CN106956785A - 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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- CN106956785A CN106956785A CN201510417377.1A CN201510417377A CN106956785A CN 106956785 A CN106956785 A CN 106956785A CN 201510417377 A CN201510417377 A CN 201510417377A CN 106956785 A CN106956785 A CN 106956785A
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Abstract
The invention discloses a kind of 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, connect the side of the vibration isolation unit of isolation spring composition in parallel with damper around vibration isolation object support plate respectively by some inner hinges, the opposite side of vibration isolation unit is connected by some outer hinges with spring elongation quantity regulating device respectively, vibration isolation unit is overall free to rotate around inside and outside hinge, when vibration isolation vibrating objects produce displacement, inside and outside hinge provides rotational freedom for vibration isolation unit, ensure that spring produces 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 particularly high-precision earth observation satellite of satellite to in-orbit micro-vibration environment.
Description
Technical field
The invention belongs to the vibration control technology field of spacecraft product, and in particular to a kind of in-orbit micro-vibration low frequency vibration isolation method and apparatus of spacecraft.
Background technology
The precision for improving spacecraft product aerial mission is an important trend of present satellites development, the field such as earth observation remote sensing, laser communication, space science experiment, survey of deep space.With the raising of task precision, the payload on satellite proposes increasingly harsher requirement to the micro-vibration environment of satellite in-orbit period, to reach the task index of design.But, the function conventional in order to ensure satellite gravity anomaly, thermal control, solar wing Direct to the sun etc., many electromechanical equipments of installation and operation can cause the small vibration of satellite structure on satellite, deteriorate the vibration environment during satellite task is performed, once micro-vibration environment can not meet 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), reduces the energy that vibration source is delivered to load.Vibration isolator can be divided into passive vibration isolation, semi-active vibration-isolating, active vibration isolation and hybrid vibration isolation.Passive vibration isolation reliability is high, low cost, does not consume extra power, there is good suppression to dither, and reduction passive vibration isolation device intrinsic frequency is to improve the effective ways of anti-vibration performance.In addition, increase damping can effectively suppress resonance, but the suppression to dither that decayed simultaneously, single-degree-of-freedom and two degrees of freedom passive vibration isolation have been widely used, such as are used as passive damping to carry out vibration suppression using viscous material.But passive vibration isolation is not suitable for suppressing random and low-frequency vibration, it is also not suitable for while suppressing resonance and high frequency response.Semi-active vibration-isolating can further improve anti-vibration performance, and it, by changing damping and rigidity, improves anti-vibration performance according to different environmental conditions, such as by changing the semi-active vibration-isolating that rigidity and damping are obtained.But the theoretical limitation of passive vibration isolation still has, such as the contradiction that resonance amplification and dither suppress, and change the complicated equipment of rigidity needs, semi-active vibration-isolating substantially nevertheless suffers from the limitation of passive vibration isolation.
With the progress of modern control technology and smart actuators technology, active vibration isolation is by increasing attention, and passive and semi-active vibration-isolating has more superior performance relatively in theory for it.In order to improve the reliability of active vibration isolation and make full use of the advantage of passive vibration isolation, active vibration isolation can be used on the basis of passive vibration isolation, hybrid vibration isolation system is constituted, the highly reliable vibration isolating effect of high accuracy is reached.Therefore, it is necessary to provide a kind of spacecraft in-orbit micro-vibration low frequency vibration isolation method and apparatus.
The content of the invention
Based on this, it is an object of the invention to provide a kind of in-orbit micro-vibration low frequency vibration isolation device of spacecraft, the isolation of the in-orbit micro-vibration of high-precision scientific instruments equipment on the spacecrafts such as satellite.
Technical scheme is as follows：
A kind of 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, described vibration isolation object support plate has the mounting interface for setting vibration isolation object；Connect the side of the vibration isolation unit of isolation spring composition in parallel with damper around vibration isolation object support plate respectively by some inner hinges, the opposite side of vibration isolation unit is connected by some outer hinges with spring elongation quantity regulating device respectively, vibration isolation unit is overall free to rotate around inside and outside hinge, isolation spring is drawing spring, for the rigidity needed for vibration isolation object provides vibration isolation；Wherein, when vibration isolation vibrating objects produce displacement, inside and outside hinge provides rotational freedom for vibration isolation unit, ensure that spring produces stretcher strain, spring elongation quantity regulating device and the side wall of concave base are attached, the incipient extension amount of isolation spring is adjusted by adjusting means, vibration isolator rigidity is set, pedestal has the mounting interface fixed with extraneous structure.
Wherein, multiple vibration isolation units are set relative to vibration isolation object into axial symmetry.
Wherein, vibration isolation unit totally four and every 90 ° is arranged to symmetrical two-by-two vibration isolation object support plate is circumferential.
Wherein, the spring in vibration isolation unit is multiple modes in parallel.
Wherein, it is the fit structure that the screw rod being located on base side wall is fastened with nut that spring, which draws high quantity regulating device,.
Wherein, screw rod is as spring elongation quantity regulating device, and one end of screw rod is fastenedly connected by nut with pedestal, when unclamping nut, screw rod movement, the other end and the chain connection of spring outwards root；By unclamping nut, mobile screw changes the incipient extension amount of spring, after regulation in place, is fastened screw rod and pedestal by nut.
Wherein, vibration isolation object support plate uses the tower structure or aluminium honeycomb skin plank frame that aluminium alloy makes.
Wherein, damper is fluid damper, MR damper or electromagnetic damper.
Further, the number of damper is identical with isolation spring number.
The present invention sets up a kind of low frequency vibration isolation device of the in-orbit micro-vibration of spacecraft, realize the vibration isolation of the in-orbit micro-vibration of spacecraft, the in-orbit disturbance component vibration isolation technique level of satellite is improved, demand of the particularly high-precision earth observation satellite of satellite to in-orbit micro-vibration environment is met.
Brief description of the drawings
Fig. 1 is the structural representation of the in-orbit micro-vibration low frequency vibration isolation device of spacecraft of the present invention；
Wherein, 1-vibration isolation object support plate；2-inner hinge；3-isolation spring；4-damper；5-outer hinge；6-spring elongation adjusting means；7-pedestal.
Fig. 2 is the spring elongation quantity regulating device structure chart in the in-orbit micro-vibration low frequency vibration isolation device of spacecraft of the present invention.
Wherein, 21 be screw rod；22 be nut；7 be pedestal.
Embodiment
The structure to the in-orbit micro-vibration low frequency vibration isolation device of spacecraft of the present invention is further described below in conjunction with the accompanying drawings, what the explanation was merely exemplary, it is no intended to limit the scope of the invention.
Fig. 1 is the structural representation of the in-orbit micro-vibration low frequency vibration isolation device of spacecraft of the present invention.Wherein, the inventive system comprises vibration isolation object support plate 1, isolation spring 3, spring elongation quantity regulating device 6, inner hinge 2, outer hinge 5, damper 4 and pedestal 7, described vibration isolation object support plate 1 has the mounting interface for setting vibration isolation object；Connect the side of the vibration isolation unit of the composition in parallel with damper 4 of isolation spring 3 around vibration isolation object support plate 1 respectively by some inner hinges 2, the opposite side of vibration isolation unit draws high adjusting means 6 with spring by some outer hinges 5 respectively and is connected, vibration isolation unit is overall around inside and outside hinge 2,5 is free to rotate, isolation spring 3 is drawing spring, for the rigidity needed for vibration isolation object provides vibration isolation；Wherein, when vibration isolation vibrating objects produce displacement, inside and outside hinge 2,5 provide rotational freedom for vibration isolation unit, ensure that spring produces stretcher strain, spring elongation quantity regulating device 6 and the side wall of concave base 7 are attached, the incipient extension amount of isolation spring 3 are adjusted by spring elongation quantity regulating device 6, vibration isolator rigidity is set, and pedestal 7 has the mounting interface fixed with extraneous structure.Specifically：
(1) vibration isolation object support plate
The main function of vibration isolation object support plate 1 is to provide the interface installed for vibration isolation object, and the shape and size of supporting plate are designed according to vibration isolation object mechanical interface, the tower structure or aluminium honeycomb skin plank frame that can be made using aluminium alloy.
(2) isolation spring
Isolation spring uses drawing spring, and multiple springs form rock-steady structure with parallel way by the connection with pedestal and vibration isolation object support plate, and vibration isolation is carried out to vibration isolation object.Support after vibration isolation object, the system that vibration isolation object is constituted with isolation mounting has relatively low intrinsic frequency, realizes the low frequency vibration isolation of vibration isolation object.Isolation spring can be used mechanical extension spring, and embodiment is altogether in three steps：
The first step, chooses spring number, circumferentially sets a spring every 90 ° generally according in vibration isolation object support plate, spring number is chosen for 4.
Second step, determines the rigidity of isolation mounting.According to the quality of vibration isolation object and isolation frequency requirement, the rigidity higher limit according to Structural Dynamics principle, according to the following formula isolation mounting：
K in formulasys_maxFor the rigidity higher limit 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 higher limit of isolation mounting is Ksys_max=2 π2×12× 5=98.7N/m.
3rd step, determines spring rate and incipient extension amount.According to isolation mounting theory of constitution, when the rigidity of isolation mounting initial position is Ksys_maxWhen, the rigidity of single spring is
N is spring number in formula, and α is spring incipient extension amount, i.e., apply the ratio of drift when the length after incipient extension is not applied to incipient extension with spring to spring.
According to above-mentioned formula, after isolation mounting rigidity, spring number are determined, rigidity and the incipient extension measurer of single spring have certain functional relation, the different spring rate of different incipient extension amount correspondences.Stable to ensure spring works state stiffness characteristics, general incipient extension is measured as 1.2~1.5, and then can determine the rigidity of single spring.
For example, vibration isolator stiffness Ksys_max=98.7N/m, spring number n=4, incipient extension amount α=1.2, then the rigidity of single spring be
(3) damper
Damper is mainly used in suppressing vibration isolator resonance, can use fluid damper, MR damper or electromagnetic damper.Damper number is identical with 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, and incipient extension amount is set to spring regulation.
Most basic embodiment is that one end of screw rod is fastenedly connected by nut with pedestal as spring elongation quantity regulating device using screw rod, and when unclamping nut, screw rod can be moved, the other end and the chain connection of spring outwards root.By unclamping nut, mobile screw changes the incipient extension amount of spring.After regulation in place, screw rod and pedestal are fastened by nut.
Above-mentioned embodiment is most basic method, and the mechanical devices such as flower basket bolt can be used to realize same function.
(5) hinge
The effect of hinge is to ensure that spring is in extended state all the time when vibration isolator object support plate opposite base vibrates.Embodiment is to use ball-type kinematic pair hinge, and hinge is arranged on both ends of the spring, wherein the chain connection spring of one end and the connection of vibration isolation object support plate, the chain connection spring and spring elongation adjusting means of the other end.Hinge can be rotated freely in the angle of restriction.When vibration isolation vibrating objects, supporting plate translation and the vibration displacement reversed therewith are driven, is connected through the hinge, it is ensured that extension spring is in extended state all the time.Above-mentioned embodiment is most basic method, and flexible hinge etc. can be used to realize same function.
(6) pedestal
The main function of pedestal is to provide the interface that vibration isolator is fixed with extraneous structure, the mounting interface of spring elongation quantity regulating device is provided, holding vibration isolator is complete result, frame-type mechanical structure can be used, stainless steel or aluminium alloy mainly are used for material, can also use the composites such as aluminium honeycomb skin to mitigate weight.
Although the embodiment to the present invention gives detailed description and explanation above; but it should be noted that; we can carry out various equivalent changes and modification according to conception of the invention to above-mentioned embodiment;, all should be within protection scope of the present invention during the spirit that function produced by it is still covered without departing from specification and accompanying drawing.
Claims (9)
1. a kind of 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, it is described
Vibration isolation object support plate has the mounting interface for setting vibration isolation object；If around vibration isolation object support plate by
Dry inner hinge connects the side of the vibration isolation unit of isolation spring composition in parallel with damper, vibration isolation unit respectively
Opposite side be connected respectively by some outer hinges with spring elongation quantity regulating device, vibration isolation unit it is overall around
Inside and outside hinge is free to rotate, and isolation spring is drawing spring, for needed for vibration isolation object provides vibration isolation
Rigidity；Wherein, when vibration isolation vibrating objects produce displacement, inside and outside hinge provides rotation certainly for vibration isolation unit
By spending, it is ensured that spring produces stretcher strain, the side wall progress of spring elongation quantity regulating device and concave base
Connection, the incipient extension amount of isolation spring is adjusted by adjusting means, sets vibration isolator rigidity,
Pedestal has the mounting interface fixed with extraneous structure.
2. micro-vibration low frequency vibration isolation device as claimed in claim 1, wherein, multiple vibration isolation unit phases
Vibration isolation object is set into axial symmetry.
3. micro-vibration low frequency vibration isolation device as claimed in claim 1, wherein, vibration isolation unit totally four
And circumferentially it is arranged to symmetrical two-by-two every 90 ° in vibration isolation object support plate.
4. micro-vibration low frequency vibration isolation device as claimed in claim 1, wherein, the bullet in vibration isolation unit
Spring is multiple modes in parallel.
5. micro-vibration low frequency vibration isolation device as claimed in claim 1, wherein, the regulation of spring elongation amount
Device is the fit structure that the screw rod being located on base side wall is fastened with nut.
6. micro-vibration low frequency vibration isolation device as claimed in claim 5, wherein, screw rod is drawn as spring
Quantity regulating device is stretched, one end of screw rod is fastenedly connected by nut with pedestal, when unclamping nut, screw rod
It is mobile, the other end and the chain connection of spring outwards root；By unclamping nut, mobile screw changes
The incipient extension amount of spring, after regulation in place, is fastened screw rod and pedestal by nut.
7. the micro-vibration low frequency vibration isolation device as described in claim any one of 1-6, wherein, vibration isolation pair
As supporting plate uses the tower structure or aluminium honeycomb skin plank frame that aluminium alloy makes.
8. the micro-vibration low frequency vibration isolation device as described in claim any one of 1-6, wherein, damper
For fluid damper, MR damper or electromagnetic damper.
9. micro-vibration low frequency vibration isolation device as claimed in claim 8, wherein, the number of damper with
Isolation spring number is identical.
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Cited By (4)
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| CN109176473A (en) * | 2018-10-08 | 2019-01-11 | 哈工大机器人（合肥）国际创新研究院 | A kind of fine-tuning active compliance floating platform and method |
| CN111129689A (en) * | 2020-01-13 | 2020-05-08 | 北京工业大学 | Vibration reduction component of large-scale self-unfolding satellite antenna |
| CN111624877A (en) * | 2020-04-28 | 2020-09-04 | 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 |
| CN115182937A (en) * | 2022-07-18 | 2022-10-14 | 西南石油大学 | Rigidity-variable laminated coupler for crankshaft vibration control |
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| CN111129689A (en) * | 2020-01-13 | 2020-05-08 | 北京工业大学 | Vibration reduction component of large-scale self-unfolding satellite antenna |
| CN111624877A (en) * | 2020-04-28 | 2020-09-04 | 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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| CN115182937A (en) * | 2022-07-18 | 2022-10-14 | 西南石油大学 | Rigidity-variable laminated coupler for crankshaft vibration control |
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