CN107579773B - Space laser transmission simulation system - Google Patents
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- CN107579773B CN107579773B CN201710854716.1A CN201710854716A CN107579773B CN 107579773 B CN107579773 B CN 107579773B CN 201710854716 A CN201710854716 A CN 201710854716A CN 107579773 B CN107579773 B CN 107579773B
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Abstract
The application discloses a space laser transmission simulation system, which comprises n single-stage optical systems; wherein n is an integer greater than or equal to 1; the single stage optical system includes: an object distance displacement reading encoder, a first guide rail and a second guide rail; the light inlet hole is used for receiving laser emitted by the laser communication terminal to be detected or receiving laser emitted by the superior optical system; the imaging lens group is used for carrying out amplification imaging on light rays transmitted from the light inlet hole; the first motor is used for adjusting the object distance of the imaging lens group; the folding lens group is used for compensating the image distance of the imaging lens group; the second motor is used for driving the second guide rail to move the folding mirror group; an image distance displacement reading encoder; the laser light source is used for transmitting the laser light emitted by the folding lens group to a light inlet of a lower optical system or a light outlet of a preset photoelectric receiving device. The invention realizes the simulation of space laser transmission at any distance by selecting the number of cascaded single-stage optical systems and the amplification factor of each stage of optical system.
Description
Technical Field
The invention relates to the field of space laser communication, in particular to a space laser transmission simulation system.
Background
In the field of spatial laser communication, the distribution of far-field energy of laser light directly affects the performance of spatial communication. However, space laser communication has the characteristics of high development cost, long period and the like, so that ground simulation experiments are particularly important. Because the distance of space communication is very far away, the distance of ground simulation experiment simulation is limited, and most of the situations depend on short-distance outfield equivalent test verification, such as the communication experiment between two ships, two mountains and unmanned aerial vehicles. However, the existence of atmospheric interference makes the experimental result have great difference from the actual situation of space communication, the reliability of the experimental result is not high, especially some terminals whose communication wavelength is not within the range of atmospheric window, so the necessary ground experimental simulation equipment is particularly important.
The prior art satellite laser communication simulation device is shown in fig. 1, and includes a tested optical emission system 01, a fourier transform lens 02, lens groups 03, 04, 05, a half mirror 08, an aperture diaphragm 09, and a photoelectric receiving device 010. With the device, because sampling points of all levels of secondary objects and image sides are fixed, discrete simulation can be carried out only on certain specific distances, however, in actual space communication, the communication distance range is large and continuously variable, obviously, in the prior art, simulation can be carried out only on space laser transmission of specific distances, and practical application of space communication is difficult to meet.
In summary, how to realize the simulation of spatial laser transmission at any distance is a problem to be solved urgently by those skilled in the art.
Disclosure of Invention
In view of the above, an object of the present invention is to provide a spatial laser transmission simulation system, which can realize spatial communication simulation at any distance. The specific scheme is as follows:
a space laser transmission simulation system comprises n single-stage optical systems; wherein n is an integer greater than or equal to 1; the single stage optical system includes:
an object distance displacement reading encoder, a first guide rail and a second guide rail;
the light inlet hole is used for receiving laser emitted by the laser communication terminal to be detected or receiving laser emitted by the superior optical system;
the imaging lens group is used for carrying out amplification imaging on the light rays transmitted from the light inlet hole;
the first motor is connected with the object distance displacement reading encoder and used for adjusting the object distance of the imaging lens group by driving the first guide rail;
the folding mirror group is used for compensating the image distance of the imaging mirror group in a moving state;
the second motor is used for driving the second guide rail to move the folding mirror group;
an image distance displacement reading encoder connected with the second motor;
and the laser emitted by the folding lens group is transmitted to a light inlet of a lower optical system or a light outlet of a preset photoelectric receiving device.
Optionally, the imaging lens group and the folding lens group both adopt reflecting mirrors; the folding mirror group adopts a plane reflecting mirror.
Optionally, the rotation angles of the mirrors adopted by the imaging mirror group are the same.
Optionally, the plane mirrors adopted by the folding mirror group are mutually perpendicular, and acute angles formed by the plane mirrors and the horizontal direction are all 45 degrees.
Optionally, the spatial laser transmission simulation system further includes:
and the collimator is used for converging the laser emitted by the laser communication terminal to be detected into a light spot and irradiating the light spot to the light inlet hole of the primary optical system.
Optionally, the spatial laser transmission simulation system further includes:
and the optical fiber sampling device is positioned behind the light outlet hole of the final optical system.
Optionally, the single-stage optical system further includes:
and the first limiting device is used for controlling the moving range of the object distance.
Optionally, the single-stage optical system further includes:
and the second limiting device is used for controlling the image distance moving range.
Optionally, the spatial laser transmission simulation system further includes:
the guide rail theoretical displacement calculation module is used for calculating the theoretical displacement of the first motor for moving the first guide rail and the theoretical displacement of the second motor for moving the second guide rail;
and the guide rail actual displacement determining module is used for determining the actual displacement of the first guide rail moved by the first motor and the actual displacement of the second guide rail moved by the second motor, sending the actual displacement of the first guide rail moved to the first motor and sending the actual displacement of the second guide rail moved to the second motor.
Optionally, the module for calculating theoretical displacement of guide rail includes:
a target magnification calculation unit for calculating the magnification of the space laser transmission simulation system according to the required simulation distance to obtain the target magnification, wherein the formula for calculating the target magnification is β ═ Ld1/Ddfpd; l is the desired simulated distance, d1As primary opticsThe diameter of a light inlet hole of the system, D is the caliber of the collimator, and D is the diameter of an optical fiber in the optical fiber sampling device; f. ofpIs the focal length of the collimator;
the system magnification determination units at all levels are used for determining the number of the single-stage optical systems of the space laser transmission simulation system and the actually required magnification of each optical system according to the target magnification;
the theoretical displacement determining unit is used for calculating the theoretical displacement of the first guide rail and the theoretical displacement of the second guide rail according to the guide rail theoretical position calculation formula by the magnification of each stage of optical system; wherein, the guide rail position calculation formula is as follows:
lobj-i＝-f(1/β0i-1/βi)
lima-i＝f[(1/βi+βi)-(1/β0i+β0i)]/2
in the formula Iobj-iWhen the current magnification of the i-th order optical system is the actually required magnification βiThe position of the first guide rail; lima-iWhen the current magnification of the i-th order optical system is the actually required magnification βiPosition of said second guide rail β0iMinimum magnification of the i-th order optical system βiSetting the current magnification of the ith-level optical system as the actually required magnification; f is the focal length of the imaging lens group of the ith-level optical system, and i is more than or equal to 1 and less than or equal to n.
Optionally, the guide rail actual displacement determining module is configured to correct errors of the theoretical displacement of the first guide rail and the theoretical displacement of the second guide rail, and obtain an actual displacement of the first guide rail and an actual displacement of the second guide rail according to a guide rail actual position calculation formula;
wherein the error comprises a system error generated by mirror surface installation debugging, guide rail preliminary positioning and encoder zero position; the calculation formula of the actual position of the guide rail is as follows:
of formula (II) to'obj-iWhen the current magnification of the i-th order optical system is the actually required magnification βiCorrected actual position of the first guide rail l'ima-iWhen the current magnification of the i-th order optical system is the actually required magnification βiCorrected actual position of said second guide rail β0iMinimum magnification of the i-th order optical system βiSetting the current magnification of the ith-level optical system as the actually required magnification; deltaobj-iWhen the current magnification of the i-th order optical system is the minimum magnification β0iError between the actual position of the first guide rail and the theoretical zero position, Δima-iWhen the current magnification of the i-th order optical system is the minimum magnification β0iThe error between the actual position of the second guide rail and the theoretical zero position.
Therefore, the space laser transmission simulation system disclosed by the invention selects the number of the cascaded single-stage optical systems and determines the amplification factor of each stage of optical system according to the distance to be simulated actually, so as to realize the simulation of the distance to be simulated actually, namely, the simulation of the space laser transmission at any distance is realized by selecting the number of the cascaded single-stage optical systems and the amplification factor of each stage of optical system.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a spatial laser communication simulation apparatus in the prior art;
fig. 2 is a schematic structural diagram of a four-stage cascade spatial laser transmission simulation system according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a single-stage optical system of the space laser transmission simulation system according to an embodiment of the present invention;
fig. 4 is a schematic diagram illustrating the positions and optical paths of a folding mirror set in a single-stage optical system of a spatial laser transmission simulation system according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of the optical path and transmission of laser light in a collimator according to an embodiment of the present invention;
fig. 6 is a schematic diagram of an output connection of an optical fiber sampling device according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention discloses a space laser transmission simulation system, which comprises n single-stage optical systems; wherein n is an integer greater than or equal to 1; the structural diagram of the system when n is 4 is shown in fig. 2, and the structural diagram of the single-stage optical system is shown in fig. 3, including:
the object distance displacement reading encoder 1, the first guide rail 17, and the second guide rail 18;
a light inlet 5 for receiving the laser emitted by the laser communication terminal to be tested or receiving the laser emitted by the superior optical system;
an imaging lens group 13 for magnifying and imaging the light transmitted from the light inlet hole;
the first motor 3 is connected with the object distance displacement reading encoder 1 and is used for adjusting the object distance of the imaging lens group 13 by driving the first guide rail 17;
a folding mirror group 9 for compensating the image distance of the imaging mirror group 13 in a moving state;
a second motor 12 for moving the folding mirror group 9 by driving a second guide rail 18;
an image distance displacement reading encoder 2 connected to the second motor 12;
and the laser light is used for transmitting the laser light emitted by the folding lens group 9 to a light inlet of a lower optical system or a light outlet of a preset photoelectric receiving device.
In this embodiment, the number of cascaded single stage optical systems is selected based on the desired simulated distance. The object distance displacement reading encoder 1 is used for reading the object distance of the imaging lens group 13, the image distance displacement reading encoder 2 is used for reading the image distance of the imaging lens group 13, and the light inlet hole 5 is usually a sampling hole and mainly used for sampling the central position of a light spot with a larger diameter.
Specifically, the sampling hole is a star point with a certain size, on one hand, sampling and selecting of light energy at the central position can be completed, on the other hand, unnecessary marginal light bands can be blocked, and the situation that the marginal light bands enter a follow-up system through irregular reflection to form stray light and interfere with an experiment is avoided.
The imaging lens group in the prior art uses lenses, and the prior art is only suitable for laser communication with a single wavelength due to chromatic aberration of the lenses, while the wavelengths of the laser generated by different types of lasers are different, for example: the wavelengths generated by the blue-violet laser are 375nm and 405nm, the wavelengths generated by the blue laser are 450nm, 457nm and 473nm, and the wavelength of the laser generated by the green laser is 532nm, thus limiting the applications thereof.
In the embodiment, the imaging lens group 13 adopts a reflecting mirror, and the reflecting mirror has no chromatic aberration, so that the imaging lens group is suitable for laser communication with any wavelength. Further, the imaging lens group 13 employs a spherical mirror, and the rotation angles of the mirror surfaces are the same, so as to ensure that the principal ray is always parallel to the guide rail. The folding mirror group 9 adopts two plane mirrors, the position and the light path schematic diagram of the plane mirrors are shown in fig. 4, the two plane mirrors are mutually perpendicular, and the acute angle formed by the two plane mirrors and the horizontal direction is 45 degrees. The folding mirror group 9 can compensate the image distance on one hand, and on the other hand, the length of the space laser communication simulation system device provided by the invention is shortened and the space is saved by changing the direction of the light path.
It should be noted that the amount of movement of the objective lens and the image distance compensation distance associated with the imaging lens group 13 and the folding lens group 9 are settled by external software, and are sent to the motor and the encoder through signal lines to perform the translational movement.
Therefore, the space laser transmission simulation system disclosed in the embodiment of the present invention selects the number of the cascaded single-stage optical systems and determines the amplification factor of each stage of optical system according to the distance to be simulated actually, so as to realize the simulation of the distance to be simulated actually.
Further, in order to make the energy of the laser beam in the space laser transmission simulation system more concentrated, the space laser transmission simulation system disclosed in the embodiment of the present invention further includes:
and the collimator is used for converging the laser emitted by the laser communication terminal to be detected into a light spot and irradiating the light spot to the light inlet hole of the primary optical system.
In the actual simulation, the collimator adopts a reflective collimator, and the light path and transmission diagram of the laser in the collimator are shown in fig. 5.
Further, in order to evaluate the final imaging quality of the spatial laser transmission simulation system, the spatial laser transmission simulation system disclosed in the embodiment of the present invention further includes:
and the optical fiber sampling device 19 is positioned behind the light outlet hole of the final optical system.
The output connection diagram of the optical fiber sampling device 19 is shown in fig. 6, and includes:
the optical fiber sampling device comprises an optical fiber 23, optical fiber seats 24 and 25, an optical fiber seat, an optical fiber adjusting hole 26, an optical fiber connecting plate 27 and an optical fiber sampling fixing hole 28.
Further, in order to make the distance of the simulation test of the space laser transmission simulation system provided by the embodiment of the present invention more pertinent, the single-stage optical system further includes:
a first limiting device 14 for controlling the moving range of the object distance;
and a second limiting device 11 for controlling the image distance moving range.
It can be understood that the range of the magnification of the imaging lens group is determined by controlling the moving range of the object distance, for example, in a specific application, the variation range of the magnification of each stage of the optical system is 3-12 times.
Furthermore, in order to make the space laser transmission simulation system provided by the embodiment of the invention intelligent, the space laser transmission simulation system further comprises a guide rail theoretical displacement calculation module and a guide rail actual displacement calculation module; in particular, the method comprises the following steps of,
the guide rail theoretical displacement calculation module is used for calculating the theoretical displacement of the first motor for moving the first guide rail and the theoretical displacement of the second motor for moving the second guide rail;
and the guide rail actual displacement determining module is used for determining the actual displacement of the first motor for moving the first guide rail and the actual displacement of the second motor for moving the second guide rail, and sending the actual displacement of the first guide rail for moving to the first motor and the actual displacement of the second guide rail for moving to the second motor.
It should be noted that the above-mentioned theoretical displacement calculation module of the guide rail and the actual displacement calculation module of the guide rail are control programs in an automatic control device, and the automatic control device may be corresponding control software, may be located in a computer, and of course, may also be located in a motor or a reading encoder in an intelligent chip manner.
Further, the guide rail theoretical displacement calculation module comprises a target amplification factor calculation unit, a system amplification factor determination unit of each level and a theoretical displacement determination unit; in particular, the method comprises the following steps of,
a target magnification calculation unit for calculating the magnification of the space laser transmission simulation system according to the required simulation distance to obtain the target magnification, wherein the formula for calculating the target magnification is β ═ Ld1/Ddfpd; l is the desired simulated distance, d1The diameter of a light inlet hole of a primary optical system, D is the caliber of the collimator, and D is the diameter of an optical fiber in the optical fiber sampling device; f. ofpIs that it isThe focal length of the collimator;
the system magnification determination units at all levels are used for determining the number of the single-stage optical systems of the space laser transmission simulation system and the actually required magnification of each optical system according to the target magnification;
the theoretical displacement determining unit is used for calculating the theoretical displacement of the first guide rail and the theoretical displacement of the second guide rail according to the guide rail theoretical position calculation formula by the magnification of each stage of optical system; wherein, the guide rail position calculation formula is as follows:
lobj-i＝-f(1/β0i-1/βi)
lima-i＝f[(1/βi+βi)-(1/β0i+β0i)]/2
in the formula Iobj-iWhen the current magnification of the i-th order optical system is the actually required magnification βiThe position of the first guide rail; lima-iWhen the current magnification of the i-th order optical system is the actually required magnification βiPosition of said second guide rail β0iMinimum magnification of the i-th order optical system βiSetting the current magnification of the ith-level optical system as the actually required magnification; f is the focal length of the imaging lens group of the ith-level optical system, and i is more than or equal to 1 and less than or equal to n.
Note that β0iThe instrument is calibrated by a limiting device after the instrument is developed.
In this embodiment, the guide rail actual displacement determining module is configured to correct errors of a theoretical displacement of the first guide rail and a theoretical displacement of the second guide rail, and obtain an actual displacement of the first guide rail and an actual displacement of the second guide rail according to a guide rail actual position calculation formula;
the errors comprise system errors generated by mirror surface installation and debugging, guide rail preliminary positioning and encoder zero position; the calculation formula of the actual position of the guide rail is as follows:
of formula (II) to'obj-iWhen the current magnification of the i-th order optical system is the actually required magnification βiCorrected actual position of the first guide rail l'ima-iWhen the current magnification of the i-th order optical system is the actually required magnification βiCorrected actual position of said second guide rail β0iMinimum magnification of the i-th order optical system βiSetting the current magnification of the ith-level optical system as the actually required magnification; deltaobj-iWhen the current magnification of the i-th order optical system is the minimum magnification β0iError between the actual position of the first guide rail and the theoretical zero position, Δima-iWhen the current magnification of the i-th order optical system is the minimum magnification β0iThe error between the actual position of the second guide rail and the theoretical zero position.
For example, when the single-stage optical system of the space laser transmission simulation system has 4 stages, the aperture of the collimator is DpThe aperture of the measured terminal is D, and the focal length of the collimator is fpThe diameter of the primary sampling hole 15 is d1The diameter of the secondary sampling hole 16 is d2And three to four are d3、d4Finally, the optical fiber hole of the optical fiber sampling 19 is d, the focal length of each stage of imaging lens group 13 is f, the devices of each stage are completely consistent, and the magnification change of each stage is β without considering the assembly errormin～βmaxAnd the initial positions are all at βminHere, the minimum simulation distance of the system is LminAccording to the sampling principle of the system, the minimum simulation distance in the four-level cascade mode is as follows:
maximum simulated distance LmaxSatisfying the following equation.
The process of arbitrarily modeling the distance L includes the steps of:
step 1: and obtaining the magnification according to the required distance, namely:
β＝Ld1/Ddfpd (3)
And step 3: the magnification of each order is directly determined according to Gaussian optics when needing to be changed, as shown in formula (5).
Wherein f is the focal length of the object space, f 'is the focal length of the image space, x is the distance between the imaged object and the focal point of the object space, and x' is the distance between the imaged object and the focal point of the image space.
And 4, according to the requirement β, determining the displacement of any secondary objective guide rail according to the following formula, and regulating the displacement to be positive along the optical axis direction.
And 5: the formula (6) is a theoretical displacement determined according to the magnification, in practice, due to the existence of system errors such as mirror surface installation and adjustment, guide rail initial positioning, encoder zero position and the like, the shaft movement rule needs to be calibrated and eliminated, the formula (6) is corrected after the elimination, and the correction result is as shown in (7).
Step 6: if the simulated distance is less than LminI.e. solved β<β4 minThe system can also be made to operate in the following mode.
The embodiment of the invention also provides a specific application process for simulating different distances by using the space laser transmission simulation system, which comprises the following steps:
assuming that the minimum simulation distance is 10km, the magnification of each order is changed to 3-12 times, the focal length of the optical system is 50mm, and assuming that the system is not corrected. The magnification of each order is shown in table 1 at different simulated distances.
TABLE 1 numerical relationship between the moving position, magnification and simulated distance of guide rails at each stage
The initial magnification β of each level in the above calculation 03, if the system accurately corrects the variation range of the focal length and the magnification, the calculation is carried out according to the formula (7), and the calculation process is carried out by control software.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The space laser transmission simulation system provided by the invention is described in detail, and the principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (10)
1. A space laser transmission simulation system is characterized by comprising n single-stage optical systems; wherein n is an integer greater than or equal to 1; the single stage optical system includes:
an object distance displacement reading encoder, a first guide rail and a second guide rail;
the light inlet hole is used for receiving laser emitted by the laser communication terminal to be detected or receiving laser emitted by the superior optical system;
the imaging lens group is used for carrying out amplification imaging on the light rays transmitted from the light inlet hole;
the first motor is connected with the object distance displacement reading encoder and used for adjusting the object distance of the imaging lens group by driving the first guide rail;
the folding mirror group is used for compensating the image distance of the imaging mirror group in a moving state;
the second motor is used for driving the second guide rail to move the folding mirror group;
an image distance displacement reading encoder connected with the second motor;
the laser emitted by the folding lens group is transmitted to a light inlet of a lower optical system or a light outlet of a preset photoelectric receiving device;
the space laser transmission simulation system selects the number of cascaded single-stage optical systems and determines the amplification factor of each stage of optical system according to the distance to be simulated actually so as to realize the distance to be simulated actually;
the movement amount of the objective lens and the image distance compensation distance related to the imaging lens group and the folding lens group are calculated through external software and are sent to a corresponding motor and an encoder through signal lines so as to execute translational motion;
and the imaging mirror group is a spherical reflector, and the rotation angles of the mirror surfaces of the spherical reflectors are the same.
2. The spatial laser transmission simulation system according to claim 1, wherein the folding mirror group is a plane mirror.
3. The spatial laser transmission simulation system according to claim 2, wherein the plane mirrors adopted by the folding mirror group are perpendicular to each other, and the acute angles formed by the plane mirrors and the horizontal direction are all 45 degrees.
4. The spatial laser transmission simulation system according to any one of claims 1 to 3, further comprising:
and the collimator is used for converging the laser emitted by the laser communication terminal to be detected into a light spot and irradiating the light spot to the light inlet hole of the primary optical system.
5. The spatial laser transmission simulation system according to claim 4, further comprising:
and the optical fiber sampling device is positioned behind the light outlet hole of the final optical system.
6. The spatial laser transmission simulation system according to claim 5, wherein the single-stage optical system further comprises:
and the first limiting device is used for controlling the moving range of the object distance.
7. The spatial laser transmission simulation system according to claim 6, wherein the single-stage optical system further comprises:
and the second limiting device is used for controlling the image distance moving range.
8. The spatial laser transmission simulation system according to claim 7, further comprising:
the guide rail theoretical displacement calculation module is used for calculating the theoretical displacement of the first motor for moving the first guide rail and the theoretical displacement of the second motor for moving the second guide rail;
and the guide rail actual displacement determining module is used for determining the actual displacement of the first guide rail moved by the first motor and the actual displacement of the second guide rail moved by the second motor, sending the actual displacement of the first guide rail to the first motor and sending the actual displacement of the second guide rail to the second motor.
9. The spatial laser transmission simulation system according to claim 8, wherein the guide rail theoretical displacement amount calculation module includes:
a target magnification calculation unit for calculating the magnification of the space laser transmission simulation system according to the required simulation distance to obtain the target magnification, wherein the formula for calculating the target magnification is β ═ Ld1/Ddfpd; l is the desired simulated distance, d1The diameter of a light inlet hole of a primary optical system, D is the caliber of the collimator, and D is the diameter of an optical fiber in the optical fiber sampling device; f. ofpIs the focal length of the collimator;
the system magnification determination units at all levels are used for determining the number of the single-stage optical systems of the space laser transmission simulation system and the actually required magnification of each optical system according to the target magnification;
the theoretical displacement determining unit is used for determining the theoretical displacement of the first guide rail and the theoretical displacement of the second guide rail according to a guide rail theoretical position calculation formula by the magnification of each stage of optical system; wherein, the guide rail position calculation formula is as follows:
lobj-i＝-f(1/β0i-1/βi)
lima-i＝f[(1/βi+βi)-(1/β0i+β0i)]/2
in the formula Iobj-iWhen the current magnification of the i-th order optical system is the actually required magnification βiThe position of the first guide rail; lima-iWhen the current magnification of the i-th order optical system is the actually required magnification βiPosition of said second guide rail β0iMinimum magnification of the i-th order optical system βiSetting the current magnification of the ith-level optical system as the actually required magnification; f is the focal length of the imaging lens group of the ith-level optical system, and i is more than or equal to 1 and less than or equal to n.
10. The spatial laser transmission simulation system according to claim 8,
the guide rail actual displacement determining module is used for correcting errors of theoretical displacement of the first guide rail and theoretical displacement of the second guide rail and obtaining actual displacement of the first guide rail and actual displacement of the second guide rail according to a guide rail actual position calculation formula;
the error comprises a system error generated by mirror surface installation and debugging, guide rail primary positioning and encoder zero position; the calculation formula of the actual position of the guide rail is as follows:
of formula (II) to'obj-iWhen the current magnification of the i-th order optical system is the actually required magnification βiCorrected actual position of the first guide rail l'ima-iWhen the current magnification of the i-th order optical system is the actually required magnification βiCorrected actual position of said second guide rail β0iMinimum magnification of the i-th order optical system βiSetting the current magnification of the ith-level optical system as the actually required magnification; deltaobj-iWhen the current magnification of the i-th order optical system is the minimum magnification β0iError between the actual position of the first guide rail and the theoretical zero position, Δima-iWhen the current magnification of the i-th order optical system is the minimum magnification β0iThe error between the actual position of the second guide rail and the theoretical zero position.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5185526A (en) * | 1990-10-31 | 1993-02-09 | Grumman Aerospace Corporation | Optical scene generator for testing infrared detector modules |
| CN1434581A (en) * | 2003-02-28 | 2003-08-06 | 中国科学院上海光学精密机械研究所 | Satellite laser communication analog device |
| CN1658539A (en) * | 2005-01-10 | 2005-08-24 | 中国科学院上海光学精密机械研究所 | Space laser communication motion double-terminal long distance transmission analog device |
-
2017
- 2017-09-20 CN CN201710854716.1A patent/CN107579773B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5185526A (en) * | 1990-10-31 | 1993-02-09 | Grumman Aerospace Corporation | Optical scene generator for testing infrared detector modules |
| CN1434581A (en) * | 2003-02-28 | 2003-08-06 | 中国科学院上海光学精密机械研究所 | Satellite laser communication analog device |
| CN1658539A (en) * | 2005-01-10 | 2005-08-24 | 中国科学院上海光学精密机械研究所 | Space laser communication motion double-terminal long distance transmission analog device |
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| CN107579773A (en) | 2018-01-12 |
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