CN106218920A - Satellite Vibration isolating device and method - Google Patents
Satellite Vibration isolating device and method Download PDFInfo
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- CN106218920A CN106218920A CN201610511834.8A CN201610511834A CN106218920A CN 106218920 A CN106218920 A CN 106218920A CN 201610511834 A CN201610511834 A CN 201610511834A CN 106218920 A CN106218920 A CN 106218920A
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- 235000006510 Nelumbo pentapetala Nutrition 0.000 claims description 4
- 238000002955 isolation Methods 0.000 claims description 4
- 239000000919 ceramic Substances 0.000 claims description 2
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- 230000003287 optical effect Effects 0.000 description 18
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- 230000009286 beneficial effect Effects 0.000 description 3
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/228—Damping of high-frequency vibration effects on spacecraft elements, e.g. by using acoustic vibration dampers
Abstract
The invention discloses a kind of Satellite Vibration isolating device and method, Satellite Vibration isolating device therein includes: upper flange, lower flange, flexible hinge and at least two driving means；Described upper flange is fixing with satellite load to be connected；Described lower flange is fixing with satellite platform to be connected；Described flexible hinge is arranged between upper flange and lower flange, and flexible hinge is fixedly connected with upper flange and lower flange；Described driving means is arranged between upper flange and lower flange, and driving means is respectively fixedly connected with upper flange and lower flange, and described driving means is followed lower flange according to the drive control signal that controller transmission comes and carried out radial rotating around satellite load.The technical scheme that the present invention provides can be that satellite load provides quiet and stable working environment, meets the satellite load requirement to stability.It addition, the Satellite Vibration isolating device of the present embodiment also has the features such as simple in construction, control accuracy height and Low rigidity coupling.
Description
Technical field
The present invention relates to satellite technology, be specifically related to a kind of Satellite Vibration isolating device and Satellite Vibration partition method.
Background technology
For the satellites such as Optical remote satellite, astronomical observation satellite and laser communications satellite, in order to improve satellite
Imaging or the performance such as communication, the volume of its satellite load is the biggest, and as relatively big in bore or focal length is longer.Volume is more
The often requirement to stability of big satellite load is the highest, but, satellite is inevitably present to affect satellite load steady
Momenttum wheel, solar array drive mechanism, control-moment gyro and antenna in disturbance factor qualitatively, such as satellite point to machine
The cycle movement of the vibration sources such as structure can produce disturbance, for another example ion propeller, the work of Cryo Refrigerator and environmental perturbation
Also vibration can be produced.
Inventor finds in realizing process of the present invention, and the frequency band of the frequency of vibration in satellite is wider, as frequency of vibration can
With less than 0.1Hz, it is also possible to reach thousand hertz, how to realize isolating technique for wider vibration frequency band, to meet satellite
The load requirement to stability, is a problem highly paid close attention to.
Summary of the invention
In view of above-mentioned technical problem, the invention provides one overcome above-mentioned technical problem or at least in part solve on
State Satellite Vibration isolating device and the method for technical problem.
According to one aspect of the present invention, it is provided that a kind of Satellite Vibration isolating device, this device specifically includes that method
Orchid, lower flange, flexible hinge and at least two driving means；Described upper flange is fixing with satellite load to be connected；Described purgation
Blue fixing with satellite platform is connected；Described flexible hinge is arranged between upper flange and lower flange, and flexible hinge and upper flange
It is fixedly connected with lower flange；Described driving means is arranged between upper flange and lower flange, and driving means and upper flange and
Lower flange is fixedly connected with, and described driving means is followed lower flange according to the drive control signal that controller transmission comes and carried around satellite
Lotus carries out radial rotating.
According to another aspect of the invention, it is provided that a kind of isolating technique method of satellite, the method specifically includes that and connects
Receive the satellite load next with the transmission of the satellite load rigidly connected Inertial Measurement Unit attitudes vibration information at inertial space；Root
Produce the drive control signal of each driving means according to described attitudes vibration information and send；Respectively driving in Satellite Vibration isolating device
The lower flange that dynamic device is followed in Satellite Vibration isolating device according to the drive control signal received carries out footpath around satellite load
To rotation.
Satellite Vibration isolating device and method that the present invention provides at least have following advantages and a beneficial effect: the present invention
By arranging flexible hinge between upper flange and lower flange, and utilize upper flange and lower flange respectively with satellite load and satellite
Platform is fixing to be connected, and makes satellite load be connected by the Satellite Vibration isolating device of the present invention with satellite platform, so, and this
Bright can utilize flexible hinge in satellite platform medium-high frequency vibrate passively isolate；The present invention by upper flange and
Driving means is set between lower flange, and this driving means can be followed according to the drive control signal that satellite controller transmission comes
Lower flange carries out radial rotating around satellite load, and so, the present invention can utilize driving means for low in satellite platform
Frequency vibration carries out active isolation；It follows that the isolating technique mode that the present invention utilizes master passively to combine can be to from low frequency
(such as 0.1Hz) is effectively isolated to the vibration in the range of the broad frequency band of high frequency (such as thousand hertz)；Thus the present invention provides
Technical scheme can be that satellite load provides quiet and stable working environment, (especially volume is relatively to meet satellite load
Big satellite load) requirement to stability.It addition, the Satellite Vibration isolating device of the present embodiment also has simple in construction, control
The features such as precision processed height and Low rigidity coupling.
Described above is only the general introduction of technical solution of the present invention, in order to better understand the technological means of the present invention,
And can be practiced according to the content of description, and in order to allow above and other objects of the present invention, the feature and advantage can
Become apparent, below especially exemplified by the detailed description of the invention of the present invention.
Accompanying drawing explanation
By reading the detailed description of hereafter preferred implementation, various other advantage and benefit common for this area
Technical staff will be clear from understanding.The accompanying drawing of the present embodiment is only used for illustrating the purpose of preferred implementation, and is not regarded as
It it is limitation of the present invention.And in whole accompanying drawing, it is denoted by the same reference numerals identical parts.In the accompanying drawings:
Fig. 1 is the axonometric chart of the Satellite Vibration isolating device of the embodiment of the present invention one；
Fig. 2 is the side view of the flexible hinge of the embodiment of the present invention one；
Fig. 3 is the schematic diagram of a concrete application of the Satellite Vibration isolating device of the embodiment of the present invention two；
Fig. 4 is the flow chart of the isolating technique method of the satellite of the embodiment of the present invention three.
Description of reference numerals:
1 Satellite Vibration isolating device；2 driving means；3 securing members；
4 flexible hinges；5 upper flanges；6 lower flanges；
7 upper flange installing holes；8 lower flange installing holes；9 lightening holes；
10 satellite load；11 satellite platforms；The 12 solar cell wings.
Detailed description of the invention
It is more fully described the exemplary embodiment of the present invention below with reference to accompanying drawings.Although accompanying drawing shows the present invention
Exemplary embodiment, it being understood, however, that may be realized in various forms the present invention and should be by embodiments set forth here
Limited.On the contrary, it is provided that these embodiments are able to be best understood from the present invention, and can be by the scope of the present invention
Intactly convey to those skilled in the art.
Below in conjunction with Fig. 1 to Fig. 4, Satellite Vibration isolating device and the Satellite Vibration partition method of the present invention are entered respectively
Row describes in detail.
Embodiment one, Satellite Vibration isolating device.The structure of this Satellite Vibration isolating device is as depicted in figs. 1 and 2.
In fig. 1 and 2, the Satellite Vibration isolating device 1 of the present embodiment includes: upper flange 5, lower flange 6, flexible hinge
4 (its side view is as shown in Figure 2) and at least two driving means 2 (showing four driving means 2 in Fig. 1)；It is also preferred that the left this
The Satellite Vibration isolating device 1 of embodiment can also include: at least two be used for measuring satellite load 10 and satellite platform 11 it
Between the position sensor (not shown) of relative attitude.
Upper flange 5 is mainly used in making Satellite Vibration isolating device 1 fix with satellite load 10 and is connected, and sets on upper flange 5
Being equipped with multiple upper flange installing hole 7, upper flange 5 is solid with satellite load 10 by upper flange installing hole 7 and corresponding securing member
Fixed connection；For another example upper flange 5 is connected by the modes such as welding are fixing with satellite load 10.The present embodiment be not intended to upper flange 5 with
The fixing specific implementation connected of satellite load 10.
Lower flange 6 is mainly used in making Satellite Vibration isolating device 1 fix with satellite platform 11 and is connected；Set on lower flange 6
Being equipped with multiple lower flange installing hole 8, lower flange 6 is solid with satellite platform 11 by lower flange installing hole 8 and corresponding securing member
Fixed connection；Flange 6 is connected by the modes such as welding are fixing with satellite platform 11 as follows.The present embodiment be not intended to lower flange 6 with
The fixing specific implementation connected of satellite platform 11.
Flexible hinge 4 is mainly used in passively isolating for the vibration in satellite platform 11.Flexible hinge 4 is arranged at
Between flange 5 and lower flange 6, and flexible hinge 4 is fixedly connected with upper flange 5 and lower flange 6；As by integrated system
The mode of work can make flexible hinge 4 be respectively fixedly connected with upper flange 5 and lower flange 6；For another example fixed by welding or be spirally connected etc.
Connected mode can make flexible hinge 4 be respectively fixedly connected with upper flange 5 and lower flange 6.Flexible hinge 4 can include multiple scratching
Property bearing, i.e. flexible hinge 4 can be spliced by multiple flexible bearings.
It addition, the subregion of the flexible hinge 4 in the present embodiment has carried out skiving process, lower flange 6 is made to carry around satellite
The rigidity of lotus 10 radial rotating is extremely low, and remaining 4 degree of freedom is (i.e. around the Z axis rotation of satellite load 10 and along satellite load
X-axis, Y-axis and the translation in three directions of Z axis of 10) keep high rigidity, in order to adjust satellite by the action of driving means 2
Relative attitude between load 10 and satellite platform 11, thus ensure that the disturbance factor of satellite platform 11 is not transferred to satellite load
On 10.The present embodiment is not intended to flexible hinge 4 and fixes, with upper flange 5 and lower flange 6, the specific implementation and flexibility being connected
The specific implementation of hinge 4.
Flexible hinge 4 in the present embodiment have two rotational freedoms, i.e. flexible hinge 4 can make upper flange 5 and under
Flange 6 produces relative motion, and more specifically, flexible hinge 4 can make lower flange 6 around radial direction (the i.e. satellite of satellite load 10
The X-axis of load and Y-axis) there is Small-angle Rotation, so that the relative attitude of upper flange 5 and lower flange 6 changes.
Driving means 2 is arranged between upper flange 5 and lower flange 6, and driving means 2 is distinguished with upper flange 5 and lower flange 6
Fixing connection, as driving means 2 is respectively fixedly connected with upper flange 5 and lower flange 6 by multiple securing members 3.
Driving means 2 is mainly used in carrying out active isolation for the vibration in satellite platform 11, concrete, driving means 2
Receive controller (being such as arranged at the controller in satellite platform or the controller being arranged in satellite load, not shown in figure)
The drive control signal that transmission comes, and perform corresponding operation (as stretch/shrink operates) according to the drive control signal received, drive
Dynamic corresponding operating performed by device 2 can be followed lower flange 6 and be carried out radial rotating around satellite load 10.One concrete example
Son, the satellite load 10 that controller comes according to Inertial Measurement Unit (not shown) rigidly connected with satellite load 10 transmission
Attitudes vibration information at inertial space calculates the driving of each driving means 2 and controls information, and to corresponding driving means 2
Sending corresponding driving control information, driving means 2, after receiving the driving control information that controller comes for its transmission, performs
Corresponding operation, the corresponding operating performed by driving means 2 can be followed lower flange 6 and be carried out radial rotating around satellite load 10.
The Satellite Vibration isolating device 1 of the present embodiment has generally comprised multiple driving means 2, and satellite as shown in Figure 1 shakes
Dynamic isolating device 1 includes four driving means 2, and these four driving means 2 are arranged at the orthogonal of satellite load 10
Article two, diametrically.The driving means 2 of the present embodiment generally can use linear electric motors, piezoelectric ceramic actuator or voice coil motor
Deng driving equipment.
The Satellite Vibration isolating device 1 of the present embodiment generally also can include multiple position sensor (not shown),
And position is set can the determining according to the actual requirements of each position sensor.Each position sensor is connected with controller respectively,
Each position sensor can to use in real time or the mode such as timing/variable interval transmits its position signalling collected to controller,
So that controller is referred to its every confidence received during the drive control signal generating driving means 2
Number.One specific example, controller can calculate satellite load 10 according to the position signalling that each position sensor transmissions is come
And the relative attitude information between satellite platform 11, and transmit the satellite load 10 come at inertial space according to Inertial Measurement Unit
Attitudes vibration information calculate the driving of each driving means 2 and control information, and send to each driving means 2 and drive control accordingly
Information processed.The present embodiment is not intended to position signalling and the Inertial Measurement Unit biography that controller comes according to each position sensor transmissions
Defeated come satellite load 10 drive the concrete of control information what the attitudes vibration information of inertial space calculated each driving means 2
Implementation.
In order to alleviate the overall weight of Satellite Vibration isolating device 1, the present embodiment can be in Satellite Vibration isolating device 1
One or more lightening hole 9 is set, as arranged one or more lightening hole 9 on upper flange 5, sets on lower flange 6 for another example
Put one or more lightening hole 9.When arranging lightening hole 9, should take into full account that the intensity of Satellite Vibration isolating device 1 is with just
Degree.
Seen from the above description, the Satellite Vibration isolating device 1 of the present embodiment is at flexible hinge 4 and the work of driving means 2
There is the X-axis around satellite load and the degree of freedom of Y-axis both direction rotation, owing to satellite (such as optical satellite etc.) is the most right under with
The vibration of the both direction rotated around the X-axis of satellite load and Y-axis is very sensitive, and what the Z axis of opposing connection satellite load 10 rotated
Vibration and along the X-axis of satellite load 10, Y-axis and the vibration of three directions translations of Z axis insensitive, therefore, the present embodiment
Satellite Vibration isolating device 1 can reach preferable isolating technique performance.Owing to the Satellite Vibration isolating device 1 of the present embodiment can
So that translation freedoms on three directions between satellite platform 11 and satellite load 10 and the Z axis around satellite load 10 turn
Dynamic degree of freedom is somewhat limited, and therefore, the Satellite Vibration isolating device 1 of the present embodiment is conducive at satellite platform
The flexible structure such as cable and pipeline is set between 11 and satellite load 10, and the setting of these flexible structures is essentially without right
The isolating technique performance of Satellite Vibration isolating device 1 produces significantly impact.It addition, the Satellite Vibration isolating device of the present embodiment
1 also has the features such as simple in construction, control accuracy height and Low rigidity coupling, and is advantageously implemented satellite platform 11 and satellite load
The exchange of heat, electricity and liquid etc. between lotus 10.
Embodiment two, a concrete application of Satellite Vibration isolating device 1.
The object lesson that the Satellite Vibration isolating device 1 of the present embodiment is applied in optical satellite is as it is shown on figure 3, scheme
Satellite Vibration isolating device 1 one aspect in 3 is fixing with satellite load 10 to be connected, and on the one hand fixes with satellite platform 11 and is connected,
And on satellite platform 11, it is provided with two solar cell wings 12；The Z axis i.e. sensing of satellite load 10, X-axis and Y-axis can be satellite
The most orthogonal two diametric(al)s of load 10.
Satellite load in optical satellite is usually space optical camera, and the Satellite Vibration isolating device 1 of the present embodiment can
So that space optical camera is operated in stable environment, i.e. the present embodiment can make optical camera have preferable attitude stabilization
Property, make the optical axis of optical camera point to stable, by measuring in real time and the action of driving means 2 of Inertial Measurement Unit, permissible
The optical axis making optical camera is stable, such that it is able to accurately set up remote sensing images and ground target definitely pointing to of inertial space
Between corresponding relation, and by with GPS survey rail combine, the positioning precision of the Pillarless caving of satellite can be effectively improved.
It addition, after optical satellite performs the mobile operation of wide-angle, the Satellite Vibration isolating device 1 of the present embodiment has
It is beneficial to optical camera and rapidly enters stable duty, advantageously reduce the time of the imaging of optical camera, thus have
It is beneficial to improve optical satellite big sector scanning search capability and imaging efficiency.
Embodiment three, Satellite Vibration partition method.The flow process of the method is as shown in Figure 4.
In Fig. 4, the Satellite Vibration partition method of the present embodiment includes: S400, S410 and S420.Below to institute in Fig. 4
The each step comprised illustrates respectively.
The satellite load 10 that S400, reception come with the transmission of satellite load 10 rigidly connected Inertial Measurement Unit is empty at inertia
Between attitudes vibration information.
Concrete, Inertial Measurement Unit is rigidly connected with satellite load 10, and this Inertial Measurement Unit can be that star is sensitive
The element such as device or high accuracy gyroscope.Inertial Measurement Unit can measure the satellite load 10 attitude at inertial space in real time
Change information, the satellite load 10 that Inertial Measurement Unit can be measured in real time is in the attitudes vibration information of inertial space
The controller being uploaded on satellite.
S410, according to satellite load 10 inertial space attitudes vibration information produce each driving means driving control letter
Number and send.
Concrete, controller can calculate according to the multiple calculation of attitudes vibration Information Pull that it receives and respectively drive
The driving of dynamic device 2 controls information, and the driving calculated for different driving device 2 controls information and generally differs.
In Satellite Vibration isolating device 1, it is provided with position sensor, and controller can receive each position sensor
In the case of the position signalling that transmission comes, controller can calculate satellite load 10 according to its position signalling received and defend
Relative attitude information between star platform 11, this relative attitude information can produce the driving control of each driving means 2 to controller
Signal processed plays assosting effect.
Each driving means 2 in S420, Satellite Vibration isolating device 1 follows satellite according to the drive control signal received
Lower flange 6 in vibration isolating device 1 carries out radial rotating around satellite load 10.
Concrete, each driving means 2 in Satellite Vibration isolating device 1 is receiving the drive control signal of its correspondence
After, perform corresponding action, thus the lower flange 6 followed in Satellite Vibration isolating device 1 carries out radially turning around satellite load 10
Dynamic, so that the sensing angle of satellite load 10 maintains target and points at angle, such that it is able to keep the sensing angle of satellite load 10
Stable (as kept the stability of the optical axis of satellite load 10), it is achieved that the active isolation to the vibration in satellite platform 11.
Algorithm and not intrinsic with any certain computer, virtual system or the miscellaneous equipment phase of display provided herein
Close.Various general-purpose systems can also be used together with based on teaching in this.As described above, construct this kind of system to be wanted
The structure asked is apparent from.Additionally, the present invention is also not for any certain programmed language.It is understood that, it is possible to use each
Plant programming language and realize the content of invention described herein, and the description done language-specific above is to disclose this
The preferred forms of invention.
In description mentioned herein, illustrate a large amount of detail.It is to be appreciated, however, that the enforcement of the present invention
Example can be put into practice in the case of not having these details.In some instances, it is not shown specifically known method, structure
And technology, in order to do not obscure the understanding of this description.
Similarly, it will be appreciated that one or more in order to simplify that the disclosure helping understands in each inventive aspect, exist
Above in the description of the exemplary embodiment of the present invention, each feature of the present invention is grouped together into single enforcement sometimes
In example, figure or descriptions thereof.But, the method for the disclosure should not be construed to reflect an intention that i.e. required guarantor
The application claims feature more more than the feature being expressly recited in each claim protected.More precisely, as following
Claims reflected as, inventive aspect is all features less than single embodiment disclosed above.Therefore,
The claims following detailed description of the invention are thus expressly incorporated in this detailed description of the invention, the most each claim itself
All as the independent embodiment of the present invention.
Those skilled in the art are appreciated that and can carry out the module in the equipment in embodiment adaptively
Change and they are arranged in one or more equipment different from this embodiment.Can be the module in embodiment or list
Unit or assembly are combined into a module or unit or assembly, and can put them in addition multiple submodule or subelement or
Sub-component.In addition at least some in such feature and/or process or unit excludes each other, can use any
Combine all features disclosed in this specification (including adjoint claim, summary and accompanying drawing) and so disclosed appoint
Where method or all processes of equipment or unit are combined.Unless expressly stated otherwise, this specification (includes adjoint power
Profit requires, summary and accompanying drawing) disclosed in each feature can be carried out generation by providing identical, equivalent or the alternative features of similar purpose
Replace.
Although additionally, it will be appreciated by those of skill in the art that embodiment described herein includes institute in other embodiments
Including some feature rather than further feature, but the combination of the feature of different embodiment means to be in the scope of the present invention
Within and form different embodiments.Such as, in the following claims, embodiment required for protection any it
One can mode use in any combination.
The all parts embodiment of the present invention can realize with hardware, or to run on one or more processor
Software module realize, or with combinations thereof realize.It will be understood by those of skill in the art that and can use in practice
Microprocessor or digital signal processor (DSP) realize optical axis for space optical camera according to embodiments of the present invention and tremble
The some or all functions of some parts in dynamic measurement apparatus.
It should be noted that above-described embodiment is that the present invention will be described rather than limits the invention, and
Those skilled in the art can design alternative embodiment without departing from the scope of the appended claims.In claim
In, any reference marks that should not will be located between bracket is configured to limitations on claims.Word " comprises " and is not excluded for depositing
In the element not arranged in the claims or step etc..Word "a" or "an" before being positioned at element does not excludes the presence of many
Individual such element.The present invention can be by means of including the hardware of some different elements and by means of properly programmed calculating
Machine realizes.If in the unit claim listing equipment for drying, several in these devices can be by same
Hardware branch specifically embodies.Word first, second and third use do not indicate that any order.Can be by these word explanations
For title.
Claims (10)
1. a Satellite Vibration isolating device, it is characterised in that described device includes: upper flange, lower flange, flexible hinge and
At least two driving means；
Described upper flange is fixing with satellite load to be connected；
Described lower flange is fixing with satellite platform to be connected；
Described flexible hinge is arranged between upper flange and lower flange, and flexible hinge is all fixing with upper flange and lower flange even
Connect；
Described driving means is arranged between upper flange and lower flange, and driving means is all fixing with upper flange and lower flange even
Connecing, described driving means is followed lower flange according to the drive control signal that controller transmission comes and is carried out radially turning around satellite load
Dynamic.
2. device as claimed in claim 1, it is characterised in that described upper flange, lower flange pass through integrally to become with flexible hinge
Type mode is fixing to be connected.
3. device as claimed in claim 1, it is characterised in that described flexible hinge includes multiple flexible bearing.
4. device as claimed in claim 1, it is characterised in that include four driving means in described Satellite Vibration isolating device
In the case of, described four driving means be arranged at satellite load orthogonal two diametrically.
5. device as claimed in claim 1, it is characterised in that described driving means includes: linear electric motors, Piezoelectric Ceramic
Device or voice coil motor.
6. device as claimed in claim 1, it is characterised in that described Satellite Vibration isolating device also includes: at least two position
Putting sensor, be arranged on upper flange, lower flange, and each position sensor is connected with controller respectively, each position sensor divides
Not transmitting its position signalling gathered to controller, described position signalling is for determining the phase between satellite load with satellite platform
To attitude, and described relative attitude is used for generating described drive control signal.
7. the device as described in any claim in claim 1 to 6, it is characterised in that:
The loss of weight of at least one weight for alleviating Satellite Vibration isolating device it is provided with in described Satellite Vibration isolating device
Hole；And/or
The subregion of described flexible hinge has carried out skiving process.
8. device as claimed in claim 7, it is characterised in that described lightening hole is arranged on upper flange and/or lower flange.
9. a Satellite Vibration isolation side based on the Satellite Vibration isolating device described in any claim in claim 1-8
Method, it is characterised in that described method includes:
Receive the satellite load next with the transmission of the satellite load rigidly connected Inertial Measurement Unit attitudes vibration at inertial space
Information；
Produce the drive control signal of each driving means according to described attitudes vibration information and send；
Each driving means in Satellite Vibration isolating device is followed lower flange according to the drive control signal received and is carried around satellite
Lotus carries out radial rotating.
10. method as claimed in claim 9, wherein, described method also includes:
In the case of the position signalling that position sensor transmission in receiving Satellite Vibration isolating device comes, according to institute's rheme
Confidence number determines the relative attitude information between satellite load and satellite platform；
And described produce the drive control signal of each driving means according to described attitudes vibration information and the step that sends includes:
The drive control signal producing each driving means according to described attitudes vibration information and described relative attitude information is concurrent
Send.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610511834.8A CN106218920A (en) | 2016-06-30 | 2016-06-30 | Satellite Vibration isolating device and method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610511834.8A CN106218920A (en) | 2016-06-30 | 2016-06-30 | Satellite Vibration isolating device and method |
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| CN201610511834.8A Pending CN106218920A (en) | 2016-06-30 | 2016-06-30 | Satellite Vibration isolating device and method |
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| CN107226220A (en) * | 2017-05-09 | 2017-10-03 | 哈尔滨工业大学 | Magnetic suspension support meanss for the stable rotation of satellite load |
| CN107757950A (en) * | 2017-09-14 | 2018-03-06 | 北京空间飞行器总体设计部 | A kind of high rail Optical remote satellite structure |
| CN107939905A (en) * | 2017-11-20 | 2018-04-20 | 航天东方红卫星有限公司 | A kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping |
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2016
- 2016-06-30 CN CN201610511834.8A patent/CN106218920A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107226220A (en) * | 2017-05-09 | 2017-10-03 | 哈尔滨工业大学 | Magnetic suspension support meanss for the stable rotation of satellite load |
| CN107226220B (en) * | 2017-05-09 | 2019-09-17 | 哈尔滨工业大学 | Stablize the magnetic suspension support device of rotation for satellite load |
| CN107757950A (en) * | 2017-09-14 | 2018-03-06 | 北京空间飞行器总体设计部 | A kind of high rail Optical remote satellite structure |
| CN107939905A (en) * | 2017-11-20 | 2018-04-20 | 航天东方红卫星有限公司 | A kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping |
| CN107939905B (en) * | 2017-11-20 | 2019-10-22 | 航天东方红卫星有限公司 | A kind of satellite and the rocket adaptive device for micro-nano satellite vibration damping |
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