A multi-component coupling structure of an airborne map correlation probe and a debugging method thereof

Abstract

The application provides a multi-component coupling structure of an airborne atlas correlation detection and a debugging method thereof, which comprises a main frame, a front optical mechanism coupled to the main frame, a two-dimensional roll-tilt servo Kude light path, a vibration-resistant switching mirror mechanism, an infrared imaging mechanism, an infrared spectrum measurement mechanism and a temperature regulation mechanism; incident light passes through the front optical mechanism and the two-dimensional roll-tilt servo Kude light path in sequence, and is dispersed by the vibration-resistant switching mirror mechanism; the infrared imaging mechanism is used for receiving the light dispersed by the vibration-resistant switching mirror mechanism to perform infrared imaging, and the infrared spectrum measurement mechanism receives the light dispersed by the vibration-resistant switching mirror mechanism to perform infrared spectrum measurement; and the temperature regulation mechanism increases or decreases the temperature during infrared spectrum measurement. In the application, the infrared imaging mechanism and the infrared spectrum measurement mechanism work under vibration conditions and temperature control conditions, can meet the vibration demand and temperature demand in the detection process, can perform spectrum measurement in an airborne environment, and improve the detection efficiency and detection result accuracy of the detection equipment.

Description

Technical Field

[0001] This invention belongs to the field of photoelectric detection, and more specifically, relates to a multi-component coupling structure for airborne image correlation detection and its debugging method. Background Technology

[0002] With the continuous development of optoelectronic countermeasures and camouflage technologies, existing optoelectronic detection equipment, based on single-band or dual-band detection techniques, can no longer meet the needs of detecting and identifying different targets in today's complex scenarios. Single-band and dual-band detection technologies are evolving towards multi-band and multi-sensor detection and identification. The number of components in optoelectronic detection systems is also gradually increasing, leading to greater system complexity and posing challenges to the information fusion and control processing of each component.

[0003] Existing infrared spectroscopy equipment is typically used in laboratories or on fixed ground platforms, and its data acquisition real-time performance is not high. Currently, there are no miniaturized detection devices on the market that couple infrared imaging and infrared spectroscopy under high vibration conditions on airborne moving platforms. For applications under airborne vibration conditions, miniaturized spectral correlation detection devices with multiple components and functions are relatively complex systems, requiring high levels of vibration resistance, complexity, and reproducibility. Furthermore, the spectral measurement modules used in complex ground scenarios are precision components with stringent requirements for operating temperature and vibration, making the system structural design even more demanding.

[0004] Therefore, how to perform information fusion and control processing of system components under the high complexity of detection equipment, and how to improve the detection effect of detection equipment under different temperature and vibration conditions, are the technical problems that urgently need to be solved. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention proposes a multi-component coupling structure and its debugging method for airborne spectrum correlation detection. The aim is to solve the problems of miniaturization of precision spectral measurement modules and complex multi-component systems of spectrum correlation detection equipment under airborne vibration conditions, and to achieve system coupling under the requirements of high vibration and wide temperature range in complex airborne operating conditions, thereby improving the detection effect of the detection equipment under different temperature and vibration conditions.

[0006] To achieve the above objectives, the present invention provides a multi-component coupling structure for airborne map correlation detection.

[0007] A multi-component coupling structure for airborne image correlation detection includes a main frame and a front optical mechanism, a two-dimensional roll-up servo Couder optical path, an anti-vibration switching mirror mechanism, an infrared imaging mechanism, an infrared spectroscopy mechanism, and a temperature control mechanism coupled to the main frame.

[0008] The front optical mechanism, the two-dimensional roll-up servo Couder optical path, and the anti-vibration switching mirror mechanism are arranged and coupled from top to bottom and located on the same optical path.

[0009] The incident light passes sequentially through the front optical mechanism and the two-dimensional roll-up servo Couder optical path, and is dispersed by the anti-vibration switching mirror mechanism;

[0010] The infrared imaging mechanism is used to receive the dispersed light from the anti-vibration switching mirror mechanism for infrared imaging.

[0011] The temperature control mechanism is coupled to the infrared spectroscopy mechanism to raise or lower the temperature during infrared spectroscopy.

[0012] In some embodiments, a plate is fixedly connected inside the main frame, and the plate divides the interior of the main frame into an upper optical compartment and a lower component compartment. The front optical mechanism, the two-dimensional roll-up servo Cood optical path and the vibration-resistant switching mirror mechanism are disposed in the optical compartment, and the infrared imaging mechanism and the infrared spectroscopy mechanism are disposed in the component compartment.

[0013] In some embodiments, the vibration-resistant switching mirror mechanism includes a plane mirror, a translational guide rail, and an electric cylinder; the translational guide rail and the electric cylinder are both fixedly connected to the plate, the plane mirror is slidably disposed on the translational guide rail via a ladder, the ladder is fixedly connected to the output end of the electric cylinder, and the electric cylinder drives the plane mirror to slide on the translational guide rail.

[0014] In some embodiments, the planar reflector has a first aperture and a second aperture, wherein the diameter of the first aperture is larger than the diameter of the second aperture.

[0015] In some embodiments, the infrared spectroscopy mechanism further includes coupling between a three-mode polarization rotation switching structure and a rotating interferometric spectroscopy structure; light passing through the first aperture or the second aperture enters the rotating interferometric spectroscopy structure through the three-mode polarization rotation switching structure and is subjected to infrared spectroscopy at the rotating interferometric spectroscopy structure.

[0016] In some embodiments, the three-mode polarization rotation switching structure includes a motor, a polarization wheel, a compensation lens, a horizontal polarization lens, and a vertical polarization lens. The center of the polarization wheel is rotatably connected to the plate, and the motor is fixedly connected to the plate. The compensation lens, the horizontal polarization lens, and the vertical polarization lens are all fixedly connected to the polarization wheel and are equidistantly arranged around the axis of the polarization wheel. The motor drives the polarization wheel to rotate to switch between the compensation lens, the horizontal polarization lens, and the vertical polarization lens.

[0017] In some embodiments, the rotating interferometric spectroscopy structure includes an interferometer body, an infrared beam splitter, a rotating refracting mirror, a split Stirling detector, and several reflectors. The interferometer body has an entrance port and an exit port. The infrared beam splitter, the rotating refracting mirror, the split Stirling detector, and the several reflectors are all disposed on the interferometer body. Light passes through the collimating lens at the entrance port and enters the interior of the interferometer body. After being split by the infrared beam splitter, it is refracted by the rotating refracting mirror and returns along the same path through the reflectors. It then passes through the infrared beam splitter and the converging mirror at the exit port before entering the split Stirling detector.

[0018] In some embodiments, the temperature control mechanism includes a temperature controller, a temperature monitoring chip, a cooling element, and a heating coil; the temperature monitoring chip, the cooling element, and the heating coil are all disposed on the interference body and are all connected to the temperature controller.

[0019] The present invention also provides a debugging method for a multi-component coupling structure of airborne map correlation detection, comprising the following steps:

[0020] S1: Complete the assembly and adjustment between the front optical mechanism, the two-dimensional roll-up servo Coulomb optical path, the vibration-resistant switching mirror mechanism, the infrared imaging mechanism, the infrared spectroscopy mechanism, and the temperature control mechanism and the main frame.

[0021] S2: Acquire inertial navigation system integration data and determine the target;

[0022] S3: Guide the multi-component coupling structure of the airborne spectrum association detection to the target using the inertial navigation combined data, perform matching tracking within the field of view and acquire the target's spectrum.

[0023] In summary, the technical solutions conceived by this invention have the following beneficial effects compared with the prior art:

[0024] This invention provides a multi-component coupling structure and its debugging method for airborne spectral correlation detection. It couples multiple mechanical components of the detection device, integrating multiple components within the complex system of the detection device to achieve high-precision optical detection, infrared imaging, and infrared spectroscopy. Furthermore, the infrared imaging and infrared spectroscopy mechanisms in this invention operate under vibration and temperature control conditions, thus meeting the vibration and temperature requirements during the detection process. This enables spectral measurements to be performed in both airborne and temperature-controlled environments, improving the detection efficiency and accuracy of the detection results. Attached Figure Description

[0025] Figure 1 This is a first-view overall structural diagram of the multi-component coupling structure for airborne map correlation detection provided in an embodiment of the present invention;

[0026] Figure 2This is a second-view overall structural schematic diagram of the multi-component coupling structure for airborne map correlation detection provided in an embodiment of the present invention;

[0027] Figure 3 This is a front view schematic diagram of the multi-component coupling structure for airborne map correlation detection provided in an embodiment of the present invention;

[0028] Figure 4 This is a schematic diagram illustrating the overall structure of the vibration-resistant switching mirror mechanism according to an embodiment of the present invention;

[0029] Figure 5 This is a schematic diagram of the overall structure of the rotating interferometric spectroscopy structure shown in an embodiment of the present invention;

[0030] Figure 6 This is a schematic diagram of the overall structure of the three-mode polarization rotation switching structure shown in an embodiment of the present invention;

[0031] Figure 7 This is a block diagram of the temperature control mechanism according to an embodiment of the present invention;

[0032] Figure 8 This is a flowchart of the multi-component coupling structure debugging method for airborne map correlation detection according to the present invention;

[0033] Figure 9 This is a schematic diagram of the internal rotational interference optical structure of the interference subject.

[0034] Reference numerals: 1. Main frame; 11. Flat plate; 12. Optical cabin; 13. Component cabin; 2. Front optical mechanism; 3. Two-dimensional roll-up servo Cood optical path; 4. Vibration-resistant switching mirror mechanism; 41. Plane mirror; 411. First aperture; 412. Second aperture; 42. Translation guide rail; 43. Electric cylinder; 44. Ladder platform; 5. Infrared imaging mechanism; 51. Infrared imaging mirror group; 52. Infrared imaging detector; 6. Infrared spectral measurement mechanism; 61. Three-mode polarization rotation switching structure; 611. Motor; 612. Polarization wheel; 613. Compensation lens; 614. Horizontal polarizing lens; 615. Vertical polarizing lens; 62. Rotating interferometric spectral measurement structure; 621. Interferometer body; 622. Reflector; 623. Rotating refracting mirror; 624. Split Stirling detector; 7. Temperature control mechanism; 71. Temperature controller; 72. Temperature monitoring chip; 73. Cooling element; 74. Heating coil. Detailed Implementation

[0035] For ease of understanding, the English abbreviations and related technical terms used in the embodiments of this application will be explained and described below.

[0036] Multi-mechanism coupling refers to the interconnection and mutual influence among multiple components in a system, in order to ensure that the system can work normally and has good reliability and stability in practical applications.

[0037] The following is an example of the embodiments of this application. Figure 1-9 The embodiments of this application are described below.

[0038] Coupling refers to the phenomenon where two or more components work closely together and influence each other, and energy is transferred from one side to the other through their interaction.

[0039] This invention provides a multi-component coupling structure for airborne spectrum correlation detection, aiming to solve the problems of miniaturization of precision spectral measurement modules under airborne vibration conditions and the complex multi-component system of spectrum correlation detection equipment under complex airborne operating conditions, high vibration and wide temperature range requirements, to achieve system coupling. The structure includes a main frame 1 and a front optical mechanism 2, a two-dimensional roll-up servo Couder optical path 3, an anti-vibration switching mirror mechanism 4, an infrared imaging mechanism 5, an infrared spectral measurement mechanism 6, and a temperature control mechanism 7, all coupled to the main frame 1. The main frame 1 serves as the main body of the entire device, accommodating all mechanisms. The main frame 1 is coupled to and connected to each mechanism. The main coupling between the main frame 1 and the infrared imaging mechanism 5 and the infrared spectral measurement mechanism 6 enables dynamic coaxial sliding of dual optical paths. The coupling between the main frame 1 and the anti-vibration switching mirror mechanism 4 enables pixel-level accurate aperture switching without angular rotation deviation.

[0040] The front optical mechanism 2, the two-dimensional roll-up servo Couder optical path 3, and the anti-vibration switching mirror mechanism 4 are arranged sequentially from top to bottom and located on the same optical path. The incident light passes through the front optical mechanism 2 and the two-dimensional roll-up servo Couder optical path 3 in sequence, and then the light is dispersed by the anti-vibration switching mirror mechanism 4. The two-dimensional roll-up servo Couder optical path 3 has a smooth circular deviation at the pixel level and a flatness deviation at the micrometer level. The anti-vibration switching mirror mechanism 4 can achieve accurate pixel-level switching of the aperture and has no angular rotation deviation. The infrared imaging mechanism 5 receives the light dispersed by the anti-vibration switching mirror mechanism 4 and performs infrared imaging. The infrared spectroscopy mechanism 6 receives the light dispersed by the anti-vibration switching mirror mechanism 4 and performs infrared spectroscopy. The temperature control mechanism 7 is used to raise or lower the temperature during infrared spectroscopy.

[0041] The overall external structure of the image association detection equipment should also be fixedly connected to a shell (not shown in the figure) to enable the mounting of small carrier aircraft such as rotary-wing UAVs. The shell is made of integrated aluminum alloy shell by milling and turning, and undergoes electroplating oxidation process to achieve anti-oxidation treatment. The front end of the shell uses a circular threaded buckle to fix the zinc selenide crystal fairing to the shell. The shell uses a two-stage stepped circular boss to realize the shell support structure to enhance the installation and fixation of the shell and the internal frame keel. The assembly and integration of the shell and the internal structure is achieved by multiple layers of evenly distributed countersunk screws. All interfaces of the whole structure adopt reinforced embedded fit. The shell has an integrated sleeve sealing design. A nitrogen gas inlet is opened at the upper end of the shell and a nitrogen gas exhaust port is opened at the lower end of the shell. By means of nitrogen replacement, the internal insulation of the whole system is achieved, and at the same time, the problem of condensation of water droplets caused by hot gas generated during equipment operation meeting the cold optical lenses is solved.

[0042] To enable the airborne operation of the map correlation detection equipment, the overall weight of the equipment should be within 30 kg. An optimized small modular multi-component structure design should be adopted to meet the prototype development requirements for achieving the desired overall weight.

[0043] In this embodiment, the main frame 1 is machined from an aluminum alloy structure, and the main frame 1 housing is designed with a two-stage stepped thickened positioning design. While confirming the installation positioning, the vibration resistance of the whole system is improved, and it can meet the high vibration level requirements in the frequency range of 20Hz to 2000Hz. After ensuring the vibration analysis of the whole structure, the structural reservations necessary for equipment assembly and adjustment are machined, and the remaining structural parts are reinforced. This allows the main frame 1 to meet the vibration requirements while reducing the redundancy of structural weight.

[0044] To reduce the coupling difficulty between the main frame 1 and various mechanisms, the main frame 1 is designed as a flat plate 11 and a cage structure. Specifically, the main frame 1 is a hollow columnar structure that is narrow at the top and wide at the bottom. The flat plate 11 is fixedly connected inside the main frame 1. The flat plate 11 divides the interior of the main frame 1 into an optical cabin 12 located at the top and a component cabin 13 located at the bottom, forming a two-stage stepped columnar cage structure. The flat plate 11 has a circular light-transmitting port to connect the optical cabin 12 and the component cabin 13. It also serves as the only docking interface between the sealed systems of the optical cabin 12 and the component cabin 13. The front optical mechanism 2, the two-dimensional roll-up servo Coulomb optical path 3, and the vibration-resistant switching mirror mechanism 4 are located in the optical cabin 12. The infrared imaging mechanism 5 and the infrared spectroscopy mechanism 6 are located in the component cabin 13. The flat plate 11 provides a fixed carrier for each mechanism, which not only facilitates modular assembly and debugging, but also provides radial structural support for the main frame 1, thereby enhancing the structural vibration resistance of the main frame 1.

[0045] The front optical mechanism 2 adopts a transmission optical telescope group and serves as the optical entrance for the entire device. Light passes through the two-dimensional roll-up servo Couder optical path 3 and is dispersed at the anti-vibration switching mirror mechanism 4. In this embodiment, the two-dimensional roll-up servo Couder optical path 3 is a lightweight Couder optical path system capable of ±20° pitch movement and 360° continuous roll of the slip ring mechanism. The anti-vibration switching mirror mechanism 4 includes a high-reflectivity plane mirror 41, a translation guide rail 42, and an electric cylinder 43. The translation guide rail 42 and the electric cylinder 43 are both fixedly connected to the plate 11. The plane mirror 41 is slidably connected to the translation guide rail 42 via a ladder 44. The ladder 44 is fixedly connected to the output end of the electric cylinder 43, and the electric cylinder 43 drives the plane mirror 41. Sliding on the translation guide rail 42 allows the plane mirror 41 to accurately switch between large and small apertures under high vibration conditions. At the same time, the mechanism has anti-vibration capability, and the switching mirror mechanism will not be deflected due to vibration, thus eliminating the imaging blur problem caused by imaging defocus and the spectral measurement blockage problem caused by spectral path offset. The aperture switching is specifically achieved by opening a first aperture hole 411 and a second aperture hole 412 on the plane mirror 41, with the diameter of the first aperture hole 411 being larger than the diameter of the second aperture hole 412. Different aperture holes of different sizes are selected according to the target size in the application scenario. The vibration-resistant switching mirror mechanism 4 can meet pixel-level translation switching without angle rotation and can meet the accurate spectral measurement in high-precision tracking.

[0046] To achieve infrared imaging, the infrared imaging mechanism 5 includes an infrared imaging mirror group 51 and an infrared imaging detector 52. The infrared imaging detector 52 is connected to the infrared imaging mirror group 51, and the plane mirror 41 splits the light into the infrared imaging mirror group 51 and the infrared imaging detector 52 for infrared imaging.

[0047] To achieve infrared spectroscopy, the infrared spectroscopy mechanism 6 includes a coupling between a three-mode polarization rotation switching structure 61 and a rotating interferometric spectroscopy structure 62. Light passing through the first aperture 411 or the second aperture 412 enters the rotating interferometric spectroscopy structure 62 through the three-mode polarization rotation switching structure 61 and is subjected to infrared spectroscopy at the rotating interferometric spectroscopy structure 62. In this embodiment, the three-mode polarization rotation switching structure 61 includes a motor 611, a polarization wheel 612, a compensation lens 613, a horizontal polarizing lens 614, and a vertical polarizing lens 615. The motor 611 is a servo motor. A fixed housing is fixedly connected to the bottom of the plate 11. The center of the polarization wheel 612 is rotatably connected between the main frame 1 and the fixed housing to achieve stable rotation switching of the polarization wheel 612. The motor 611 is fixedly connected to the plate 11. On plate 11, compensation lens 613, horizontal polarizing lens 614, and vertical polarizing lens 615 are all fixedly connected to polarizing wheel 612 and are equidistantly arranged around the axis of polarizing wheel 612. Motor 611 drives polarizing wheel 612 to rotate to switch compensation lens 613, horizontal polarizing lens 614, and vertical polarizing lens 615. Gear is fixedly connected to the output shaft of motor 611. Gear groove is opened on the outer peripheral wall of polarizing wheel 612. Gear meshes with gear groove. By driving polarizing wheel 612 through motor 611, the rapid switching of compensation lens 613, horizontal polarizing lens 614, and vertical polarizing lens 615 is realized. The polarization state spectrum obtained after the radiation and reflection energy of target materials of different materials passes through polarizing lens increases the spectral data of two different modal dimensions compared with the original spectrum, increasing the dimensional diversity of material identification.

[0048] Because the light inlet of the rotating interferometric spectroscopy structure 62 is less affected by small-range translations along the horizontal axis, but is more sensitive to angular rotation in the direction of the incident light axis, the assembly structure of the rotating interferometric spectroscopy structure 62 is designed as a three-sided fixed stepped anti-cantilever structure. The main mounting surface of the three-sided reinforced structure is in the direction of the central axis of the L-shaped equipment. Both sides adopt reinforced structural bosses that fit into the grooves of the main cabin structure. After being fixed with screws, the vibration resistance of the entire rotating interferometric spectroscopy structure 62 mounting step is improved. The main mounting surface of the rotating interferometric spectroscopy structure 62 is a multi-hole fixed surface perpendicular to the optical axis. The plate 11 is the main mounting surface of the rotating interferometric spectroscopy structure 62. The vibration resistance of the rotating interferometric spectroscopy structure 62 is improved by adopting a three-sided encircling method at the light inlet and outlet apertures. This solves the problem of optical path offset caused by vibration in the spectroscopy module introduced by airborne vibration, which leads to the final spectroscopy abnormality and prevents angular rotation and vibration amplification of the rotating interferometric spectroscopy structure 62.

[0049] The rotating interferometric spectroscopy structure 62 includes an interferometer body 621, an infrared beam splitter (located inside the interferometer body, not shown in the figure), a rotating refracting mirror 623, a split Stirling detector 624, and several reflectors 622. The interferometer body 621 has an entrance port and an exit port. A collimating lens is fixedly connected to the entrance port, and a converging mirror is fixedly connected to the exit port. The infrared beam splitter, rotating refracting mirror 623, split Stirling detector 624, and several reflectors 622 are all fixedly connected inside the interferometer body 621. To achieve the rotation of the rotating refracting mirror 623, it is connected to the output shaft of a drive motor located outside the interferometer body 621. Light enters the interior of the interferometer body 621 through the entrance port, is split by the infrared beam splitter, refracted by the rotating refracting mirror 623, and then passes through the rotating refracting mirror 623. The light returns via the reflector 622 and passes through the infrared beam splitter and the converging lens at the output port to enter the split Stirling detector 624. The input port of the interference body 621 adopts a rotary adjustable design, which can complete the integration and adjustment of the entire spectral measurement module through rotation adjustment. This design greatly reduces the complexity of the spectral measurement optical path assembly and adjustment and the difficulty of coupling the modular system. The output port converging window and the split Stirling cooled detector adopt an adjustable focal length lens tube design to integrate the detector and the main optical path of the spectral measurement module, reducing the assembly and adjustment difficulty. This spectral measurement structure has a fast measurement speed and can realize wide-band spectral measurement in the infrared short-wave, mid-wave, and long-wave bands. It realizes a high-sensitivity, high-resolution, lightweight, and structurally stable rotary interferometric spectral measurement structure 62, which can be applied to various moving platform carriers and field sites.

[0050] according to Figure 9 The diagram illustrates the internal rotating interference optical structure of the interference body 621. Incident light enters through the field stop FS, passes through the correction lens LC, and is projected onto the beam splitter (beam splitter) BS (semi-reflective, semi-transparent). One half of the light is reflected to the top mirror M, then passes through the rotating refractor R, and finally is reflected by the bottom mirror ME, returning to the beam splitter BS along its original path. The other half of the light incident on the beam splitter BS is reflected by the bottom mirror M, transmitted through the rotating refractor R, reflected by the top mirror ME, and then returned to the beam splitter BS along its original path. The two reflected light beams recombine at the beam splitter BS (phase interference) and are then focused by the focusing lens LF onto the spectral detector D. The interference light is converted into a voltage signal by the detector, and as the rotating refractor R rotates, different optical path differences (OPD) are formed. Each rotation produces four points with an optical path difference of 0, thus four frames of interference spectrum are acquired per rotation.

[0051] To meet the vibration requirements of the rotating interferometric spectroscopy structure 62, the interferometric body 621 adopts a complete aluminum alloy structure with six circular lenses machined and milled inside to pass through the optical path. The light inlet, light outlet and bottom surface of the interferometric body 621 are all set as constraint planes with different directions, which enhances the vibration resistance in three directions. Finally, the rotating interferometric spectroscopy structure 62 can achieve vibration on the order of 10G.

[0052] The temperature control mechanism 7 includes a temperature controller 71, a temperature monitoring chip 72, a cooling element 73, and a heating coil 74. The temperature monitoring chip 72, the cooling element 73, and the heating coil 74 are all fixedly mounted on the interferometric body 621 and are all connected to the temperature controller 71. The temperature monitoring chip 72 monitors the temperature of the interferometric body 621 in real time. When the ambient temperature is higher than the set temperature, the temperature controller 71 controls the cooling element 73 to cool down the interferometric body 621, thus achieving the cooling function. When the ambient temperature is lower than the set temperature, the temperature controller 71 controls the heating coil 74 to heat up, thus achieving the heating function. The temperature of the temperature-sensitive spectral measurement module can be maintained within its stable operating temperature range, making the application scenarios of the rotating interferometric spectral measurement structure 62 more extensive.

[0053] The present invention also discloses a debugging method for a multi-component coupling structure of an airborne map correlation detection system.

[0054] A debugging method for a multi-component coupling structure of an airborne map correlation detection system includes the following steps:

[0055] S1: Assemble and adjust the front optical mechanism 2, the two-dimensional roll-up servo Coulette optical path 3, the vibration-resistant switching mirror mechanism 4, the infrared imaging mechanism 5, the infrared spectroscopy mechanism 6, and the temperature control mechanism 7 with the main frame 1; after assembling the front optical mechanism 2 and the two-dimensional roll-up servo Coulette optical path 3, adjust the flatness and angle errors to pixel-level deviations; perform loop adjustment on the vibration-resistant switching mirror mechanism 4, the infrared imaging mechanism 5, and the infrared spectroscopy mechanism 6.

[0056] S2: Acquire inertial navigation system integration data and determine the target;

[0057] S3: Guide the multi-component coupling structure of the airborne spectrum association detection to the target using the inertial navigation combined data, perform matching tracking within the field of view and acquire the target's spectrum.

[0058] The debugging method of airborne image association detection equipment is tested under the condition of a static ground platform, after the integration of multiple mechanisms, for image association target acquisition, tracking, detection and identification. Under the condition of a moving ground platform, the image association detection equipment achieves target guidance through GPS information combined with inertial navigation, and completes matching tracking and spectral measurement of targets in complex ground backgrounds in the field of view, realizing the infrared imaging and infrared spectral measurement debugging method of the target.

[0059] Furthermore, the debugging method for airborne map correlation detection equipment also includes:

[0060] (1) The first step in the assembly and adjustment of the Kude optical path is to use an autocollimator to adjust the optical axis so that the tilt angle is minimized when the optical axis rotates with the mechanical axis. Then, the telescope and imaging detector are used to adjust the motion trajectory of the image rotating with the rotation axis so that the motion trajectory is minimized. Finally, the interferometer is used to detect the surface shape of the Kude optical path mirror to avoid surface shape changes introduced during the assembly and adjustment process. The above three steps are repeated to finally complete the assembly and adjustment of the two-dimensional roll-tilt servo Kude optical path 3.

[0061] (2) Place the telescope group in front of the collimator, place a striped target with a 1mm interval at the focal plane of the collimator, record the target image through the infrared detector, adjust the distance between the infrared imaging detector 52 and the telescope group until the target image is clear, the back intercept matches the theoretical design value, and the infrared imaging quality is good. Finally, the assembly and adjustment of the infrared imaging optical path is completed.

[0062] (3) Place the blackbody at the light inlet of the rotating interferometric spectral measurement structure 62, calibrate the blackbody to complete the spectral detector position assembly, and after the external assembly and adjustment of the rotating interferometric spectral measurement structure 62 is completed, integrate the rotating interferometric spectral measurement structure 62 into the whole structure, and quantitatively measure the spectrum of the light source until the spectrum is confirmed to be the position after the spectrum of the light source matches, and finally complete the assembly and adjustment of the infrared spectral measurement optical path;

[0063] Furthermore, the entire process of target-guided matching and tracking is as follows:

[0064] (1) Inertial navigation guidance calculates servo control parameters by using real-time acquired inertial navigation data and known target GPS data, and controls the servo to turn towards the target direction by controlling the motion angle;

[0065] (2) Using the positional relationship between the landmarks and the target in the landmark file, and using the real-time GPS information, attitude angle information and servo angle information of the inertial navigation system, the final matching point is obtained by calculating the matching response output map through perspective transformation; the target's precise position is obtained by controlling the servo to complete the target matching in the local area of ​​the field of view.

[0066] (3) After obtaining the precise target coordinate position, it enters the relevant filter position and scale estimation tracker to realize the rapid calculation and output of the target position and scale and update it in real time. It outputs the pixel deviation value of the target center, calculates the servo angular velocity value and transmits it to the servo rotation structure, and controls the servo to straighten the target image spectral center to complete the tracking spectral measurement.

[0067] (4) Pull the three targets in the field of view to the spectral measurement area in the center of the image in sequence for spectral measurement. Identify and classify the spectra of the three targets in the field of view of the ice fruit, return the real machine information number, use the target coordinate information stored in the real target number to control the servo movement, pull the real target to the center of the image and continuously track it until it exceeds the line of sight distance.

[0068] It should be understood that expressions such as “comprising” and “may include” used in this application indicate the existence of the disclosed functions, operations, or constituent elements, and do not limit one or more additional functions, operations, and constituent elements. In this application, terms such as “comprising” and / or “having” are to be interpreted as indicating a particular characteristic, number, operation, constituent element, component, or combination thereof, but not to exclude the existence or possibility of adding one or more other characteristics, numbers, operations, constituent elements, components, or combinations thereof.

[0069] Furthermore, in this application, the expression "and / or" includes any and all combinations of the associated listed words. For example, the expression "A and / or B" may include A, may include B, or may include both A and B.

[0070] In the description of the embodiments of this application, it should be noted that, unless otherwise explicitly specified and limited, the term "connection" should be interpreted broadly. For example, "connection" can be a detachable connection or a non-detachable connection; it can be a direct connection or an indirect connection through an intermediate medium. "Fixed connection" refers to a connection where the relative positional relationship remains unchanged after connection. "Rotary connection" refers to a connection where the components can rotate relative to each other after connection. "Sliding connection" refers to a connection where the components can slide relative to each other after connection. The directional terms mentioned in the embodiments of this application, such as "top," "bottom," "inner," "outer," "left," and "right," are only for reference to the directions in the accompanying drawings. Therefore, the directional terms used are for better and clearer explanation and understanding of the embodiments of this application, and are not intended to indicate or imply that the device or component 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 embodiments of this application.

[0071] Furthermore, the mathematical concepts mentioned in the embodiments of this application, such as symmetry, equality, parallelism, and perpendicularity, are limitations specific to the current technological level, rather than absolute and strict mathematical definitions. Slight deviations are permissible; approximations of symmetry, equality, parallelism, and perpendicularity are all acceptable. For example, "A and B are parallel" means that A and B are parallel or approximately parallel, and the angle between A and B can be between 0 and 10 degrees. "A and B are perpendicular" means that A and B are perpendicular or approximately perpendicular, and the angle between A and B can be between 80 and 100 degrees.

[0072] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A multi-component coupling structure for airborne map correlation detection, characterized in that, It includes a main frame (1) and a front optical mechanism (2) coupled to the main frame (1), a two-dimensional roll-up servo Couder optical path (3), an anti-vibration switching mirror mechanism (4), an infrared imaging mechanism (5), an infrared spectroscopy mechanism (6), and a temperature control mechanism (7); The front optical mechanism (2), the two-dimensional roll-up servo Coulomb optical path (3), and the anti-vibration switching mirror mechanism (4) are arranged and coupled from top to bottom and located on the same optical path; The incident light passes sequentially through the front optical mechanism (2) and the two-dimensional roll-up servo Couder optical path (3), and is dispersed by the anti-vibration switching mirror mechanism (4); The infrared imaging mechanism (5) is used to receive the light dispersed by the anti-vibration switching mirror mechanism (4) for infrared imaging; The infrared spectroscopy mechanism (6) is used to receive the light dispersed by the anti-vibration switching mirror mechanism (4) for infrared spectroscopy. The temperature control mechanism (7) is coupled to the infrared spectroscopy mechanism (6) to raise or lower the temperature during infrared spectroscopy. The main frame (1) is fixedly connected to a plate (11), which divides the interior of the main frame (1) into an optical compartment (12) located above and a component compartment (13) located below. The front optical mechanism (2), the two-dimensional roll-up servo Cood optical path (3) and the anti-vibration switching mirror mechanism (4) are located in the optical compartment (12), and the infrared imaging mechanism (5) and the infrared spectral measurement mechanism (6) are located in the component compartment (13). The vibration-resistant switching mirror mechanism (4) includes a plane mirror (41), a translation guide rail (42), and an electric cylinder (43); the translation guide rail (42) and the electric cylinder (43) are both fixedly connected to the plate (11), the plane mirror (41) is slidably mounted on the translation guide rail (42) via a ladder (44), the ladder (44) is fixedly connected to the output end of the electric cylinder (43), and the electric cylinder (43) drives the plane mirror (41) to slide on the translation guide rail (42); The plane mirror (41) has a first aperture (411) and a second aperture (412), and the diameter of the first aperture (411) is larger than the diameter of the second aperture (412). The infrared spectroscopy mechanism (6) includes a coupling between a three-mode polarization rotation switching structure (61) and a rotating interferometric spectroscopy structure (62). Light passing through the first aperture (411) or the second aperture (412) enters the rotating interferometric spectroscopy structure (62) through the three-mode polarization rotation switching structure (61) and is subjected to infrared spectroscopy at the rotating interferometric spectroscopy structure (62).

2. The multi-component coupling structure for airborne map correlation detection according to claim 1, characterized in that, The three-mode polarization rotation switching structure (61) includes a motor (611), a polarization wheel (612), a compensation lens (613), a horizontal polarization lens (614), and a vertical polarization lens (615). The center of the polarization wheel (612) is rotatably connected to the plate (11), and the motor (611) is fixedly connected to the plate (11). The compensation lens (613), the horizontal polarization lens (614), and the vertical polarization lens (615) are all fixedly connected to the polarization wheel (612) and are equidistantly arranged around the axis of the polarization wheel (612). The motor (611) drives the polarization wheel (612) to rotate to switch the compensation lens (613), the horizontal polarization lens (614), and the vertical polarization lens (615).

3. The multi-component coupling structure for airborne map correlation detection according to claim 1, characterized in that, The rotating interferometric spectral measurement structure (62) includes an interferometer body (621), an infrared beam splitter, a rotating refracting mirror (623), a split Stirling detector (624), and several reflectors (622). The interferometer body (621) has an entrance port and an exit port. The infrared beam splitter, the rotating refracting mirror (623), the split Stirling detector (624), and several reflectors (622) are all mounted on the interferometer body (621). The light passes through the collimating lens of the entrance port and enters the interior of the interferometer body (621). After being split by the infrared beam splitter, the light is refracted by the rotating refracting mirror (623) and then returns along the same path through the reflectors (622). The light then passes through the infrared beam splitter and the converging mirror of the exit port before entering the split Stirling detector (624).

4. The multi-component coupling structure for airborne map correlation detection according to claim 3, characterized in that, The temperature control mechanism (7) includes a temperature controller (71), a temperature monitoring chip (72), a cooling chip (73), and a heating coil (74); the temperature monitoring chip (72), the cooling chip (73), and the heating coil (74) are all disposed on the interference body (621) and are all connected to the temperature controller (71).

5. A debugging method for a multi-component coupling structure based on airborne map correlation detection according to any one of claims 1-4, characterized in that, Includes the following steps: S1: Complete the assembly and adjustment between the front optical mechanism (2), the two-dimensional roll-up servo Coulomb optical path (3), the anti-vibration switching mirror mechanism (4), the infrared imaging mechanism (5), the infrared spectroscopy mechanism (6), and the temperature control mechanism (7) and the main frame (1); S2: Acquire inertial navigation system integration data and determine the target; S3: Guide the multi-component coupling structure of the airborne spectrum association detection to the target using the inertial navigation combined data, perform matching tracking within the field of view and acquire the target's spectrum.

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