CN115996088B - On-orbit self-calibration device and method for satellite-borne laser communication terminal - Google Patents
On-orbit self-calibration device and method for satellite-borne laser communication terminal Download PDFInfo
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Abstract
The invention relates to an on-orbit self-calibration device and method of a satellite-borne laser communication terminal in the field of free space optical communication. The device comprises a pyramid, a coarse pointing mechanism, a main beam expanding system, a quick reflector, a dichroic mirror, an advanced sighting telescope, a transmitting lens, a signal transmitting laser, an optical filter, a spectroscope, a signal focusing mirror, a signal receiving detector, a tracking focusing mirror and a tracking receiving detector. The signal emitting laser is returned to the signal receiving system by rotating the coarse pointing mechanism to align the pyramid, and the parallelism among the optical axes of the signal emitting light path, the signal receiving light path, the tracking receiving light path and the like is judged by the signal receiving power and the spot mass center position on the tracking detector, so that the on-orbit self-calibration of the terminal optical axis deviation is realized. The invention can meet the requirement of the satellite-borne laser communication terminal for realizing the on-orbit self-calibration without matching with a ground optical communication system or other on-orbit satellite laser communication terminals or matching with a beacon light or an additional laser light source.
Description
Technical Field
The invention relates to the field of free space optical communication, in particular to an on-orbit self-calibration device and method of a satellite-borne laser communication terminal.
Background
Compared with microwave communication, free space laser communication has the main advantages of large transmission capacity, safety and confidentiality, strong anti-interference capability, small communication time delay, low power consumption and the like, and inter-satellite laser communication is not influenced by atmospheric turbulence, so that the free space laser communication becomes a hot spot for development in the field of free space optical communication. In recent years, china has rapidly developed in the field of inter-satellite laser communication, and test verification of a plurality of laser communication and networking projects such as 'Hongyun', 'Hongyan', 'Xingyun', 'Tiandi integrated network', 'Beidou', 'Weili' and the like is carried out. Multiple inter-satellite laser link communication experiments have also been conducted in the united states, europe, japan, etc.
In the field of satellite-borne laser communication, optical axes such as a signal transmitting optical path, a signal receiving optical path and a tracking receiving optical path of a communication terminal need to be kept parallel. As communication distance increases, the smaller the signal divergence angle is required to ensure the communication link power headroom. The signal divergence angle becomes small to several tens of micro radians, and parallelism of each optical path is required to be within ten micro radians. Because the satellite-borne laser communication terminal is subjected to vibration and impact in the processes of transportation, emission, on-orbit running and the like, the parallelism among optical axes is seriously affected, and therefore the parallelism of each optical path is very important in on-orbit calibration. Along with the development of commercial aerospace, stringent requirements are put forward on cost, weight, reliability and the like of a laser communication terminal, and currently, heavy projects such as micro-scale and star-net put forward beaconing-free emission and rough tracking receiving light paths for the satellite-borne laser communication terminal, so that higher requirements are put forward on the system of on-orbit self-calibration of the laser communication terminal.
In the prior art, CN202011291747 (an on-orbit self-calibration device of a spatial laser communication terminal and a calibration method thereof) uses a frame movably connected with a rotating shaft to perform self-calibration of beacon transceiving and signal transceiving on the switching of a total light reflection prism. The defects are as follows: the rotating shaft is movably connected with the frame to align with the total light reflection prism, an additional switching device is arranged, the reliability of the system is reduced, the switching precision is low, and meanwhile, a beacon emission light path is arranged for self-calibration.
In the prior art, CN201811554230 (an on-orbit calibration and receiving-transmitting coaxiality correction device and method for a satellite optical communication terminal) performs calibration on a signal transmitting optical path, a signal receiving optical path and a tracking optical path by using an external calibration transmitting branch, a signal internal calibration transmitting branch, a beacon internal calibration transmitting branch, a calibration reflector and the like. The defects are as follows: the beacon external calibration transmitting branch comprises a beacon laser and a signal laser, and the beacon internal calibration transmitting branch also exists, so that the device is more in devices and the method is complex.
In the prior art, CN202210141497 (an on-orbit self-calibration device of a satellite-borne laser communication machine and a calibration method thereof) is used for detecting and compensating the centroid position of a light spot by opening an optical switch to a receiving light path or a transmitting light path and then reflecting the light power to the receiving light path through a pyramid to detect and track the centroid position of the light spot, thereby realizing the coaxial self-calibration of the receiving light path, the transmitting light path and the tracking light path. The defects are as follows: there are calibrating lasers, optical switches, optical fiber couplers, etc., and the device has many devices and complex methods.
In the prior art, CN202111508835 (a novel optical self-calibration device and method for a laser communication system) and CN201810945384 (an optical axis self-calibration device and method for an optical communication system) reflect calibration laser to a receiving optical path and a tracking optical path through a spectroscope or a pyramid, so as to realize coaxial self-calibration of the receiving optical path, the transmitting optical path and the tracking optical path. The defects are as follows: the device has a plurality of devices and the method is complex.
Disclosure of Invention
The invention aims at overcoming the defects of the prior art, and provides an on-orbit self-calibration device and method for a satellite-borne laser communication terminal, which are capable of directly utilizing signal lasers without beacon lasers or other laser sources, setting proper signal emission laser power through calculation of link power margin of a self-calibration light path, solving the problem of on-orbit parallelism self-calibration of the satellite-borne laser communication terminal, and reducing the weight, power consumption and cost of the self-calibration device.
The invention adopts the technical scheme that:
an on-orbit self-calibration device of a satellite-borne laser communication terminal comprises a pyramid, a coarse pointing mechanism, a main beam expanding system, a quick reflector, a dichroic mirror, an advanced sighting telescope, a transmitting lens, a signal transmitting laser, an optical filter, a spectroscope, a signal focusing mirror, a signal receiving detector, a tracking focusing mirror and a tracking receiving detector;
the signal emitting laser emits laser to enter the pyramid through the emitting lens, the advanced sighting telescope, the dichroic mirror, the quick reflector, the main beam expanding system and the coarse directing mechanism in sequence, then the laser is totally reflected back through the pyramid to reach the spectroscope through the coarse directing mechanism, the main beam expanding system, the quick reflector, the dichroic mirror and the optical filter in sequence, the spectroscope divides the laser into two beams, one path is coupled to the signal receiving detector through the signal focusing mirror, the signal receiving detector detects signal receiving power, the other path is focused to the tracking receiving detector through the tracking focusing mirror, and the tracking receiving detector extracts and processes the facula centroid.
Further, the light transmission caliber of the pyramid is related to the link power margin of the self-calibration optical path, and the link power margin of the self-calibration optical path is related to the maximum power allowed to be transmitted by the signal laser during on-track calibration, the back and forth loss of the self-calibration optical path and the sensitivity of the signal receiving detector.
Furthermore, the pyramid is a reflective pyramid or a pyramid prism, the pyramid is arranged at a position where the coarse pointing mechanism can normally enter, the pyramid realizes normal incidence of incident light rays through angle control of the coarse pointing mechanism, the angle condition of the pyramid total reflection tolerance is met, and the pyramid is in a total reflection state; the coarse pointing mechanism is a two-dimensional turntable or a two-dimensional swing mirror.
Further, the main beam expanding system adopts an off-axis reflective type, an on-axis reflective type or a transmission type beam expanding system, and if the main beam expanding system is a transmission type beam expanding system, the main beam expanding system needs to eliminate chromatic aberration between the laser emission wavelength and the receiving wavelength.
Further, the quick reflector is a piezoelectric control system or a two-dimensional galvanometer control system.
Further, the signal emitting laser is a laser with optical fiber coupling output or a laser with space light output.
Further, the emission lens is a collimating lens if the signal emission laser is a laser with optical fiber coupling output, and is a beam expanding lens group if the signal emission laser is a laser with spatial light output.
Furthermore, the advanced sighting telescope is a piezoelectric control system or a two-dimensional galvanometer control system, the signal receiving detector is an APD detector or a receiving optical fiber, and the tracking receiving detector is a CCD detector or a four-quadrant photoelectric detector.
An on-orbit self-calibration method of a satellite-borne laser communication terminal comprises the following steps:
step 1, checking initial parameters of an on-orbit self-calibration device, including parameters of a signal emitting laser, a signal receiving detector, a tracking receiving detector, a quick reflector, an advanced sighting telescope and a coarse pointing mechanism, determining a power value of signal laser emission, turning on the signal emitting laser, and controlling the coarse pointing mechanism to align with a pyramid;
step 2, the laser emitted by the signal emitting laser sequentially enters a pyramid through an emitting lens, an advanced sighting telescope, a dichroic mirror, a quick reflecting mirror, a main beam expanding system and a coarse directing mechanism, then is totally reflected back through the pyramid and sequentially passes through the coarse directing mechanism, the main beam expanding system, the quick reflecting mirror, the dichroic mirror and a light filter to a spectroscope, the spectroscope divides the reflected laser into two beams, one beam is directly coupled to a signal receiving detector through a signal focusing mirror or indirectly coupled into a signal receiving optical fiber and then enters the signal receiving detector, and the other beam is focused to a tracking receiving detector through a tracking focusing mirror;
step 3, adjusting the pointing parameter of the advanced sighting telescope so that the signal receiving detector receives the maximum power value and records and changes the pointing parameter of the advanced sighting telescope at the center of a receiving view field, and completing the calibration of the optical axis parallelism of a signal transmitting optical path and a signal receiving optical path;
and 4, after the optical axis parallelism of the signal transmitting optical path and the signal receiving optical path is calibrated, when a light spot appears in the tracking receiving detector, recording and extracting the barycenter coordinate of the light spot, comparing the barycenter coordinate of the light spot which is calibrated originally with the barycenter coordinate of the light spot which is extracted, obtaining the deviation amount of the optical axis of the corresponding signal transmitting optical path and the optical axis of the tracking receiving optical path, correcting the tracking deviation by using the obtained deviation amount, changing the original tracking point into a new tracking point, and completing the optical axis parallelism calibration of the signal transmitting optical path and the tracking receiving optical path.
Compared with the background technology, the invention has the advantages that:
the invention directly uses signal laser without beacon laser or other laser sources, and sets proper signal emission laser power through the calculation of the link power margin of the self-calibration optical path, thereby not only realizing the self-calibration of the on-orbit parallelism of the satellite-borne laser communication terminal, but also reducing the weight, the power consumption and the cost of the self-calibration device.
Drawings
Fig. 1 is a schematic diagram of an implementation of the present invention.
Description of the embodiments
The invention is further explained below with reference to the drawings.
The on-orbit self-calibration device and method of the satellite-borne laser communication terminal are not only suitable for an intensity modulation laser communication system, but also suitable for a coherent laser communication system.
As shown in FIG. 1, the on-orbit self-calibration device of the satellite-borne laser communication terminal comprises a pyramid, a coarse pointing mechanism, a main beam expanding system, a quick reflector, a dichroic mirror, a front sighting telescope, a transmitting lens, a signal transmitting laser, an optical filter, a spectroscope, a signal focusing mirror, a signal receiving detector, a tracking focusing mirror and a tracking receiving detector;
the signal emitting laser emits laser to enter the pyramid through the emitting lens, the advanced sighting telescope, the dichroic mirror, the quick reflector, the main beam expanding system and the coarse directing mechanism in sequence, then the laser is totally reflected back through the pyramid to reach the spectroscope through the coarse directing mechanism, the main beam expanding system, the quick reflector, the dichroic mirror and the optical filter in sequence, the spectroscope divides the laser into two beams, one path is coupled to the signal receiving detector through the signal focusing mirror, the signal receiving detector detects signal receiving power, the other path is focused to the tracking receiving detector through the tracking focusing mirror, and the tracking receiving detector extracts and processes the facula centroid.
The light transmission caliber of the pyramid is related to the self-calibration optical path link power allowance, and is generally 5 mm-28 mm, and the comprehensive angle difference is smaller than 1'; the link power margin of the self-calibration optical path is related to the maximum power allowed to be transmitted by the signal laser during on-orbit calibration, the back and forth loss of the self-calibration optical path and the sensitivity of the signal receiving detector; the pyramid can be a reflective pyramid or a pyramid prism; the pyramid is mounted in a position where the coarse pointing mechanism can be normally incident, but does not affect the normal laser communication link.
The angle control of the coarse pointing mechanism is used for realizing normal incidence of incident light rays, the angle condition of the total reflection tolerance of the pyramid is met, the pyramid is in a total reflection state, and on-orbit self-calibration is performed at the moment; after calibration, the angle pointing of the coarse pointing mechanism is changed, so that the scanning, capturing and tracking and the chain building process of the opposite-end satellite-borne laser communication terminal are realized.
The coarse directing mechanism can realize low-speed coarse precision control of beam directing, the precision is within about 100urad, and the bandwidth is 10 Hz-200 Hz, and the coarse directing mechanism can be a two-dimensional turntable or a two-dimensional swinging mirror.
Wherein the main beam expanding system adopts an off-axis or on-axis reflection type or transmission type beam expanding system. If a transmission type beam expanding system is adopted, the main beam expanding system needs to eliminate the chromatic aberration of the laser emission wavelength and the receiving wavelength.
The rapid reflecting mirror can realize rapid and accurate control of beam pointing, the precision is within about 5urad, the bandwidth is 1 kHz-10 kHz, and the rapid reflecting mirror can be a piezoelectric control system or a two-dimensional galvanometer control system.
The signal emitting laser is a laser with optical fiber coupling output or a laser with space light output. When the signal emitting laser is in a self-calibration state, the proper optical power is emitted, the sensitivity of the signal emitting laser is slightly higher than that of the signal receiving detector and the tracking detector, high-power laser is not allowed to be emitted, and the signal light is prevented from returning to damage the signal laser.
The emitting lens is a collimating lens if the signal emitting laser is a laser with optical fiber coupling output; if the laser is a laser with space light output, the emission lens is a beam expander lens group.
The advanced sighting telescope can realize low-speed control of beam pointing, the precision is within about 5urad, the bandwidth is 10 Hz-100 Hz, and the advanced sighting telescope can be a piezoelectric control system or a two-dimensional galvanometer control system.
The signal receiving detector is an APD detector or a receiving optical fiber.
Wherein the tracking receiving detector is a CCD detector or a four-quadrant photoelectric detector.
An on-orbit self-calibration method of a satellite-borne laser communication terminal comprises the following steps:
step 1, checking initial parameters of an on-orbit self-calibration device, including parameters of a signal emitting laser, a signal receiving detector, a tracking receiving detector, a quick reflector, an advanced sighting telescope and a coarse pointing mechanism, determining a power value of signal laser emission, turning on the signal emitting laser, and controlling the coarse pointing mechanism to align with a pyramid;
step 2, the laser emitted by the signal emitting laser sequentially enters a pyramid through an emitting lens, an advanced sighting telescope, a dichroic mirror, a quick reflecting mirror, a main beam expanding system and a coarse directing mechanism, then is totally reflected back through the pyramid and sequentially passes through the coarse directing mechanism, the main beam expanding system, the quick reflecting mirror, the dichroic mirror and a light filter to a spectroscope, the spectroscope divides the reflected laser into two beams, one beam is directly coupled to a signal receiving detector through a signal focusing mirror or indirectly coupled into a signal receiving optical fiber and then enters the signal receiving detector, and the other beam is focused to a tracking receiving detector through a tracking focusing mirror;
step 3, adjusting the pointing parameter of the advanced sighting telescope so that the signal receiving detector receives the maximum power value and records and changes the pointing parameter of the advanced sighting telescope at the center of a receiving view field, and completing the calibration of the optical axis parallelism of a signal transmitting optical path and a signal receiving optical path;
and 4, when the tracking and receiving detector generates a light spot, recording and extracting the barycenter coordinate of the light spot, comparing the barycenter coordinate of the light spot calibrated originally with the barycenter coordinate of the light spot extracted to obtain the deviation amount of the optical axis of the corresponding signal transmitting optical path and the optical axis of the tracking and receiving optical path, correcting the tracking and aiming deviation by using the obtained deviation amount, changing the original tracking point into a new tracking point, and completing the calibration of the parallelism degree of the optical axes of the signal transmitting optical path and the tracking and receiving optical path.
Claims (6)
1. The on-orbit self-calibration device of the satellite-borne laser communication terminal is characterized by comprising a pyramid, a coarse pointing mechanism, a main beam expanding system, a quick reflector, a dichroic mirror, an advanced sighting telescope, a transmitting lens, a signal transmitting laser, an optical filter, a spectroscope, a signal focusing mirror, a signal receiving detector, a tracking focusing mirror and a tracking receiving detector;
the method comprises the steps that laser emitted by a signal emitting laser sequentially enters a pyramid through an emitting lens, an advanced sighting telescope, a dichroic mirror, a quick reflector, a main beam expanding system and a coarse directing mechanism, then is totally reflected back through the pyramid and sequentially reaches a spectroscope through the coarse directing mechanism, the main beam expanding system, the quick reflector, the dichroic mirror and a light filter, the spectroscope divides the laser into two beams, one beam is coupled to a signal receiving detector through a signal focusing mirror, the signal receiving detector detects signal receiving power, the other beam is focused to a tracking receiving detector through a tracking focusing mirror, and the tracking receiving detector extracts and processes the centroid of a light spot;
the light transmission aperture of the pyramid and the link power margin of the self-calibration optical path form a set relation, and the link power margin of the self-calibration optical path and the maximum power allowed to be transmitted by the signal laser during on-orbit calibration, the back and forth loss of the self-calibration optical path and the sensitivity of the signal receiving detector form a set relation;
the pyramid is a reflective pyramid or a pyramid prism, the pyramid is arranged at a position where the coarse pointing mechanism can normally enter, normal incidence of incident light rays is realized by angle control of the coarse pointing mechanism, the angle condition of the pyramid total reflection tolerance is met, and the pyramid is in a total reflection state; the coarse pointing mechanism is a two-dimensional turntable or a two-dimensional swing mirror; the main beam expanding system adopts off-axis reflection type, on-axis reflection type or transmission type beam expanding system, and if the main beam expanding system is a transmission type beam expanding system, the chromatic aberration of the laser emission wavelength and the receiving wavelength needs to be eliminated.
2. The on-orbit self-calibration device of a satellite-borne laser communication terminal according to claim 1, wherein the fast mirror is a piezoelectric control system or a two-dimensional galvanometer control system.
3. The on-orbit self-calibration device of a satellite-borne laser communication terminal according to claim 1, wherein the signal emitting laser is a fiber coupled output laser or a spatial light output laser.
4. An on-orbit self-calibration device for a satellite-borne laser communication terminal according to claim 3, wherein the transmitting lens is a collimating lens if the signal transmitting laser is a laser with optical fiber coupling output, and is a beam expanding lens group if the signal transmitting laser is a laser with spatial light output.
5. The on-orbit self-calibration device of the satellite-borne laser communication terminal according to claim 1, wherein the advanced sighting telescope is a piezoelectric control system or a two-dimensional galvanometer control system, the signal receiving detector is an APD detector or a receiving optical fiber, and the tracking receiving detector is a CCD detector or a four-quadrant photoelectric detector.
6. An on-orbit self-calibration method of a satellite-borne laser communication terminal based on the on-orbit self-calibration device as claimed in claim 1, which is characterized by comprising the following steps:
step 1, checking initial parameters of an on-orbit self-calibration device, including parameters of a signal emitting laser, a signal receiving detector, a tracking receiving detector, a quick reflector, an advanced sighting telescope and a coarse pointing mechanism, determining a power value of signal laser emission, turning on the signal emitting laser, and controlling the coarse pointing mechanism to align with a pyramid;
step 2, the laser emitted by the signal emitting laser sequentially enters a pyramid through an emitting lens, an advanced sighting telescope, a dichroic mirror, a quick reflecting mirror, a main beam expanding system and a coarse directing mechanism, then is totally reflected back through the pyramid and sequentially passes through the coarse directing mechanism, the main beam expanding system, the quick reflecting mirror, the dichroic mirror and a light filter to a spectroscope, the spectroscope divides the reflected laser into two beams, one beam is directly coupled to a signal receiving detector through a signal focusing mirror or indirectly coupled into a signal receiving optical fiber and then enters the signal receiving detector, and the other beam is focused to a tracking receiving detector through a tracking focusing mirror;
step 3, adjusting the pointing parameter of the advanced sighting telescope so that the signal receiving detector receives the maximum power value and records and changes the pointing parameter of the advanced sighting telescope at the center of a receiving view field, and completing the calibration of the optical axis parallelism of a signal transmitting optical path and a signal receiving optical path;
and 4, after the optical axis parallelism of the signal transmitting optical path and the signal receiving optical path is calibrated, when a light spot appears in the tracking receiving detector, recording and extracting the barycenter coordinate of the light spot, comparing the barycenter coordinate of the light spot which is calibrated originally with the barycenter coordinate of the light spot which is extracted, obtaining the deviation amount of the optical axis of the corresponding signal transmitting optical path and the optical axis of the tracking receiving optical path, correcting the tracking deviation by using the obtained deviation amount, changing the original tracking point into a new tracking point, and completing the optical axis parallelism calibration of the signal transmitting optical path and the tracking receiving optical path.
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| CN116781168A (en) * | 2023-06-14 | 2023-09-19 | 蓝星光域(上海)航天科技有限公司 | Integrated laser communication terminal |
| CN117614518B (en) * | 2024-01-22 | 2024-04-09 | 北京融为科技有限公司 | Satellite-borne laser load receiving and transmitting coaxial calibration method and system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103501203A (en) * | 2013-09-26 | 2014-01-08 | 北京空间飞行器总体设计部 | Laser satellite-ground communication link test system suitable for remote sensing satellite |
| CN106323198A (en) * | 2016-08-07 | 2017-01-11 | 哈尔滨工业大学 | High precision, wide range and large working distance laser auto-collimation device and method |
| CN109738160A (en) * | 2018-12-29 | 2019-05-10 | 湖北航天技术研究院总体设计所 | Multi-light axis consistency test device and method based on laser communication system |
| CN110231610A (en) * | 2019-05-24 | 2019-09-13 | 武汉大学 | The active hot spot energy-probe detection calibrating platform of spaceborne laser altimeter system instrument and method |
| CN112564822A (en) * | 2020-11-18 | 2021-03-26 | 西安理工大学 | On-orbit self-calibration device and method for space laser communication terminal |
| WO2022052432A1 (en) * | 2020-09-11 | 2022-03-17 | 中国科学院西安光学精密机械研究所 | Lightweight and scalable multi-user optical antenna and communication method |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108333692B (en) * | 2018-02-08 | 2019-12-24 | 中国科学院光电技术研究所 | Space light-to-optical fiber coupling system |
| CN109150302B (en) * | 2018-08-20 | 2021-02-12 | 中国科学院上海技术物理研究所 | Optical axis self-calibration device and method of optical communication system |
| CN109787686B (en) * | 2018-12-18 | 2020-06-16 | 中国科学院西安光学精密机械研究所 | Satellite optical communication terminal on-orbit calibration and transmitting-receiving coaxiality correction device and method |
| CN110971296B (en) * | 2019-11-12 | 2021-02-19 | 中国科学院西安光学精密机械研究所 | Space beacon-free optical communication terminal scanning system |
| CN110850436B (en) * | 2019-11-28 | 2023-03-31 | 中国科学院合肥物质科学研究院 | Device and method for measuring spectrum of airborne hyperspectral imaging laser radar in real time |
| CN114200687B (en) * | 2021-12-10 | 2023-09-29 | 北京遥测技术研究所 | Optical self-calibration device and method for laser communication system |
| CN114189284B (en) * | 2022-02-16 | 2022-05-24 | 之江实验室 | On-orbit self-calibration device and calibration method of satellite-borne laser communication machine |
| CN115801117A (en) * | 2022-09-19 | 2023-03-14 | 北京遥测技术研究所 | Novel laser communication receiving and transmitting light beam integrated monitoring system and monitoring method |
| CN115426043B (en) * | 2022-11-04 | 2023-03-24 | 之江实验室 | On-orbit self-calibration system and method for optical axis of space laser communication terminal |
-
2023
- 2023-03-23 CN CN202310286368.8A patent/CN115996088B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103501203A (en) * | 2013-09-26 | 2014-01-08 | 北京空间飞行器总体设计部 | Laser satellite-ground communication link test system suitable for remote sensing satellite |
| CN106323198A (en) * | 2016-08-07 | 2017-01-11 | 哈尔滨工业大学 | High precision, wide range and large working distance laser auto-collimation device and method |
| CN109738160A (en) * | 2018-12-29 | 2019-05-10 | 湖北航天技术研究院总体设计所 | Multi-light axis consistency test device and method based on laser communication system |
| CN110231610A (en) * | 2019-05-24 | 2019-09-13 | 武汉大学 | The active hot spot energy-probe detection calibrating platform of spaceborne laser altimeter system instrument and method |
| WO2022052432A1 (en) * | 2020-09-11 | 2022-03-17 | 中国科学院西安光学精密机械研究所 | Lightweight and scalable multi-user optical antenna and communication method |
| CN112564822A (en) * | 2020-11-18 | 2021-03-26 | 西安理工大学 | On-orbit self-calibration device and method for space laser communication terminal |
Non-Patent Citations (1)
| Title |
|---|
| 量子导航定位***中的捕获和粗跟踪技术;丛爽;汪海伦;邹紫盛;尚伟伟;隋岩;;空间控制技术与应用(第01期) * |
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