CN103454729A - Spaceborne space optical switch and implementation method - Google Patents
Spaceborne space optical switch and implementation method Download PDFInfo
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- CN103454729A CN103454729A CN2013104162180A CN201310416218A CN103454729A CN 103454729 A CN103454729 A CN 103454729A CN 2013104162180 A CN2013104162180 A CN 2013104162180A CN 201310416218 A CN201310416218 A CN 201310416218A CN 103454729 A CN103454729 A CN 103454729A
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Abstract
The invention discloses a spaceborne space optical switch and an implementation method, and belongs to the field of satellite communication. The spaceborne space optical switch comprises two rectangular prisms (1, 2) with a clearance, a micrometric displacement driver (3) and a connecting piece (4), light-pervious areas (5) are arranged at the corresponding positions of the inclined faces of the two rectangular prisms and are used for transmitting light, absorbing index-matching fluid (7) and microprocessing the surfaces of the inclined faces, the light-pervious areas (5) are made to have super wettability, and light-tight areas (6) have super hydrophobic oil performance. The connecting piece (4) is fixedly connected with one rectangular prism, the micrometric displacement driver (3) is fixedly connected with the other rectangular prism, the connected rectangular prisms are controlled to carry out reciprocating motion in the direction perpendicular to the inclined faces, and the index-matching fluid (7) is made to be separated and fused. The spaceborne space optical switch is used for a spaceborne optical terminal, the on-off rejection ratio of the spectral branch of the spaceborne space optical switch is high, high reliability is achieved, the light beam polarization state can be maintained, stray light is not generated, and the requirement for the accuracy of a micrometric displacement device is low.
Description
Technical field
The invention belongs to satellite communication field, be specifically related to a kind of for the photoswitch on spaceborne optical terminus.
Background technology
The satellite laser communications Terminal Design adopts take the method for designing that link equation is core, and its most important requirement is to guarantee that the catching of terminal, tracking and communication leg all have enough link budgets.The method of the link allowance of current raising satellite laser communications terminal commonly used mainly contains: (1) function merges to reduce the system optics branch road.By developing skill, complexity reduces system complexity, and can improve the optical power density of optics branch road, such as adopting the integrated method of communication tracking that the tracking and communication function of terminal is merged on an optics branch road, the laser coherence communication terminal that for example German TESAT company is the development of TerraSAR-X satellite adopts the binary detector, the Communications And Tracking branch road is integrated, for system has been cut down a tracking branch road.(2) power merges to improve the power density of optics branch road.Utilize suitable light shutter device and gating strategy in the different operating stage of terminal (catch, follow the tracks of, communicate by letter), luminous power is focused on the work at present branch road to improve the link budget of this branch road, and realize seamlessly transitting between work branch.
In the mode of the power density that improves the optics branch road, the application of spatial optical switches contributes to improve greatly acquisition probability more than can promoting the budget 10dB that catches branch road, reduces capture time.The photoswitch type of broad sense is various at present, but all can not meet the requirement of satellite laser communications terminal.Such as traditional mechanical optical switch exists rebound shake and the poor problem of repeatability, can't meet the high precision optical axis stable requirement of satellite laser communications terminal; Micro-machinery switch and fibers/waveguides class switch can't meet the angle pencil of ray requirement of satellite laser communications system; Liquid crystal optical switch can change the polarization state of light beam.
Current, the satellite laser communications terminal of having tested in-orbit or having moved is (as Japanese LUCE, the ARTEMIS light load of France, the TerraSAR-X satellite LCT load of Germany, No. 2, ocean satellite LCT load and the international space station laser communication load of China) do not adopt photoswitch to be caught-follow the tracks of dynamic light splitting and the light path switching of communication leg, because the photoswitch (waveguide type or free space type) be widely used in fibre system all can't be transplanted in the spaceborne optical terminus as the satellite laser communications terminal, at first these photoswitches all need to couple light into inside of optical fibre, and the spatial light under spaceborne environment is to the coupling efficiency of optical fiber and stability extreme difference all, can't within the whole length of service of satellite laser communications terminal, keep high reliability request.Therefore need a kind of spaceborne spatial optical switches that is applicable to the angle pencil of ray bore to complete the function of light path gating.
Although the existing a large amount of research of the photoswitch based on the coupling of biprism evanescent wave, if be applied on spaceborne optical terminus, have implacable contradiction between its luminous energy transmitance and reliability.In order to keep being greater than 97% luminous energy transfer, prism gap must be controlled to the sub-wavelength magnitude; Be less than 0.1 wavelength and work as two prism gap, molecular force between two prism local surfaces can attract two prisms directly (this process is called as the optical cement phenomenon) glued together, destroy the dynamics of switching process, can not meet the reliability requirement under spaceborne condition.
Summary of the invention
Goal of the invention of the present invention is: for the problem of above-mentioned existence, provide the spaceborne photoswitch that completes high rejection ratio under a kind of condition of the displacement driver in larger prism gap and low precision.
Spaceborne spatial optical switches of the present invention, comprise the first right-angle prism 1 and the second right-angle prism 2 and micro-displacement driver 3, web member 4;
Web member 4 one ends are fixedly connected with the first right-angle prism 1, one end and are fixedly connected with spaceborne optical terminus, and the incident beam optical axis angle at 45 ° of the inclined-plane of the first right-angle prism 1 and spaceborne optical terminus; Described micro-displacement driver 3 is fixedly connected with the second right-angle prism 2, controls the second right-angle prism 2 and moves reciprocatingly on the direction perpendicular to inclined-plane;
The correspondence position on the inclined-plane of the first right-angle prism 1 and the second right-angle prism 2 arranges transparent zone territory 5, the surface contact angle in described transparent zone territory 5 is less than 90 °, minimum edge is apart from the incident beam diameter that is greater than spaceborne optical terminus, the surface in the non-transparent zone territory 6 on inclined-plane is super oleophobic surface, and each right angle face is provided with anti-reflection film;
The refractive index of described the first right-angle prism 1 and the second right-angle prism 2 equates, be equipped with the index-matching fluid 7 of corresponding right-angle prism refractive index on transparent zone territory 5, when micro-displacement driver 3 is controlled the second right-angle prism 2 near the first right-angle prism 1, the first right-angle prism 1 merges mutually with the index-matching fluid 7 on the second right-angle prism 2; The second right-angle prism 2 is during away from the first right-angle prism 1, and the index-matching fluid 7 of fusion separates, and is adsorbed on each transparent zone territory 5.
Simultaneously, the invention allows for a kind of implementation method of spaceborne spatial optical switches, comprise the following steps:
S1: the first right-angle prism, the second right-angle prism that refractive index equates carry out pre-service:
Each right angle face is carried out to precise polished and plating anti-reflection film;
Each inclined-plane opposite position is defined as to the transparent zone territory, and the minimum edge distance in described transparent zone territory is greater than the incident beam diameter of spaceborne optical terminus, and the surface micro-structure processing is carried out in the transparent zone territory, makes its surface contact angle be less than 90 °;
Surface micro-structure processing, chemical modification processing are carried out in the non-transparent zone territory on each inclined-plane, and making its surface is super oleophobic surface;
S2: the first right-angle prism is fixedly connected on spaceborne optical terminus, and with incident beam optical axis angle at 45 °; The second right-angle prism is fixedly connected with micro-displacement driver, and the inclined-plane that two right-angle prisms are set relatively and have a gap, and inject the index-matching fluid of corresponding right-angle prism refractive index in gap, control the second right-angle prism by micro-displacement driver moves reciprocatingly on the direction perpendicular to inclined-plane, make separation and the fusion of index-matching fluid: during released state, the inclined-plane of the first right-angle prism is reflected incident beam; During the fusion state, the first right-angle prism, based on index-matching fluid, exports the incident beam coupling to second right-angle prism.
The present invention is based on total internal reflection principle, by taking to inject the index-matching fluid (glass refraction of the corresponding right-angle prism of the refractive index of index-matching fluid in the middle of gap, two right-angle prism inclined-planes, be that both equate, allow to exist error, limit error is less than 10 usually
-4), form the adjustable clearance spatial optical switches of a sandwich structure.The invention has the beneficial effects as follows:
At first, the index-matching fluid term of validity that industry is produced at present can reach 10-20, meets the demand in serviceable life of spaceborne optical terminus; Its refractivity precision reaches 10
-4, the evanescent wave coupling efficiency of being induced by index-matching fluid is close to 100%;
Secondly, mobility and filling capacity due to liquid, switch is controlled displacement accuracy and can greatly be reduced, according to the index liquid injected the number, even lower than micron-sized precision, can meet the switch displacement and control requirement, and the dynamic range of control displacement is large (nanoscale～micron order is greater than 30dB) very, and this can increase the reliability of switch module undoubtedly;
Again, under space environment, the index liquid that is adsorbed on prism surface can form smooth surface, and its smooth degree is far longer than the prism surface of machining, therefore there is better reflection characteristic, can reduce to a certain extent the optics processing request of prism surface.
The accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is the structural representation of the space switching of embodiment;
Fig. 2 is the planimetric map on inclined-plane of right-angle prism of the space switching of embodiment;
Fig. 3 is the working state figure of space switching when index-matching fluid merges of embodiment;
Wherein, 1---the first right-angle prism, 2---the second right-angle prism, 3---micro-displacement driver, 4---web member, 5---the transparent zone territory, 6---the non-transparent zone territory on right-angle prism inclined-plane, 7---index-matching fluid.
Embodiment
Disclosed all features in this instructions, or the step in disclosed all methods or process, except mutually exclusive feature and/or step, all can combine by any way.
Disclosed arbitrary feature in this instructions (comprising any accessory claim, summary and accompanying drawing), unless special narration all can be replaced by other equivalences or the alternative features with similar purpose.That is,, unless special narration, each feature is an example in a series of equivalences or similar characteristics.
Spaceborne spatial optical switches of the present invention is mainly equated the right-angle prism of (error is less than 10-4) by two refractive indexes, be preferably structure size identical, so that processing, the index-matching fluid that equates (error is less than 10-4) with the refractive index of right-angle prism, and Micro-displacement Driving, optical terminus web member form, its structural representation as shown in Figure 1:
At first two identical right-angle prisms (1 shown in Fig. 1 and 2) are carried out to pre-service:
4 right angle faces of two right-angle prisms all need precise polished and plating anti-reflection film, and anti-reflection film should the meeting spatial application demand, comprises reliability and transmitance demand;
By the inclined-plane of two right-angle prisms corresponding location positioning be transparent zone territory 5(as shown in Figure 2), the minimum edge in this transparent zone territory 5 is apart from the incident beam diameter that is greater than spaceborne optical terminus, the center that optimum position is inclined-plane, be shaped as circle, being convenient to processing realizes, and the surface micro-structure processing is carried out in transparent zone territory 5, can adopt photoetching, corrosion, the methods such as ultra-precision machine tool cutting form the surface of micro-nano structure, thereby make its surface contact angle be less than 90 °, to realize the good wet between right-angle prism surface and index-matching fluid, interface does not have cavity, when separating, two right-angle prisms still have a considerable amount of rate matching fluids of penetrating evenly to be attached to each transparent zone territory, center,
The non-transparent zone territory 6(on two right-angle prism inclined-planes as shown in Figure 2, the fringe region do not overlapped with the transparent zone territory), also to carry out the surface micro-structure processing, and doing the surface chemical modification processing (can adopt fluoride to modify, the methods such as silica polymer precipitation), making the surface in non-transparent zone territory 6 is super oleophobic surface, and the surface-stable contact angle is greater than 150 °, to realize the super thin characteristic between prism surface and index-matching fluid 7.Such measure is in order to ensure under agravic environment, when switch of the present invention separates, be extruded the index-matching fluid 7 that expands to fringe region and can under the effect of surface tension of liquid, shrink back central area, and can not spread on the right angle face of right-angle prism by the switch gap.
After pre-service is carried out in the surface of two right-angle prisms, to be fixedly connected with (being that right-angle prism 1 is the mode of being rigidly connected with spaceborne optical terminus) on spaceborne optical terminus by web member 4 as the right-angle prism 1 of light input reference, its inclined-plane should with the incident beam optical axis of spaceborne optical terminus in angle of 45 degrees, with the polarization state that guarantees the reflection and transmission light beam, do not change, this is the basic demand of laser coherence communication terminal.
To be fixedly connected with (being rigidly secured on micro-displacement driver 3) with micro-displacement driver 3 as the right-angle prism 2 of optically-coupled output, by controlling micro-displacement driver 3, make right-angle prism 2 move reciprocatingly on the direction perpendicular to its inclined-plane, kinematic accuracy reaches nanometer scale, and the stroke of motion reaches tens of micron dimensions.While realizing, micro-displacement driver 3 can adopt piezoelectric ceramics PZT, but the materials and devices of the controlled changes such as magnetostriction materials self length, and should be all aerospace level product, with the reliability requirement of meeting spatial application.
The workflow of spaceborne spatial optical switches of the present invention is: an end of the web member 4 of switch is fixed on definite outside installed surface, when two right-angle prism gaps enough large (as being greater than 3 wavelength), index-matching fluid 7 on two right-angle prisms is when released state, evanescent wave can't be coupled, all incident lights are all reflected away by the inclined-plane of right-angle prism 1, enter one of them optics branch road of spaceborne optical terminus; And at another working stage (as shown in Figure 3), micro-displacement driver 3 drives right-angle prism 2 close to right-angle prism 1, when two parts index-matching fluid 7 merges, all incident light will transmit from the right angle face of right-angle prism 2, enter another optics branch road of spaceborne optical terminus, above-mentioned two duties realize the gated optical switch of a high rejection ratio jointly.
The present invention utilizes mobility characteristic and the total internal reflection principle of index-matching fluid, by controlling separation and the fusion of index-matching fluid, realizes the light path gating function of incident beam transmission and reflection.The prism inclined-plane is carried out to the subregion surface treatment simultaneously, realize the control to liquid fluidity.Photoswitch involved in the present invention has following advantage: angle pencil of ray is applicable, low aberration, and the high speed of response, the break-make rejection ratio of light splitting branch road is high, can keep light polarization, does not produce parasitic light, low to the accuracy requirement of micrometric displacement device, and reliability is high.Can greatly promote capture terminal and follow the tracks of the link budget of branch road, strengthen acquisition probability, reduce capture time.
The present invention is not limited to aforesaid embodiment.The present invention expands to any new feature or any new combination disclosed in this manual, and the arbitrary new method disclosed or step or any new combination of process.
Claims (4)
1. a spaceborne spatial optical switches, is characterized in that, comprises the first right-angle prism (1) and the second right-angle prism (2) and micro-displacement driver (3), web member (4);
Web member (4) one ends are fixedly connected with the first right-angle prism (1), and an end is fixedly connected with spaceborne optical terminus, and the incident beam optical axis angle at 45 ° of the inclined-plane of the first right-angle prism (1) and spaceborne optical terminus; Described micro-displacement driver (3) is fixedly connected with the second right-angle prism (2), controls the second right-angle prism (2) and moves reciprocatingly on the direction perpendicular to inclined-plane;
The correspondence position on the inclined-plane of the first right-angle prism (1) and the second right-angle prism (2) arranges transparent zone territory (5), the surface contact angle in described transparent zone territory (5) is less than 90 °, minimum edge is apart from the incident beam diameter that is greater than spaceborne optical terminus, the surface in the non-transparent zone territory (6) on inclined-plane is super oleophobic surface, and each right angle face is provided with anti-reflection film;
The refractive index of described the first right-angle prism (1) and the second right-angle prism (2) equates, be equipped with the index-matching fluid (7) of corresponding right-angle prism refractive index on transparent zone territory (5), when micro-displacement driver (3) is controlled the second right-angle prism (2) near the first right-angle prism (1), the first right-angle prism (1) merges mutually with the index-matching fluid (7) on the second right-angle prism (2); The second right-angle prism (2) is during away from the first right-angle prism (1), and the index-matching fluid of fusion (7) separates, and is adsorbed on each transparent zone territory (5).
2. spatial optical switches as claimed in claim 1, is characterized in that, described transparent zone territory (5) is positioned at the center on the inclined-plane of the first right-angle prism (1) and the second right-angle prism (2).
3. spatial optical switches as claimed in claim 1 or 2, is characterized in that, described transparent zone territory is circular, and its diameter is greater than the incident beam diameter of spaceborne optical terminus.
4. the implementation method of a spaceborne spatial optical switches, is characterized in that, comprises the following steps:
S1: the first right-angle prism, the second right-angle prism that refractive index equates carry out pre-service:
Each right angle face is carried out to precise polished and plating anti-reflection film;
Each inclined-plane opposite position is defined as to the transparent zone territory, and the minimum edge distance in described transparent zone territory is greater than the incident beam diameter of spaceborne optical terminus, and the surface micro-structure processing is carried out in the transparent zone territory, makes its surface contact angle be less than 90 °;
Surface micro-structure processing, chemical modification processing are carried out in the non-transparent zone territory on each inclined-plane, and making its surface is super oleophobic surface;
S2: the first right-angle prism is fixedly connected on spaceborne optical terminus, and with incident beam optical axis angle at 45 °; The second right-angle prism is fixedly connected with micro-displacement driver, and the inclined-plane that two right-angle prisms are set relatively and have a gap, and inject the index-matching fluid of corresponding right-angle prism refractive index in gap, control the second right-angle prism by micro-displacement driver moves reciprocatingly on the direction perpendicular to inclined-plane, make separation and the fusion of index-matching fluid: during released state, the inclined-plane of the first right-angle prism is reflected incident beam; During the fusion state, the first right-angle prism, based on index-matching fluid, exports the incident beam coupling to second right-angle prism.
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| CN201310416218.0A CN103454729B (en) | 2013-09-12 | 2013-09-12 | A kind of spaceborne space optical switch and implementation method |
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| CN201310416218.0A CN103454729B (en) | 2013-09-12 | 2013-09-12 | A kind of spaceborne space optical switch and implementation method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109975945A (en) * | 2019-03-25 | 2019-07-05 | 南京帕克光电科技有限公司 | A kind of truncated cone-shaped prism and its sealing structure |
| CN113517928A (en) * | 2021-04-26 | 2021-10-19 | 长春理工大学 | All-optical capturing method and device applied to space laser communication |
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| US6438283B1 (en) * | 1999-10-08 | 2002-08-20 | Optical Switch Corporation | Frustrated total internal reflection switch using double pass reflection and method of operation |
| CN1381930A (en) * | 2001-04-18 | 2002-11-27 | 中国科学院理化技术研究所 | Nonlinear optical crystal laser frequency conversion coupler |
| WO2004066006A1 (en) * | 2003-01-20 | 2004-08-05 | Polatis Ltd | Optical connector with total internal reflection abutting surface |
| CN102436028A (en) * | 2011-12-23 | 2012-05-02 | 宋齐望 | Planar optical waveguide structure and manufacturing method thereof |
| CN103185962A (en) * | 2013-03-12 | 2013-07-03 | 南京邮电大学 | Electrowetting piston optical switch |
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2013
- 2013-09-12 CN CN201310416218.0A patent/CN103454729B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6438283B1 (en) * | 1999-10-08 | 2002-08-20 | Optical Switch Corporation | Frustrated total internal reflection switch using double pass reflection and method of operation |
| CN1381930A (en) * | 2001-04-18 | 2002-11-27 | 中国科学院理化技术研究所 | Nonlinear optical crystal laser frequency conversion coupler |
| WO2004066006A1 (en) * | 2003-01-20 | 2004-08-05 | Polatis Ltd | Optical connector with total internal reflection abutting surface |
| CN102436028A (en) * | 2011-12-23 | 2012-05-02 | 宋齐望 | Planar optical waveguide structure and manufacturing method thereof |
| CN103185962A (en) * | 2013-03-12 | 2013-07-03 | 南京邮电大学 | Electrowetting piston optical switch |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109975945A (en) * | 2019-03-25 | 2019-07-05 | 南京帕克光电科技有限公司 | A kind of truncated cone-shaped prism and its sealing structure |
| CN113517928A (en) * | 2021-04-26 | 2021-10-19 | 长春理工大学 | All-optical capturing method and device applied to space laser communication |
| CN113517928B (en) * | 2021-04-26 | 2022-03-25 | 长春理工大学 | All-optical capturing method and device applied to space laser communication |
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