CN1845031A - Combined feedback-controlled vibration compensation system based on accelerometer - Google Patents
Combined feedback-controlled vibration compensation system based on accelerometer Download PDFInfo
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- CN1845031A CN1845031A CNA2006100100024A CN200610010002A CN1845031A CN 1845031 A CN1845031 A CN 1845031A CN A2006100100024 A CNA2006100100024 A CN A2006100100024A CN 200610010002 A CN200610010002 A CN 200610010002A CN 1845031 A CN1845031 A CN 1845031A
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Abstract
The invention relates to a composite feedback control vibration compensate system based on accelerator, belonging to the planet optical communication technique. It can avoid the terminal antenna pointing error caused by the vibration of planet platform, to solve the problem that present vibration compensate system has limit detect visual field. Wherein, the X-axis accelerator (3-1), the Y-axis accelerator (3-2) and the Z-axis accelerator (3-3) are independently mounted on three space axis of planet platform to measure the acceleration changes along said three space axis; part light output by the signal light generator (4) is expanded by the optical antenna (1) and emitted to the target terminal, another part is imaged on the CCD detector (7); the accurate aim lens controller (5) can control the deflection of accurate aim lens according to the information of three accelerators and the information of (7), to compensate the effect caused by the more than 50% vibration of planet platform. The invention uses accelerator as vibration detector, to improve the sampling rate, without limited by visual field.
Description
Technical field
The present invention relates to the satellite optical communication technical field.
Background technology
The satellite optical communication terminal is carrying with the satellite platform, and the vibration of satellite platform will make terminal antenna point to produce deviation, the flashlight that causes terminal the to be sent optical communication terminal (setting up terminal on the ground based terminal of link or the star with it) that departs from objectives.The signal light power that this situation will make target terminal receive decays, and will cause the interruption of satellite laser communications link when serious.Therefore vibration proposes effective compensation method to satellite platform, is one of crux problem in the satellite optical communication technical research.Have the vibration-compensated system based on the combined type FEEDBACK CONTROL of ccd detector at present, it is a satellite platform vibration detecting element with the area array CCD detector, exists the detection ken limited, the not high shortcoming of sampling rate.
Summary of the invention
The terminal antenna error in pointing that causes for fear of vibration owing to satellite platform, and solve existing vibration-compensated system and survey the limited problem of the ken, the invention provides a kind of combined feedback-controlled vibration compensation system based on accelerometer.
Bucking-out system of the present invention comprises optical antenna and the flashlight generator that is on the satellite platform, described bucking-out system comprises that also essence takes aim at mirror, essence is taken aim at the mirror controller, ccd detector, imaging lens group, light splitting piece, the X-axis accelerometer, Y-axis accelerometer and Z axis accelerometer, the X-axis accelerometer, Y-axis accelerometer and Z axis accelerometer be separately fixed on three spatial axes of satellite platform and be used for the instrumented satellite platform along three spatial axes to acceleration change, the X-axis accelerometer, the data output end of Y-axis accelerometer and Z axis accelerometer is connected three data input ends that essence is taken aim at the mirror controller respectively; Essence is taken aim at mirror and is made of completely reflecting mirror and movement executing mechanism, movement executing mechanism is used to control completely reflecting mirror deflection, the completely reflecting mirror that the flashlight of flashlight generator output is taken aim at mirror by essence changes the light input end that incides light splitting piece after the light path, a part of flashlight of described flashlight generator output incides the light input end of the secondary mirror of optical antenna after the light splitting piece reflection, and be transmitted into target terminal behind the primary mirror expansion bundle of this flashlight by optical antenna, another part flashlight of described flashlight generator output is input to the light input end of imaging lens group after the light splitting piece transmission, light output end in imaging lens group obtains focused beam and imaging on ccd detector, and the output terminal of ccd detector connects the smart picture signal input end of taking aim at the mirror controller.
Principle of work: when the satellite optical communication terminal according to prediction direction during to the flashlight of target terminal emission, because the vibration of satellite platform can make the transmit direction of flashlight change, thereby the direction that departs from prediction then needs the vibration of satellite platform is compensated.Thereby bucking-out system of the present invention utilizes three accelerometers to come three spatial axes of instrumented satellite platform to obtain the Oscillation Amplitude and the direction of satellite platform to situation of movement earlier, and then utilize the smart deflection of taking aim at mirror to come the transmit direction of control signal light, feasible essence is taken aim at the deflection of mirror and the vibration of satellite platform offsets, and makes the transmit direction of flashlight consistent with prediction direction.The deflection that the present invention also utilizes ccd detector to take aim at mirror for essence provides feedback information, guarantees that essence takes aim at mirror and can accurately locate.Be installed on the change of the accelerometer of satellite platform by the test platform vibration acceleration, computing platform is with respect to the rotational angle theta of optical communication terminal emission optical axis azimuth direction
h, with the axial rotational angle theta of pitching
vIf terminal optical antenna enlargement ratio is ρ, then essence take aim at mirror driver will be with θ
h, θ
vBe input instruction, the control essence is taken aim at mirror at azimuth axis direction rotation ρ θ
h, pitch axis direction rotation ρ θ
v, make terminal output signal light still along the prediction direction outgoing, offset platform vibration effect.Ccd detector detection essence is taken aim at the mirror anglec of rotation and whether is reached the steering order requirement, calculates and ρ θ
h, ρ θ
vDifference, and difference is imported essence takes aim at the mirror controller, essence is taken aim at mirror carries out feedback closed loop control, improve essence and take aim at mirror corner control accuracy.
The invention effect: the present invention, makes that bucking-out system sampling rate height of the present invention, precision height, volume are little, low in energy consumption, it is spaceborne to be convenient to, and adopts the method for mechanical vibration measuring as the vibration detecting element with accelerometer, do not have the limited problem of the ken.Bucking-out system of the present invention has been carried out real-time detection to the vibration of satellite platform, and can effectively compensate the influence that the satellite platform vibration more than 50% is produced.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Embodiment
Referring to Fig. 1, the bucking-out system of this embodiment is by the optical antenna 1 that is on the satellite platform, flashlight generator 4, essence is taken aim at mirror 2, essence is taken aim at mirror controller 5, ccd detector 7, imaging lens group 8, light splitting piece 6, X-axis accelerometer 3-1, Y-axis accelerometer 3-2 and Z axis accelerometer 3-3 form, X-axis accelerometer 3-1, Y-axis accelerometer 3-2 and Z axis accelerometer 3-3 be separately fixed on three spatial axes of satellite platform and be used for the instrumented satellite platform along three spatial axes to acceleration change, X-axis accelerometer 3-1, the data output end of Y-axis accelerometer 3-2 and Z axis accelerometer 3-3 is connected three data input ends that essence is taken aim at mirror controller 5 respectively; Essence is taken aim at mirror 2 and is made of completely reflecting mirror 2-1 and movement executing mechanism 2-2, movement executing mechanism 2-2 is used to control completely reflecting mirror 2-1 deflection, the completely reflecting mirror 2-1 that the flashlight of flashlight generator 4 output is taken aim at mirror 2 by essence changes the light input end that incides light splitting piece 6 after the light path, a part of flashlight of described flashlight generator 4 outputs incides the light input end of the secondary mirror 1-1 of optical antenna 1 after light splitting piece 6 reflections, and be transmitted into target terminal behind the primary mirror 1-2 expansion bundle of this flashlight by optical antenna 1, another part flashlight of described flashlight generator 4 outputs is input to the light input end of imaging lens group 8 after light splitting piece 6 transmissions, light output end in imaging lens group 8 obtains focused beam and imaging on ccd detector 7, and the output terminal of ccd detector 7 connects the smart picture signal input end of taking aim at mirror controller 5.
It is that 100mm, enlargement ratio are that 20 times Cassegrain formula telescope is the terminal optical antenna that described optical antenna 1 is selected bore for use.The MTV-1801 planar array type ccd video camera that described ccd detector 7 selects for use Taiwan Min Tong company to produce, its major parameter is: spectral response range is that 400nm～1100nm, pixel number are that 795 (H) * 596 (V), pixel dimension are that 10 μ rad, line frequency are that 15625Hz, field frequency are that 50Hz, resolution are that 600TVL (line), detection sensitivity are 0.021x (lux), signal to noise ratio (S/N ratio) greater than being DC12V (2W) for 46dB, working temperature-10 ℃～50 ℃, power supply.The pixel spacing of described ccd detector 7 has determined satellite platform angular oscillation detection accuracy, the pixel element has determined its search angle Oscillation Amplitude scope, the spectral response scope has determined the application band of vibration-compensated system, holds the model that mentioned above principle can be determined ccd detector 7 as required.The focal length of described imaging lens group 8 is 50mm.The centre wavelength of described flashlight generator 4 is 800nm, and beam divergence angle is 600 μ rad.Described X-axis accelerometer 3-1, Y-axis accelerometer 3-2 and Z axis accelerometer 3-3 select the CX3-2A molded lines accelerometer of group company of ZhongDian Science ﹠ Technology the 26 Research Institute for use.
Described essence is taken aim at mirror 2 and essence and is taken aim at mirror controller 5 and integrate, select the MPT-2JRL001 type piezoelectricity deflecting mirror and the driver thereof of the development of rich real precise measurement and control company limited of Harbin Institute of Technology for use, the range of deflection of this deflecting mirror is ± 250 μ rad, frequency is 1kHz, the reflecting surface diameter is 40mm, and the deflection precision is 2 μ rad (calculating according to displacement transducer feedback numerical value).The work stage body of this deflecting mirror adopts ultralumin LC4; Bonding K9 substrate of glass catoptron, i.e. completely reflecting mirror 2-1 on the platform bottom surface; This mirror back surface is fixed with two yawing axis that formed by two orthogonal flexure hinge mechanisms, be fixed with two blocks of German PI piezoelectric ceramics (P841.20 type) on these two yawing axis respectively, when a piezoelectric ceramics output displacement, to make catoptron produce certain deflection, two deflections that piezoelectric ceramics produced are separate, can be scaled the deflection angle of catoptron by calculating piezoelectric ceramics in locational displacement separately.
Claims (1)
1, combined feedback-controlled vibration compensation system based on accelerometer, described bucking-out system comprises optical antenna (1) and the flashlight generator (4) that is on the satellite platform, it is characterized in that described bucking-out system comprises that also essence takes aim at mirror (2), essence is taken aim at mirror controller (5), ccd detector (7), imaging lens group (8), light splitting piece (6), X-axis accelerometer (3-1), Y-axis accelerometer (3-2) and Z axis accelerometer (3-3), X-axis accelerometer (3-1), Y-axis accelerometer (3-2) and Z axis accelerometer (3-3) be separately fixed on three spatial axes of satellite platform and be used for the instrumented satellite platform along three spatial axes to acceleration change, X-axis accelerometer (3-1), the data output end of Y-axis accelerometer (3-2) and Z axis accelerometer (3-3) is connected three data input ends that essence is taken aim at mirror controller (5) respectively; Essence is taken aim at mirror (2) and is made of completely reflecting mirror (2-1) and movement executing mechanism (2-2), movement executing mechanism (2-2) is used to control completely reflecting mirror (2-1) deflection, the completely reflecting mirror (2-1) that the flashlight of flashlight generator (4) output is taken aim at mirror (2) by essence changes the light input end that incides light splitting piece (6) after the light path, a part of flashlight of described flashlight generator (4) output incides the light input end of the secondary mirror (1-1) of optical antenna (1) after light splitting piece (6) reflection, and be transmitted into target terminal behind primary mirror (1-2) the expansion bundle of this flashlight by optical antenna (1), another part flashlight of described flashlight generator (4) output is input to the light input end of imaging lens group (8) after light splitting piece (6) transmission, light output end in imaging lens group (8) obtains focused beam and goes up imaging at ccd detector (7), and the output terminal of ccd detector (7) connects the picture signal input end that essence is taken aim at mirror controller (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100100024A CN100517155C (en) | 2006-04-30 | 2006-04-30 | Combined feedback-controlled vibration compensation system based on accelerometer |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100100024A CN100517155C (en) | 2006-04-30 | 2006-04-30 | Combined feedback-controlled vibration compensation system based on accelerometer |
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| Publication Number | Publication Date |
|---|---|
| CN1845031A true CN1845031A (en) | 2006-10-11 |
| CN100517155C CN100517155C (en) | 2009-07-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2006100100024A Expired - Fee Related CN100517155C (en) | 2006-04-30 | 2006-04-30 | Combined feedback-controlled vibration compensation system based on accelerometer |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102023051A (en) * | 2010-09-29 | 2011-04-20 | 北京控制工程研究所 | Method for measuring high frequency micro vibration of triaxial angular displacement of satellite payload |
| CN102323450A (en) * | 2011-05-19 | 2012-01-18 | 中国科学院测量与地球物理研究所 | Satellite-borne accelerometer data calibrating method based on dual-satellite adjacent energy difference principle |
| CN107728472A (en) * | 2017-09-04 | 2018-02-23 | 中国科学院光电技术研究所 | A kind of fast anti-mirror disturbance observation compensating control method based on single accelerometer |
| CN112415888A (en) * | 2020-11-24 | 2021-02-26 | 东方红卫星移动通信有限公司 | Fine aiming mirror double-position ring switching control method and control system |
-
2006
- 2006-04-30 CN CNB2006100100024A patent/CN100517155C/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102023051A (en) * | 2010-09-29 | 2011-04-20 | 北京控制工程研究所 | Method for measuring high frequency micro vibration of triaxial angular displacement of satellite payload |
| CN102023051B (en) * | 2010-09-29 | 2012-06-13 | 北京控制工程研究所 | Method for measuring high frequency micro vibration of triaxial angular displacement of satellite payload |
| CN102323450A (en) * | 2011-05-19 | 2012-01-18 | 中国科学院测量与地球物理研究所 | Satellite-borne accelerometer data calibrating method based on dual-satellite adjacent energy difference principle |
| CN102323450B (en) * | 2011-05-19 | 2012-10-24 | 中国科学院测量与地球物理研究所 | Satellite-borne accelerometer data calibrating method based on dual-satellite adjacent energy difference principle |
| CN107728472A (en) * | 2017-09-04 | 2018-02-23 | 中国科学院光电技术研究所 | A kind of fast anti-mirror disturbance observation compensating control method based on single accelerometer |
| CN112415888A (en) * | 2020-11-24 | 2021-02-26 | 东方红卫星移动通信有限公司 | Fine aiming mirror double-position ring switching control method and control system |
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| Publication number | Publication date |
|---|---|
| CN100517155C (en) | 2009-07-22 |
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