CN206195786U - Communication transmitter device that contains optics radome fairing suitable for machine carries photoelectricity platform - Google Patents
Communication transmitter device that contains optics radome fairing suitable for machine carries photoelectricity platform Download PDFInfo
- Publication number
- CN206195786U CN206195786U CN201621305308.8U CN201621305308U CN206195786U CN 206195786 U CN206195786 U CN 206195786U CN 201621305308 U CN201621305308 U CN 201621305308U CN 206195786 U CN206195786 U CN 206195786U
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- radome fairing
- communication
- angle
- transmitting antenna
- sphere
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Abstract
The utility model discloses communication transmitter device that contains optics radome fairing suitable for machine carries photoelectricity platform belongs to laser communication technical field, including launching fiber head, emit antenna, compensating lens and radome fairing. The laser signal that the launching fiber hair was penetrated at first incides to emit antenna, after the emit antenna plastic, passes through compensating lens and radome fairing in proper order, and transmission at last is to at a distance. The radome fairing is endocentric hemisphere in inside and outside surface or spherical radome fairing, and emit antenna can rotate around universal node to to the different position transmission communication light beam of half -angle in no longer than 54 cone angle. Emit antenna's universal node does not coincide with the centre of sphere on the inside and outside surface of radome fairing, nevertheless lies in the axis of radome fairing. Compensating lens is the meniscus of sphere for inside and outside surface. The utility model discloses use a slice sphere compensating lens, solved the radome fairing and leaded to communicating the light beam problem of far field angle of divergence grow in various degree appears when different emission angle, increased communication distance.
Description
Technical field
The utility model belongs to laser communication field, more particularly, to the communication launcher containing optical rectification cover.
Background technology
Airborne laser communication is an important development direction in laser communication field.Relative to ground surface platform, airborne platform
Not only have strict dimensional weight and power consumption requirements to load, and with translational speed it is fast, vibration is big, bad environments, installation side
The features such as formula is more special.
Airborne photoelectric platform front end is often coated with hemisphere or spherical optical rectification cover, is taking into account platform aeroperformance
Play a part of method, apparatus after protection simultaneously.In order to the target with diverse location carries out information mutual communication, airborne laser communication optics
Antenna can be rotated around its gimbal point, change beam emissions angle.When the gimbal point and the inside and outside table of concentric spherical radome fairing
When the centre of sphere in face is misaligned, radome fairing will introduce asymmetric aberration to the light beam of the non-zero angle of departure, so as to cause Communication ray beam spreading
Angle increase, become more to dissipate, cause can communication distance reduce, and Communication ray launch angle difference in the case of, beam divergence angle increase
Big effect is also different.Research both at home and abroad at present to be devoted to after the radome fairing caused to radome fairing under detection system image quality
Drop is compensated, and does not almost correct the side of the far-field divergence angle change caused by communication laser light beam from radome fairing inside outgoing
The relevant report of method.
Utility model content
Goal of the invention of the present utility model there is provided the hair of the communication containing optical rectification cover suitable for airborne photoelectric platform
Injection device, radome fairing can be corrected in the range of ± 54 ° of angles of departure and expands effect to the far-field divergence angle that communication launching light band comes.
In order to achieve the above object, the utility model proposes a kind of suitable for airborne photoelectric platform cover containing optical rectification
Communication launcher, it is characterized in that：Including launching fiber head, transmitting antenna, offset lens and radome fairing, in the propagation side of light
Upwards, the launching fiber head, transmitting antenna, offset lens and radome fairing are placed on airborne photoelectric platform in order successively, and
The axis of offset lens is conllinear with the axis of radome fairing, and wherein transmitting antenna has gimbal point, and gimbal point is located at
On the axis of radome fairing, transmitting antenna is rotated by gimbal point；
Wherein radome fairing is the concentric hemispherical in inner surface, outer surface or spherical radome fairing；
The wherein gimbal point of transmitting antenna is misaligned with the centre of sphere of rectification cover inner surface, outer surface.
Further, the clear aperature size of the transmitting antenna no more than radome fairing outer surface curvature radius three/
One.
Further, the angle of the transmitting antenna transmitting communication beam is less than or equal to 54 ° with the axis angle of radome fairing.
Further, the offset lens is falcate, and its inner surface and outer surface are sphere.
By above-mentioned design, the utility model can bring following beneficial effect：In the prior art, airborne laser is worked as
Communication transmitting light beam center of rotation not its photoelectric platform the concentric spherical optical rectification cover inner and outer surfaces centre of sphere situation
Under, radome fairing will give the influence that the light beam of different launch angles brings the different angles of divergence to increase.The utility model is in radome fairing
Front adds a piece of offset lens, and the negative power that radome fairing cover body causes is compensated.Offset lens is in ± 54 ° of angles of departure
The phenomenon that the communication beam angle of divergence that radome fairing causes expands is have modified in the range of degree well, than not plus before offset lens significantly
Increased communication distance.Offset lens simple structure, will not excessively take the confined space of engine room inside, lens front and rear surfaces face
Shape is sphere, and less, cost is relatively low for processing detection difficulty.
Brief description of the drawings
Fig. 1 is that the utility model is applied to the communication launcher containing optical rectification cover of airborne photoelectric platform in Communication ray
Schematic diagram when the beam angle of departure is 0 °.
Fig. 2 is that the utility model is applied to the communication launcher containing optical rectification cover of airborne photoelectric platform in Communication ray
Schematic diagram when the beam angle of departure is 54 °.
Fig. 3 is the schematic diagram for not adding 0 ° of light beam that transmitting antenna sends before offset lens to pass through radome fairing.
Fig. 4 is the schematic diagram for not adding 54 ° of light beams that transmitting antenna sends before offset lens to pass through radome fairing.
In figure：1- launching fibers head, 2- transmitting antennas, 3- offset lens, 4- radome fairings.
Specific embodiment
The utility model embodiment is elaborated below in conjunction with the accompanying drawings, machine is applied to the utility model proposes one kind
The communication launcher containing optical rectification cover of photoelectric platform is carried, as shown in figure 1, including launching fiber first 1, transmitting antenna 2, mending
Lens 3 and radome fairing 4 are repaid, wherein, it is prominent the utility model emphasis, the laser connected before not shown launching fiber first 1,
Modulator etc..
The laser signal of first 1 transmitting of launching fiber is incident to transmitting antenna 2, the shaping of emitted antenna 2, by launching light
Fine first 1 laser shaping sent is collimated light beam outgoing, sequentially passes through offset lens 3 and radome fairing 4, is finally launched at a distance.
The radome fairing 4 is the concentric spherical radome fairing of inner and outer surfaces, and outer surface curvature radius are 100mm, inner surface
Radius of curvature is 95mm, and thickness is 5mm, and material is H-K9, and refractive index is 1.517 at 1550nm.The maximum thang-kng of radome fairing 4
Bore is 160mm, and communication beam bore is 30mm, and wavelength is 1550nm.
The transmitting antenna 2 can be rotated around gimbal point, and the different azimuth in solid angle to half-angle no more than 54 ° is launched
Communication beam.Accompanying drawing 1 and accompanying drawing 2 are respectively the utility model in 0 ° of communication beam angle of departure and 54 ° of communication beam angles of departure
Schematic diagram.
The gimbal point of the transmitting antenna 2 is misaligned with the centre of sphere of the inner and outer surfaces of radome fairing 4, but positioned at radome fairing 4
On axis, away from the inner surface 64.5mm of radome fairing 4.
The clear aperture of the transmitting antenna 2 is 27mm, i.e., be 27mm from the communication beam width of the outgoing of transmitting antenna 2,
Not less than 1/3rd of the outer surface curvature radius of radome fairing 4.
In the present embodiment, transmitting antenna 2 is reduced to a perfect lens for ignoring mismachining tolerance, and launching fiber first 1 is sent out
The laser shaping for coming is collimated light beam outgoing.Now the far-field divergence angle from the light beam of the outgoing of transmitting antenna 2 is regarded as diffraction
Limiting angle, it is only relevant with diffraction bore and light beam wavelength.(referring to Jiang Huilin, Tong Shoufeng《FreeSpace Laser Communications Technique and system》,
National Defense Industry Press, p94)
The communication beam angle of divergence (full-shape) now can be calculated by equation below：
δ0=2.44 λ/D
=2.44 × 1550nm/27mm
≈140μrad
Wherein λ is light beam wavelength, and D is communication transmitting antenna bore.
The glass material H-ZF7 of the material selection Chengdu light company production of the offset lens 3, reflects at 1550nm
Rate is about 1.805, more than the refractive index (H-K9,1.517) of the material of radome fairing 4.The inner surface of the lens of offset lens 3 and outer surface
It is sphere.
Offset lens 3 is falcate, and its inner surface, outer surface curvature radius are respectively -257.025 and -243.740mm.
Its positive light coke for carrying, can offset the negative power that most radome fairings 4 bring.
The utility model is applied to the specific light of communication launcher each several part containing optical rectification cover of airborne photoelectric platform
Parameter is learned (to be emulated using the optical software ZEMAX of Focus companies of the U.S.) referring to table 1：
Table 1 is applied to the communication launcher detailed optical parameter containing optical rectification cover of airborne photoelectric platform
0 ° and 54 ° that transmitting antenna 2 sends when the present embodiment does not add offset lens 3 of light beam is respectively referring to Fig. 3 and Fig. 4
By the schematic diagram of radome fairing 4.
Table 2 for the present embodiment be not added with offset lens 3 when, the far-field divergence angle of communication beam under the different angles of departure.Due to swashing
Optical communication system typically uses single mode light source, and it is Gaussian beam that transmitting light beam can be approximately considered, thus far-field divergence angle data
(trace parameter setting is obtained by way of Gaussian beam trace：X, Y-direction half-size scale with a tight waist are 13.5mm, are girdled the waist and the 2nd face
Overlap, start surface：2, final surface：7).By table 2, introduced to light beam under the different angles of departure due to radome fairing 4
Asymmetric aberration is different, and the far-field divergence angle of light beam is also not quite similar, and increases with the increase of launch angle.Table 3 is this
The far-field divergence angle of communication beam under different angles of departure when embodiment adds offset lens 3.
When table 2 does not add offset lens 3, the far-field divergence angle of communication beam under the different angles of departure
When table 3 plus offset lens 3, the communication beam far-field divergence angle under the different angles of departure
| The angle of departure (°) | The far field beam angle of divergence (mrad) |
| 0 | 0.1883 |
| 20 | 0.2997 |
| 40 | 0.2730 |
| 54 | 0.3495 |
Comparison sheet 2, table 3 understand that the present embodiment have modified the light of radome fairing 4 well in the range of whole launch angle
The communication beam angle of divergence caused by focal power expands, and far-field divergence angle scope is narrowed down to from 4.7427mrad~5.8091mrad
188.3 μ rad~349.5 μ rad, can communication distance so as to improve.
Finally illustrate, above example is only used to illustrate the technical solution of the utility model and unrestricted, although logical
Cross the utility model is described with reference to preferred embodiment of the present utility model, but one of ordinary skill in the art
It should be appreciated that various changes can be made to it in the form and details, without departing from appended claims institute
The utility model of restriction.
Claims (4)
1. suitable for the communication launcher containing optical rectification cover of airborne photoelectric platform, it is characterized in that：Including launching fiber head
(1), transmitting antenna (2), offset lens (3) and radome fairing (4), in the direction of propagation of light, the launching fiber head (1), hair
Antenna (2), offset lens (3) and radome fairing (4) is penetrated to be placed on airborne photoelectric platform in order successively, and offset lens (3)
Axis is conllinear with the axis of radome fairing (4), and wherein transmitting antenna (2) is with gimbal point, and gimbal point is located at rectification
Cover on the axis of (4), transmitting antenna (2) is rotated by gimbal point；
Wherein radome fairing (4) be inner surface, the concentric hemispherical in outer surface or spherical radome fairing；
The wherein gimbal point of transmitting antenna (2) is misaligned with the centre of sphere of radome fairing (4) inner surface, outer surface.
2. the communication launcher containing optical rectification cover suitable for airborne photoelectric platform according to claim 1, it is special
Levying is：/ 3rd of the clear aperature size of the transmitting antenna (2) no more than radome fairing (4) outer surface curvature radius.
3. the communication launcher containing optical rectification cover suitable for airborne photoelectric platform according to claim 1, it is special
Levying is：The angle of transmitting antenna (2) the transmitting communication beam is less than or equal to 54 ° with the axis angle of radome fairing (4).
4. the communication launcher containing optical rectification cover suitable for airborne photoelectric platform according to claim 1, it is special
Levying is：The offset lens (3) is falcate, and its inner surface and outer surface are sphere.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621305308.8U CN206195786U (en) | 2016-12-01 | 2016-12-01 | Communication transmitter device that contains optics radome fairing suitable for machine carries photoelectricity platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621305308.8U CN206195786U (en) | 2016-12-01 | 2016-12-01 | Communication transmitter device that contains optics radome fairing suitable for machine carries photoelectricity platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206195786U true CN206195786U (en) | 2017-05-24 |
Family
ID=58723461
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621305308.8U Withdrawn - After Issue CN206195786U (en) | 2016-12-01 | 2016-12-01 | Communication transmitter device that contains optics radome fairing suitable for machine carries photoelectricity platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206195786U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106712853A (en) * | 2016-12-01 | 2017-05-24 | 长春理工大学 | Onboard photoelectric platform communication launcher with optical fairing |
-
2016
- 2016-12-01 CN CN201621305308.8U patent/CN206195786U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106712853A (en) * | 2016-12-01 | 2017-05-24 | 长春理工大学 | Onboard photoelectric platform communication launcher with optical fairing |
| CN106712853B (en) * | 2016-12-01 | 2023-03-31 | 长春理工大学 | Communication transmitting device with optical fairing applicable to airborne photoelectric platform |
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Legal Events
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170524 Effective date of abandoning: 20230331 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20170524 Effective date of abandoning: 20230331 |
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| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |