongation quantity regulating device, spiral shell
One end of bar is fastenedly connected by nut and pedestal, and when unclamping nut, screw rod is mobile, the hinge of the other end and spring outwards root
Chain link；By unclamping nut, mobile screw changes the initial tensile amount of spring, after adjusting in place, by nut by screw rod with
Pedestal fastening.
7. micro-vibration low frequency vibration isolation device as claimed in any one of claims 1 to 6, wherein vibration isolation object support plate is closed using aluminium
The tower structure or aluminum honeycomb covering plank frame of gold production.
8. micro-vibration low frequency vibration isolation device as claimed in any one of claims 1 to 6, wherein damper is fluid damper, magnetic
Rheological damper or electromagnetic damper.
9. micro-vibration low frequency vibration isolation device as claimed in claim 8, wherein the number of damper and isolation spring number phase
Together.
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| CN111129689B (en) * | 2020-01-13 | 2021-10-01 | 北京工业大学 | Vibration reduction component of large-scale self-unfolding satellite antenna |
| CN111624877B (en) * | 2020-04-28 | 2022-07-05 | 北京控制工程研究所 | Spacecraft three-super-control self-adaptive variable-stiffness variable-damping full-frequency-band disturbance suppression method |
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| JP4571891B2 (en) * | 2005-07-01 | 2010-10-27 | 富士通株式会社 | Vibration isolator |
| CN100436261C (en) * | 2006-08-25 | 2008-11-26 | 郑钢铁 | Integrated shock absorbing vibrating isolation device for stellite |
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| CN103758921B (en) * | 2014-01-08 | 2016-02-17 | 上海大学 | A kind of for suppressing the non-linear vibration damping device of astrovehicle micro-vibration in-orbit |
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