CN1838569B - Satellite optical communication high precision advance sighting angle compensating device - Google Patents
Satellite optical communication high precision advance sighting angle compensating device Download PDFInfo
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- CN1838569B CN1838569B CN200610009979A CN200610009979A CN1838569B CN 1838569 B CN1838569 B CN 1838569B CN 200610009979 A CN200610009979 A CN 200610009979A CN 200610009979 A CN200610009979 A CN 200610009979A CN 1838569 B CN1838569 B CN 1838569B
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Abstract
This invention relates to satellite light communication high precision aiming at angle advance compensation arrangement, which composed of the computing processor (1), driving controller (2), aiming operating structure (3) and angle sensor (4), the outlet of (1) connects with one inlet of (2), the outlet of (2) connects with the inlet of (3), (4) is arranged on (3), the outlet of (4) connects withthe other inlet, (3) is composed of number one piezo-electric ceramic pole (3-1), number two piezo-electric ceramic pole (3-2), working platform (3-3), working platform (3-4) and flexble hinge (3-5), (3-5) is fixed at the edge of the (3-4)'s down face and (3-3)'s upper face, (3-1), (3-2) are arranged in (3-2), (3-1) and (3-2)' upper face prop up the down face of (3-4), (3-5) is arranged at (3-1)and (3-2)'s sides and has the same distance with (3-1) and (3-2).
Description
Technical field
The present invention relates to the satellite optical communication device, be specifically related to the compensation arrangement of aiming in advance in the satellite optical communication device.
Background technology
The distance of signal transmission is far in the inter-satellite optical communication, makes that the relaxation time of transmission is longer.When considering two inter-satellites in relative motion, transmitting terminal must receive actual " the place ahead " of receiving terminal that be targeted to of light beam so that receiving terminal carries out signal.That is to say that transmitting terminal must be considered additional the moving between two stars that beam Propagation was taken place in the relaxation time when aiming, to be registered to the position, angle of expectation.Usually claim this aiming process to be aiming in advance.The principle of the existing angle compensation device that aims in advance is the orbital data according to two satellites that communicate that obtain, and dopes the advance sighting angle value of current time, and compensates by certain control algolithm and actuator.But its actuator's more complicated, the speed of dynamic response is slow.
Summary of the invention
The purpose of this invention is to provide a kind of satellite optical communication high precision advance sighting angle compensating device, to overcome prior art actuator more complicated, the slow-footed shortcoming of dynamic response.It is by arithmetic processor 1, driving governor 2, aiming actuator 3 and angular transducer 4 are formed, the output of arithmetic processor 1 that can orbital data via satellite calculates the advance sighting angle value of current time connects an input of driving governor 2, the output of driving governor 2 connects the input of aiming actuator 3, angular transducer 4 is arranged in the aiming actuator 3 with its anglec of rotation of real-time measurement, the output of angular transducer 4 connects another input of driving governor 2 to realize the angle feedback, aiming actuator 3 is by a piezoelectric ceramic post 3-1, No. two piezoelectric ceramic post 3-2, work stage body 3-3, work top 3-4 and flexible hinge 3-5 form, work top 3-4 is arranged on the top of work stage body 3-3, flexible hinge 3-5 is fixed on the edge of the edge of work top 3-4 lower surface and the stage body 3-3 upper surface of working, a piezoelectric ceramic post 3-1, No. two piezoelectric ceramic post 3-2 is arranged in the work stage body 3-3, the upper surface of a piezoelectric ceramic post 3-1 and No. two piezoelectric ceramic post 3-2 withstands on the lower surface of work top 3-4, flexible hinge 3-5 is arranged on the side of a piezoelectric ceramic post 3-1 and No. two piezoelectric ceramic post 3-2 and equates with the distance of the two, and a flexible hinge 3-5 and a piezoelectric ceramic post 3-1 and No. two piezoelectric ceramic post 3-2 constitute an isosceles triangle.When the present invention works, the device that is used for transmitting optical signal is arranged at the upper surface of work top 3-4, arithmetic processor 1 is extrapolated the advance sighting angle of current time according to orbital data, and send to driving governor 2, driving governor 2 drives a piezoelectric ceramic post 3-1 and No. two piezoelectric ceramic post 3-2 stretch, push work top 3-4 and rotate around flexible hinge 3-5, angular transducer 4 is used to realize the feedback of work top 3-4 rotational angle, thereby finishes aiming in advance.Aiming of the present invention actuator 3 only is made up of two piezoelectric ceramic posts, work stage body, work top and flexible hinge, and structure is very simple, and type of drive is also simple, and it is fast that dynamic response gets speed, overcome the defective of prior art.The present invention can be applied to various optical communication terminals, as low-orbit satellite (LEO) optical communication terminal, geosynchronous satellite (GEO) optical communication terminal and ground light communication terminal etc.Platform obtains the orbital data of two satellites via satellite, can extrapolate each advance sighting angle constantly, carry out the advance sighting angle compensation in real time at the different phase of satellite transit, more than the control frequency 100Hz of driving governor, precision can satisfy the requirement to the laser link tenacious tracking in 2 μ rad.
Description of drawings
Fig. 1 is a structural representation of the present invention, and Fig. 2 is the structural representation of aiming actuator 3 in the execution mode one, and Fig. 3 is the structural representation of driving governor 2 in the execution mode two, and Fig. 4 is the structural representation of execution mode three, and Fig. 5 is the A-A cutaway view of Fig. 2.
Embodiment
Embodiment one: specify present embodiment below in conjunction with Fig. 1, Fig. 2 and Fig. 5.Present embodiment is by arithmetic processor 1, driving governor 2, aiming actuator 3 and angular transducer 4 are formed, the output of arithmetic processor 1 that can orbital data via satellite calculates the advance sighting angle value of current time connects an input of driving governor 2, the output of driving governor 2 connects the input of aiming actuator 3, angular transducer 4 is arranged in the aiming actuator 3 with its anglec of rotation of real-time measurement, the output of angular transducer 4 connects another input of driving governor 2 to realize the angle feedback, aiming actuator 3 is by a piezoelectric ceramic post 3-1, No. two piezoelectric ceramic post 3-2, work stage body 3-3, work top 3-4 and flexible hinge 3-5 form, work top 3-4 is arranged on the top of work stage body 3-3, flexible hinge 3-5 is fixed on the edge of the edge of work top 3-4 lower surface and the stage body 3-3 upper surface of working, a piezoelectric ceramic post 3-1, No. two piezoelectric ceramic post 3-2 is arranged in the work stage body 3-3, the upper surface of a piezoelectric ceramic post 3-1 and No. two piezoelectric ceramic post 3-2 withstands on the lower surface of work top 3-4, and flexible hinge 3-5 is arranged on the side of a piezoelectric ceramic post 3-1 and No. two piezoelectric ceramic post 3-2 and equates with the distance of the two.
Embodiment two: specify present embodiment below in conjunction with Fig. 3.The difference of present embodiment and execution mode one is: angular transducer 4 is made up of a micro-displacement sensor 4-1 and No. two micro-displacement sensor 4-2, a micro-displacement sensor 4-1 and No. two micro-displacement sensor 4-2 select resistance strain type sensor for use and are built in piezoelectric ceramic post 3-1 respectively No. one, among No. two piezoelectric ceramic post 3-2, described driving governor 2 is made up of a Drive and Control Circuit 2-1 and No. two Drive and Control Circuit 2-2 of same structure, an output of the input concatenation operation processor 1 of a Drive and Control Circuit 2-1, another input of a Drive and Control Circuit 2-1 connects the output of a micro-displacement sensor 4-1, another output of the input concatenation operation processor 1 of No. two Drive and Control Circuit 2-2, another input of No. two Drive and Control Circuit 2-2 connects the output of No. two micro-displacement sensor 4-2, select the PI P841.20 type piezoelectric ceramic of Germany in the present embodiment for use, promptly be built-in with resistance strain type sensor.When any one piezoelectric ceramic post output displacement, all will make work top 3-4 that the deflection of a direction takes place, the deflection of both direction is separate, and amount of deflection can both be respectively by two micro-displacement sensor collections and conversion.
Embodiment three: specify present embodiment below in conjunction with Fig. 4.The difference of present embodiment and execution mode two is: a Drive and Control Circuit 2-1 is by resistance R 1, resistance R 2, resistance R 3, resistance R 4, resistance R 5, resistance R 6, capacitor C, integrated operational amplifier U1A and integrated operational amplifier U2B form, an output of one end concatenation operation processor 1 of resistance R 1, the other end of resistance R 1 connects an end of resistance R 4 and the reverse input end of integrated operational amplifier U1A, the input in the same way of integrated operational amplifier U1A connects an end of resistance R 3 and an end of resistance R 2, the other end ground connection of resistance R 3, the other end of resistance R 2 connects the output of a micro-displacement sensor 4-1, the output of integrated operational amplifier U1A connects the input in the same way of integrated operational amplifier U2B by resistance R 5, the reverse input end of integrated operational amplifier U2B connects an end of resistance R 6 and an end of capacitor C, the other end ground connection of resistance R 6, the other end of capacitor C connects output and piezoelectric ceramic post 3-1 of integrated operational amplifier U2B.The Drive and Control Circuit of present embodiment adopts the PID closed-loop control, adopts operational amplifier completed percentage and integral and calculating, makes dynamic response fast, accurately.
Claims (2)
1. satellite optical communication high precision advance sighting angle compensating device, it is by arithmetic processor (1), driving governor (2), aiming actuator (3) and angular transducer (4) are formed, the output of arithmetic processor (1) that can orbital data via satellite calculates the advance sighting angle value of current time connects an input of driving governor (2), the output of driving governor (2) connects the input of aiming actuator (3), angular transducer (4) is arranged on aiming actuator (3) and goes up with its anglec of rotation of real-time measurement, the output of angular transducer (4) connects another input of driving governor (2) to realize the angle feedback, it is characterized in that aiming at actuator (3) by a piezoelectric ceramic post (3-1), No. two piezoelectric ceramic posts (3-2), work stage body (3-3), work top (3-4) and flexible hinge (3-5) are formed, work top (3-4) is arranged on the top of work stage body (3-3), flexible hinge (3-5) is fixed on the edge of the edge of work top (3-4) lower surface and stage body (3-3) upper surface of working, a piezoelectric ceramic post (3-1), No. two piezoelectric ceramic posts (3-2) are arranged in the work stage body (3-3), the upper surface of a piezoelectric ceramic post (3-1) and No. two piezoelectric ceramic posts (3-2) withstands on the lower surface of work top (3-4), flexible hinge (3-5) is arranged on the side of a piezoelectric ceramic post (3-1) and No. two piezoelectric ceramic posts (3-2) and equates with the distance of the two, and flexible hinge (3-5) constitutes an isosceles triangle with a piezoelectric ceramic post (3-1) and No. two piezoelectric ceramic posts (3-2).
2. satellite optical communication high precision advance sighting angle compensating device according to claim 1, it is characterized in that angular transducer (4) is made up of a micro-displacement sensor (4-1) and No. two micro-displacement sensors (4-2), a micro-displacement sensor (4-1) and No. two micro-displacement sensors (4-2) are all selected resistance strain type sensor for use and are built in a piezoelectric ceramic post (3-1) respectively, in No. two piezoelectric ceramic posts (3-2), described driving governor (2) is made up of a Drive and Control Circuit (2-1) and No. two Drive and Control Circuit (2-2) of same structure, an output of an input concatenation operation processor (1) of a Drive and Control Circuit (2-1), another input of a Drive and Control Circuit (2-1) connects the output of a micro-displacement sensor (4-1), another output of an input concatenation operation processor (1) of No. two Drive and Control Circuit (2-2), another input of No. two Drive and Control Circuit (2-2) connects the output of No. two micro-displacement sensors (4-2), described satellite optical communication high precision advance sighting angle compensating device, it is characterized in that a Drive and Control Circuit (2-1) is by resistance R 1, resistance R 2, resistance R 3, resistance R 4, resistance R 5, resistance R 6, capacitor C, integrated operational amplifier U1A and integrated operational amplifier U2B form, an output of one end concatenation operation processor 1 of resistance R 1, the other end of resistance R 1 connects an end of resistance R 4 and the reverse input end of integrated operational amplifier U1A, the input in the same way of integrated operational amplifier U1A connects an end of resistance R 3 and an end of resistance R 2, the other end ground connection of resistance R 3, the other end of resistance R 2 connects the output of a micro-displacement sensor (4-1), the output of integrated operational amplifier U1A connects the other end of resistance R 4 and connects the input in the same way of integrated operational amplifier U2B by resistance R 5, the reverse input end of integrated operational amplifier U2B connects an end of resistance R 6 and an end of capacitor C, the other end ground connection of resistance R 6, the other end of capacitor C connects an output and the piezoelectric ceramic post (3-1) of integrated operational amplifier U2B.
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| Application Number | Priority Date | Filing Date | Title |
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| CN200610009979A CN1838569B (en) | 2006-04-28 | 2006-04-28 | Satellite optical communication high precision advance sighting angle compensating device |
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| CN200610009979A CN1838569B (en) | 2006-04-28 | 2006-04-28 | Satellite optical communication high precision advance sighting angle compensating device |
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| CN1838569A CN1838569A (en) | 2006-09-27 |
| CN1838569B true CN1838569B (en) | 2010-05-12 |
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| CN101630970B (en) * | 2009-08-14 | 2012-07-18 | 中国科学院上海光学精密机械研究所 | Satellite laser communication compound axis light tracking device and control method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1598482A (en) * | 2004-08-31 | 2005-03-23 | 哈尔滨工业大学 | Satellite light communication high speed tracking detector and its detecting method |
| CN1710835A (en) * | 2005-06-10 | 2005-12-21 | 哈尔滨工业大学 | High-speed large view-field capture tracing detecting apparatus in space optical communication |
| CN1713019A (en) * | 2005-05-31 | 2005-12-28 | 哈尔滨工业大学 | Transmit-receive off-axis optical communication track sight of satellite |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1598482A (en) * | 2004-08-31 | 2005-03-23 | 哈尔滨工业大学 | Satellite light communication high speed tracking detector and its detecting method |
| CN1713019A (en) * | 2005-05-31 | 2005-12-28 | 哈尔滨工业大学 | Transmit-receive off-axis optical communication track sight of satellite |
| CN1710835A (en) * | 2005-06-10 | 2005-12-21 | 哈尔滨工业大学 | High-speed large view-field capture tracing detecting apparatus in space optical communication |
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