An airborne optoelectronic payload and method for real-time calibration of multi-sensor boresights

Abstract

The application provides an airborne photoelectric load for real-time calibration of multiple-sensor visual axes and a method, and relates to the technical field of aerial optical imaging. The airborne photoelectric load comprises a front telescope system, a calibration device, a calibration reticle, a light splitting unit, an imaging light path and an imaging sensor. The calibration reticle is placed on the primary image plane of the front telescope system, and multiple imaging units are arranged in parallel to realize simultaneous imaging on multiple imaging sensors. Since the calibration reticle has a grid line structure with alignment features, the visual axis deviation of multiple sensors can be corrected and adjusted in real time, and the operation is simple and reliable. The correction efficiency is improved, and real-time imaging adjustment can be performed during the task execution of the airborne load. The technical problems of the prior art, such as dependence on manual operation, complicated operation process and low efficiency, are solved.

Description

Technical Field

[0001] This invention relates to the field of aerospace optical imaging technology, specifically to an airborne optoelectronic payload and method for real-time calibration of the line of sight of multiple sensors. Background Technology

[0002] Airborne optoelectronic payloads enable military applications such as long-range imaging, target designation, ranging, tracking, surveillance, and reconnaissance. Among these, the line-of-sight consistency of multiple sensors is a key indicator for ensuring system detection accuracy and target identification capabilities. Because airborne environmental conditions, thermal fluctuations, vibrations, or any other interference to the optical system during operation can affect the line-of-sight deviation of multiple sensors, this deviation often changes continuously during flight. If deviation exists, it can cause the same target to shift its position in different sensor images, leading to laser ranging errors or aiming mistakes.

[0003] In existing technologies, line-of-sight deviation is detected and corrected before the load leaves the factory. The specific method is to make the optical system image a common target board at a distance so that all sensors can observe the common target board, and then detect and adjust the deviation in the optical system. This solution relies on manual visual calibration, which is time-consuming and cumbersome. It often drifts over time, which requires periodic adjustment of the target board. This requires a lot of manpower, material resources and time. In addition, the repeatability of manual calibration makes it difficult to meet the accuracy requirements of rapid field maintenance. Summary of the Invention

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defects in the prior art, thereby providing an airborne optoelectronic payload and method for real-time calibration of multi-sensor line of sight.

[0005] An airborne optoelectronic payload for real-time calibration of multiple sensor line-of-sight includes: a forward telescope system, a calibration device, and an imaging unit. The calibration device is equipped with a calibration reticle, which has a grid-like structure. The calibration reticle is located on the primary image plane of the forward telescope system, and the calibration reticle and the forward telescope system are located on the same optical axis. Multiple imaging units are arranged in parallel. Each imaging unit includes a beam splitting unit, an imaging optical path, and an imaging sensor arranged laterally. The beam splitting unit is located on the output optical path of the forward telescope system.

[0006] Furthermore, the calibration device includes a motor, a calibration reticle mounting bracket, and a motor mounting bracket. The motor is mounted on the motor mounting bracket, the calibration reticle is mounted on the calibration reticle mounting bracket, and the calibration reticle mounting bracket is fixedly connected to the power output shaft of the motor.

[0007] Furthermore, the calibration device also includes an upper limit device and a lower limit device. The upper limit device is located above one side of the motor mounting bracket, and the lower limit device is located below the other side of the motor mounting bracket. An upper limit block is provided on the side of the upper limit device near the calibration reticle mounting bracket.

[0008] Furthermore, an upper gear is fixedly connected to the power output shaft of the motor, a lower gear meshes with the upper gear, and a position sensor is fixedly connected to the lower gear.

[0009] Furthermore, the forward telescope system includes a primary mirror, a secondary mirror, and a corrective mirror assembly. The primary mirror, secondary mirror, corrective mirror assembly, and calibration reticle are located on the same optical axis. The beam splitting unit is a dichroic beam splitter, and the dichroic beam splitter is located in the output light path of the corrective mirror assembly.

[0010] Furthermore, the front telescope system includes a front telescope mirror group and a rear telescope mirror group. The front telescope mirror group, the calibration reticle, and the rear telescope mirror group are located on the same optical axis, and the dichroic beam splitter is located in the output light path of the rear telescope mirror group.

[0011] Furthermore, the calibration device also includes an upper limit device connecting frame and a mounting base. The upper limit device connecting frame is connected to the motor mounting frame, the upper limit device is connected to the upper limit device connecting frame, and the mounting base is fixedly connected to the lower part of the motor mounting frame.

[0012] Furthermore, the calibration device also includes a position sensor mounting bracket, which is connected to the motor mounting bracket, and the position sensor is mounted on the position sensor mounting bracket.

[0013] Furthermore, the calibration device also includes an adapter mounting component, the calibration reticle mounting bracket is fixedly connected to the adapter mounting component, and the adapter mounting component is fixedly connected to the power output shaft of the motor.

[0014] The present invention also includes a method for real-time calibration of the line of sight of multiple sensors. This method is based on an airborne optoelectronic payload for real-time calibration of the line of sight of multiple sensors as described in any of the above claims. The airborne optoelectronic payload receives electromagnetic radiation from an external target. The electromagnetic radiation is incident on a forward telescope system and a calibration reticle, and then exits to a beam splitter. The electromagnetic radiation is transmitted through the beam splitter to the imaging optical path and then imaged on the imaging sensor. The electromagnetic radiation is also refracted through the beam splitter to adjacent imaging units. The imaging deviations of multiple imaging sensors are detected, and the deviations of the image are corrected to complete the calibration of the line of sight of multiple imaging sensors.

[0015] The technical solution of this invention has the following advantages:

[0016] In the technical solution provided by the present invention, by placing the calibration reticle on the primary image plane of the forward telescope system and arranging multiple imaging units in parallel, imaging can be achieved simultaneously on multiple imaging sensors. Since the calibration reticle has a grid-line structure and alignment features, it can correct and adjust the line-of-sight deviation of multiple sensors in real time. The operation is simple and reliable, the correction efficiency is improved, and it can be used for real-time imaging adjustment during the airborne payload's mission. Attached Figure Description

[0017] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a system block diagram of the onboard photoelectric payload when the present invention employs a hybrid optical system of refraction and reflection;

[0019] Figure 2 This is a system block diagram of the onboard photoelectric payload when using a refractive telescope system in this invention;

[0020] Figure 3 This is a schematic diagram of the position sensor and motor mounting bracket of the present invention;

[0021] Figure 4 This is a schematic diagram of the upper limit device and the upper limit device connecting frame of the present invention;

[0022] Figure 5 This is a state diagram of the reticle cutting into the optical path according to the present invention;

[0023] Figure 6 This is a structural diagram of the reticle of the present invention when it is a grid-line structure;

[0024] Figure 7 This is a structural diagram of the reticle of the present invention when it is a cross-shaped engraving structure;

[0025] Figure 8 To utilize the effect of this invention on imaging axis deviation Figure 1 ;

[0026] Figure 9 To utilize the effect of this invention on imaging axis deviation Figure 2 ;

[0027] Figure 10 To utilize the effect of this invention on imaging axis deviation Figure 3 .

[0028] Explanation of reference numerals in the attached figures:

[0029] 1-Front-view telescope system; 101-Primary mirror; 102-Secondary mirror; 103-Correcting mirror assembly; 104-Front telescope mirror assembly; 105-Rear telescope mirror assembly; 2-Calibration device; 201-Calibration reticle; 202-Calibration reticle mounting bracket; 203-Motor; 204-Upper gear; 205-Position sensor; 206-Mounting base; 207-Upper limit device; 208-Connecting screw; 209-Lower gear; 210-Motor mount Mounting bracket; 211-Lower limit device; 212-Upper limit device connecting bracket; 213-Position sensor mounting bracket; 214-Upper limit block; 215-Adapter mounting component; 3-First dichroic beam splitter; 4-Second dichroic beam splitter; 5-Third dichroic beam splitter; 6-First imaging optical path; 7-Second imaging optical path; 8-Third imaging optical path; 9-First imaging sensor; 10-Second imaging sensor; 11-Third imaging sensor. Detailed Implementation

[0030] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0032] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0033] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0034] like Figures 1-5 The airborne optoelectronic payload for real-time calibration of multiple sensor line-of-sight includes: a front telescope system 1, a calibration device 2, and an imaging unit. A calibration reticle 201 is fixedly connected to the calibration device 2. The calibration reticle 201 has a grid-line structure and is located on the primary image plane of the front telescope system 1. The primary image plane refers to the first imaging image plane in the front telescope system 1. The calibration reticle 201 and the front telescope system 1 are located on the same optical axis. Multiple imaging units are arranged in parallel. Each imaging unit includes a beam splitting unit, an imaging optical path, and an imaging sensor arranged in a horizontal sequence. The beam splitting unit is located on the outgoing optical path of the front telescope system 1.

[0035] The aforementioned airborne optoelectronic payload for real-time calibration of multiple sensor line-of-sight is achieved by placing the calibration reticle 201 on the primary image plane of the forward telescope system 1 and arranging multiple imaging units in parallel, thereby enabling simultaneous imaging on multiple imaging sensors. Since the calibration reticle 201 has a grid-line structure and alignment features, it can correct and adjust the deviation of multiple sensor line-of-sight in real time. The operation is simple and reliable, improving the calibration efficiency, and it can perform real-time imaging adjustment during the airborne payload's mission.

[0036] like Figures 1-7 As shown, in this embodiment, the calibration device 2 includes a motor 203, a calibration reticle mounting bracket 202, and a motor mounting bracket 210. The motor 203 is mounted on the motor mounting bracket 210, and the calibration reticle 201 is mounted on the calibration reticle mounting bracket 202. The calibration reticle mounting bracket 202 is fixedly connected to the power output shaft of the motor 203. The motor mounting bracket 210 has mounting holes corresponding to the power output shaft of the motor 203. The main structure of the motor 203 is fixedly connected to the motor mounting bracket 210 by bolts, and the power output shaft of the motor 203 is located in the mounting holes. It should be noted that the motor 203... Both ends of the reticle have power output shafts. The power output shaft mounted on the calibration reticle mounting bracket 202 is not located in the mounting hole, but rather on the side of the motor 203 away from the motor mounting bracket 210. This design aims to ensure sufficient space for the motor 203 to drive the calibration reticle mounting bracket 202 to rotate the calibration reticle 201, allowing the calibration reticle 201 to enter the optical path when calibration is needed and exit the optical path when calibration is not needed. The calibration reticle 201 is a light-transmitting flat plate structure, and its surface is engraved with corresponding opaque lines. The engraving structure on the calibration reticle 201 is as shown in the attached instruction manual. Figure 6 The grid pattern shown, or the pattern on the calibration reticle 201, can also be as described in the instruction manual. Figure 7The cross-shaped engraving structure shown can also be concentric circles, horseshoe shape, star pattern, radial pattern, or any other shape with alignment features. The cross-section of the calibration reticle mounting bracket 202 is an OI composite structure, with the O part on top and the I part on the bottom. The O part and the I part are integrally machined, and the calibration reticle 201 is fixedly installed in the O part. The O-shaped structure of the O part disperses its stress through its bending shape, reduces stress concentration points, and thus improves the stability of the structure. The I-shaped structure of the I part also has good stability. Through the design of the OI composite structure, the structural stability of the calibration reticle mounting bracket 202 and the accuracy of the movement process can be improved.

[0037] like Figures 1-5 As shown, in this embodiment, the calibration device 2 further includes an upper limit device 207 and a lower limit device 211. The upper limit device 207 is disposed above one side of the motor mounting bracket 210, and the lower limit device 211 is disposed below the other side of the motor mounting bracket 210. An upper limit block 214 is fixedly disposed on the side of the upper limit device 207 near the calibration reticle mounting bracket 202. The rotation angle of the calibration reticle mounting bracket 202 is limited by the upper limit device 207 and the lower limit device 211. Since the motor mounting bracket 210 has a cuboid structure, by fixing the upper limit device 207 to the upper side of one side of the motor mounting bracket 210 with bolts, and fixing the lower limit device 211 to the lower side of the other side of the motor mounting bracket 210 with bolts, the angle between the upper limit device 207 and the lower limit device 211 is limited to ninety degrees. When the calibration reticle mounting bracket 202 is in the lower limit position, the calibration reticle mounting bracket 202 rotates according to... Figure 5 When the reticle mounting bracket 202 rotates in the direction indicated by the arrow and contacts the lower limit device 211, the reticle mounting bracket 202 is in a horizontal state and the reticle 201 is in the optical path entry state. When the reticle mounting bracket 202 is in the upper limit position and contacts the upper limit block 214, the reticle mounting bracket 202 is in a vertical state and the reticle 201 is in the optical path exit state. Limiting the rotation angle of the reticle mounting bracket 202 and the reticle 201 to ninety degrees not only enables the reticle 201 to enter and exit the optical path, but also avoids the reticle mounting bracket 202 from colliding and being damaged by other devices due to excessive rotation angle during operation, thus affecting the operation of the airborne optoelectronic payload.

[0038] like Figures 3-5As shown, in this embodiment, an upper gear 204 is fixedly connected to the power output shaft of the motor 203, a lower gear 209 meshes with the upper gear 204, and a position sensor 205 is fixedly connected to the lower gear 209. The upper gear 204 is fixedly installed on the power output shaft of the motor 203 placed in the placement hole. The motor 203 drives the upper gear 204 to rotate, which in turn drives the lower gear 209 meshing with the upper gear 204 to rotate. The position sensor 205 is fixedly connected to the lower gear 209, which in turn drives the position sensor 205 to rotate. The position sensor 205 can detect the angle of rotation of the motor 203 and calibrate whether the calibration reticle mounting bracket 202 is in a horizontal or vertical state, thereby accurately controlling whether the calibration reticle 201 enters or exits the optical path.

[0039] like Figures 1-5As shown, in this embodiment, the front-mounted telescope system 1 includes a primary mirror 101, a secondary mirror 102, and a corrective mirror group 103. The primary mirror 101, secondary mirror 102, corrective mirror group 103, and calibration reticle 201 are located on the same optical axis. The beam splitting unit is a dichroic beam splitter, and the dichroic beam splitter is located on the output light path of the corrective mirror group 103. The front-mounted telescope system 1 also includes a front telescope mirror group 104 and a rear telescope mirror group 105. The front telescope mirror group 104, calibration reticle 201, and rear telescope mirror group 105 are located on the same optical axis, and the dichroic beam splitter is located on the output light path of the rear telescope mirror group 105. The corrective mirror group 103 is located at the central aperture of the primary mirror 101. The front-mounted telescope system 1 is a secondary imaging telescope system. The primary image plane is located between the secondary mirror 102 and the corrector lens group 103, while the calibration reticle 201 is located at the primary image plane. The optical path is as follows: the front telescope system 1 is a parallel light incident system. The parallel light first enters the primary mirror 101, is reflected by the primary mirror 101 to the secondary mirror 102, and then is sequentially transmitted from the secondary mirror 102 to the calibration reticle 201 and the corrector lens group 103. Finally, the parallel light exits to the dichroic beam splitter. The front telescope system 1 is used to extend the imaging limit, achieving high-resolution imaging, accurate measurement, and detail resolution of distant targets. The optical path composed of the primary mirror 101, secondary mirror 102, and corrector lens group 103 is a hybrid refractive and reflective optical system. In addition, the front telescope system 1 can also be a reflective optical system or... The system is a refractive optical system. When the front telescope system 1 is a refractive telescope system, the front telescope system 1 includes a front telescope mirror group 104 and a rear telescope mirror group 105. The calibration reticle 201 is located at the primary image plane between the front telescope mirror group 104 and the rear telescope mirror group 105. The calibration reticle 201, the front telescope mirror group 104, and the rear telescope mirror group 105 are located on the same optical axis. The optical path is as follows: the front telescope system 1 has parallel light incident. The parallel light first enters the front telescope mirror group 104, then is transmitted sequentially to the calibration reticle 201 and the rear telescope mirror group 105, and finally exits as parallel light to the dichroic beam splitter. The dichroic beam splitter has both refraction and transmission functions. The electromagnetic radiation incident on the dichroic beam splitter, that is, the electromagnetic radiation exiting the dichroic beam splitter, is also reflected in the beam splitter. Parallel light from the beam splitter can be transmitted through the dichroic beam splitter to the corresponding imaging optical path and imaging sensor, and imaged on the imaging sensor. Simultaneously, it can also be refracted through the dichroic beam splitter to the dichroic beam splitter of the adjacent imaging unit, following the same principle. By analogy, it can image on multiple imaging sensors, thereby realizing the line-of-sight detection of multiple sensors and subsequent calibration. The dichroic beam splitter can also be replaced by a plane mirror or cubic prism coated with a beam-splitting film. Both the plane mirror and cubic prism coated with a beam-splitting film can ensure that both refraction and transmission functions are realized simultaneously. The dichroic beam splitter is used to separate two or more spectral bands for imaging by two or more imaging units. The imaging sensor can be a CCD detector or a CMOS detector.

[0040] like Figures 1-5 As shown, in this embodiment, the calibration device 2 also includes an upper limit device connecting frame 212 and a mounting base 206. The upper limit device connecting frame 212 is connected to the motor mounting frame 210, and the upper limit device 207 is connected to the upper limit device connecting frame 212. The cross-sectional structure of the upper limit device connecting frame 212 is Z-shaped. The Z-shaped structure design ensures that the upper limit device connecting frame 212 and the motor mounting frame 210 are tightly fitted together by screws. The upper limit device 207 is also connected to the upper limit device connecting frame 212 by screws to form an integral structure, ensuring the stable connection of the upper limit device 207. The mounting base 206 is fixedly connected to the lower part of the motor mounting frame 210. The mounting base 206 is the support and installation structure of the entire calibration device 2. The motor mounting frame 210 is fixedly installed on the mounting base 206, and then the components on the motor mounting frame 210 are also installed. After that, the calibration device 2 can be installed in the working position for imaging and calibration work.

[0041] like Figures 1-4 As shown, in this embodiment, the calibration device 2 further includes a position sensor mounting bracket 213, which is connected to the motor mounting bracket 210. The position sensor 205 is mounted on the position sensor mounting bracket 213. The position sensor mounting bracket 213 is fixedly connected to the motor mounting bracket 210 by bolts. The position sensor 205 is rotatably mounted on the position sensor mounting bracket 213. The mounting bracket 213 provides a stable support for the position sensor 205, ensuring the normal operation of the position sensor 205.

[0042] like Figures 1-5 As shown, in this embodiment, the calibration device 2 further includes an adapter mounting component 215. The calibration reticle mounting bracket 202 is fixedly connected to the adapter mounting component 215, and the adapter mounting component 215 is fixedly connected to the power output shaft of the motor 203. The adapter mounting component 215 is used to install the calibration reticle mounting bracket 202, and both the adapter mounting component 215 and the calibration reticle mounting bracket 202 have mounting holes at their bottoms corresponding to the power output shaft of the motor 203, so that the calibration reticle mounting bracket 202 is mounted on the adapter. While mounting component 215 is in place, both the adapter mounting component 215 and the calibration reticle mounting bracket 202 are fitted onto the power output shaft of motor 203 through the mounting port. Then, the adapter mounting component 215, the calibration reticle mounting bracket 202 and the power output shaft of motor 203 are fixedly connected by connecting screws 208, so that the adapter mounting component 215 and the calibration reticle mounting bracket 202 rotate with the power output shaft of motor 203. Specifically, the adapter mounting component 215 contacts the upper limit block 214 to form a limit.

[0043] like Figures 1-5As shown, the present invention also includes a method for real-time calibration of the line of sight of multiple sensors. This method is based on an airborne optoelectronic payload for real-time calibration of the line of sight of multiple sensors as described in any of the above claims. The airborne optoelectronic payload receives electromagnetic radiation from an external target. The electromagnetic radiation is incident on the forward telescope system 1 and the calibration reticle 201, and then exits to the beam splitting unit. The electromagnetic radiation is transmitted through the beam splitting unit to the imaging optical path and then imaged on the imaging sensor. The electromagnetic radiation is also refracted through the beam splitting unit to adjacent imaging units. The imaging deviation of multiple imaging sensors is detected, and the deviation of the image is corrected to complete the calibration of the line of sight of multiple imaging sensors.

[0044] Specifically, when calibration is required, motor 203 drives the calibration reticle mounting bracket 202 to rotate to the lower limit position, whereby the calibration reticle mounting bracket 202 contacts the lower limit device 211. At this time, the calibration reticle 201 enters the optical path. After calibration is completed and no further calibration is needed, motor 203 drives the calibration reticle mounting bracket 202 to rotate to the upper limit position, whereby the calibration reticle mounting bracket 202 contacts the upper limit block 214. At this time, the calibration reticle 201 exits the optical path. The airborne optoelectronic payload receives signals from external targets. Electromagnetic radiation, if the front telescope system 1 is a hybrid refractive and reflective optical system, parallel light first enters the primary mirror 101, is reflected by the primary mirror 101 to the secondary mirror 102, and then sequentially transmitted from the secondary mirror 102 to the calibration reticle 201 and the corrective mirror group 103, finally exiting as parallel light to the dichroic beam splitter; if the front telescope system 1 is a refractive telescope system, parallel light first enters the front telescope mirror group 104, then sequentially transmitted to the calibration reticle 201 and the rear telescope mirror group 105, finally exiting as parallel light to the dichroic beam splitter. Figure 1Or, as shown in Figure 2, the first dichroic beam splitter 3, the first imaging optical path 6, and the first imaging sensor 9 are arranged horizontally in sequence; the second dichroic beam splitter 4, the second imaging optical path 7, and the second imaging sensor 10 are arranged horizontally in sequence; and the third dichroic beam splitter 5, the third imaging optical path 8, and the third imaging sensor 11 are arranged horizontally in sequence. All imaging units are arranged in parallel. Light emitted from the first dichroic beam splitter 3 is transmitted through it to the corresponding first imaging optical path 6 and first imaging sensor 9, and simultaneously refracted by the first dichroic beam splitter 3 to the second dichroic beam splitter 6. The first imaging sensor 9, the second imaging sensor 10, and the third imaging sensor 11 are sequentially transmitted through the second dichroic beam splitter 4 to the corresponding second imaging optical path 7 and the second imaging sensor 10. Simultaneously, the light is refracted by the second dichroic beam splitter 4 to the third dichroic beam splitter 5, and then sequentially transmitted through the third dichroic beam splitter 5 to the corresponding third imaging optical path 8 and the third imaging sensor 11. Finally, after the first imaging sensor 9, the second imaging sensor 10, and the third imaging sensor 11 form an image, the imaging deviation of the first imaging sensor 9, the second imaging sensor 10, and the third imaging sensor 11 is detected, and the image is then processed using an image buffering and synthesis system. The system corrects for image deviations and calibrates the visual axes of multiple imaging sensors. It should be noted that multiple imaging units can be configured according to calibration requirements, allowing for simultaneous real-time calibration and correction of multiple sensors. The imaging optical path can achieve imaging of visible light, near-infrared, mid-wave infrared, or long-wave infrared spectra. The communication interface of the airborne optoelectronic payload connects to an external main control system for signal or command transmission. The communication interface is also connected to the payload control system for signal transmission. The payload control system is connected to moving parts within the payload, such as position sensor 205 or motor 203. The payload control system controls the rotation of motor 203 or the zoom function of the front telescope system 1. The payload control system is also sequentially connected to the CCD control and processing system, image buffer and synthesis system, and data transmission interface. The CCD control and processing system is connected to the imaging sensor for controlling image capture and feedback. The image buffer and synthesis system corrects for image deviations and transmits the data to a designated external system via the data transmission interface. The payload control system, CCD control and processing system, and image buffer and synthesis system are existing technologies configured by those skilled in the art according to actual needs.

[0045] like Figure 3 , Figure 4 , Figure 5 , Figure 8 , Figure 9 and Figure 10 As shown in this embodiment, Figure 8 To utilize the effect of this invention on imaging axis deviation Figure 1 , Figure 9 To utilize the effect of this invention on imaging axis deviation Figure 2 , Figure 10 To utilize the effect of this invention on imaging axis deviation Figure 3 All three imaging techniques target the same target, using the scribe lines on reticle 201 as a reference. Therefore, the effect... Figure 1 Based on the baseline, the effect Figure 2 The sensor in the middle has a horizontal deviation, which affects the effect. Figure 3 The sensors in the system have vertical and rotational deviations. The sensors can be corrected according to the above diagram to achieve fast and real-time alignment between sensors. This method can be used for real-time calibration during flight or for calibration and correction during ground assembly and testing. At the same time, the calibration reticle 201 can be used to measure and correct the distortion and image flatness of multiple sensors in the optical system.

[0046] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. An airborne optoelectronic payload for real-time calibration of multi-sensor line-of-sight, comprising: A front-mounted telescope system (1), a calibration device (2), and an imaging unit are characterized in that the calibration device (2) is provided with a calibration reticle (201), the calibration reticle (201) is a grid-line structure, the calibration reticle (201) is located on the primary image plane of the front-mounted telescope system (1), and the calibration reticle (201) and the front-mounted telescope system (1) are located on the same optical axis. Multiple imaging units are arranged in parallel. The imaging unit includes a beam splitting unit, an imaging optical path, and an imaging sensor arranged in a horizontal sequence. The beam splitting unit is located on the outgoing optical path of the front-mounted telescope system (1). The calibration device (2) includes a motor (203), a calibration reticle mounting bracket (202), and a motor mounting bracket (210). The motor (203) is mounted on the motor mounting bracket (210), and the calibration reticle (201) is mounted on the calibration reticle mounting bracket (202). The calibration reticle mounting bracket (202) is fixedly connected to the power output shaft of the motor (203).

2. The airborne optoelectronic payload for real-time calibration of multi-sensor line-of-sight as described in claim 1, characterized in that, The calibration device (2) further includes an upper limit device (207) and a lower limit device (211). The upper limit device (207) is located above one side of the motor mounting bracket (210), and the lower limit device (211) is located below the other side of the motor mounting bracket (210). An upper limit block (214) is provided on the side of the upper limit device (207) near the calibration reticle mounting bracket (202).

3. The airborne optoelectronic payload for real-time calibration of multi-sensor line-of-sight as described in claim 1, characterized in that, An upper gear (204) is fixedly connected to the power output shaft of the motor (203), a lower gear (209) meshes with the upper gear (204), and a position sensor (205) is fixedly connected to the lower gear (209).

4. The airborne optoelectronic payload for real-time calibration of multi-sensor line-of-sight as described in claim 1, characterized in that, The front telescope system (1) includes a primary mirror (101), a secondary mirror (102), and a corrector mirror group (103). The primary mirror (101), the secondary mirror (102), the corrector mirror group (103), and the calibration reticle (201) are located on the same optical axis. The beam splitting unit is a dichroic beam splitter, and the dichroic beam splitter is located on the outgoing light path of the corrector mirror group (103).

5. An airborne optoelectronic payload for real-time calibration of multi-sensor line-of-sight according to claim 1, characterized in that, The front telescope system (1) includes a front telescope mirror group (104) and a rear telescope mirror group (105). The front telescope mirror group (104), the calibration reticle (201), and the rear telescope mirror group (105) are located on the same optical axis. The beam splitting unit is a dichroic beam splitter, which is located on the outgoing light path of the rear telescope mirror group (105).

6. An airborne optoelectronic payload for real-time calibration of multi-sensor line-of-sight according to claim 2, characterized in that, The calibration device (2) further includes an upper limit device connecting frame (212) and a mounting base (206). The upper limit device connecting frame (212) is connected to the motor mounting frame (210), the upper limit device (207) is connected to the upper limit device connecting frame (212), and the mounting base (206) is fixedly connected to the lower part of the motor mounting frame (210).

7. An airborne optoelectronic payload for real-time calibration of multi-sensor line-of-sight according to claim 3, characterized in that, The calibration device (2) also includes a position sensor mounting bracket (213), which is connected to the motor mounting bracket (210), and the position sensor (205) is mounted on the position sensor mounting bracket (213).

8. An airborne optoelectronic payload for real-time calibration of multi-sensor line-of-sight according to claim 1, characterized in that, The calibration device (2) also includes an adapter (215), the calibration reticle mounting bracket (202) is fixedly connected to the adapter (215), and the adapter (215) is fixedly connected to the power output shaft of the motor (203).

9. A method for real-time calibration of multi-sensor line-of-sight, the method being implemented based on an airborne optoelectronic payload for real-time calibration of multi-sensor line-of-sight as described in any one of claims 1 to 8, characterized in that, The airborne optoelectronic payload receives electromagnetic radiation from external targets. The electromagnetic radiation is incident on the forward telescope system (1) and the calibration reticle (201), and then emitted to the beam splitting unit. The electromagnetic radiation is transmitted through the beam splitting unit to the imaging optical path and then imaged on the imaging sensor. The electromagnetic radiation is also refracted through the beam splitting unit to the adjacent imaging unit. The imaging deviation of multiple imaging sensors is detected, and the deviation of the image is corrected to complete the calibration of the line of sight of multiple imaging sensors.

Images