CN103448921B - The vibration isolating method of aclinal satellite sensitive load - Google Patents
The vibration isolating method of aclinal satellite sensitive load Download PDFInfo
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- CN103448921B CN103448921B CN201310345398.8A CN201310345398A CN103448921B CN 103448921 B CN103448921 B CN 103448921B CN 201310345398 A CN201310345398 A CN 201310345398A CN 103448921 B CN103448921 B CN 103448921B
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Abstract
The present invention relates to a kind of vibration isolating method of aclinal satellite sensitive load, for the performance figure requirement of load, vibrating isolation system bandwidth sum decoupling zero degree is analyzed, compared for different arrangement form and different transverse and longitudinal ratio of rigidity to the impact of system performance, propose a kind of aclinal vibrating isolation system method for arranging.Described vibrating isolation system comprises transverse direction and supports with longitudinal rigidity is more in parallel than 3 flexible unit between 0.4 ~ 0.8, and with load barycenter vertical curve for axle is uniform, aclinal is placed.Native system does not need transition contiguous block, lightweight, and barycenter is low, six-degree-of-freedom vibration isolation excellent performance.The present invention can carry by the weight of vibration isolation object, ensure technological while, the transmission of effective separating vibration, reaches the object that vibrating isolation system frequency band is low and system decoupling is good.
Description
Technical field
The present invention relates to the vibration isolation of satellite sensitive load, especially by the layout of flexible unit in design vibrating isolation system, take the vertical modes of emplacement of aclinal, while considering manufacturability and energy saving, realize the vibration isolation of satellite sensitive load, be specifically related to a kind of vibration isolating method of aclinal satellite sensitive load.
Background technology
Along with the development of space technology, improving constantly of load performance and precision, the requirement of sensitive load to the stability of satellite platform of Seeds of First Post-flight is more and more higher.During satellite operation on orbit, the motion of rotatable parts may be coupled with the elastic oscillation of the flexible part such as sun battle array, magnetometer, and cause the vibration of satellite structure platform, this operating accuracy that will inevitably reduce load even may cause the failure of its task.
Conventional vibration isolation design complex structure, quality is large, is not suitable for space environment, therefore, need to isolate the vibration passing of satellite platform to sensitive load, designing a kind of vibrating isolation system not only considered manufacturability but also considered energy saving, is one of main path of dealing with problems.
Summary of the invention
The invention provides a kind of vibration isolating method of aclinal satellite sensitive load, it uses three flexible unit to be arranged symmetrically with, and 3 aclinal parallel connections support, while having load-carrying capacity, possesses good anti-vibration performance, the lower and good object of system decoupling of vibrating isolation system frequency band.
For achieving the above object, present invention employs following technical scheme:
A vibration isolating method for aclinal satellite sensitive load, comprises the steps:
Step 1: analyze load performance index request;
Step 2: ensure stable load, determine supported at three point mode;
Step 3: according to satellite platform layout and load initial conditions, considers interface position and manufacturability simultaneously, determines the installation site of the vibration isolation unit of vibrating isolation system;
Step 4: find attachment point of equal value, 3 elastic elements are after the stiffness combination of its true point of connection, consistent with the rigidity of attachment point of equal value, and the stiffness matrix namely after synthesis is diagonal matrix at attachment point place of equal value;
Step 5: computing system bandwidth and decoupling zero degree;
Step 6: analyze the different setting angle of flexible unit to the impact of anti-vibration performance, determine aclinal mounting means;
Step 7: the impact of the different horizontal longitudinal rigidity Compare System anti-vibration performance of com-parison and analysis vibration isolator;
Step 8, selects optimum horizontal longitudinal rigidity ratio, considers carrying, anti-vibration performance and manufacturability simultaneously, carries out designing and emulates, determine lateral stiffness and longitudinal rigidity to vibration isolator.
Preferably, also comprise the steps:
Step 9, carries out verification experimental verification to vibrating isolation system.
Preferably, vibrating isolation system comprises 3 flexible unit parallel connection supports of responsible vibration isolation.
Preferably, vibration isolator laterally and longitudinal rigidity than between 0.4 ~ 0.8,3 flexible unit for axle is uniform, vertically place aclinal with load barycenter vertical curve.
Preferably, described flexible unit is installed between satellite sensitive load and satellite platform.
Preferably, vibration isolator is directly connected with satellite platform and satellite sensitive load, does not need additional connecting device.
Preferably, satellite platform imbedded by vibration isolator, to reduce load height.
The present invention, compared to prior art, has following advantage and good effect:
1, adopt the mode of supported at three point, utilize 3 coplanar, make load base plate steady, prevent load self-deformation, cause unwanted vibrations;
2, vertically place, design configuration is simple, has good design flexibility, realizes economy and assembly process process, and Interface design is convenient;
3, vertically placement can be avoided using contiguous block, by reducing the vibrating isolation system weight of half, alleviates satellite burden;
4, vertically place and flexible unit can be imbedded celestial body structure, reduce load barycenter, make load more stable;
Although according to certain angle, 5 arrange that coupling is good, when practical set, three vibration isolator axis are difficult to cross, and joint is also difficult to ensure to overlap with load center of mass point, and the unavoidable like this coupling performance that makes declines.Use vertical modes of emplacement, vertical easily guarantee, and easy to assembly, economize on resources.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is that the present invention arranges schematic diagram.
In figure:
1 is flexible vibration isolation unit;
2 is load;
3 is satellite platform.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
First, according to by the layout scenarios on vibration isolation quality of loads 309.5kg and satellite top board, flexible vibration isolation unit quantity is 3, and the scope of installing diameter is 509.3mm ~ 776.1mm, according to the design of conceptual level, design and installation diameter is 728mm(radius 364mm).
The distribution form of flexible vibration isolation unit as shown in Figure 1.Z-direction isolation frequency setting about 14Hz (corresponding axial stiffness is about 800N/mm), Z-direction amount of compression is at about 1.27mm.The support angle that the basis of above condition finds suitable lateral stiffness and vibration isolation unit reaches the lower and good object of system decoupling of vibrating isolation system frequency band.
According to the impact on bandwidth and system fundamental frequency under lateral stiffness and flexible unit change of pitch angle situation of known Parameter analysis.The ratio of setting lateral stiffness and axial stiffness is u, and its variation range is that 0.2 ~ 2.0(can realize according to engineering and the actual factor used considers), the angle change of support is from 0 to 90 °.
The each order frequency of vertical installation system and coupling condition as shown in the table: maximum distribution radius R max=410mm, height of center of mass 364mm, rigidity is X-direction 640N/mm, Y-direction 640N/mm, Z-direction 889N/mm(ratio of rigidity u=0.72).
The each order frequency of table 1 and coupling condition
| Frequency | X | Y | Z | RXX | RYY | RZZ | |
| 1 | 6.04171 | 0.03 | 40.49 | 0.00 | 59.41 | 0.02 | 0.00 |
| 2 | 7.07232 | 58.44 | 0.05 | 0.00 | 0.05 | 33.45 | 4.21 |
| 3 | 8.64557 | 6.81 | 0.00 | 0.00 | 0.00 | 2.31 | 95.70 |
| 4 | 14.7741 | 0.00 | 0.00 | 100.00 | 0.00 | 0.00 | 0.00 |
| 5 | 15.4699 | 0.04 | 59.44 | 0.00 | 40.48 | 0.01 | 0.00 |
| 6 | 18.8125 | 34.67 | 0.02 | 0.00 | 0.10 | 66.95 | 2.79 |
Calculate: along with ratio of rigidity coefficient u is larger, the bandwidth of system is also larger, but practical application u is also unsuitable too small, otherwise vibrating isolation system natural frequency is too small, vibration isolator intensity reduces, and suitable span is about 0.4 ~ 0.8 (less than 1.0); It is better that vibration isolator inclination installation seems coupling performance, but Rmax is certain during vibration isolator actual installation, tilt will the distribution radius rmax of vibration isolator and load attachment point be caused to reduce, vibrating isolation system be with less by the rmax distribution radius of vibration isolation object, then system performance is poorer.Therefore, offset on a large scale due to the fixing of Rmax, advantage is no longer obvious; Vibration isolation efficiency is more than 95%.
Therefore, the present invention is carrying the weight of vibrating isolation system, ensure technological while, and the transmission of effective separating vibration, reaches the lower and good object of system decoupling of vibrating isolation system frequency band.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (5)
1. a vibration isolating method for aclinal satellite sensitive load, is characterized in that, comprises the steps:
Step 1: analyze load performance index request;
Step 2: ensure stable load, determine supported at three point mode;
Step 3: according to satellite platform layout and load initial conditions, considers interface position and manufacturability simultaneously, determines the installation site of the vibration isolation unit of vibrating isolation system;
Step 4: find attachment point of equal value, 3 elastic elements are after the stiffness combination of its true point of connection, consistent with the rigidity of attachment point of equal value, and the stiffness matrix namely after synthesis is diagonal matrix at attachment point place of equal value;
Step 5: computing system bandwidth and decoupling zero degree;
Step 6: analyze the different setting angle of flexible unit to the impact of anti-vibration performance, determine aclinal mounting means;
Step 7: the impact of the different horizontal longitudinal rigidity Compare System anti-vibration performance of com-parison and analysis vibration isolator;
Step 8, selects optimum horizontal longitudinal rigidity ratio, considers carrying, anti-vibration performance and manufacturability simultaneously, carries out designing and emulates, determine lateral stiffness and longitudinal rigidity to vibration isolator;
Vibration isolator laterally and longitudinal rigidity than between 0.4 ~ 0.8,3 flexible unit for axle is uniform, vertically place aclinal with load barycenter vertical curve;
Satellite platform imbedded by vibration isolator, to reduce load height.
2. the vibration isolating method of aclinal satellite sensitive load according to claim 1, is characterized in that, also comprise the steps:
Step 9, carries out verification experimental verification to vibrating isolation system.
3. the vibration isolating method of aclinal satellite sensitive load according to claim 1, is characterized in that, 3 flexible unit parallel connections that vibrating isolation system comprises responsible vibration isolation support.
4. the vibration isolating method of aclinal satellite sensitive load according to claim 1, is characterized in that, described flexible unit is installed between satellite sensitive load and satellite platform.
5. the vibration isolating method of aclinal satellite sensitive load according to claim 1, is characterized in that, vibration isolator is directly connected with satellite platform and satellite sensitive load.
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| CN201310345398.8A CN103448921B (en) | 2013-08-08 | 2013-08-08 | The vibration isolating method of aclinal satellite sensitive load |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103939514A (en) * | 2014-03-20 | 2014-07-23 | 上海卫星工程研究所 | Three-way equivalent-rigidity vibration isolator for satellite |
| CN104268382B (en) * | 2014-09-16 | 2017-05-03 | 上海卫星工程研究所 | Rapid design and analysis method applicable to satellite micro-vibration isolation system |
| CN106347717B (en) * | 2016-09-22 | 2018-08-14 | 北京空间飞行器总体设计部 | Encircling type is adjustable installation pointing accuracy sensor damping frame |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5820078A (en) * | 1996-09-27 | 1998-10-13 | Hughes Electronics Corporation | Control motion gyro with vibration isolation |
| CN102486212A (en) * | 2011-03-11 | 2012-06-06 | 清华大学 | Multiple-degree-of-freedom vibration isolator and multiple-degree-of-freedom vibration isolating system for effective load and satellite |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5961078A (en) * | 1997-06-27 | 1999-10-05 | Mcdonnell Douglas Corporation | Passive axial vibration isolation system for a spacecraft launch vehicle |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5820078A (en) * | 1996-09-27 | 1998-10-13 | Hughes Electronics Corporation | Control motion gyro with vibration isolation |
| CN102486212A (en) * | 2011-03-11 | 2012-06-06 | 清华大学 | Multiple-degree-of-freedom vibration isolator and multiple-degree-of-freedom vibration isolating system for effective load and satellite |
Non-Patent Citations (1)
| Title |
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| 高精度光学有效载荷微振动隔振***设计与分析;申军烽等;《机械动力学理论及其应用》;20110729;第124-128页 * |
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