CN103454729B - A kind of spaceborne space optical switch and implementation method - Google Patents
A kind of spaceborne space optical switch and implementation method Download PDFInfo
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- CN103454729B CN103454729B CN201310416218.0A CN201310416218A CN103454729B CN 103454729 B CN103454729 B CN 103454729B CN 201310416218 A CN201310416218 A CN 201310416218A CN 103454729 B CN103454729 B CN 103454729B
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Abstract
The invention discloses a kind of spaceborne space optical switch and implementation method, belong to satellite communication field.The present invention includes two right-angle prisms (1 that there is gap, 2), micro-displacement driver (3), web member (4), territory, transparent zone (5) is established at the correspondence position on the inclined-plane of two right-angle prisms, for logical light and absorption index-matching fluid (7), and micro-process chamfered surface, make territory, transparent zone (5) have super wetting state, territory, non-transparent zone (6) has super oleophobic performance; Web member (4) is fixedly connected with a right-angle prism, and micro-displacement driver (3) is fixedly connected with another right-angle prism, and the right-angle prism controlling to connect is moving reciprocatingly perpendicular on the direction on inclined-plane, index-matching fluid (7) is separated and merges.The present invention is used for spaceborne optical terminus, and the break-make rejection ratio of its light splitting branch road is high, and high reliability can keep light polarization, not produce parasitic light, low to the accuracy requirement of micrometric displacement device.
Description
Technical field
The invention belongs to satellite communication field, be specifically related to a kind of photoswitch on spaceborne optical terminus.
Background technology
It take link equation as the method for designing of core that satellite laser communications Terminal Design adopts, and its most important requirement guarantees the catching of terminal, to follow the tracks of and communication leg all has enough link budgets.The method of the link margin of current conventional raising satellite laser communications terminal mainly contains: (1) function merges to reduce system optics branch road.By developing skill, complexity reduces system complexity, and the optical power density of optical branch can be improved, the method of communication tracking integration is such as adopted the tracking and communication function of terminal to be merged on an optical branch, such as German TESAT company is that namely the laser coherence communication terminal of TerraSAR-X satellite development adopts binary detector, Communications And Tracking branch road is integrated, for system reduces a tracking branch road.(2) power merges with the power density improving optical branch.Utilize suitable light shutter device and gating scheme in the different operating stage (catch, follow the tracks of, communicate) of terminal, luminous power is focused on to improve the link budget of this branch road on work at present branch road, and realize seamlessly transitting between work branch.
In the mode of power density improving optical branch, the application of spatial optical switches can promote more than the budget 10dB catching branch road, contributes to improving acquisition probability greatly, reduces capture time.The photoswitch type of current broad sense is various, but all can not meet the requirement of satellite laser communications terminal.There is the problem that rebound is shaken and repeatability is poor in such as traditional mechanical optical switch, cannot meet the high precision optical axis stable requirement of satellite laser communications terminal; Micro-machinery switch and fibers/waveguides class switch then cannot meet the angle pencil of ray requirement of satellite laser communications system; Liquid crystal optical switch then can change the polarization state of light beam.
Current, the satellite laser communications terminal of Orbital detection or operation is (as the LUCE of Japan, the ARTEMIS light load of France, the TerraSAR-X satellite LCT load of Germany, No. 2, the ocean satellite LCT load of China and international space station laser communication load) do not adopt photoswitch to carry out the dynamic light splitting of catching-following the tracks of communication leg and light path to switch, because the photoswitch (waveguide type or free space type) be widely used in fibre system all cannot be transplanted in the spaceborne optical terminus as satellite laser communications terminal, all first these photoswitches need to couple light into inside of optical fibre, and spatial light under spaceborne environment is to the coupling efficiency of optical fiber and stability all extreme differences, high reliability request cannot be kept within the whole length of service of satellite laser communications terminal.Therefore need a kind of spaceborne space optical switch being applicable to angle pencil of ray bore to complete the function of light path gating.
Although have large quantifier elimination based on the photoswitch of biprism evanescent wave coupling, if be applied on spaceborne optical terminus, between its light-transmissive rate and reliability, there is implacable contradiction.In order to keep the luminous energy transfer being greater than 97%, prism gap must be controlled to sub-wavelength magnitude; And when two prism gap are less than 0.1 wavelength, molecular force between two prism local surfaces can attract two prisms directly (this process is called as optical cement phenomenon) glued together, destroy the dynamics of switching process, the reliability requirement under spaceborne condition can not be met.
Summary of the invention
Goal of the invention of the present invention is: for above-mentioned Problems existing, provides a kind of spaceborne photoswitch completing high rejection ratio under the displacement driver condition of larger prism gap and low precision.
Spaceborne space optical switch of the present invention, 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 end is fixedly connected with the first right-angle prism 1, and one 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 is moving reciprocatingly perpendicular on the direction on inclined-plane;
The correspondence position on the inclined-plane of the first right-angle prism 1 and the second right-angle prism 2 arranges territory, transparent zone 5, the surface contact angle in territory, described transparent zone 5 is less than 90 °, minimum edge is apart from the incident beam diameter being greater than spaceborne optical terminus, the surface in the territory, non-transparent zone 6 on inclined-plane is super oleophobic surface, and each right-angle surface is provided with anti-reflection film;
The refractive index of described first right-angle prism 1 and the second right-angle prism 2 is equal, territory, transparent zone 5 is equipped with the index-matching fluid 7 of corresponding right-angle prism refractive index, when micro-displacement driver 3 controls 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; When second right-angle prism 2 is away from the first right-angle prism 1, the index-matching fluid 7 of fusion is separated, and is adsorbed on territory, each transparent zone 5.
Meanwhile, the invention allows for a kind of implementation method of spaceborne space optical switch, comprise the following steps:
S1: the first right-angle prism that refractive index is equal, the second right-angle prism carry out pre-service:
Precise polished and plating anti-reflection film is carried out to each right-angle surface;
Each inclined-plane opposite position is defined as territory, transparent zone, and the minimum edge in territory, described transparent zone apart from the incident beam diameter being greater than spaceborne optical terminus, and carries out surface micro-structure process to territory, transparent zone, makes its surface contact angle be less than 90 °;
Surface micro-structure process, chemical modification process are carried out to the territory, non-transparent zone on each inclined-plane, makes its surface for super oleophobic surface;
S2: the first right-angle prism is fixedly connected on spaceborne optical terminus, and angle at 45 ° with incident beam optical axis; Second right-angle prism is fixedly connected with micro-displacement driver, and the inclined-plane arranging two right-angle prisms relatively and there is gap, and in gap, inject the index-matching fluid of corresponding right-angle prism refractive index, control the second right-angle prism by micro-displacement driver moving reciprocatingly perpendicular on the direction on inclined-plane, make separation and the fusion of index-matching fluid: during released state, the inclined-plane of the first right-angle prism reflects incident beam; During Fusion Strain, the first right-angle prism based on index-matching fluid, by incident beam coupling output to the 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 refractive index of index-matching fluid in the middle of gap, two right-angle prism inclined-planes, namely both are equal, and allow to there is error, usual limit error is less than 10
-4), form the adjustable clearance spatial optical switches of a sandwich structure.The invention has the beneficial effects as follows:
First, the index-matching fluid term of validity that current industry is produced 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, due to mobility and the filling capacity of liquid, switch control rule displacement accuracy can greatly reduce, according to inject index liquid number, even can meet switch displacement control overflow lower than micron-sized precision, and the dynamic range of command displacement very large (nanoscale ~ micron order, is greater than 30dB), this can increase the reliability of switch module undoubtedly;
Again, under space environment, the index liquid being adsorbed on prism surface can form smooth surface, and its smooth degree is far longer than the prism surface of machining, therefore there is more excellent reflection characteristic, the optical manufacturing requirement of prism surface can be reduced to a certain extent.
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 the inclined-plane of the 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---territory, transparent zone, 6---the territory, non-transparent zone on right-angle prism inclined-plane, 7---index-matching fluid.
Embodiment
All features disclosed 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.
Arbitrary feature disclosed in this instructions (comprising any accessory claim, summary and accompanying drawing), unless specifically stated otherwise, all can be replaced by other equivalences or the alternative features with similar object.That is, unless specifically stated otherwise, each feature is an example in a series of equivalence or similar characteristics.
Spaceborne space optical switch of the present invention is primarily of the right-angle prism of two refractive indexes equal (error is less than 10-4), be preferably structure size identical, so that processing, the index-matching fluid of equal with the refractive index of right-angle prism (error is less than 10-4), and Micro-displacement Driving, optical terminus web member form, its structural representation as shown in Figure 1:
First pre-service is carried out to two identical right-angle prisms (1 shown in Fig. 1 and 2):
4 right-angle surface of two right-angle prisms all need precise polished and plating anti-reflection film, and anti-reflection film should meeting spatial application demand, comprises reliability and transmitance demand;
Position corresponding for the inclined-plane of two right-angle prisms is defined as territory, transparent zone 5(as shown in Figure 2), the minimum edge in this territory, transparent zone 5 is apart from the incident beam diameter being greater than spaceborne optical terminus, optimum position is the center on inclined-plane, shape is circular, be convenient to processing realize, and surface micro-structure process is carried out to territory, transparent zone 5, photoetching can be adopted, corrosion, the methods such as ultra-precision machine tool cutting form the surface of micro-nano structure, thus 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, still a considerable amount of rate matching fluid of penetrating is had evenly to be attached to territory, transparent zone, each center when two right-angle prisms are separated,
The non-transparent zone territory 6(on two right-angle prism inclined-planes as shown in Figure 2, namely the fringe region do not overlapped with territory, transparent zone), also surface micro-structure process will be carried out, and doing surface chemical modification process (can adopt fluoride to modify, the methods such as silica polymer precipitation), make the surface in territory, non-transparent zone 6 for super oleophobic surface, namely 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 is separated, be extruded the index-matching fluid 7 expanding to fringe region and can shrink back central area under the effect of surface tension of liquid, and can not be spread in the right-angle surface of right-angle prism by switch gap.
After pre-service is carried out to the surface of two right-angle prisms, right-angle prism 1 as light input reference is fixedly connected with (namely right-angle prism 1 and spaceborne optical terminus are rigid connection) on spaceborne optical terminus by web member 4, its inclined-plane should with the incident beam optical axis of spaceborne optical terminus in angle of 45 degrees, to ensure that the polarization state of reflection and transmission light beam does not change, this is the basic demand of laser coherence communication terminal.
The right-angle prism 2 exported as optically-coupled is fixedly connected with micro-displacement driver 3 (being namely rigidly secured on micro-displacement driver 3), by controlling micro-displacement driver 3, right-angle prism 2 is being moved reciprocatingly perpendicular on the direction on its inclined-plane, kinematic accuracy reaches nanometer scale, and the stroke of motion reaches some tens of pm magnitude.When realizing, micro-displacement driver 3 can adopt piezoelectric ceramics PZT, and magnetostriction materials etc. can the materials and devices of controlled change its length, and should be all aerospace level product, with the reliability requirement of meeting spatial application.
The workflow of spaceborne space optical switch of the present invention is: one end of the web member 4 of switch is fixed on the outside installed surface determined, when two right-angle prism gaps enough large (as being greater than 3 wavelength), when index-matching fluid 7 on two right-angle prisms is in released state, evanescent wave cannot be coupled, all incident lights are all gone out by the slant reflection of right-angle prism 1, enter one of them optical branch 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, right-angle surface from right-angle prism 2 transmits by whole incident light, enter another optical branch 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 transmittance and reflectance.Subregion surface treatment is carried out to prism hypotenuse/facet surfaces simultaneously, realize the control to liquid fluidity.Photoswitch involved in the present invention has following advantage: angle pencil of ray is suitable for, and low aberration, the high speed of response, the break-make rejection ratio of light splitting branch road is high, can keep light polarization, not produce parasitic light, low to the accuracy requirement of micrometric displacement device, and reliability is high.The link budget of branch road can be followed the tracks of by significant increase capture terminal, strengthen acquisition probability, reduce capture time.
The present invention is not limited to aforesaid embodiment.The present invention expands to any new feature of disclosing in this manual or any combination newly, and the step of the arbitrary new method disclosed or process or any combination newly.
Claims (4)
1. a spaceborne space optical switch, 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 end is fixedly connected with the first right-angle prism (1), and one 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 is moving reciprocatingly perpendicular on the direction on its inclined-plane;
The correspondence position on the inclined-plane of the first right-angle prism (1) and the second right-angle prism (2) arranges territory, transparent zone (5), the surface contact angle in territory, described transparent zone (5) is less than 90 °, minimum edge is apart from the incident beam diameter being greater than spaceborne optical terminus, the surface in the territory, non-transparent zone (6) on inclined-plane is super oleophobic surface, and each right-angle surface is provided with anti-reflection film;
The refractive index of described first right-angle prism (1) and the second right-angle prism (2) is equal, territory, transparent zone (5) is equipped with the index-matching fluid (7) of corresponding right-angle prism refractive index, when micro-displacement driver (3) controls the second right-angle prism (2) close 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); When second right-angle prism (2) is away from the first right-angle prism (1), the index-matching fluid (7) of fusion is separated, and is adsorbed on territory, each transparent zone (5).
2. spatial optical switches as claimed in claim 1, it is characterized in that, territory, described transparent zone (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, territory, described transparent zone is circular, and its diameter is greater than the incident beam diameter of spaceborne optical terminus.
4. an implementation method for spaceborne space optical switch, is characterized in that, comprises the following steps:
S1: the first right-angle prism that refractive index is equal, the second right-angle prism carry out pre-service:
Precise polished and plating anti-reflection film is carried out to each right-angle surface;
Each inclined-plane opposite position is defined as territory, transparent zone, and the minimum edge in territory, described transparent zone apart from the incident beam diameter being greater than spaceborne optical terminus, and carries out surface micro-structure process to territory, transparent zone, makes its surface contact angle be less than 90 °;
Surface micro-structure process and chemical modification process are carried out to the territory, non-transparent zone on each inclined-plane, makes its surface for super oleophobic surface;
S2: the first right-angle prism is fixedly connected on spaceborne optical terminus, and angle at 45 ° with incident beam optical axis; Second right-angle prism is fixedly connected with micro-displacement driver, and the inclined-plane arranging two right-angle prisms relatively and there is gap, and in gap, inject the index-matching fluid of corresponding right-angle prism refractive index, control the second right-angle prism by micro-displacement driver moving reciprocatingly perpendicular on the direction on its inclined-plane, make separation and the fusion of index-matching fluid: during released state, the inclined-plane of the first right-angle prism reflects incident beam; During Fusion Strain, the first right-angle prism based on index-matching fluid, by incident beam coupling output to the 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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| CN103454729B true CN103454729B (en) | 2016-01-20 |
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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 | Variable-frequency laser coupler with non-linear optical crystal |
| 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 |
-
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 | Variable-frequency laser coupler with non-linear optical crystal |
| 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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