CN103448921A - No-inclination vibration isolation method for satellite sensitive load - Google Patents
No-inclination vibration isolation method for satellite sensitive load Download PDFInfo
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- CN103448921A CN103448921A CN2013103453988A CN201310345398A CN103448921A CN 103448921 A CN103448921 A CN 103448921A CN 2013103453988 A CN2013103453988 A CN 2013103453988A CN 201310345398 A CN201310345398 A CN 201310345398A CN 103448921 A CN103448921 A CN 103448921A
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Abstract
The invention relates to a no-inclination vibration isolation method for satellite sensitive load. Aiming to performance indicator requirements of load, the bandwidth and decoupling degree of a vibration isolation system are analyzed, influences on system performances by different arranging forms and different vertical and horizontal stiffness ratios are compared, and a no-inclination vibration isolation system arranging method is provided. The vibration isolation system comprises three soft units with the vertical and horizontal stiffness ratio ranging from 0.4 to 0.8; the units are connected in parallel and support, are distributed evenly around a load centroid vertical line as an axis and are placed without inclination. The system is free of transit connecting blocks, light in weight, low in centroid, and excellent in six-free-degree vibration isolation performances. By the aid of the method, weight of an objected to be vibration isolated can be beard, manufacturability can be guaranteed, vibration transmission can be isolated effectively, and the purposes of low vibration isolation system frequency band and good system decoupling performance can be achieved.
Description
Technical field
The present invention relates to the vibration isolation of the responsive load of satellite, especially by the layout of flexible unit in the design vibrating isolation system, take the vertical modes of emplacement of aclinal, when considering manufacturability and energy saving, realize the vibration isolation of the responsive load of satellite, be specifically related to the vibration isolating method of the responsive load of a kind of aclinal satellite.
Background technology
Along with the development of space technology, the improving constantly of load performance and precision, the responsive load of Seeds of First Post-flight is more and more higher to the requirement of the stability of satellite platform.During the satellite operation on orbit, the motion of rotatable parts may be coupled with the elastic oscillation of the flexible parts such as sun battle array, magnetometer, causes the vibration of satellite structure platform, and this operating accuracy that will inevitably reduce load even may cause the failure of its task.
Conventional vibrating isolation system project organization complexity, quality is large, is not suitable for space environment, therefore, need to be isolated to the vibration transmission of responsive load satellite platform, design a kind of vibrating isolation system of not only having considered manufacturability but also having considered energy saving, be one of main path of dealing with problems.
Summary of the invention
The invention provides the vibration isolating method of the responsive load of a kind of aclinal satellite, it uses three flexible unit to be arranged symmetrically with, and 3 in parallel supports of aclinal, when having load-carrying capacity, possess good anti-vibration performance, the lower and system decoupling of vibrating isolation system frequency band is purpose preferably.
For achieving the above object, the present invention has adopted following technical scheme:
The vibration isolating method of the responsive load of a kind of aclinal satellite, comprise the steps:
Step 1: analyze the load performance index request;
Step 2: guarantee load stability, determine the supported at three point mode;
Step 3: according to satellite platform layout and load initial conditions, consider interface position and manufacturability simultaneously, determine 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 after synthesizing is diagonal matrix at attachment point of equal value place;
Step 5: computing system bandwidth and decoupling zero degree;
Step 6: analyze the impact of the different setting angles of flexible unit on anti-vibration performance, determine the aclinal mounting means;
Step 7: analyze the relatively different laterally impacts of longitudinal rigidity Compare System anti-vibration performance of vibration isolator;
Step 8, select optimum horizontal longitudinal rigidity ratio, considers carrying, anti-vibration performance and manufacturability simultaneously, and vibration isolator is designed and emulation, determines lateral stiffness and longitudinal rigidity.
Preferably, also comprise the steps:
Step 9, carry out verification experimental verification to vibrating isolation system.
Preferably, vibrating isolation system comprises the support in parallel of 3 flexible unit being responsible for vibration isolation.
Preferably, vibration isolator laterally and longitudinal rigidity than between 0.4～0.8, it is uniform as axle that 3 flexible unit be take load barycenter vertical curve, vertically places aclinal.
Preferably, described flexible unit is installed between the responsive load of satellite and satellite platform.
Preferably, vibration isolator directly is connected with the responsive load of satellite platform and satellite, does not need additional connecting device.
Preferably, vibration isolator is imbedded satellite platform, to reduce load height.
The present invention, than prior art, has following advantage and good effect:
1, adopt the mode of supported at three point, utilize 3 coplanar, make the load base plate steady, prevent the load self-deformation, cause unnecessary vibration;
2, vertically place, design configuration is simple, good design flexibility is arranged, realize economy and assembly process process, and Interface design is convenient;
3, vertically placement can avoid using contiguous block, by reducing the vibrating isolation system weight of half, alleviates the satellite burden;
4, vertically placement can be imbedded flexible unit the celestial body structure, reduces the load barycenter, makes load more stable;
Although 5 arrange that according to certain angle coupling is good, when practical set, three vibration isolator axis are difficult to cross, and joint also is difficult to guarantee to overlap with the load center of mass point, make coupling performance decline unavoidably like this.Use vertical modes of emplacement, vertical easily assurance, and easy to assembly, economize on resources.
The accompanying drawing explanation
By reading the detailed description of non-limiting example being done with reference to the following drawings, it is more obvious that other features, objects and advantages of the present invention will become:
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.
The specific embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art further to understand the present invention, but not limit in any form the present invention.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and improvement.These all belong to protection scope of the present invention.
At first, according to the layout situation by vibration isolation quality of loads 309.5kg and satellite top board, flexible vibration isolation unit quantity is 3, and the scope that diameter is installed is 509.3mm～776.1mm, according to the design of conceptual level, the design and installation diameter is 728mm(radius 364mm).
The distribution form of flexible vibration isolation unit as shown in Figure 1.The Z-direction isolation frequency is set 14Hz left and right (the corresponding about 800N/mm of axial stiffness), and the Z-direction amount of compression is in the 1.27mm left and right.The support angle of finding suitable lateral stiffness and vibration isolation unit on the basis of above condition reaches the lower and system decoupling of vibrating isolation system frequency band purpose preferably.
According to known parameter analysis impact on bandwidth and system fundamental frequency in lateral stiffness and flexible unit change of pitch angle situation.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 of using is considered), the angle of support changes from 0 to 90 °.
Vertically each order frequency of installation system and coupling situation are as shown in the table: maximum distribution radius R max=410mm, and height of center of mass 364mm, rigidity is directions X 640N/mm, Y-direction 640N/mm, Z direction 889N/mm(ratio of rigidity u=0.72).
Each order frequency of table 1 and coupling situation
| ? | 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 the ratio of rigidity coefficient, u is larger, and the bandwidth of system is also just larger, but practical application u is also unsuitable too small, otherwise the vibrating isolation system natural frequency is too small, the vibration isolator strength decreased, and suitable span is 0.4～0.8 left and right (below 1.0); It is better that vibration isolator inclination installation seems coupling performance, but during the vibration isolator actual installation, Rmax is certain, inclination will cause the distribution radius rmax of vibration isolator and load attachment point to reduce, and vibrating isolation system is with less by the rmax distribution radius of vibration isolation object, and system performance is poorer.Therefore, due to the fixing of Rmax, offset on a large scale, advantage is no longer obvious; Vibration isolation efficiency is more than 95%.
Therefore, the present invention in the weight that can carry vibrating isolation system, guarantee the technological while, the effectively transmission of separating vibration, reached the lower and system decoupling of vibrating isolation system frequency band purpose preferably.
Above specific embodiments of the invention are described.It will be appreciated that, the present invention is not limited to above-mentioned specific implementations, and those skilled in the art can make various distortion or modification within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (7)
1. the vibration isolating method of the responsive load of aclinal satellite, is characterized in that, comprises the steps:
Step 1: analyze the load performance index request;
Step 2: guarantee load stability, determine the supported at three point mode;
Step 3: according to satellite platform layout and load initial conditions, consider interface position and manufacturability simultaneously, determine 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 after synthesizing is diagonal matrix at attachment point of equal value place;
Step 5: computing system bandwidth and decoupling zero degree;
Step 6: analyze the impact of the different setting angles of flexible unit on anti-vibration performance, determine the aclinal mounting means;
Step 7: analyze the relatively different laterally impacts of longitudinal rigidity Compare System anti-vibration performance of vibration isolator;
Step 8, select optimum horizontal longitudinal rigidity ratio, considers carrying, anti-vibration performance and manufacturability simultaneously, and vibration isolator is designed and emulation, determines lateral stiffness and longitudinal rigidity.
2. the vibration isolating method of the responsive load of aclinal satellite according to claim 1, is characterized in that, also comprises the steps:
Step 9, carry out verification experimental verification to vibrating isolation system.
3. the vibration isolating method of the responsive load of aclinal satellite according to claim 1, is characterized in that, vibrating isolation system comprises the support in parallel of 3 flexible unit being responsible for vibration isolation.
4. the vibration isolating method of the responsive load of aclinal satellite according to claim 3, is characterized in that, vibration isolator laterally and longitudinal rigidity than between 0.4～0.8, it is uniform as axle that 3 flexible unit be take load barycenter vertical curve, vertically places aclinal.
5. the vibration isolating method of the responsive load of aclinal satellite according to claim 1, is characterized in that, described flexible unit is installed between the responsive load of satellite and satellite platform.
6. the vibration isolating method of the responsive load of aclinal satellite according to claim 1, is characterized in that, vibration isolator directly is connected with the responsive load of satellite platform and satellite.
7. the vibration isolating method of the responsive load of aclinal satellite according to claim 1, is characterized in that, vibration isolator is imbedded satellite platform, to reduce load height.
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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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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104268382A (en) * | 2014-09-16 | 2015-01-07 | 上海卫星工程研究所 | Rapid design and analysis method applicable to satellite micro-vibration isolation system |
| CN106347717A (en) * | 2016-09-22 | 2017-01-25 | 北京空间飞行器总体设计部 | Embraced type sensor vibration reducing bracket with adjustable installing and pointing accuracy |
Citations (3)
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|---|---|---|---|---|
| US5820078A (en) * | 1996-09-27 | 1998-10-13 | Hughes Electronics Corporation | Control motion gyro with vibration isolation |
| WO1999000301A1 (en) * | 1997-06-27 | 1999-01-07 | Mcdonnell Douglas Corporation | Passive axial vibration isolation system for a spacecraft launch vehicle |
| 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 |
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2013
- 2013-08-08 CN CN201310345398.8A patent/CN103448921B/en active Active
Patent Citations (3)
| 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 |
| WO1999000301A1 (en) * | 1997-06-27 | 1999-01-07 | Mcdonnell Douglas Corporation | Passive axial vibration isolation system for a spacecraft launch vehicle |
| 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 |
|---|
| 申军烽等: "高精度光学有效载荷微振动隔振系统设计与分析", 《机械动力学理论及其应用》, 29 July 2011 (2011-07-29), pages 124 - 128 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104268382A (en) * | 2014-09-16 | 2015-01-07 | 上海卫星工程研究所 | Rapid design and analysis method applicable to satellite micro-vibration isolation system |
| 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 |
| CN106347717A (en) * | 2016-09-22 | 2017-01-25 | 北京空间飞行器总体设计部 | Embraced type sensor vibration reducing bracket with adjustable installing and pointing accuracy |
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| CN103448921B (en) | 2016-01-06 |
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