CN101719792B - Platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement - Google Patents
Platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement Download PDFInfo
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- CN101719792B CN101719792B CN 200910310565 CN200910310565A CN101719792B CN 101719792 B CN101719792 B CN 101719792B CN 200910310565 CN200910310565 CN 200910310565 CN 200910310565 A CN200910310565 A CN 200910310565A CN 101719792 B CN101719792 B CN 101719792B
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Abstract
The invention discloses a platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement, relating to the field of satellite photo communication and solving the problem that the overall process of the satellite link dynamic tracking performance can not be simulated and detected by utilizing the prior platform for simulating satellite-to-satellite relative sighting angle movement. The platform consists of an upper computer 1, a lead rail controller 2, a rotary table controller 3, a one-dimensional lead rail 4 and a double-shaft rotary table 5. The upper computer 1 works out a group of expected positions corresponding to the double-shaft rotary table 5 and the one-dimensional lead rail 4; the rotary table controller 3 is utilized to control the double-shaft rotary table 5 to move so as to enable the double-shaft rotary table 5 to reach the self corresponding expected position, and the lead rail controller 2 is utilized to control the one-dimensional lead rail 4 to enable the one-dimensional lead rail 4 to reach the self corresponding expected position, and thereby, the simulation of the sighting angle deviation generated by a measured photo-communication terminal 7 is completed. The invention is suitable for simulation experiments of conditions of satellite-to-satellite photo-communication terminal links.
Description
Technical field
The present invention relates to the satellite optical communication field, be specifically related to the platform of the relative sighting angle motion of a kind of analog link satellite optical communication terminal room.
Background technology
The inter-satellite laser link refers between two or multi-satellite and carrys out transmission information by light as carrier, in the satellite link process, needs terminal to carry out real-Time Compensation to due to satellite orbit and attitude, changing the angular motion caused.Before carrying out the test of Aerospace Satellite link, usually need to carry out on ground test fully to assure success.Due to two intersatellite distance of link, relative motion speed is high, directly carry out Aerospace Satellite link simulation test on ground more difficult, therefore build the task abnormity key that the platform of angular motion between a kind of analog satellite completes Aerospace Satellite link simulation test.Between existing analog satellite, the platform of angular motion is the multidimensional guide rail, by the relative motion between the multidimensional guide rail, two intersatellite angular motions are simulated, the shortcoming of utilizing described multidimensional guide rail to complete satellite link performance of dynamic tracking simulation test as the platform of angular motion between analog satellite is segmentation to carry out analog detection, there is certain limitation, can't carry out analog detection to the overall process of satellite link performance of dynamic tracking.
Summary of the invention
Can't carry out the problem of analog detection to the overall process of satellite link performance of dynamic tracking in order to solve the platform that utilizes angular motion between existing analog satellite, the invention provides the platform of the relative sighting angle motion of a kind of analog link satellite optical communication terminal room.
The platform of the relative sighting angle motion of a kind of analog link satellite optical communication terminal room of the present invention, it is by host computer, the guide rail controller, turntable controller, one dimension guide rail and two axle turntables form, described two axle turntables comprise pitch axis and azimuth axis, the range of movement of described pitch axis is at least-60 °～+ 60 °, the range of movement of described azimuth axis is at least-180 °～+ 180 °, a signal output part of described host computer is connected with the signal input part of guide rail controller, on the guide rail of the signal output part of described guide rail controller and one dimension guide rail, mover moves the control signal input and is connected, another signal output part of host computer is connected with the signal input part of turntable controller, the signal output part of described turntable controller is connected with the turntable rotation control signal input of two axle turntables, two axle turntables are fixed on the mover of one dimension guide rail, tested optical communication terminal is fixed on two axle turntables, and the position of tested optical communication terminal is changed with the pitch axis of two axle turntables and the motion of azimuth axis, host computer calculates the two dimension angular vector that two relative sighting angles of link satellite optical communication terminal room are moved corresponding
and dope the light beam translation amount
described two dimension angular vector
according to real-time track and the attitude delta data of two link satellite optical communication terminals, calculate, according to described two dimension angular vector
with described light beam translation amount
common generate one group respectively corresponding to the desired locations of two axle turntables and one dimension guide rail, utilizing turntable controller to control two axle turntable motions reaches and self corresponding desired locations two axle turntables, and utilize guide rail controller control one dimension guide rail movement that the one dimension guide rail is reached and self corresponding desired locations, complete the simulation of tested optical communication terminal generation sighting angle deviation.
Beneficial effect of the present invention is: in the satellite laser link overall process, track and attitude situation of change according to the link satellite, the excursion that adopts general account form can obtain sighting angle is: pitch axis is-60 °～+ 60 °, azimuth axis is-180 °～+ 180 °, and the present invention is by calculating the two dimension angular vector
with the light beam translation amount
corresponding introducing has two axle turntables and the one dimension guide rail of pitch axis and azimuth axis, can gamut simulate above-mentioned angle, and not need to carry out subregion, and whole process has been simulated the inter-satellite two-dimensional phase sighting angle is moved.
The accompanying drawing explanation
Fig. 1 is the device schematic diagram of the platform of the relative sighting angle motion of a kind of analog link satellite optical communication terminal room of the present invention;
Fig. 2 is the perspective view of the specific embodiment of the present invention two.
Embodiment
Embodiment one: according to Figure of description 1, illustrate present embodiment, the platform of the relative sighting angle motion of the described a kind of analog link satellite optical communication terminal room of present embodiment, it is by host computer 1, guide rail controller 2, turntable controller 3, one dimension guide rail 4 and two axle turntables 5 form, described two axle turntables 5 comprise pitch axis and azimuth axis, the range of movement of described pitch axis is at least-60 °～+ 60 °, the range of movement of described azimuth axis is at least-180 °～+ 180 °, a signal output part of described host computer 1 is connected with the signal input part of guide rail controller 2, on the guide rail of the signal output part of described guide rail controller 2 and one dimension guide rail 4, mover moves the control signal input and is connected, another signal output part of host computer 1 is connected with the signal input part of turntable controller 3, the signal output part of described turntable controller 3 is connected with the turntable rotation control signal input of two axle turntables 5, two axle turntables 5 are fixed on the mover of one dimension guide rail 4, tested optical communication terminal 7 is fixed on two axle turntables 5, and the position of tested optical communication terminal 7 is changed with the pitch axis of two axle turntables 5 and the motion of azimuth axis, host computer 1 calculates the two dimension angular vector that two relative sighting angles of link satellite optical communication terminal room are moved corresponding
and dope the light beam translation amount
described two dimension angular vector
according to real-time track and the attitude delta data of two link satellite optical communication terminals, calculate, according to described two dimension angular vector
with described light beam translation amount
common generate one group respectively corresponding to the desired locations of two axle turntables 5 and one dimension guide rail 4, utilizing turntable controller 3 to control two axle turntable 5 motions reaches and self corresponding desired locations two axle turntables 5, and utilize 2 control one dimension guide rail 4 motions of guide rail controller that one dimension guide rail 4 is reached and self corresponding desired locations, complete the simulation that the sighting angle deviations occur tested optical communication terminal 7.
In present embodiment, when two axle turntables 5 according to the two dimension angular vector
during motion, tested optical communication terminal 7 goes out the tested optical communication terminal sighting angle of current time deviation according to the input from supporting light source 6 received, utilize the sighting device (azimuth axis and pitch axis) of described tested optical communication terminal 7 to carry out real-Time Compensation to the sighting angle deviation, until the vanishing of sighting angle deviation can be detected the performance of dynamic tracking of described tested optical communication terminal 7 according to the compensation effect of tested optical communication terminal 7.The light source that supporting light source 6 is complementary for parameters such as the reception light wavelength with tested optical communication terminal or frequencies, described supporting light source 6 has represented the signal launch terminal in the satellite optical communication.
Two dimension angular vector described in present embodiment
mean two-dimentional turntable 5 t constantly pitch axis in amplitude of accommodation Az and the amplitude of accommodation El of azimuth axis on horizontal plane of z direction, described light beam translation amount
mean that one dimension guide rail 4 is engraved in the amplitude of accommodation x on horizontal plane when t, described horizontal plane is vertical with the z direction.
Embodiment two: according to Figure of description 2, illustrate present embodiment, the difference of present embodiment and embodiment one is that two axle turntables 5 comprise turntable pitch axis 5-1, movable frame 5-3, pitching frame 5-4, pedestal 5-5 and turntable azimuth axis, described turntable azimuth axis comprises turntable orientation axle sleeve 5-2 and azimuth axis R, tested optical communication terminal 7 comprises reception signal terminal 7-1, terminal pitch axis 7-2 and terminal azimuth axis, described terminal azimuth axis comprises terminal orientation axle sleeve 7-3, turntable pitch axis 5-1 is positioned on movable frame 5-3, and described movable frame 5-3 and pitching frame 5-4 are hinged by turntable pitch axis 5-1, terminal orientation axle sleeve 7-3 is between pedestal 5-5 and turntable orientation axle sleeve 5-2, and terminal orientation axle sleeve 7-3 and turntable orientation axle sleeve 5-2 all are enclosed within on azimuth axis R, thereby the lower end of azimuth axis R is connected to, pedestal 5-5 is upper realizes the action of described azimuth axis R around himself axis rotation, terminal pitch axis 7-2 is connected with the upper end of azimuth axis R, thereby described azimuth axis R and turntable orientation axle sleeve 5-2 and terminal orientation axle sleeve 7-3 fix described azimuth axis R and rotate with the two motion, terminal pitch axis 7-2 is connected with reception signal terminal 7-1, make reception signal terminal do elevating movement with the motion of terminal pitch axis 7-2.
Embodiment three: according to Figure of description 2, illustrate present embodiment, present embodiment is further illustrating embodiment two, the range of movement of this embodiment intermediate station pitch axis 5-1 and terminal pitch axis 7-2 is-80 °～+ 80 °, and the range of movement of turntable azimuth axis and terminal azimuth axis is-180 °～+ 180 °.
In present embodiment, one dimension guide rail 4 is also for the translation error of the aiming beam that compensates tested optical communication terminal 7.
For present embodiment, carry out instance analysis:
Pitching frame 5-4 is the tuning-fork type open design, and this tuning-fork type open design makes the tested optical communication terminal 7 can unobstructed communication in range of movement, and this tuning-fork type open design is convenient to the installment and debugging of tested optical communication terminal 7.Movable frame 5-3 and pitching frame 5-4 all adopt the cast aluminium structure of hollow, to reduce weight, improve vibration frequency.Turntable pitch axis 5-1 adopts the bimoment motor to drive, and adjusts the phase angle of described bimoment motor when described bimoment motor is installed, and by same driver, described bimoment motor is powered.Adjust as required the dead-center position of turntable azimuth axis, turntable pitch axis 5-1 and turntable azimuth axis two-axle interlocking can be by the two-dimensional phase that is fixed in the tested optical communication terminal 7 on azimuth axis R to sighting angle motion vector points space any directions, and then analog satellite attitude and track in-orbit changes.Utilize one dimension guide rail 4 to carry out translational motion, the stroke of one dimension guide rail 4 is 1m, and it is used for compensating the translation error due to aiming beam in the overall process ground simulation detection of carrying out the satellite link performance of dynamic tracking.Tested optical communication terminal 7 belongs to periscopic two pillow blocks, when two axle turntable 5 analog satellite attitudes and track variation, tested optical communication terminal 7 can arrive by the optical signal detecting received the sighting angle deviation of current time, progressively adjust sighting angle by terminal pitch axis 7-2 and the terminal azimuth axis of controlling tested optical communication terminal 7, to realize pencil tracing.
Claims (1)
1. the platform of the relative sighting angle motion of an analog link satellite optical communication terminal room, it is characterized in that it is by host computer (1), guide rail controller (2), turntable controller (3), one dimension guide rail (4) and two axle turntables (5) form, described two axle turntables (5) comprise turntable pitch axis (5-1) and turntable azimuth axis, the range of movement of described turntable pitch axis (5-1) is at least-60 ° ~+60 °, the range of movement of described turntable azimuth axis is at least-180 ° ~+180 °, a signal output part of described host computer (1) is connected with the signal input part of guide rail controller (2), the signal output part of described guide rail controller (2) moves the control signal input with mover on the guide rail of one dimension guide rail (4) and is connected, another signal output part of host computer (1) is connected with the signal input part of turntable controller (3), the signal output part of described turntable controller (3) is connected with the turntable rotation control signal input of two axle turntables (5), two axle turntables (5) are fixed on the mover of one dimension guide rail (4), tested optical communication terminal (7) is fixed on two axle turntables (5), and the position of tested optical communication terminal (7) is changed with the turntable pitch axis (5-1) of two axle turntables (5) and the motion of turntable azimuth axis, host computer (1) calculates the two dimension angular vector that two relative sighting angles of link satellite optical communication terminal room are moved corresponding
and dope the light beam translation amount
described two dimension angular vector
according to real-time track and the attitude delta data of two link satellite optical communication terminals, calculate, according to described two dimension angular vector
with described light beam translation amount
common generate one group respectively corresponding to the desired locations of two axle turntables (5) and one dimension guide rail (4), utilizing turntable controller (3) to control two axle turntable (5) motions reaches and self corresponding desired locations two axle turntables (5), and utilize guide rail controller (2) control one dimension guide rail (4) motion that one dimension guide rail (4) is reached and self corresponding desired locations, complete the simulation that the sighting angle deviation occurs tested optical communication terminal (7),
Described two dimension angular vector
mean two-dimentional turntable (5) t constantly turntable pitch axis (5-1) in amplitude of accommodation Az and the amplitude of accommodation El of turntable azimuth axis on horizontal plane of z direction, described light beam translation amount
mean that one dimension guide rail (4) is engraved in the amplitude of accommodation x on horizontal plane when t, described horizontal plane is vertical with the z direction;
Two axle turntables (5) comprise turntable pitch axis (5-1), movable frame (5-3), pitching frame (5-4), pedestal (5-5) and turntable azimuth axis, described turntable azimuth axis comprises turntable orientation axle sleeve (5-2) and azimuth axis R, tested optical communication terminal (7) comprises reception signal terminal (7-1), terminal pitch axis (7-2) and terminal azimuth axis, described terminal azimuth axis comprises terminal orientation axle sleeve (7-3), turntable pitch axis (5-1) is positioned on movable frame (5-3), and described movable frame (5-3) is hinged by turntable pitch axis (5-1) with pitching frame (5-4), terminal orientation axle sleeve (7-3) is positioned between pedestal (5-5) and turntable orientation axle sleeve (5-2), and terminal orientation axle sleeve (7-3) and turntable orientation axle sleeve (5-2) all are enclosed within on azimuth axis R, the lower end of azimuth axis R is connected to pedestal (5-5) thereby upper realizes the action of described azimuth axis R around himself axis rotation, terminal pitch axis (7-2) is connected with the upper end of azimuth axis R, described azimuth axis R and turntable orientation axle sleeve (5-2) and terminal orientation axle sleeve (7-3) thus fixing described azimuth axis R rotates with the two motion, terminal pitch axis (7-2) is connected with reception signal terminal (7-1), make reception signal terminal do elevating movement with the motion of terminal pitch axis (7-2),
The range of movement of turntable pitch axis (5-1) and terminal pitch axis (7-2) is-80 ° ~+80 °, and the range of movement of turntable azimuth axis and terminal azimuth axis is-180 ° ~+180 °; Tested optical communication terminal (7) belongs to periscopic two pillow blocks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910310565 CN101719792B (en) | 2009-11-27 | 2009-11-27 | Platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910310565 CN101719792B (en) | 2009-11-27 | 2009-11-27 | Platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement |
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| Publication Number | Publication Date |
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| CN101719792A CN101719792A (en) | 2010-06-02 |
| CN101719792B true CN101719792B (en) | 2013-06-19 |
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| CN 200910310565 Expired - Fee Related CN101719792B (en) | 2009-11-27 | 2009-11-27 | Platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103401056B (en) * | 2013-08-12 | 2017-02-15 | 四川九洲电器集团有限责任公司 | Rotary table for portable ground satellite station |
| CN103871075B (en) * | 2013-12-30 | 2015-11-18 | 华中科技大学 | A kind of large oval remote sensing satellite earth background relative motion method of estimation |
| DK3611850T3 (en) * | 2015-12-31 | 2021-08-02 | Viasat Inc | BROADBAND SATELLITE COMMUNICATION SYSTEM USING OPTICAL FEEDER LINKS |
| CN106227245B (en) * | 2016-09-07 | 2019-10-11 | 西安交通大学 | Improve the electrostriction micromotion structure and its control method of two-axis platcform tracking accuracy |
| CN108039913B (en) * | 2017-12-18 | 2023-09-01 | 中国科学院西安光学精密机械研究所 | Coarse tracking device for light and small space laser communication terminal |
| CN109443813B (en) * | 2018-09-28 | 2020-06-09 | 中国空间技术研究院 | Rotation test method for satellite electric propulsion vector adjusting mechanism |
| CN112751605B (en) * | 2020-12-29 | 2022-12-27 | 上海卫星工程研究所 | Method, system and medium for testing capturing and tracking characteristics of double-star dynamic inter-satellite link |
| CN113641182B (en) * | 2021-07-27 | 2023-12-01 | 中国星网网络应用有限公司 | High-precision aiming and pointing method and system for inter-satellite laser communication system |
| CN114427983A (en) * | 2021-12-28 | 2022-05-03 | 航天东方红卫星有限公司 | Satellite attitude control and measurement platform and system |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1561016A (en) * | 2004-02-16 | 2005-01-05 | 中国科学院上海光学精密机械研究所 | Satellite orbit simulation test system |
| CN101030816A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工业大学 | Simulator for laser link relative-corner movement between satellites |
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2009
- 2009-11-27 CN CN 200910310565 patent/CN101719792B/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1561016A (en) * | 2004-02-16 | 2005-01-05 | 中国科学院上海光学精密机械研究所 | Satellite orbit simulation test system |
| CN101030816A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工业大学 | Simulator for laser link relative-corner movement between satellites |
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Inventor after: Yu Siyuan Inventor after: Ma Jing Inventor after: Tan Liying Inventor after: Song Yiwei Inventor after: Wu Feng Inventor after: Yang Zhonghua Inventor after: Liu Qingfeng Inventor after: Cao Kairui Inventor before: Yu Siyuan Inventor before: Ma Jing Inventor before: Tan Liying Inventor before: Song Yiwei Inventor before: Wu Feng |
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Free format text: CORRECT: INVENTOR; FROM: YU SIYUAN MA JING TAN LIYING SONG YIWEI WU FENG TO: YU SIYUAN MA JING TAN LIYING SONG YIWEI WU FENG YANG ZHONGHUA LIU QINGFENG CAO KAIRUI |
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Granted publication date: 20130619 |