CN111258078B - Internal compensation optical system and light beam stability control method - Google Patents
Internal compensation optical system and light beam stability control method Download PDFInfo
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- CN111258078B CN111258078B CN201911381752.6A CN201911381752A CN111258078B CN 111258078 B CN111258078 B CN 111258078B CN 201911381752 A CN201911381752 A CN 201911381752A CN 111258078 B CN111258078 B CN 111258078B
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- G—PHYSICS
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- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
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- G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
- G02B27/10—Beam splitting or combining systems
- G02B27/106—Beam splitting or combining systems for splitting or combining a plurality of identical beams or images, e.g. image replication
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
- G02B27/10—Beam splitting or combining systems
- G02B27/12—Beam splitting or combining systems operating by refraction only
Abstract
The invention provides an internal compensation optical system and a light beam stability control method, wherein the system comprises a light source, a collimation optical system and a light beam expanding system, wherein the light source is positioned at the image surface position of the collimation optical system, and the light beam expanding system is positioned in a parallel emergent light path of the collimation optical system; the light source is collimated by the collimating optical system to form a parallel light beam incident beam expanding system, and the light beam expanding system is used for expanding incident parallel light beams and then emitting the expanded incident parallel light beams; the light source is longitudinally movable to vary the exit angle of the exit beam of the collimating optical system to compensate for pitch of the carrier. Compared with the prior external stable compensation mode that the posture of the emitted light beam is changed by integrally rotating the optical system, the invention does not need a stable platform with a shaft system, and can obviously reduce the height of the system and the weight. And the structure is more compact, and the adaptability of the system is greatly improved.
Description
Technical Field
The embodiment of the invention relates to the field of optical landing assistance, in particular to an internal compensation optical system and a light beam stability control method.
Background
The optical internal compensation technology can be used in the field of optical carrier landing guide or similar functions. The landing guiding light beam of the airplane is generally a strip-shaped light beam with a large length-width ratio, and the optical compensation is used for carrying out real-time decoupling compensation on the longitudinal and transverse rolling motion of the aircraft platform by controlling the strip-shaped light beam so as to realize the stable effect of the light beam in the visual angle of a pilot.
Currently, most of the existing optical compensation technologies adopt an external stabilization mode for compensation, that is, the whole optical system is loaded on a two-axis stabilization platform, and the two-axis platform is used for counteracting the longitudinal and rolling motions of a carrier platform. However, in this way, since the optical system loaded on the two-axis stabilized platform is not light in weight, the two-axis stabilized platform is often large in structural size and weight in order to improve the load capacity of the two-axis stabilized platform. Meanwhile, a rotating shaft system of the stable platform has a rotating sealing link, and a rubber sealing ring used for rotating sealing has relaxation phenomenon after being in service for a long time, so that the rotating resistance moment of the shaft system can be reduced, and the servo performance of the stable platform is influenced.
Disclosure of Invention
The embodiment of the invention provides an internal compensation optical system and a light beam stability control method, which are used for solving the problems that the optical system is integrally loaded on a two-axis stable platform in the prior art, the structure is complex, the size and the weight are large, and the installation and the use are inconvenient.
In a first aspect, an embodiment of the present invention provides an internal compensation optical system, including a light source, a collimating optical system, and a beam expanding system, where the light source is located at an image plane of the collimating optical system, and the beam expanding system is located in a parallel emergent light path of the collimating optical system;
the light source is collimated by the collimating optical system to form a parallel light beam incident beam expanding system, the light beam expanding system is used for expanding incident parallel light beams and emitting the expanded incident parallel light beams, and the light source can move longitudinally to change an emitting angle of the emitted light beams of the collimating optical system so as to compensate the pitching of the carrier.
Further, the beam expanding system is a cylindrical beam expanding lens, a plurality of cylindrical mirror units are uniformly arranged on the incident surface of the cylindrical beam expanding lens at intervals from top to bottom, and a plane mirror unit is arranged between each cylindrical mirror unit;
the cylindrical mirror unit can rotate around the visual axis of the cylindrical mirror unit, so that the emergent light beam of the cylindrical beam expander synchronously rotates, and the rotating angle of the emergent light beam of the cylindrical beam expander is used for compensating the carrier rolling.
Further, the emergent light opening angle alpha of the cylindrical mirror unit0Comprises the following steps:
when the incident angle of the cylindrical mirror unit is δ, the variation Δ of the opening angle of the emergent light of the cylindrical mirror unit is:
in the formula, f is the focal length of the cylindrical mirror unit, and s is the chord length of the cylindrical mirror unit.
Further, when the light source moves longitudinally for a distance h, the emergent angle θ of the emergent beam of the collimating optical system0Comprises the following steps: theta0＝arctan(h/f')
Where f' is the focal length of the collimating optical system.
In a second aspect, an embodiment of the present invention provides a light beam stability control method based on the internal compensation optical system in the first aspect, where the internal compensation optical system includes a light source, a collimating optical system, and a light beam expanding system, the light source is located at an image plane of the collimating optical system, and the light beam expanding system is located in a parallel emergent light path of the collimating optical system. The beam stabilization control method includes:
moving the high and low positions of the light source to change the emergent angle of the emergent beam of the collimating optical system and compensate the carrier pitch;
and rotating the cylindrical mirror unit around the visual axis of the cylindrical mirror unit so as to synchronously rotate the emergent light beam of the cylindrical beam expander to compensate the carrier rolling.
Further, the beam stabilization control method further includes:
calculating a pitch compensation angle and a roll compensation angle based on a central light ray stabilization mechanism of the guide light beam and a tilt stabilization mechanism of the guide light beam with the aim of ensuring the central light ray stabilization of the guide light beam; the guided light beam is an emergent light beam of the cylindrical beam expander.
Further, based on the central light stabilization mechanism of the guide beam, to guarantee that the central light of the guide beam is stable as the target, calculate the pitch compensation angle, specifically include:
defining the central light of the guiding light beam in the longitudinal light supplementing beam coordinate system O-XFYFZFThe first vector of (1) is
The coordinates of said central ray in the geodetic coordinate system
Comprises the following steps:
when the carrier is tilted alpha and tilted beta, the tilt compensation theta and the tilt compensation of the corresponding internal compensation optical system
The coordinates of the guided light beam in the geodetic coordinate system
Comprises the following steps:
to ensure the central light of the guided beam to be stable, it is required that:
the pitch compensation angle θ thus obtained is:
in the above formula, the first and second carbon atoms are,
a change matrix representing the carrier coordinate system relative to the geodetic coordinate system;
representing the variation of a global coordinate system of an internal compensation optical system relative to a global coordinate system of a carrierMatrix formation;
a change matrix representing the longitudinal compensation relative coordinate system relative to the coordinate system of the inner compensation optical system integral; and lambda represents the installation angle of the internal compensation optical system and the carrier.
Further, based on the slope stabilization mechanism of the guiding beam, to guarantee that the central light of the guiding beam is stable as the target, the rolling compensation angle is calculated, which specifically includes:
defining the tilt of the guided beam in the guided beam coordinate system O-XLYLZLIs a feature vector of
The coordinates of this feature vector in the geodetic coordinate system
Comprises the following steps:
when the carrier is tilted alpha and tilted beta, the tilt compensation theta and the tilt compensation of the corresponding internal compensation optical system
The coordinates of the guided light beam in the geodetic coordinate system
Comprises the following steps:
to ensure the central light of the guided beam to be stable, it is required that:
thereby obtaining the roll compensation angle
Comprises the following steps:
in the above formula, the first and second carbon atoms are,
a change matrix representing the carrier coordinate system relative to the geodetic coordinate system;
representing a change matrix of the integrated coordinate system of the internal compensation optical system relative to the carrier coordinate system;
representing a change matrix of the guided beam coordinate system relative to the global coordinate system of the internal compensation optical system.
Compared with the prior art, the internal compensation optical system and the light beam stability control method provided by the embodiment of the invention have the following beneficial effects:
1) compared with the prior external stable compensation mode that the poses of the light beams emitted by the optical system are changed by integrally rotating the optical system, the internal compensation optical system provided by the embodiment of the invention does not need a stable platform with a shaft system, and can obviously reduce the height of the system and reduce the weight.
2) Compared with the prior art that the optical system is integrally loaded on a two-axis stable platform, the internal compensation optical system provided by the embodiment of the invention has a more compact structure and greatly improves the adaptability of the system.
3) The internal compensation optical system provided by the embodiment of the invention does not need to be provided with a two-axis stable platform, and compared with the prior art, the internal compensation optical system does not have the rotary seal of a platform shaft system, and has higher servo stability.
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, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of an internal compensation optical system according to an embodiment of the present invention;
FIG. 2 is a schematic optical diagram of a collimating optical system;
FIG. 3 is a partial enlarged view of a cylindrical beam expander;
FIG. 4 is a schematic diagram of the optical principle of a single cylindrical mirror unit;
FIG. 5 is a schematic flow chart of a method for controlling beam stability according to an embodiment of the present invention;
fig. 6 is a schematic diagram of coordinate system definition of the principle of beam stabilization control.
In the drawings, the components represented by the respective reference numerals are listed below:
1. light source, 2, collimating optical system, 2.1, first lens, 2.2, second lens, 2.3, third lens, 2.4, fourth lens, 2.5, fifth lens, 2.6, sixth lens, 3, beam expanding system.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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 some, but not all, embodiments of the present invention. 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.
Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the application. The appearances of the phrase in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. It is explicitly and implicitly understood by one skilled in the art that the embodiments described herein can be combined with other embodiments.
Most of the current optical compensation technologies adopt an external stabilization method for compensation, that is, the whole optical system is loaded on a two-axis stabilization platform, and the two-axis platform is used for counteracting the longitudinal and rolling motions of a carrier platform. However, in this way, since the optical system loaded on the two-axis stabilized platform is not light in weight, in order to improve the load capacity of the two-axis stabilized platform, the two-axis stabilized platform is often large in structural size and weight, and inconvenient to install and use.
Therefore, embodiments of the present invention provide an internal compensation optical system, which controls the change of the pose of a ribbon-type beam by changing the pose of a main optical element in the optical system, and compared to the prior external stabilization compensation method in which the pose of a light beam emitted by the optical system is changed by rotating the optical system as a whole, the present invention does not require a stable platform with a shaft system, and can significantly reduce the height and weight of the system. And the structure is more compact, and the adaptability of the system is greatly improved. The problem of prior art load on the stable platform of diaxon with optical system whole, the structure is complicated, size and weight are too big is solved. The following description and description will proceed with reference being made to various embodiments.
Fig. 1 is a schematic structural diagram of an internal compensation optical system according to an embodiment of the present invention, and as shown in fig. 1, the internal compensation optical system includes a light source 1, a collimating optical system 2, and a beam expanding system 3, where the light source 1 is located at an image plane of the collimating optical system 2, and the beam expanding system 3 is located in a parallel emergent light path of the collimating optical system 2;
the light source 1 is collimated by the collimating optical system 2 to form a parallel light beam incident beam expanding system 3, the light beam expanding system 3 is used for expanding incident parallel light beams and emitting the expanded incident parallel light beams, and the light source 1 can move longitudinally to change the emitting angle of the emitting light beams of the collimating optical system, so that the pitching of the carrier is compensated.
Specifically, the internal compensation optical system provided by this embodiment may be applied to optical carrier landing guidance, a carrier landing guidance beam of an aircraft is generally a strip-shaped beam with a large length-width ratio, and the internal compensation optical system provided by this embodiment performs real-time decoupling compensation on longitudinal and transverse motions of an airborne platform by controlling the carrier landing guidance beam, so as to achieve a stable effect of the beam in a pilot view angle. In the embodiment, the internal compensation means that the carrier landing guiding light beam is controlled to perform real-time decoupling compensation on the longitudinal and transverse rolling motion of the carrier platform by changing the pose of an optical element in an optical system.
Referring to fig. 1, the internal compensation optical system includes a light source 1, a collimating optical system 2, and a beam expanding system 3. The collimating optical system 2 is capable of collimating a diverging light beam into a parallel light beam. Referring to fig. 1, in the present embodiment, the collimating optical system 2 includes a first lens 2.1, a second lens 2.2, a third lens 2.3, a fourth lens 2.4, a fifth lens 2.5, and a sixth lens 2.6. The light source 1 is collimated by the collimating optical system 2 to form a parallel light beam incident beam expanding system 3, and the incident parallel light beam is expanded by the light beam expanding system 3 and then emitted. In the embodiment of the invention, the emergent light beam of the light beam expanding system 3 is a landing guiding light beam of an airplane.
Fig. 2 is a schematic diagram of the optical principle of the collimating optical system, and the exit angle of the light beam exiting from the collimating optical system 2 can be changed by moving the high and low positions of the light source 1, so as to compensate the pitch of the carrier. Referring to fig. 2, when the light source moves longitudinally by a distance h, the exit angle θ of the exit beam of the collimating optical system0Is theta0Arctan (h/f'). Where f' is the focal length of the collimating optical system.
Compared with the prior art, the internal compensation optical system and the light beam stability control method provided by the embodiment of the invention have the following beneficial effects:
1) compared with the prior external stable compensation mode that the poses of the light beams emitted by the optical system are changed by integrally rotating the optical system, the internal compensation optical system provided by the embodiment of the invention does not need a stable platform with a shaft system, and can obviously reduce the height of the system and reduce the weight.
2) Compared with the prior art that the optical system is integrally loaded on a two-axis stable platform, the internal compensation optical system provided by the embodiment of the invention has a more compact structure and greatly improves the adaptability of the system.
On the basis of the above embodiment, the beam expanding system is a cylindrical beam expander, and fig. 3 is a partially enlarged view of the cylindrical beam expander, that is, a partially enlarged view of the point i in fig. 1. Referring to fig. 1 and 3, a plurality of cylindrical mirror units are uniformly arranged on the incident surface of the cylindrical beam expander at intervals from top to bottom, and a plane mirror unit is arranged between each cylindrical mirror unit;
the cylindrical mirror unit can rotate around the visual axis of the cylindrical mirror unit, so that the emergent light beam of the cylindrical beam expander synchronously rotates, and the rotating angle of the emergent light beam of the cylindrical beam expander is used for compensating the carrier rolling.
Specifically, fig. 4 is an optical schematic diagram of a single cylindrical mirror unit, and as shown in fig. 4, an exit light opening angle α of the cylindrical mirror unit0Comprises the following steps:
when the incident angle of the cylindrical mirror unit is delta, the emergent light opening angle of the cylindrical mirror unit is beta0The variation Δ of the opening angle of the emergent light of the cylindrical mirror unit is:
in the formula, f is the focal length of the cylindrical mirror unit, and s is the chord length of the cylindrical mirror unit.
Taking a practical application as an example, the following parameter values are taken: emergent light opening angle alpha of cylindrical mirror unit0Not less than 20 °, when the cylindrical mirror chord length s is 5mm and the cylindrical mirror incident angle is 0.4 °, the value Δ is found to be less than 2.52 ″, which is much smaller than the beam angle 20 °, and therefore, the exit beam angle α of the cylindrical beam expander mirror 3 can be considered approximately as being0The beam expanding range of the cylindrical mirror unit is always expanded along a section vertical to the convex cylindrical surface without being influenced by the incident angle of incident light of the cylindrical mirror unit. Based on this principleWhen the incident light of the cylindrical mirror unit is unchanged, the cylindrical mirror unit rotates around the visual axis of the cylindrical mirror unit, the emergent light beam band of the cylindrical beam expander 3 synchronously rotates around the visual axis of the cylindrical beam expander, and the rotating angle can be used for compensating the carrier rolling. It is understood that the present embodiment is applied to optical landing guidance, and the carrier is referred to as a ship hull.
Fig. 5 is a schematic flow chart of a light beam stabilization control method according to an embodiment of the present invention, where the light beam stabilization control method according to the first aspect of the present invention includes:
Specifically, the light beam stability control method provided by the embodiment is applied to optical carrier landing guidance, a carrier landing guidance light beam of an aircraft is generally a strip-shaped light beam with a large length-width ratio, and the light beam stability control method provided by the embodiment performs real-time decoupling compensation on carrier longitudinal and transverse motions by controlling the guidance light beam so as to realize a stable effect of the light beam in a pilot visual angle. The guided light beam is an emergent light beam of the cylindrical beam expander.
On the basis of the above embodiment, fig. 6 is a schematic diagram of a coordinate system definition of a beam stabilization control principle, and referring to fig. 6, the beam stabilization control method further includes:
calculating a pitch compensation angle and a roll compensation angle based on a central light ray stabilization mechanism of the guide light beam and a tilt stabilization mechanism of the guide light beam with the aim of ensuring the central light ray stabilization of the guide light beam; the guided light beam is an emergent light beam of the cylindrical beam expander.
Specifically, based on the central light stabilization mechanism of the guide beam, calculating a pitch compensation angle with the goal of ensuring the central light stabilization of the guide beam, includes:
defining the central light of the guiding light beam in the longitudinal light supplementing beam coordinate system O-XFYFZFThe first vector of (1) is
The coordinates of said central ray in the geodetic coordinate system
Comprises the following steps:
when the carrier is tilted alpha and tilted beta, the tilt compensation theta and the tilt compensation of the corresponding internal compensation optical system
The coordinates of the guided light beam in the geodetic coordinate system
Comprises the following steps:
to ensure the central light of the guided beam to be stable, it is required that:
the pitch compensation angle θ thus obtained is:
in the above formula, the first and second carbon atoms are,
a change matrix representing the carrier coordinate system relative to the geodetic coordinate system;
representing a change matrix of the integrated coordinate system of the internal compensation optical system relative to the carrier coordinate system;
a change matrix representing the longitudinal compensation relative coordinate system relative to the coordinate system of the inner compensation optical system integral; and lambda represents the installation angle of the internal compensation optical system and the carrier.
Further, based on the mechanism of the tilt stabilization of the guided light beam, the method calculates the roll compensation angle with the goal of ensuring the stability of the central light of the guided light beam, and specifically includes:
defining the tilt of the guided beam in the guided beam coordinate system O-XLYLZLIs a feature vector of
The coordinates of this feature vector in the geodetic coordinate system
Comprises the following steps:
when the carrier is tilted alpha and tilted beta, the tilt compensation theta and the tilt compensation of the corresponding internal compensation optical system
The coordinates of the guided light beam in the geodetic coordinate system
Comprises the following steps:
to ensure the central light of the guided beam to be stable, it is required that:
thereby obtaining the roll compensation angle
Comprises the following steps:
in the above formula, the first and second carbon atoms are,
a change matrix representing the carrier coordinate system relative to the geodetic coordinate system;
representing a change matrix of the integrated coordinate system of the internal compensation optical system relative to the carrier coordinate system;
representing a change matrix of the guided beam coordinate system relative to the global coordinate system of the internal compensation optical system.
According to the method provided by the above embodiment, the pitch compensation angle θ and the roll compensation angle β can be calculated according to the carrier pitch angle α and the carrier roll angle β
Based on the principle, the invention can be provided with a sensor, a processor and a driving mechanism which are electrically connected in sequence. The carrier pitch angle alpha and the carrier roll angle beta are collected through the sensor and sent to the processor, and the processor calculates the pitch compensation angle theta and the roll compensation angle beta based on the carrier pitch angle alpha and the carrier roll angle beta according to the method provided by the embodiment
The processor then compares the pitch compensation angle θ and the roll compensation angle θ
Converting the control signal into control signal of the driving mechanism, controlling the driving mechanism to adjust the height position of the light source so as to change the emergent angle of the emergent beam of the collimating optical system and compensate the carrierThe body is pitched. Meanwhile, the driving mechanism adjusts the cylindrical mirror unit to rotate around the visual axis of the cylindrical mirror unit so as to compensate the carrier rolling.
Compared with the prior art, the internal compensation optical system and the light beam stability control method provided by the embodiment of the invention have the following beneficial effects:
1) compared with the prior external stable compensation mode that the poses of the light beams emitted by the optical system are changed by integrally rotating the optical system, the internal compensation optical system provided by the embodiment of the invention does not need a stable platform with a shaft system, and can obviously reduce the height of the system and reduce the weight.
2) Compared with the prior art that the optical system is integrally loaded on a two-axis stable platform, the internal compensation optical system provided by the embodiment of the invention has a more compact structure and greatly improves the adaptability of the system.
3) The internal compensation optical system provided by the embodiment of the invention does not need to be provided with a two-axis stable platform, and compared with the prior art, the internal compensation optical system does not have the rotary seal of a platform shaft system, and has higher servo stability.
The above-described embodiments of the apparatus are merely illustrative, and the units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware. With this understanding in mind, the above-described technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium such as ROM/RAM, magnetic disk, optical disk, etc., and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods described in the embodiments or some parts of the embodiments.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (7)
1. An internal compensation optical system is characterized by comprising a light source, a collimating optical system and a beam expanding system, wherein the light source is positioned at the image surface of the collimating optical system, and the beam expanding system is positioned in a parallel emergent light path of the collimating optical system;
the light source is collimated by the collimating optical system to form a parallel light beam incident beam expanding system, and the light beam expanding system is used for expanding incident parallel light beams and then emitting the expanded incident parallel light beams; the light source can move longitudinally to change the emergent angle of the emergent beam of the collimating optical system so as to compensate the pitching of the carrier;
the beam expanding system is a cylindrical beam expanding lens, a plurality of cylindrical mirror units are uniformly arranged on the incident surface of the cylindrical beam expanding lens at intervals from top to bottom, and plane mirror units are arranged among the cylindrical mirror units;
the cylindrical mirror unit can rotate around the visual axis of the cylindrical mirror unit, so that the emergent light beam of the cylindrical beam expander synchronously rotates, and the rotating angle of the emergent light beam of the cylindrical beam expander is used for compensating the carrier rolling.
2. The internal compensation optical system according to claim 1, wherein an exit opening angle α of the cylindrical lens unit0Comprises the following steps:
when the incident angle of the cylindrical mirror unit is δ, the variation Δ of the opening angle of the emergent light of the cylindrical mirror unit is:
in the formula, f is the focal length of the cylindrical mirror unit, and s is the chord length of the cylindrical mirror unit.
3. The internal compensation optical system according to claim 1, wherein an exit angle θ of an exit beam of the collimating optical system when the light source is longitudinally moved by a distance h0Comprises the following steps:
θ0＝arctan(h/f')
where f' is the focal length of the collimating optical system.
4. A light beam stabilization control method of the internal compensation optical system according to claim 1, wherein the internal compensation optical system includes a light source, a collimating optical system, and a light beam expanding system, the light source is located at an image plane position of the collimating optical system, and the light beam expanding system is located in a parallel emergent light path of the collimating optical system; the light beam stabilization control method is characterized by comprising the following steps:
moving the high and low positions of the light source to change the emergent angle of the emergent beam of the collimating optical system and compensate the carrier pitch;
and rotating the cylindrical mirror unit around the visual axis of the cylindrical mirror unit so as to synchronously rotate the emergent light beam of the cylindrical beam expander to compensate the carrier rolling.
5. The beam stabilization control method according to claim 4, further comprising:
calculating a pitch compensation angle and a roll compensation angle based on a central light ray stabilization mechanism of the guide light beam and a tilt stabilization mechanism of the guide light beam with the aim of ensuring the central light ray stabilization of the guide light beam; the guided light beam is an emergent light beam of the cylindrical beam expander.
6. The method according to claim 5, wherein calculating the pitch compensation angle based on a central ray stabilization mechanism of the guided beam with a goal of ensuring central ray stabilization of the guided beam specifically comprises:
defining the central light of the guiding light beam in the longitudinal light supplementing beam coordinate system O-XFYFZFThe first vector of (1) is
The coordinates of said central ray in the geodetic coordinate system
Comprises the following steps:
when the carrier is tilted alpha and tilted beta, the tilt compensation theta and the tilt compensation of the corresponding internal compensation optical system
The coordinates of the guided light beam in the geodetic coordinate system
Comprises the following steps:
to ensure the central light of the guided beam to be stable, it is required that:
the pitch compensation angle θ thus obtained is:
in the above formula, the first and second carbon atoms are,
a change matrix representing the carrier coordinate system relative to the geodetic coordinate system;
representing a change matrix of the integrated coordinate system of the internal compensation optical system relative to the carrier coordinate system;
a change matrix representing the longitudinal compensation relative coordinate system relative to the coordinate system of the inner compensation optical system integral; and lambda represents the installation angle of the internal compensation optical system and the carrier.
7. The method according to claim 6, wherein the calculating of the roll compensation angle based on the tilt stabilization mechanism of the guided light beam with the goal of ensuring the stability of the central light of the guided light beam comprises:
defining the tilt of the guided beam in the guided beam coordinate system O-XLYLZLIs a feature vector of
The coordinates of this feature vector in the geodetic coordinate system
Comprises the following steps:
when the carrier is tilted alpha and tilted beta, the tilt compensation theta and the tilt compensation of the corresponding internal compensation optical system
The coordinates of the guided light beam in the geodetic coordinate system
Comprises the following steps:
to ensure the central light of the guided beam to be stable, it is required that:
thereby obtaining the roll compensation angle
Comprises the following steps:
in the above formula, the first and second carbon atoms are,
a change matrix representing the carrier coordinate system relative to the geodetic coordinate system;
representing a change matrix of the integrated coordinate system of the internal compensation optical system relative to the carrier coordinate system;
representing a change matrix of the guided beam coordinate system relative to the global coordinate system of the internal compensation optical system.
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| CN102938534A (en) * | 2012-11-09 | 2013-02-20 | 维林光电(苏州)有限公司 | Semiconductor laser and method for generating high-quality and high-stability light beams by semiconductor laser |
| CN105044916A (en) * | 2015-09-07 | 2015-11-11 | 江苏大学 | High-power laser beam expander lens system with automatic temperature compensation function |
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| US5140608A (en) * | 1991-05-29 | 1992-08-18 | Optrotech Ltd, Israel Company | Optical system for focusing a light beam on to an image plane |
| CN1530944A (en) * | 2003-01-22 | 2004-09-22 | ���µ�����ҵ��ʽ���� | Optical head, optical information recording/reproducing device and applied apparatus |
| CN102226690A (en) * | 2011-03-29 | 2011-10-26 | 浙江大学 | Method and device for high-accuracy and small-angle measurement |
| CN102938534A (en) * | 2012-11-09 | 2013-02-20 | 维林光电(苏州)有限公司 | Semiconductor laser and method for generating high-quality and high-stability light beams by semiconductor laser |
| CN105044916A (en) * | 2015-09-07 | 2015-11-11 | 江苏大学 | High-power laser beam expander lens system with automatic temperature compensation function |
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