CN207638661U - A kind of small-sized laser space communication terminal rough tracking device - Google Patents
A kind of small-sized laser space communication terminal rough tracking device Download PDFInfo
- Publication number
- CN207638661U CN207638661U CN201721772371.7U CN201721772371U CN207638661U CN 207638661 U CN207638661 U CN 207638661U CN 201721772371 U CN201721772371 U CN 201721772371U CN 207638661 U CN207638661 U CN 207638661U
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- China
- Prior art keywords
- line style
- displacement sensor
- receiver
- optical transmitter
- eddy current
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Abstract
The technical issues of can not being suitable for moonlet optical communication terminal to solve existing rough tracking device due to its volume is big, weight is big, precision is low, the utility model provides a kind of small-sized laser space communication terminal rough tracking device.Optical transmitter and receiver is connected by the utility model using flexible hinge with pedestal, carries out the regulative mode of two point drivings to optical transmitter and receiver using line style actuator, is avoided using the problem that frame strip next volume in pitching orientation is big, weight is big；Since line style actuator thrust is big, small, light-weight, displacement accuracy is high, weight is can be controlled within 1Kg, and flexible hinge weight, within 0.5Kg, in addition necessary connecting joint, rough tracking device total weight can be controlled in 2~3Kg.
Description
Technical field
The utility model belongs to photoelectric tracking capture field, is related to a kind of Photoelectric Tracking and Aiming device, and in particular to a kind of sky
Between laser communication terminal rough tracking device.
Background technology
Moonlet optical communication terminal is due to its low SWaP (Size, Weight and Power), the development cycle is short, is provided on star
Source consumes few feature, is studied and is applied extensively both at home and abroad.Moonlet laser space communication generally first pass through satellite posture adjustment into
Row optical axis is initially aligned, and error angle is then compensated by way of rough tracking, reduces the mission requirements of optic communication load in this way,
So moonlet optic communication load has the characteristics that antenna aperture small (be less than 100mm), small, light-weight, this is just logical to light
Believe that more stringent requirements are proposed for terminal rough tracking system.
The structure that existing rough tracking structure generally uses has periscopic, O-shaped posture, longitude and latitude ceremony or pendulum mirror.It is latent to hope
Formula is suitable for 100mm~150mm bore optical transmitter and receivers；O-shaped posture is suitable for the bigbore optical transmitter and receivers of 200mm~300mm；Put mirror
Need installation space larger；Longitude and latitude ceremony range of deflection is larger (90 °~180 °), is applicable to the satellite light of wide-angle adjusting
Terminal, and weight is big, volume is big, can not be suitable for moonlet optical communication terminal, and the rough tracking device of these types of structure
Mechanical axis is all used, since gear has the problem of gyration aperture, backlash, friction, optical axis error in pointing can be caused.
Utility model content
It can not be logical suitable for moonlet light due to its volume is big, weight is big, precision is low in order to solve existing rough tracking device
The technical issues of believing terminal, the utility model provides a kind of small-sized laser space communication terminal rough tracking device.
The technical solution of the utility model is：
A kind of small-sized laser space communication terminal rough tracking device is applied in moonlet optical communication system；It is described small
Intersatellite Optical Communication System includes satelloid；The rough tracking device includes optical transmitter and receiver and pedestal；It is characterized in that：
Further include two degrees of freedom flexible hinge, azimuth axis line style actuator and pitch axis line style actuator, the first current vortex
Displacement sensor and the second eddy current displacement sensor, the driver of line style actuator and eddy current displacement sensor it is preposition
Device；
Optical transmitter and receiver is mounted on by the two degrees of freedom flexible hinge on pedestal；The revolution of the two degrees of freedom flexible hinge
Center is overlapped with the centre of gyration of optical transmitter and receiver；
Azimuth axis line style actuator is identical as the structure of pitch axis line style actuator；The azimuth axis line style actuator includes
Mover, flexible link and stator；One end of mover and one end of flexible link connect；The other end of flexible link connects with optical transmitter and receiver mounting surface
It connects；The other end of mover stretches into stator, is wound with coil outside mover, permanent magnet is provided between coil and stator；
Azimuth axis line style actuator is connected with optical transmitter and receiver with the flexible link of pitch axis line style actuator, stator be used to by
Actuator is integrally connected with the satelloid；Azimuth axis line style actuator is located at optical transmitter and receiver revolution with pitch axis line style actuator
0 ° of center and 90 ° of orientation, and the distance of the two to the optical transmitter and receiver centre of gyration is equal；
The structure of first eddy current displacement sensor and the second eddy current displacement sensor is identical, is mounted on the satellite
On body；First eddy current displacement sensor is for detecting optical transmitter and receiver at the test point corresponding to the first eddy current displacement sensor
Displacement of the lines, the second eddy current displacement sensor is for detecting optical transmitter and receiver at the test point corresponding to the second eddy current displacement sensor
Displacement of the lines；The installation center and light of the installation center of first eddy current displacement sensor, the pitch axis line style actuator
The centre of gyration three of terminal is conllinear；The installation of the installation center, azimuth axis line style actuator of second eddy current displacement sensor
The centre of gyration three of center and optical transmitter and receiver is conllinear；First eddy current displacement sensor and the second eddy current displacement sensor arrive
The distance of the optical transmitter and receiver centre of gyration is equal；
Driver is for driving the azimuth axis line style actuator and pitch axis line style actuator operation；Fore-lying device is used for will
The detectable signal of first eddy current displacement sensor and the second eddy current displacement sensor is amplified, is filtered；It drives
Dynamic device and fore-lying device are installed on the pedestal.
Further, the cutting section of above-mentioned two degrees of freedom flexible hinge is parabolic type, hyperbolic-type, cartwheel
Type or ellipse.
Further, the cutting section of above-mentioned two degrees of freedom flexible hinge is ellipse.
Further, there is said base cavity, the driver and fore-lying device to be arranged in the cavity.
Further, above-mentioned second eddy current displacement sensor is outer for anti-electric magnetic disturbance in probe including probe, setting
Shell, connection screw thread bar, support base and cable；Connection screw thread bar is integrated with shell, by upper fastening nut with it is lower tight
Gu nut is mounted on the support base；Support base lower end offers the connecting hole for connecting satelloid；Cable is stretched from shell
Go out and is connected with the fore-lying device.
Compared with prior art, the advantages of the utility model：
1, the utility model is avoided using the regulative mode of 2 points of drivings of line style actuator using pitching orientation frame strip
The problem that next volume is big, weight is big；Line style actuator thrust is big, small, light-weight, displacement accuracy is high, and weight is controllable
System is within 1Kg, and flexible hinge weight is within 0.5Kg, in addition necessary connecting joint, rough tracking device total weight is controllable
System is in 2~3Kg；Qualitative attribute promotes 2 times or more compared with prior art, and line style actuator displacement accuracy and current vortex displacement pass
For sensor accuracy of detection up to um ranks, the difference of the distance according to installation site apart from the centre of gyration realizes angular displacement essence
Degree is controllable.
2, due to rough tracking need not be very high bandwidth, the utility model use the asymmetric mounting means of two point form
Line style actuator is installed, compared to traditional bikini and four point symmetry type mounting means, two point form structure small light degree
Higher.
3, the two degrees of freedom flexible hinge of the utility model uses cutting section that can expire simultaneously for the flexible hinge of ellipse
Sufficient flexibility and degree of regulation.
4, optical transmitter and receiver is connected by the utility model using flexible hinge with pedestal, compared to the rough tracking of existing machinery shafting
Device, with no backlash, without friction, gapless, noiseless, without abrasion, bulk is small, autokinesis is high, fortune easy to control
The advantages that dynamic stability and high angular displacement precision.
5, line style actuator mover is connected by the utility model using flexible link with optical transmitter and receiver, and flexible link is axially square
To there is good rigidity, and have preferable flexibility in its tangential direction, can to avoid due to optical transmitter and receiver moves when cause it is excessive
Shearing force and damage line style actuator.
6, on the one hand the pedestal of the utility model can provide support for flexible hinge, have cavity in another aspect pedestal,
The fore-lying device of the driver of line style actuator and eddy current displacement sensor is placed in the cavity of pedestal, is further reduced
Tracks of device volume.
Description of the drawings
Fig. 1 is that the structure after the small-sized laser space communication terminal rough tracking device of the utility model is connect with satelloid is shown
It is intended to；
Fig. 2 is the schematic view of the mounting position of line style actuator and flexible hinge；
Fig. 3 is the shafting schematic diagram that azimuth axis line style actuator and the second eddy current displacement sensor form；
Fig. 4 is the shafting schematic diagram that pitch axis line style actuator and the first eddy current displacement sensor form；
Fig. 5 a are azimuth axis line style actuator construction schematic diagram；
State diagram when Fig. 5 b are azimuth axis line style actuator operation shown in Fig. 5 a；
Fig. 6 a are two degrees of freedom flexible hinge schematic diagram；
Fig. 6 b are driver, the scheme of installation of two degrees of freedom flexible hinge shown in fore-lying device and Fig. 6 a；
Fig. 7 a are the second eddy current displacement sensor structural schematic diagram；
Fig. 7 b are the second eddy current displacement sensor axonometric drawing shown in Fig. 7 a；
Fig. 8 be azimuth direction movement relation schematic diagram (pitching is identical with azimuth motion relationship, therefore only provides orientation side
To schematic diagram)；
Reference sign：1- optical transmitter and receivers；101- optical transmitter and receiver mounting surfaces；2- two degrees of freedom flexible hinges；3- azimuth axis
Type actuator；301- fastening nuts；302- gaskets；304- threaded holes；305- flexible links；306- permanent magnets；307- movers；308-
Stator；309- coils；4- pitch axis line style actuators；The first eddy current displacement sensors of 5-；The second current vortex displacements of 6- sense
Device；601- pops one's head in；602- shells；603- connection screw thread bars；The upper fastening nuts of 604-；605- fulcrum bearings；Fastening nut under 606-；
607- connecting holes；608- cables；7- satelloids；8- pedestals；801- drivers；802- fore-lying devices.
Specific implementation mode
It elaborates to the utility model below in conjunction with attached drawing.
Referring to Fig. 1-Fig. 2, small-sized laser space communication terminal rough tracking device provided by the utility model, including light
The equal azimuth axis line style actuator 3 of terminal 1, two degrees of freedom flexible hinge 2, load inertia and pitch axis line style actuator 4,
One eddy current displacement sensor 5, the second eddy current displacement sensor 6 and pedestal 8.
Optical transmitter and receiver 1 is mounted on by two degrees of freedom flexible hinge 2 on pedestal 8, the centre of gyration of two degrees of freedom flexible hinge 2
It is overlapped with the centre of gyration of optical transmitter and receiver 1；The flexible shaft cut surface of two degrees of freedom flexible hinge 2 can be parabolic type, hyperbola
Type, cartwheel types etc.；Incline in order to balance swinging range and angular accuracy, the flexible shaft cut surface of two degrees of freedom flexible hinge 2
It is preferred that ellipse；Entire rough tracking device is connect by pedestal 8 with satelloid 7；The drive of line style actuator is also equipped in pedestal 8
The fore-lying device 802 of dynamic device 801 and eddy current displacement sensor.Driver 801 and the placement form of fore-lying device 802 are not limited to
Form shown in Fig. 6 b, the size of pedestal 8 are also not limited to size shown in Fig. 6 b, actual size can according to driver 801 with
The specific size of fore-lying device 802 designs.
Azimuth axis line style actuator 3 is identical with pitch axis line style 4 structures of actuator, azimuth axis line style actuator 3 it is specific
Structure as shown in figure 5 a and 5b, including mover 307, flexible link 305, stator 308, fastening nut 301, gasket 302；Mover
307 one end is connect by threaded hole 304 with one end of flexible link 305；The other end of flexible link 305 and optical transmitter and receiver mounting surface
101 are threadedly coupled, and are fastened by gasket 302 and fastening nut 301；The other end of mover 307 stretches into stator 308, mover
It is wound with coil 309 outside 307, permanent magnet 306 is provided between coil 309 and stator 308；Flexible link can reduce line style actuator
Damage of the shearing force generated to line style actuator is acted, while the rigidity when push-and-pull of line style actuator being provided.
Azimuth axis line style actuator 3, pitch axis line style actuator 4 flexible link be connected with optical transmitter and receiver 1, stator passes through
Screw is connected with satelloid 7；Also, azimuth axis line style actuator 3 and pitch axis line style actuator 4 are located in the revolution of optical transmitter and receiver 1
0 ° of the heart and 90 ° of orientation, and the distance of the two to 1 centre of gyration of optical transmitter and receiver is equal；Pass through 3 He of control azimuth axis type actuator
The size of current of 4 mover coil of pitch axis line style actuator, control Lorentz force are pushed away to push its flexible link, then by flexible link
Dynamic optical transmitter and receiver 1 makees orientation and pitching movement；Fig. 8 is the movement relation schematic diagram of azimuth direction, and M points and N point lines are side in figure
The axis of bit line type actuator 3, M points are the tie point of flexible link 305 and optical transmitter and receiver 1；M points and O point lines are light end before movement
The initial position of machine mounting surface 101, the distance between M points and O points are L；O points and P point lines are flexible hinge rotating shaft axis,
Point N is the axis and 7 intersection point of satelloid of orientation line style actuator 3, and point P is the rotating shaft and satellite of two degrees of freedom flexible hinge 2
7 intersection point of body；HO is after optical transmitter and receiver 1 is driven by orientation line style actuator 3, and the new position of optical transmitter and receiver mounting surface 101, Q points are from H points
The intersection point obtained to MO as vertical line；If distance is Δ x between MQ, the distance between HQ is Δ y, can obtain optical transmitter and receiver 1 in side
Position direction rotational angle be：
First eddy current displacement sensor 5 is identical with 6 structure of the second eddy current displacement sensor, and the second current vortex displacement passes
The structure of sensor 6 as illustrated in figs. 7 a and 7b, including probe 601, be arranged probe 601 outside for anti-electric magnetic disturbance shell 602,
Connection screw thread bar 603；Connection screw thread bar 603 is integrated with shell 602, passes through upper fastening nut 604 and lower fastening nut 606
On support base 605；Support base 605 is mounted on by the connecting hole 607 of its lower end on satelloid 7；Cable 608 is from shell
602 stretchings are connected with the fore-lying device 802 of eddy current displacement sensor, detectable signal are sent to fore-lying device 802, by fore-lying device
The processing such as 802 pairs of signals are amplified, filter, detection, are then transferred to master control computer on the star of moonlet optical communication system,
The rotational angle of 1 current pitching of optical transmitter and receiver and/or azimuth axis is obtained by calculation in master control computer on star；
First eddy current displacement sensor 5 is for detecting optical transmitter and receiver 1 in the 5 corresponding detection of the first eddy current displacement sensor
Displacement of the lines at point, the first eddy current displacement sensor 5 are mounted on by its support base on satelloid 7, the first current vortex displacement
The centre of gyration three of the installation center of sensor 5, the installation center of pitch axis line style actuator 4 and optical transmitter and receiver 1 is conllinear；The
Two eddy current displacement sensors 6 are for detecting line position of the optical transmitter and receiver 1 at the test point corresponding to the second eddy current displacement sensor 6
It moves, the second eddy current displacement sensor 6 is mounted on by its support base on satelloid 7, the peace of the second eddy current displacement sensor 6
The centre of gyration three at dress center, the installation center of azimuth axis line style actuator 3 and optical transmitter and receiver 1 is conllinear；First current vortex position
The distance of displacement sensor 5 and the second eddy current displacement sensor 6 to 1 centre of gyration of optical transmitter and receiver is equal；First current vortex displacement passes
The specific installation site of sensor 5 and the second eddy current displacement sensor 6 can be determined according to range；After the completion of assembly, the first electricity
Eddy displacement sensor 5 constitutes a shafting, the second eddy current displacement sensor 6 and azimuth axis with pitch axis line style actuator 4
Line style actuator 3 constitutes a shafting, as shown in Figure 3, Figure 4.
Claims (5)
1. a kind of small-sized laser space communication terminal rough tracking device is applied in moonlet optical communication system；The little Wei
Starlight communication system includes satelloid (7)；The rough tracking device includes optical transmitter and receiver (1) and pedestal (8)；It is characterized in that：
Further include two degrees of freedom flexible hinge (2), azimuth axis line style actuator (3) and pitch axis line style actuator (4), the first electricity
Eddy displacement sensor (5) and the second eddy current displacement sensor (6), the driver (801) of line style actuator and current vortex position
The fore-lying device (802) of displacement sensor；
Optical transmitter and receiver (1) is mounted on by the two degrees of freedom flexible hinge (2) on pedestal (8)；The two degrees of freedom flexible hinge
(2) the centre of gyration is overlapped with the centre of gyration of optical transmitter and receiver (1)；
Azimuth axis line style actuator (3) is identical as the structure of pitch axis line style actuator (4)；The azimuth axis line style actuator
(3) include mover (307), flexible link (305) and stator (308)；One end of mover (307) connects with one end of flexible link (305)
It connects；The other end of flexible link (305) is connect with optical transmitter and receiver mounting surface (101)；The other end of mover (307) stretches into stator (308)
It is interior, it is wound with coil (309) outside mover (307), permanent magnet (306) is provided between coil (309) and stator (308)；
Azimuth axis line style actuator (3) is connected with optical transmitter and receiver (1) with the flexible link of pitch axis line style actuator (4), and stator is equal
For actuator entirety to be connected with the satelloid (7)；Azimuth axis line style actuator (3) and pitch axis line style actuator
(4) it is located at 0 ° and 90 ° of orientation of optical transmitter and receiver (1) centre of gyration, and the distance of the two to optical transmitter and receiver (1) centre of gyration is equal；
First eddy current displacement sensor (5) is identical with the structure of the second eddy current displacement sensor (6), is mounted on described defend
On celestial body (7)；First eddy current displacement sensor (5) is for detecting optical transmitter and receiver (1) in the first eddy current displacement sensor (5) institute
Displacement of the lines at corresponding test point, the second eddy current displacement sensor (6) is for detecting optical transmitter and receiver (1) in the second current vortex displacement
Displacement of the lines at test point corresponding to sensor (6)；The installation center of first eddy current displacement sensor (5), the pitch axis
The installation center of line style actuator (4) and the centre of gyration three of optical transmitter and receiver (1) are conllinear；Second eddy current displacement sensor
(6) installation center of installation center, azimuth axis line style actuator (3) and the centre of gyration three of optical transmitter and receiver (1) are conllinear；The
The distance of one eddy current displacement sensor (5) and the second eddy current displacement sensor (6) to optical transmitter and receiver (1) centre of gyration is equal；
Driver (801) is for driving the azimuth axis line style actuator (3) to be acted with pitch axis line style actuator (4)；It is preposition
Device (802) be used for by the detectable signal of first eddy current displacement sensor (5) and the second eddy current displacement sensor (6) into
Row amplification is filtered；Driver (801) and fore-lying device (802) are installed on the pedestal (8).
2. small-sized laser space communication terminal rough tracking device according to claim 1, it is characterised in that：Described two certainly
It is parabolic type, hyperbolic-type, cartwheel types or ellipse by the cutting section of degree flexible hinge (2).
3. small-sized laser space communication terminal rough tracking device according to claim 2, it is characterised in that：Described two certainly
It is ellipse by the cutting section of degree flexible hinge (2).
4. small-sized laser space communication terminal rough tracking device according to claim 1 or 2 or 3, it is characterised in that：Institute
Stating pedestal (8), there is cavity, the driver (801) and fore-lying device (802) to be arranged in the cavity.
5. small-sized laser space communication terminal rough tracking device according to claim 4, it is characterised in that：Described second
Eddy current displacement sensor (6) include probe (601), setting probe (601) outside be used for anti-electric magnetic disturbance shell (602),
Connection screw thread bar (603), support base (605) and cable (608)；Connection screw thread bar (603) is integrated with shell (602), is led to
Fastening nut (604) is crossed to be mounted on the support base (605) with lower fastening nut (606)；Support base (605) lower end opens up
It is useful for the connecting hole (607) of connection satelloid (7)；Cable (608) stretches out and the fore-lying device (802) phase from shell (602)
Even.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721772371.7U CN207638661U (en) | 2017-12-18 | 2017-12-18 | A kind of small-sized laser space communication terminal rough tracking device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721772371.7U CN207638661U (en) | 2017-12-18 | 2017-12-18 | A kind of small-sized laser space communication terminal rough tracking device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207638661U true CN207638661U (en) | 2018-07-20 |
Family
ID=62863988
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721772371.7U Withdrawn - After Issue CN207638661U (en) | 2017-12-18 | 2017-12-18 | A kind of small-sized laser space communication terminal rough tracking device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207638661U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108039913A (en) * | 2017-12-18 | 2018-05-15 | 中国科学院西安光学精密机械研究所 | A kind of small-sized laser space communication terminal rough tracking device |
| CN113602536A (en) * | 2021-07-15 | 2021-11-05 | 西北工业大学 | Dynamic stiffness on-orbit monitoring device and method for space inflation expandable support structure |
-
2017
- 2017-12-18 CN CN201721772371.7U patent/CN207638661U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108039913A (en) * | 2017-12-18 | 2018-05-15 | 中国科学院西安光学精密机械研究所 | A kind of small-sized laser space communication terminal rough tracking device |
| 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 |
| CN113602536A (en) * | 2021-07-15 | 2021-11-05 | 西北工业大学 | Dynamic stiffness on-orbit monitoring device and method for space inflation expandable support structure |
| CN113602536B (en) * | 2021-07-15 | 2023-06-23 | 西北工业大学 | Dynamic stiffness on-orbit monitoring device and method for space inflatable expandable support structure |
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