CN116366155B - Compact annular vision field satellite laser communication terminal - Google Patents
Compact annular vision field satellite laser communication terminal Download PDFInfo
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- CN116366155B CN116366155B CN202310642761.6A CN202310642761A CN116366155B CN 116366155 B CN116366155 B CN 116366155B CN 202310642761 A CN202310642761 A CN 202310642761A CN 116366155 B CN116366155 B CN 116366155B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/118—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
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Abstract
The invention discloses a compact annular vision satellite laser communication terminal, and belongs to the field of satellite laser communication. The system comprises an antenna scanning integrated module, a tail end light path and an electronics subsystem; the antenna scanning integrated module comprises a main reflecting mirror, a scanning reflecting mirror and a collimating mirror; the scanning reflector is provided with a central hole and is spatially positioned between the main reflector and the collimating mirror; the tail end light path comprises a fine sighting telescope, a beam splitter, a receiving light path, a transmitting light path and a plane mirror; the electronic subsystem comprises a system main control module, a photoelectric detector, a laser light source, a modulation and demodulation module and a motion control module; the optical signal received by the receiving optical path is connected with a photoelectric detector in the electronic subsystem in an optical fiber mode or a space optical path mode; the emission light path is connected with a laser light source in the electronics subsystem in an optical fiber mode or a space light path mode; the fine sighting telescope is connected with a motion control module in the electronics subsystem. The invention can effectively reduce the size and weight of the laser communication terminal.
Description
Technical Field
The invention belongs to the technical field of satellite laser communication, and particularly relates to a compact annular vision satellite laser communication terminal.
Background
Compared with the existing microwave communication technology, the satellite laser communication technology has the remarkable advantages of high data rate, good anti-interference and confidentiality and the like, and is an effective supplementary technical means for satellite communication in the future. At present, a plurality of satellite optical communication in-orbit tests are developed at home and abroad, military and commercial aerospace applications are being developed gradually, and satellite internet technology plays a role in international competition, so that the development trend is becoming clear.
In satellite internet applications, most of the solutions being implemented or already proposed use a communication constellation based on a laser communication scheme. Communication constellations typically consist of multiple satellites at the same orbital level, and there are complex constellations that are predominantly at one orbital level, but that include satellites at other orbital levels. In the communication links of the communication constellation, most of the communication links are between two satellites between the same orbital heights except for a small number of inter-satellite communication links which span different orbital heights. Satellite communication between the same orbit height can be further divided into co-orbit communication and off-orbit communication according to the condition that the orbit surfaces of the satellites at two sides of the communication link are consistent.
In the current satellite internet development process, in order to realize low-cost batch launching of multiple satellites with the same orbit height, a satellite stacking technology (stacking) becomes a mainstream launching means for satellite constellation construction. Satellite stacking technology, which mainly consists of combining a plurality of satellites together before transmission, has originated in the fifty years of the last century, has been developed and has been widely used in recent years by SpaceX corporation. The satellite stacking technology can maximize the payload, reduce the transmission cost and improve the transmission efficiency. Meanwhile, in order to fully utilize the stacking technology and increase the number of satellites in single transmission, the technology also puts severe requirements on the size and weight of the satellites, especially the height in the vertical direction, and the satellites are usually required to be designed in a flat mode, and the typical value of the height is only 100-200 mm.
The height of the laser communication satellite in the vertical direction is mainly limited by the optical path size of the laser communication terminal. The laser communication terminal can be divided into an electric control subsystem, a tail end light path, an optical antenna and a coarse sighting mechanism, wherein the optical antenna and the coarse sighting mechanism are main factors influencing the height dimension of the terminal. Optical antennas for laser communication generally include three types, refractive, on-axis and off-axis; whereas its coarse-aiming mechanism generally comprises the following: (1) In the theodolite form, a laser communication light path is arranged on a two-dimensional turntable, and the movement of the two-dimensional turntable realizes the view range of the theodolite in a hemispherical range (except for a zenith blind area); (2) periscope form; the two reflectors are used for scanning the light beams in two orthogonal degrees of freedom, so that the view of the hemispherical range can be realized; (3) The single pendulum mirror mode can realize annular vision by scanning in two orthogonal degrees of angular freedom by one mirror. For satellite communication between different orbit altitudes, the first and second modes of coarse aiming mechanism form are needed to provide a larger viewing range; for satellite communication between the same orbit heights, the annular viewing area can meet the application requirements, so that the three coarse aiming mechanism modes are all applied to the satellite laser communication. However, all the three coarse sighting mechanisms have the defects of large weight and high size, and in the height direction, besides the tail end optical path and the telescope optical path of laser communication, the coarse sighting mechanism also needs to occupy a larger size, so that the size of the whole optical-mechanical structure of the typical 60-80 mm caliber laser communication terminal optical path is difficult to compress to 100-200 mm.
In order to construct a satellite constellation based on laser communication at low cost, a satellite stacking technology is a necessary means, so for a laser communication terminal applying the satellite constellation, it is highly desirable to effectively compress the dimension of the laser communication terminal in the height direction based on the prior art, or to realize an optical caliber as large as possible under the condition of restricting the specified height direction, so as to improve the transmitting gain and receiving gain of laser communication, thereby achieving the purposes of improving the laser communication rate and increasing the communication distance.
Disclosure of Invention
The invention provides a compact annular vision field satellite laser communication terminal aiming at the requirement of the height dimension of a compressed laser communication terminal required by a satellite stacking technology, so that a scanning light path and a telescope light path are overlapped in the height direction under the condition that annular vision field (typical value is azimuth +/-180 degrees and pitching +/-10 degrees) can be realized, the light path height of the laser communication terminal can be greatly compressed, the dimension and the weight of the laser communication terminal can be effectively reduced, the number of single-shot satellites of the satellite stacking technology can be increased while the original laser communication emission gain and the receiving gain are maintained, the emission cost is greatly reduced, and the aim of improving the satellite constellation construction efficiency is fulfilled.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
a compact annular vision satellite laser communication terminal comprises an antenna scanning integrated module, a tail end light path and an electronics subsystem;
the antenna scanning integrated module comprises a main reflecting mirror, a scanning reflecting mirror and a collimating mirror; the scanning reflector is provided with a central hole and is spatially positioned between the main reflector and the collimating mirror;
the tail end light path comprises a fine sighting telescope, a beam splitter, a receiving light path, a transmitting light path and a plane mirror;
the electronic subsystem comprises a system main control module, a photoelectric detector, a laser light source, a modulation and demodulation module and a motion control module; the optical signal received by the receiving optical path is connected with a photoelectric detector in the electronic subsystem in an optical fiber mode or a space optical path mode; the emission light path is connected with a laser light source in the electronics subsystem in an optical fiber mode or a space light path mode; the fine sighting telescope is connected with a motion control module in the electronics subsystem.
Further, in the antenna scanning integrated module, the main reflector adopts an aspherical reflector, and the intersection point of the lens of the scanning reflector and the optical axis and the vertex of the main reflector meet the following conditions: axial distance between the twodIs that，/>Is the radius of curvature of the primary mirror; the main reflector, the collimating mirror and the scanning reflector satisfy the following mathematical relationship:
wherein D is the caliber of the laser communication terminal, < >>Is the radius of curvature of the primary mirror;
wherein->Is the focal length of the collimating mirror.
Further, the scanning reflector is a two-dimensional angle-adjustable reflector, the azimuth angle range is 360 degrees, and the angle is in the pitching directionIs +.>Corresponding beam deflection angleIn the range of->。
Further, the scanning mirror is angled in the pitch directionThe mechanical movement range of (2) isCorresponding beam deflection angle->In the range of->。
Further, the common optical axis of the main reflector and the collimating mirror is inclined, and the scanning reflector is inclined in the pitching directionIs +.>。
Further, the scanning mode of the scanning reflector adopts a mode of windingzThe scanning mirror is rotated around the axis or both the main mirror and the scanning mirror are integrally formedzThe shaft rotates.
Further, the central hole of the lens of the scanning reflector adopts a conical hole or a stepped hole, the hole size on the reflecting working surface is smaller than the back hole size, and the taper of the central holeD is the caliber of the laser communication terminal, < +.>Is the radius of curvature of the primary mirror; the axial distance d between the hole on the reflecting working surface and the vertex of the main reflector is +.>The method comprises the steps of carrying out a first treatment on the surface of the When the scanning reflector moves in two degrees of freedom in the azimuth angle direction and the pitch angle direction, the movement rotation shafts of the scanning reflector pass through the center of the hole at the reflection working surface of the lens of the scanning reflector.
Further, the collimating mirror is folded by adopting a plane reflecting mirror and then collimated; or a reflecting mirror with the functions of turning and collimation and in an off-axis aspheric form is adopted.
The beneficial effects of the invention are as follows:
the invention provides a compact annular vision satellite laser communication terminal, so that a scanning light path and a telescope light path are overlapped in the height direction under the condition that the annular vision can be realized, and the light path height of the compact annular vision satellite laser communication terminal can be greatly compressed. The effective effects of the method comprise the following aspects:
(1) The height of the laser communication terminal can be greatly reduced, the number of single-shot satellites based on the satellite stacking technology can be increased, the emission cost is reduced, and the satellite constellation construction efficiency is improved;
(2) Simultaneously, the size and the weight of the laser communication terminal load are effectively reduced, and the transmitting cost is further reduced;
(3) Compared with other coaxial reflection type optical antennas, the mode has extremely small central blocking ratio, and can improve the optics;
(4) The invention has the advantages of excellent stray light eliminating characteristic, can obviously reduce the interference of sunlight on communication, reduce the temporary avoidance angle in normal work and improve the usability of a laser communication link;
(5) Obviously, under the design constraint of size (especially height direction size) and weight, the invention can also be used for realizing the optical caliber as large as possible so as to improve the emission gain and the receiving gain of laser communication, thereby achieving the beneficial effects of improving the laser communication speed or increasing the communication distance.
Drawings
Fig. 1 is a laser communication terminal of the present invention;
FIG. 2 shows an antenna scanning integrated module in an inclined manner according to an embodiment of the present invention;
FIG. 3 is a schematic view of a lens aperture of a scanning mirror;
fig. 4 shows the reflected light path with the advance sight according to an embodiment of the present invention.
Detailed Description
The present invention is further illustrated in the following drawings and detailed description, which are to be understood as being merely illustrative of the invention and not limiting the scope of the invention.
As shown in fig. 1, a compact annular vision satellite laser communication terminal of the present embodiment includes an antenna scanning integrated module 1, a terminal optical path 2, and an electronics subsystem 3;
the antenna scanning integrated module 1 comprises a main reflecting mirror 101, a scanning reflecting mirror 102 and a collimating mirror 103;
the tail end light path 2 comprises a fine sighting telescope 201, a beam splitter 202, a receiving light path 203, a transmitting light path 204 and a plane mirror 205;
the electronics subsystem 3 comprises a system main control 301, a photoelectric detector 302, a laser light source 303, a modem module 304 and a motion control module 305; the scanning reflector is provided with a central hole and is spatially positioned between the main reflector and the collimating mirror; the optical signal received by the receiving optical path 203 is connected with the photoelectric detector 302 in the electronics subsystem 3 in an optical fiber mode; the emission light path 204 is connected with a laser light source 303 in the electronics subsystem 3 in an optical fiber mode; the fine mirror 201 is connected to a motion control module 305 in the electronics subsystem 3.
By adopting the above scheme, the cooperative working mode of each part of the compact annular vision satellite laser communication terminal of the embodiment is described as follows:
the system main control 301 in the electronic subsystem 3 controls the modulation and demodulation module 304, modulates the laser light source 303, outputs the laser light source 303 to be transmitted into the emission light path 204 in an optical fiber mode, forms parallel light beams after passing through the emission collimating lens, reflects the parallel light beams through the beam splitter 202, adjusts the angle of the light beams through the fine sighting telescope 201, further expands the light beams through the antenna scanning integrated module 1, deflects the light beams in a certain range, and directs to the laser communication terminal at the other side;
the laser beam carrying the modulated signal from the laser communication terminal on the other side is subjected to scanning withdrawal and beam shrinking through the antenna scanning integrated module 1, is subjected to angle adjustment through the fine sighting telescope 201, is transmitted through the beam splitter 202, enters the receiving optical path 203, is connected to the photoelectric detector 302 in the electronic subsystem 3 in an optical fiber mode, is converted into an electric signal by the photoelectric detector, is demodulated by the modulation and demodulation module 304, and is subjected to proper decoding and error correction and is output to the outside.
The embodiment adopts an antenna scanning integrated module to replace an optical antenna module and a light beam rough aiming module in the traditional laser communication terminal; in fig. 1, the receive optical path 203 and the transmit optical path 204 may be tiled in a horizontal plane (i.e., the x-y plane) without taking up additional height dimensions; the electronics subsystem 3 is connected to the other parts by means of cables and optical fibers, and can be placed in the satellite cabin without taking up additional height dimensions. Therefore, the height dimension of the optical path of the laser communication terminal of the present embodiment can be greatly reduced.
The antenna scanning integrated module 1 in the embodiment is composed of a main reflecting mirror 101, a scanning reflecting mirror 102 and a collimating mirror 103; the main reflecting mirror 101 and the collimating mirror 103 form a perfect optical subsystem for eliminating on-axis aberration, and the collimating mirror 103 can adopt a refraction form or a reflection form; the center of the scanning mirror 102 contains an aperture. The antenna scanning integrated module 1 realizes the functions of an optical antenna and a light beam rough aiming in a common laser communication terminal in an integrated mode, namely, on one hand, the beam shrinking/expanding function of a laser beam is realized, namely, a small-caliber laser beam in a terminal light path (such as a receiving light path 4 and a transmitting light path 5) and a large-caliber laser beam transmitted between the terminal are converted; on the other hand, the coarse aiming function of the large-caliber laser beam in a larger angle range is realized in a certain view range, the scanning function is realized on the emitted beam, and the scanning returning function is realized on the received beam. Compared with the mode of forming two parts of an independent optical antenna and a coarse sighting mechanism, the antenna scanning integrated module 1 greatly compresses the occupied space, especially the height size of a laser communication terminal.
The working principle of the antenna scanning integrated module is as follows: taking the emission light beam as an example, the small-caliber emission light beam is converged by the collimator 103, so that the converged small-size laser spot (in a non-collimation state) can pass through the central hole of the scanning reflector 102, and then is collimated by the main reflector 101 to form a large-caliber parallel light beam, and the parallel light beam is output in a direction approaching to a horizontal angle after being reflected by the scanning reflector 102 again. The received beam is similar to the transmitted beam but the path is reversed.
Example 2:
the difference between this embodiment and embodiment 1 is that in the antenna scanning integrated module in this embodiment, the main reflector adopts an aspherical reflector, and the intersection point of the lens of the scanning reflector and the optical axis and the vertex of the main reflector satisfy: axial distance between the twodIs that，/>Is the radius of curvature of the primary mirror; the main reflector, the collimating mirror and the scanning reflector satisfy the following mathematical relationship:
wherein D is the caliber of the laser communication terminal, < >>Is the radius of curvature of the primary mirror;
wherein->Is the focal length of the collimating mirror.
Example 3:
this embodiment differs from embodiment 1 in that,
the scanning mirror is a two-dimensional angle-adjustable mirror, and the scanning mirror 102 is a two-dimensional angle-adjustable mirror, and is a mirror that is adjustable in the azimuth direction (in fig. 1zDirection) can be rotated by a large angle and can be rotated in the pitch direction (in fig. 1, aroundyShaft) performs a small angle rotation. Both degrees of freedom of movement can be achieved by means of mechanical structures which are well known in the art. By the mode, the laser communication terminal can realize a larger light beam scanning range, and the view range is as follows:
azimuth direction: the antenna scanning integrated module 1 can realize 360-degree azimuth angle without dead angle, however, in practical application, the laser communication terminal is usually installed on the side face of a flat stacked-emission satellite, and at the moment, the azimuth angle can at least coverIs provided for the angular range of (a).
Elevation direction the elevation direction range of the antenna scanning integrated module 1 depends on the mechanical angle of its elevation axisThe smaller the maximum value thereof, the more advantageous is the height dimension of the compressed antenna scanning integrated module 1. A typical value of the mechanical range of motion is, while avoiding interference between the scanning mirror 102 and the collimator mirror 103The corresponding beam deflection angle range is +.>. For inter-satellite communication between generally the same orbital heights, the typical value of the beam deflection angle range is that the requirement corresponds to the mechanical range of motion: />。
The azimuth axis scanning method of 1 in the antenna scanning integrated module in this embodiment can be adopted by windingzIn the method of rotating the scanning mirror 102 about the axis, both the main mirror 101 and the scanning mirror 102 may be wound as a wholezThe shaft rotates;
the antenna scanning integrated module 1 can adopt an inclined angle mode, so that the height dimension is further compressed; as shown in fig. 2, in which the angle of the pitch axis of the scanning mirror 102 is the same in the horizontal outgoing state of the light beamHas a value of less than 45 DEG, which typically ranges from +.>The optical path height can be further compressed. In this way, the scanning direction of the coarse scanning is not parallel to the satellite coordinate system x-y-z, its scanning angle requires the electronic control subsystem 3 to perform conversion, and to some extent, the effective scanning range in its azimuth direction needs to be sacrificed.
Example 4:
in this embodiment, the center of the reflecting surface of the scanning mirror has a center hole 1021, which is a tapered hole, or a stepped hole, and the hole size on the reflecting working surface is smaller than the back hole size, and the taper of the center holeD is the caliber of the laser communication terminal, < +.>Is the radius of curvature of the primary mirror; axial distance between the aperture in the reflective working surface and the apex of the primary mirrordIs->When the scanning reflector assembly moves in two degrees of freedom in the azimuth direction and the pitch direction, the movement rotation axis of the scanning reflector assembly passes through or approaches to the center of a hole at the reflection working surface of a lens passing through the scanning reflector assembly; in the lens processing process of the scanning reflector, processing technology such as ultrasonic wave can be adopted, and an inclined conical hole 1022 is processed at the back of the scanning reflector, so that the diameter of the hole on the reflecting surface of the scanning reflector (typically, the diameter can be 0.5 mm-1.5 mm) is reduced when the working beam can normally penetrate through the lens;
in this way, there are the following advantages: (1) The central blocking is greatly reduced, the advantages of light weight and small volume of the coaxial optical antenna are fully utilized, the defect of large central blocking is overcome, and the energy utilization rate is improved; (2) The stray light performance (as shown in fig. 4, the light beam deviated from the working angle by a certain angle cannot enter the subsequent light path through the central hole) is remarkably improved, the interference of sunlight on communication can be remarkably reduced, the temporary avoidance angle in normal working is reduced, and the usability of the laser communication link is improved.
Example 5:
in this embodiment, the collimating mirror 103 is turned by a plane mirror and then collimated; or a reflecting mirror with the functions of turning and collimation and in an off-axis aspheric form is adopted.
Furthermore, its end optical path 2 may be complicated on the present basis, including but not limited to: the reflection mirror is added to realize deflection, the fine sighting telescope is added, the advance sighting telescope is added, the polarization optical element is added, and the optical filter is added; and adding a beacon light path, adding a tracking imaging light path, etc. Depending on the actual field angle requirements of the individual branches of their end beam paths 2, this may preferably correspond to the size of the reflecting surface openings in the scanning mirror 102.
Specific test cases:
taking a certain 80mm caliber space-based laser communication terminal developed by the company as a reference, a typical implementation scheme is as follows:
the effective optical caliber of the laser communication terminal is 80mm, the angular magnification of the antenna scanning integrated module 1 is 10x, the main reflecting mirror 101 is a concave paraboloid, R= -192mm and k= -1, the collimating mirror 103 is a refractive lens group, the focal length is 9.6mm, and the caliber is 8mm;
the lens of the scanning reflector 102 is made of fused quartz, the effective caliber is elliptic, the short axis is 81mm, the long axis is 120mm, the scanning range of the azimuth axis is-120 to +120 degrees, the mechanical scanning range of the pitching axis is 40 to 47 degrees, and the corresponding optical pitching scanning range is-4 to +10 degrees;
the maximum field angle of the tail end light path 2 is 1mrad, the size of the small hole of the corresponding required scanning reflector 102 is not less than 0.096mm, the size of the small hole actually processed is 1+/-0.05 mm, and the corresponding central blocking ratio is slightly more than 1%;
the laser emission of the terminal adopts a single-mode fiber, the core diameter is 9um, the NA0.14 is of the model Corning SMF28+. The adopted emission wavelength is 1550nm;
taking a plurality of model models developed by the company as an example, under the condition that the effective optical caliber is 80mm, the heights of the laser communication terminals in the form of theodolite and periscope are respectively about 305mm and 315mm, the height of the laser communication terminal in the form of single pendulum mirror is about 245mm, and the height of the laser communication terminal is reduced to 167mm based on the laser communication terminal. In terms of weight, only the optical machine part of the laser communication terminal is considered, a single swing mirror structure (the weight of the single swing mirror structure is superior to that of theodolite and periscope) is taken as an example, the typical weight of the single swing mirror structure is about 8.7kg based on an off-axis optical antenna, and if the typical weight of the single swing mirror structure is 7.4kg based on an on-axis optical antenna, the corresponding weight of the laser communication terminal adopting the technical scheme can be reduced to 6.3kg, and the weight is obviously reduced. Meanwhile, the center blocking ratio of the single-pendulum mirror structure based on the coaxial optical antenna is typically 10% -20%, and the center blocking ratio of the laser communication terminal in the technical scheme is typically 0.5% -2%, so that the single-pendulum mirror structure is remarkably improved. By means of simulation of stray light caused by sunlight incidence, the solar evasion angle is reduced from 2.4 degrees to 0.9 degrees, and comparison shows that the technical scheme has obvious technical advantages compared with the laser communication terminal optical path modes in other modes under the condition that the effective optical caliber is the same, the height dimension of the technical scheme is obviously reduced, the weight is reduced, the central blocking ratio is effectively controlled, and the solar evasion angle is reduced.
It should be noted that the foregoing merely illustrates the technical idea of the present invention and is not intended to limit the scope of the present invention, and that a person skilled in the art may make several improvements and modifications without departing from the principles of the present invention, which fall within the scope of the claims of the present invention.
Claims (6)
1. The compact annular vision satellite laser communication terminal is characterized by comprising an antenna scanning integrated module, a tail end light path and an electronics subsystem;
the antenna scanning integrated module comprises a main reflecting mirror, a scanning reflecting mirror and a collimating mirror; the lens of the scanning reflector is provided with a central hole and is spatially positioned between the main reflector and the collimating mirror;
the tail end light path comprises a fine sighting telescope, a beam splitter, a receiving light path, a transmitting light path and a plane mirror;
the electronic subsystem comprises a system main control module, a photoelectric detector, a laser light source, a modulation and demodulation module and a motion control module; the optical signal received by the receiving optical path is connected with a photoelectric detector in the electronic subsystem in an optical fiber mode or a space optical path mode; the emission light path is connected with a laser light source in the electronics subsystem in an optical fiber mode or a space light path mode; the fine sighting telescope is connected with a motion control module in the electronics subsystem;
in the antenna scanning integrated module, the main reflector adopts an aspherical reflector, and the intersection point of the lens of the scanning reflector and the optical axis and the vertex of the main reflector meet the following conditions: the axial distance d1 between the two is 0.40 r pm ≤d1≤0.60*R pm ，R pm Is the radius of curvature of the primary mirror; the main reflector, the collimating mirror and the scanning reflector satisfy the following mathematical relationship:
1.6*D≤R pm 3*D, wherein D is the caliber of the laser communication terminal, R pm Is the radius of curvature of the primary mirror;
0.033*R pm ≤f c ≤0.1*R pm wherein f c Is the focal length of the collimating mirror;
the central hole of the lens of the scanning reflector adopts a conical hole or a stepped hole, the hole size on the reflecting working surface is smaller than the back hole size, and the taper of the central hole is 1.4 x D/R pm ≤t≤2.6*D/R pm D is the caliber of the laser communication terminal, R pm Is the radius of curvature of the primary mirror; the axial distance d2 between the aperture on the reflecting working surface and the apex of the main reflector is 0.47 r pm ≤d2≤0.53*R pm The method comprises the steps of carrying out a first treatment on the surface of the When the scanning reflector moves in two degrees of freedom in the azimuth angle direction and the pitch angle direction, the movement rotation shafts of the scanning reflector pass through the center of the hole at the reflection working surface of the lens of the scanning reflector.
2. The compact annular view satellite laser communication terminal as set forth in claim 1, wherein said scanning mirror is a two-dimensional angularly adjustable mirror, adjustable in azimuth angle range of 360 degrees, and adjustable in elevation direction angle θ yM The mechanical movement range of the device is 35 degrees less than or equal to theta yM Less than or equal to +55°, corresponding to a beam deflection angle θ yO In the range of-20 DEG < theta yO ＜+20°。
3. A compact annular vision satellite laser communication terminal as defined in claim 2, wherein saidAngle θ 'of the scanning mirror in the pitch direction' yM The mechanical movement range of (2) is 44.5 DEG < theta' yM < +40°, corresponding to the beam deflection angle θ' yO The range is-1 DEG to theta%' yO ≤+10°。
4. A compact annular view satellite laser communication terminal according to claim 2, wherein the common optical axis of the primary mirror and the collimator mirror is tilted, and the scanning mirror is tilted at an angle θ in the pitch direction yM The mechanical movement range of the device is 25 degrees less than or equal to theta yM ≤35°。
5. The compact annular view satellite laser communication terminal according to claim 2, wherein the scanning mode of the scanning mirror is rotated about the z-axis by rotating the scanning mirror about the z-axis or by rotating both the main mirror and the scanning mirror as a whole.
6. The compact annular view satellite laser communication terminal according to claim 1 or 2, wherein the collimating mirror is turned by a plane mirror before being collimated; or a reflecting mirror with the functions of turning and collimation and in an off-axis aspheric form is adopted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310642761.6A CN116366155B (en) | 2023-06-01 | 2023-06-01 | Compact annular vision field satellite laser communication terminal |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310642761.6A CN116366155B (en) | 2023-06-01 | 2023-06-01 | Compact annular vision field satellite laser communication terminal |
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| CN116366155A CN116366155A (en) | 2023-06-30 |
| CN116366155B true CN116366155B (en) | 2023-09-15 |
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Denomination of invention: A compact circular field of view satellite laser communication terminal Granted publication date: 20230915 Pledgee: Industrial and Commercial Bank of China Limited Nanjing Science and technology sub branch Pledgor: NANJING INTANE OPTICS ENGINEERING Co.,Ltd. Registration number: Y2024980002850 |