CN112130305A - Satellite tracking and aiming system and wide-angle pointing method thereof - Google Patents
Satellite tracking and aiming system and wide-angle pointing method thereof Download PDFInfo
- Publication number
- CN112130305A CN112130305A CN202010960633.2A CN202010960633A CN112130305A CN 112130305 A CN112130305 A CN 112130305A CN 202010960633 A CN202010960633 A CN 202010960633A CN 112130305 A CN112130305 A CN 112130305A
- Authority
- CN
- China
- Prior art keywords
- satellite
- light source
- electro
- incident light
- deflection
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B17/00—Systems with reflecting surfaces, with or without refracting elements
- G02B17/02—Catoptric systems, e.g. image erecting and reversing system
- G02B17/06—Catoptric systems, e.g. image erecting and reversing system using mirrors only, i.e. having only one curved mirror
-
- G—PHYSICS
- G02—OPTICS
- G02F—OPTICAL DEVICES OR ARRANGEMENTS FOR THE CONTROL OF LIGHT BY MODIFICATION OF THE OPTICAL PROPERTIES OF THE MEDIA OF THE ELEMENTS INVOLVED THEREIN; NON-LINEAR OPTICS; FREQUENCY-CHANGING OF LIGHT; OPTICAL LOGIC ELEMENTS; OPTICAL ANALOGUE/DIGITAL CONVERTERS
- G02F1/00—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics
- G02F1/29—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the position or the direction of light beams, i.e. deflection
Abstract
The invention provides a satellite tracking and aiming system and a wide-angle pointing method thereof, wherein the satellite tracking and aiming system comprises a first satellite, a second satellite, a light source transmitting end and an emergent laser capturing device, and the satellite tracking and aiming system comprises: the reflecting device is a concave reflecting mirror; the light source emission end comprises an incident light source and an electro-optical deflection crystal assembly, wherein the incident light source is positioned on the optical axis of the concave reflector; the light source transmitting end and the reflecting device are arranged on an installation platform of the first satellite; the emergent laser capturing device is arranged on a second satellite; laser signals emitted by the light source emitting end are reflected on the surface of the reflecting device and then enter the emergent laser capturing device; the incident light source emits parallel light, when the incident light is not deflected, the incident light is incident along the optical axis of the concave reflector, and when the incident light beam is deflected, the deflection angle of the reflected light beam is as follows:
the initial deflection angle of an incident beam is rho, the curvature of the reflection point of the curved surface reflector is rho, the electro-optic deflection crystal is positioned on the optical axis, and L is the distance between the electro-optic deflection crystal and the concave surface reflector.
Description
Technical Field
The invention relates to the field of laser communication, in particular to a satellite tracking and aiming system and a wide-angle pointing method thereof.
Background
Compared with the existing radio frequency communication, the satellite laser communication has the advantages of high communication rate, large communication capacity, low power consumption, small size, light weight, interference resistance, high confidentiality and the like, is considered to be the best scheme for realizing the inter-satellite high-code-rate communication, and has been widely regarded in the military and civil fields. However, the relative position between the satellites is not fixed during satellite laser communication, and the relative movement speed between the terminals is also high, so that a satellite tracking system needs to be configured. The existing satellite tracking and aiming system adopts satellite attitude adjustment or an L-shaped arm theodolite or a rotating double-prism structure, and the rotation of the satellite tracking and aiming system is controlled by a stepping motor, so that the rotation of the moving part of the whole terminal is realized (such as an SILEX system in the European space). The system needs a plurality of beam deflection mirrors, a plurality of other optical devices, a turntable and other equipment to finish beam pointing control together, so that the whole system is quite complex, the volume and the quality are increased, the reliability is reduced, and the system is not beneficial to being used on the satellite.
Disclosure of Invention
The invention solves the problems that the existing satellite tracking and aiming system has complex structure and large mass and is not beneficial to being used on the satellite; to solve the problems, the invention provides a satellite tracking and aiming system and a wide-angle pointing method thereof.
The invention provides a satellite tracking and aiming system, which comprises: the device comprises a first satellite, a second satellite, a light source transmitting end and an emergent laser capturing device; further comprising: the reflecting device is a concave reflecting mirror; the light source emission end comprises an incident light source and an electro-optical deflection crystal assembly; the light source transmitting end and the reflecting device are arranged on an installation platform of the first satellite; the emergent laser capturing device is arranged on a second satellite; and the laser signal emitted by the light source emitting end is reflected on the surface of the reflecting device and then enters the emergent laser capturing device.
Further, the incident light source emits parallel light, when the incident light is not deflected, the incident light is incident along the optical axis of the concave reflecting mirror, and when the incident light beam is deflected, the deflection angle of the reflected light beam is as follows:
wherein the content of the first and second substances,
the initial deflection angle of an incident beam is rho, the curvature of the reflection point of the curved surface reflector is rho, the electro-optic deflection crystal is positioned on the optical axis, and L is the distance between the electro-optic deflection crystal and the concave surface reflector.
Further, rho L is more than or equal to 10 and less than or equal to 100.
Further, the electro-optical deflection crystal is any one of gallium arsenide, cadmium telluride or magnesium-doped lithium niobate crystal.
Further, the electro-optical deflection crystal is mounted to a movable device having a degree of freedom to move in a direction perpendicular to the optical axis.
Furthermore, the incident light source emits parallel light, when the incident light is not deflected, the incident light is incident in parallel to the optical axis of the concave reflecting mirror, and when the incident light beam is deflected, the deflection angle of the reflected light beam is
Wherein the content of the first and second substances,
the initial deflection angle of an incident beam is L, the projection of the distance between the electro-optical deflection crystal and the concave mirror in the optical axis direction is d, the distance of the electro-optical deflection crystal moving in the direction vertical to the optical axis is d, and r is the radius of the concave mirror.
The invention also provides a wide-angle pointing method of the satellite tracking and aiming system, which comprises the following steps: step one, calculating an azimuth angle of an emergent laser capture device relative to a light source transmitting end; and secondly, adjusting any one or two of the initial deflection angle of the incident light beam and the position of the electro-optical deflection crystal perpendicular to the optical axis direction of the concave reflector, so that the deflection angle of the reflected light beam is larger than or equal to the azimuth angle.
The advantages of the invention include:
during laser communication, laser emitted by a light source emitting end is incident on the concave reflector, and according to the Snell law, the reflection angle of an emergent light beam is the same as the incident angle of an incident light beam; the angle of incidence and the angle of reflection will vary with the position or curvature of the reflecting point on the curved mirror. The radius of curvature of the mirror can be set as appropriate according to the need. Under the condition that the relative position of the satellite is determined, the laser pointing in a large range can be realized by adjusting the position of incident laser; meanwhile, the concave mirror is selected to realize the convergence pointing of the laser beams, reduce the size of a light spot during long-distance transmission and increase the transmission distance of laser communication.
The laser communication pointing device does not need a large turntable or a reflecting plate with a precise design position to perform multiple reflections, and has a simple structure; the pointing of the whole sky field can be realized only by finely adjusting the incident angle of the incident laser, the complexity of the satellite-borne laser communication equipment is greatly simplified, and support is provided for realizing miniaturized remote satellite-borne laser communication.
Drawings
FIG. 1 is a schematic diagram of a wide angle pointing method of a satellite tracking system in accordance with the present invention;
fig. 2 is a schematic structural diagram of a satellite tracking system according to a first embodiment of the present invention;
FIG. 3 is a schematic diagram illustrating the direction of movement of an electro-optic deflection crystal of a satellite tracking system according to a second embodiment of the present invention;
FIG. 4 is a schematic diagram of a satellite tracking system according to a second embodiment of the present invention;
fig. 5 is an installation diagram of a satellite tracking system according to an embodiment of the present invention.
Detailed Description
The spirit and substance of the present invention will be further described below with reference to the accompanying drawings and examples.
As shown in FIG. 1, in the satellite-borne laser communication wide-angle pointing method of the satellite tracking system provided by the invention, the incident beam is controlled to generate a tiny deflection angle
The light enters a curved mirror with radius r, curvature ρ (ρ 1/r) and center C. The incident angle at the incident point P is theta, and the deflection angle of the emergent light beam PP 'relative to the initial incident light ray OO' is determined according to the law of reflection
When the incident angle is changed
In a very small situation
Wherein L is the distance from the deflection point of the laser light source to the fixed point of the curved surface reflector. It can be seen that, in the case where the incident deflection angle is small, the magnitude of the exit deflection angle is mainly determined by the changes in the curvatures ρ and L of the concave mirrors.
When rho and L are increased, the emergent deflection angle is relatively large, and the large-angle deflection of the laser ray can be obtained by designing a concave mirror at a small deflection angle in principle, but if rho is large, the radius of the corresponding concave mirror is reduced, and the processing difficulty is high; meanwhile, laser communication has light spots with a certain size when information is transmitted, and the fact that the deflection angles of different areas of the light spots are consistent can be guaranteed only by the aid of a large enough reflection surface on the concave reflecting mirror, so that the curvature of the concave reflecting mirror cannot be too large. On the other hand, the satellite has a limited size structure, limiting the size of L. In consideration of the system implementation, the rho L can be set between 10 and 100, so that when the incident deflection angle is 1 degree at most, the system emergent deflection angle can reach a deflection angle of 100 degrees, and a large enough area can be basically covered, thereby solving the bottleneck problem that the coverage area of the satellite-borne laser communication equipment is not large enough. In addition, the large-range laser communication technology does not need mechanical parts such as a swing mirror and a rotary table, and the system is simple and reliable and is particularly suitable for being used in space equipment such as satellites.
Fig. 2 is a schematic structural diagram of a satellite tracking system according to a first embodiment of the present invention, and fig. 5 is a schematic installation diagram of the satellite tracking system according to the first embodiment of the present invention. With reference to fig. 5 and fig. 2, a satellite tracking system provided in a first embodiment includes: a first satellite 105, a second satellite (not shown), a light source emitting end 103, an emergent laser capturing device (not shown); further comprising: a reflecting device which is a concave reflecting mirror 102; the light source emitting end 103 comprises a combination of an incident light source and the electro-optical deflection crystal 101; the light source transmitting end and the reflecting device are arranged on an installation platform of the first satellite; the emergent laser capturing device is arranged on a second satellite; and the laser signal emitted by the light source emitting end is reflected on the surface of the reflecting device and then enters the emergent laser capturing device.
The wide angle pointing device disclosed by the embodiments of the present invention has advantages over the features of conventional laser communication pointing devices. One advantage relates to the size, mass and power consumption of the inventive system. For these features, the disclosed wide-angle pointing device is only less than 10cm in size, less than 0.5kg in mass, and less than 0.5W in power consumption. The corresponding conventional laser communication pointing system is generally 10cm & 10cm in size, the mass is more than 5kg, and the power consumption is more than 20W. A second advantage relates to pointing orientation of the system, the disclosed wide-angle pointing system can be pointed at orientations up to 90 deg. or more, whereas conventional laser communication pointing systems are typically pointed at orientations less than 60 deg.. A third advantage relates to pointing speed, the pointing time of the disclosed wide-angle pointing device is less than 10s, whereas conventional laser communication pointing systems typically point for times greater than 1 minute. The fourth advantage relates to the service life of the system, in the space environment, the service life of the turntable is generally 50000 times of rotation, and the electro-optical crystal can be loaded with electric signals for more than 100000 times.
With continued reference to fig. 1, the laser light is deflected by an electro-optical deflection crystal 101 after being corrected and shaped after being generated, and the electro-optical deflection crystal 101 may be any one of gallium arsenide, cadmium telluride, or magnesium-doped lithium niobate crystals. The concave mirror 102 is a spherical mirror with radius r and curvature p. The optical axis of the laser is OO ', the distance between the electro-optical deflection crystal on the optical axis OO' and the spherical reflector is L after passing through the spherical center C of the spherical reflector. When a voltage is applied to the electro-optical deflection crystal 101, the laser light is deflected by the electro-optical deflection crystal 101. As the voltage applied to the electro-optic deflection crystal 101 increases, the incident deflection angle
The corresponding exit deflection angle theta is increased along with the increase of the total exit deflection angle theta, so that the aim of large exit angle deflection angle is fulfilled. According to the formula hereinbefore
An appropriate deflection angle can be selected according to the distance and the direction between the concave reflector and the target satellite, and the curvature radius of the concave reflector and the distance between the deflection position and the curved reflector are designed according to actual conditions. In particular, in this embodiment, the first satellite and the second satellite may be combined according to the structure and layout of the satellite platformSetting the curvature radius of the concave reflector and the distance between the deflection position and the curved reflector, and then adjusting the voltage on the electro-optic deflection crystal 101 according to the relative positions of the first satellite and the second satellite in the communication process so as to adjust the incident deflection angle
Further adjusting deflection angle to realize wide-angle directional communication.
In a second embodiment of the invention, the electro-optical deflection crystal 101 is on a movable device, and with combined reference to fig. 3 and 4, the electro-optical deflection crystal is movable along the optical axis OO 'and also in the Oy direction or the Oz direction perpendicular to the optical axis OO'. The mirror 102 remains fixed. When deflection crystal 101 is moved along OO', the distance L will change, causing the laser beam deflection angle γ to change. The rate of change of the beam deflection angle can be adjusted by adjusting the relative position of the deflection crystal 101 with respect to the curved mirror 102. When the deflection crystal 101 is moved in the Oy direction or Oz direction, as shown in FIG. 4, when the crystal movement distance is d, if the crystal is not powered, the laser deflection angle is
If power is applied to the crystal, the laser beam passing through the crystal is
The system deflection angle at this time
As can be seen from figure 4 of the drawings,
wherein s is OdThe length of the C is the length of the C,
it can be derived that:
namely, a large exit deflection angle can be obtained by adjusting the crystal movement distance and the entrance deflection angle.
The concave reflector 102 may be configured with concave spherical surfaces with different radii of curvature, so that different incident/deflection angles can be selected to obtain different deflection change rates.
The invention also provides a satellite-borne laser communication wide-angle pointing method adopting the satellite tracking and aiming system.
In conclusion, the invention is used in the field of satellite-borne laser communication and realizes large-range directional communication. The satellite tracking and aiming system and the wide-angle pointing method thereof change the micro deflection or displacement of the emergent laser beam, and the emergent laser beam is incident to different positions of a space curved surface to form different incidence angles. According to Snell's law, the exit angle of the exiting beam and the incident angle of the incident beam are the same and vary continuously together. The size of the reflection angle can be adjusted by designing and adjusting the curvature of the space curved surface and the relative position of the space curved surface and incident light, so that large-range directional laser communication is realized. The laser pointing range is related to system configuration parameters. The emergent laser can deflect to other directions except the direction shielded by the satellite, and the spherical transmission of 2 pi at the maximum can be realized without the need of satellite attitude adjustment. The facula will grow in the laser transmission process, through concave mirror 104 convergence, can realize the facula of certain degree and reduce, in long distance laser communication, the receiving terminal will catch less laser facula, acquires higher communication SNR.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (5)
1. A satellite tracking system, comprising:
a first satellite;
a second satellite;
a reflecting means comprising a concave mirror;
the light source emitting end comprises an incident light source and an electro-optic deflection crystal assembly, wherein the incident light source is positioned on an optical axis of the concave reflector, the light source emitting end and the reflecting device are installed on an installation platform of a first satellite, a laser signal emitted by the light source emitting end is reflected on the surface of the reflecting device and then enters the emergent laser capturing device, the incident light source emits parallel light, when the incident light is not deflected, the incident light enters along the optical axis of the concave reflector, and when the incident light beam is deflected, the deflection angle of the reflected light beam is as follows:
wherein the content of the first and second substances,
the initial deflection angle of an incident beam is rho, the curvature of the reflection point of the curved surface reflector is rho, the electro-optic deflection crystal is positioned on an optical axis, L is the distance between the electro-optic deflection crystal and the concave surface reflector, and the rho L is more than or equal to 10 and less than or equal to 100; and
and an outgoing laser capturing device attached to the second satellite.
2. The satellite tracking system according to claim 1, wherein the electro-optic deflection crystal is any one of gallium arsenide, cadmium telluride, or magnesium doped lithium niobate crystals.
3. The satellite tracking system according to claim 1, wherein the electro-optic deflection crystal is mounted to a movable device having freedom to move in a direction perpendicular to the optical axis.
4. The satellite tracking system of claim 3, wherein the incident light source emits parallel light, the incident light beam, when undeflected, is incident parallel to the optical axis of the concave mirror, and the incident light beam, when deflected, is deflected at a deflection angle of the reflected light beam,
wherein the content of the first and second substances,
the initial deflection angle of an incident beam is L, the projection of the distance between the electro-optical deflection crystal and the concave mirror in the optical axis direction is d, the distance of the electro-optical deflection crystal moving in the direction vertical to the optical axis is d, and r is the radius of the concave mirror.
5. A wide-angle pointing method using the satellite tracking system provided in any one of claims 1 to 4, comprising: step one, calculating an azimuth angle of an emergent laser capture device relative to a light source transmitting end; and secondly, adjusting any one or two of the initial deflection angle of the incident light beam and the position of the electro-optical deflection crystal perpendicular to the optical axis direction of the concave reflector, so that the deflection angle of the reflected light beam is larger than or equal to the azimuth angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010960633.2A CN112130305A (en) | 2017-05-26 | 2017-05-26 | Satellite tracking and aiming system and wide-angle pointing method thereof |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710383338.3A CN106990516B (en) | 2017-05-26 | 2017-05-26 | Satellite-borne laser communication wide-angle pointing device |
| CN202010960633.2A CN112130305A (en) | 2017-05-26 | 2017-05-26 | Satellite tracking and aiming system and wide-angle pointing method thereof |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710383338.3A Division CN106990516B (en) | 2017-05-26 | 2017-05-26 | Satellite-borne laser communication wide-angle pointing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112130305A true CN112130305A (en) | 2020-12-25 |
Family
ID=59420389
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010960633.2A Pending CN112130305A (en) | 2017-05-26 | 2017-05-26 | Satellite tracking and aiming system and wide-angle pointing method thereof |
| CN201710383338.3A Active CN106990516B (en) | 2017-05-26 | 2017-05-26 | Satellite-borne laser communication wide-angle pointing device |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710383338.3A Active CN106990516B (en) | 2017-05-26 | 2017-05-26 | Satellite-borne laser communication wide-angle pointing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN112130305A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108390715A (en) * | 2018-04-20 | 2018-08-10 | 宁波光舟通信技术有限公司 | A kind of terminal layout structure of laser beam communications satellite |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1422447A (en) * | 2000-04-14 | 2003-06-04 | 威罗门飞行公司 | Mobile radio communication system |
| CN101309112A (en) * | 2008-07-04 | 2008-11-19 | 中国科学院上海光学精密机械研究所 | Bi-terminal bidirectional distant transmission simulation of satellite laser communication and gourd detection apparatus |
| CN101620316A (en) * | 2009-01-19 | 2010-01-06 | 深圳大学 | Optical deflection accelerator |
| CN101625080A (en) * | 2009-07-22 | 2010-01-13 | 深圳大学 | Strobe point light stroboflash generator with extremely high frequency |
| CN102576925A (en) * | 2007-03-16 | 2012-07-11 | 移动卫星有限公司 | A vehicle mounted antenna and methods for transmitting and/or receiving signals |
| CN103078678A (en) * | 2012-12-29 | 2013-05-01 | 中国航天科技集团公司第五研究院第五一三研究所 | Satellite-borne laser wireless energy transmission system |
| CN105867435A (en) * | 2016-05-11 | 2016-08-17 | 西北工业大学 | Smooth and steady pointing maneuvering control method for satellite optical load |
| CN106025551A (en) * | 2016-01-18 | 2016-10-12 | 贵港市嘉特电子科技有限公司 | Mobile satellite receiving system |
| CN106299699A (en) * | 2016-09-19 | 2017-01-04 | 中信海洋（舟山）卫星通信有限公司 | System and method is followed the tracks of in a kind of double-reflecting face satellite antenna rotary missing plot |
| CN206003969U (en) * | 2016-09-19 | 2017-03-08 | 中信海洋（舟山）卫星通信有限公司 | A kind of double-reflecting face satellite antenna rotary missing plot tracking system |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7050015B2 (en) * | 2003-08-11 | 2006-05-23 | Bruchie Chris E | Dish antenna kit including alignment tool and method of use thereof |
| CN204374411U (en) * | 2014-12-16 | 2015-06-03 | 中国测绘科学研究院 | Satellite laser ranging system |
| CN205900801U (en) * | 2016-08-02 | 2017-01-18 | 哗裕实业股份有限公司 | Utensil moves effect mutually and surface form radiation pattern's disk -type antenna |
| CN106602203A (en) * | 2016-11-03 | 2017-04-26 | 航天恒星科技有限公司 | Portable satellite antenna |
-
2017
- 2017-05-26 CN CN202010960633.2A patent/CN112130305A/en active Pending
- 2017-05-26 CN CN201710383338.3A patent/CN106990516B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1422447A (en) * | 2000-04-14 | 2003-06-04 | 威罗门飞行公司 | Mobile radio communication system |
| CN102576925A (en) * | 2007-03-16 | 2012-07-11 | 移动卫星有限公司 | A vehicle mounted antenna and methods for transmitting and/or receiving signals |
| CN101309112A (en) * | 2008-07-04 | 2008-11-19 | 中国科学院上海光学精密机械研究所 | Bi-terminal bidirectional distant transmission simulation of satellite laser communication and gourd detection apparatus |
| CN101620316A (en) * | 2009-01-19 | 2010-01-06 | 深圳大学 | Optical deflection accelerator |
| CN101625080A (en) * | 2009-07-22 | 2010-01-13 | 深圳大学 | Strobe point light stroboflash generator with extremely high frequency |
| CN103078678A (en) * | 2012-12-29 | 2013-05-01 | 中国航天科技集团公司第五研究院第五一三研究所 | Satellite-borne laser wireless energy transmission system |
| CN106025551A (en) * | 2016-01-18 | 2016-10-12 | 贵港市嘉特电子科技有限公司 | Mobile satellite receiving system |
| CN105867435A (en) * | 2016-05-11 | 2016-08-17 | 西北工业大学 | Smooth and steady pointing maneuvering control method for satellite optical load |
| CN106299699A (en) * | 2016-09-19 | 2017-01-04 | 中信海洋（舟山）卫星通信有限公司 | System and method is followed the tracks of in a kind of double-reflecting face satellite antenna rotary missing plot |
| CN206003969U (en) * | 2016-09-19 | 2017-03-08 | 中信海洋（舟山）卫星通信有限公司 | A kind of double-reflecting face satellite antenna rotary missing plot tracking system |
Non-Patent Citations (2)
| Title |
|---|
| AI YUEXIA，CHEN HONGYI，LI JINGZHEN，WU QINGYANG，AND CAI YI: "Optical-deflection accelerating techniques in streak camera", 《JOURNAL OF SHENZHEN UNIVERSITY SCIENCE AND ENGINEERING》 * |
| 刘阳: "《声音与光 闪电和雷原来会拐弯》", 30 January 2013, 吉林出版集团有限责任公司 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106990516B (en) | 2020-10-02 |
| CN106990516A (en) | 2017-07-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1952562B1 (en) | Acquisition, pointing, and tracking architecture for laser communication | |
| US20120068880A1 (en) | System and Method for Dual-Band Antenna Pointing, Acquisition, And Tracking | |
| US9812775B2 (en) | Large aperture antenna with narrow angle fast beam steering | |
| US7109937B2 (en) | Phased array planar antenna and a method thereof | |
| US7680516B2 (en) | Mobile millimeter wave communication link | |
| US7786945B2 (en) | Beam waveguide including Mizuguchi condition reflector sets | |
| USRE37218E1 (en) | Satellite-tracking millimeter-wave reflector antenna system for mobile satellite-tracking | |
| US7385768B2 (en) | System, method and device for rapid, high precision, large angle beam steering | |
| CA1067204A (en) | Satellite tracking antenna with multiple reflectors | |
| KR20010020390A (en) | Terminal-antenna device for moving satellite constellation | |
| US20120002973A1 (en) | Dual band radio frequency (rf) & optical communications antenna and terminal design methodology and implementation | |
| US10082581B2 (en) | User terminal having a linear array antenna with electronic and mechanical actuation system | |
| JP6062071B2 (en) | Laser communication terminal and laser communication method | |
| KR20160065156A (en) | Low cost cableless ground station antenna for medium earth orbit satellite communication systems | |
| JP2018514137A (en) | A low-cost cableless ground station antenna for medium-orbit satellite communication systems. | |
| CN106990516B (en) | Satellite-borne laser communication wide-angle pointing device | |
| CN111130615B (en) | APT subsystem and communication system of spacecraft | |
| US7292789B1 (en) | Multi-channel wide-field laser communications method and apparatus | |
| US6449076B1 (en) | Optical beam director for communications applications | |
| JP2002141729A (en) | Control method for orbit satellite tracking antenna and orbit satellite tracking antenna system | |
| CN117254841B (en) | Communication method and device | |
| US11456540B2 (en) | Antenna device and antenna adjustment method | |
| US20230136379A1 (en) | Free space optical communication system with free space optical beam separator and point-ahead | |
| RU2106749C1 (en) | Space optical communication line between two objects | |
| Mai et al. | Variable Focus Lens-Based Optical Beam Steering and Adaptive Beam Control Techniques for Free-Space Optical Communications |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20201225 |
|
| RJ01 | Rejection of invention patent application after publication |