Measuring device and method for measuring thickness of polar ice cover by laser ranging-assisted aerial radar

Abstract

The invention relates to the technical field of polar region environment monitoring, in particular to a measuring device and method for measuring the thickness of a polar region ice cover through an aviation radar assisted by laser ranging, and the device comprises a gradient annular liquid vibration reduction cabin, a vertical vibration reduction cabin, a transverse supplement cabin and a dual self-locking device. The gradient annular liquid vibration reduction cabin realizes high-frequency and low-frequency full-frequency coverage through the density-viscosity gradient design of high / medium / low layers of liquid, and solves the problem of sensor data offset caused by vibration of a flying platform in polar region aviation detection; the vertical vibration reduction cabin is located below the gradient annular liquid vibration reduction cabin, cabin liquid is supplemented through the transverse supplementing cabin, the liquid flowing path is prolonged through an internal spiral flow guide plate, and the high-frequency vibration energy dissipation efficiency is remarkably improved. Through laser ranging and millimeter wave radar data fusion, the target distance calculation error is reduced, and high-precision measurement of the thickness of the polar ice cover is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of polar environment monitoring, and in particular to a device and method for measuring the thickness of polar ice sheets using laser ranging-assisted aviation radar, which is suitable for glaciology research and climate change monitoring. Background Art

[0002] Accurately measuring the thickness of the polar ice sheet is crucial for studying glacier dynamics, assessing sea level changes, and predicting climate evolution. Existing technologies rely on aerial radar combined with laser ranging to achieve thickness measurement, but their hardware design is insufficiently able to suppress the effects of vibration. Continuous high-frequency vibrations during scientific research aircraft measurement flights can cause micro-displacements in the mounting bases of the laser and radar sensors, resulting in spatial alignment deviations between the two types of data. At the same time, vibrations can interfere with the timestamp accuracy of the synchronization control unit, leading to the accumulation of time synchronization errors between the surface elevation and the bottom-layer reflection signal. The superposition of the scattered noise from the snow layer and the signal jitter caused by vibration makes it more difficult to extract the weak reflection signal from the bottom of the ice layer. Therefore, a full-link solution from hardware anti-vibration design to data fusion algorithm is urgently needed to suppress the erosion of measurement accuracy caused by aviation platform vibration and achieve highly robust detection of the thickness of the polar ice sheet. Summary of the Invention

[0003] To address the shortcomings of existing technologies, the present invention provides a device and method for measuring polar ice sheet thickness using laser ranging-assisted aviation radar. This device uses a gradient liquid vibration damping chamber to suppress sensor displacement caused by high-frequency vibrations of the aircraft, ensuring the accuracy of the laser module's elevation measurement. The device also synchronously controls the aviation radar to penetrate the ice layer to obtain reflected signals from the ice-rock interface. The laser module then acquires high-precision elevation data of the ice surface in real time, directly calculating the vertical thickness of the ice layer and achieving high-precision and efficient detection of polar ice thickness. To achieve the above objectives, the present invention provides the following technical solutions: A measuring device for laser ranging-assisted aviation radar in measuring the thickness of polar ice sheets comprises a gradient annular liquid vibration damping cabin, a vertical vibration damping cabin, a transverse supplementary cabin, and a double self-locking device. The gradient annular liquid vibration damping cabin is located above the vertical vibration damping cabin, with the double self-locking device supported by a connecting arm in the middle, providing an installation platform for laser ranging equipment and an aerial camera. The transverse supplementary cabin is located at the bottom of the entire device and is filled with inert gas to adjust pressure balance, thereby achieving coordinated offsetting of multi-directional vibrations between the gradient annular liquid vibration damping cabin and the vertical vibration damping cabin.

[0004] Furthermore, the gradient annular liquid vibration damping cabin includes an annular vibration damping cabin body, a top layer of liquid, a middle layer of liquid, a bottom layer of liquid, an annular cabin fixing ring, a vibration damping spring, a load-bearing shell, a connecting arm fixing block, a connecting arm and a vibration damping spring loading plate; the gradient annular liquid vibration damping cabin includes an annular vibration damping cabin body in an annular shape, which is filled with a top layer of liquid, a middle layer of liquid and a bottom layer of liquid; the top layer of liquid is a low-density and high-fluidity liquid used to absorb high-frequency micro-vibrations; the middle layer of liquid is a medium-density liquid used to deal with medium-frequency vibrations; the bottom layer of liquid is a high-density viscous liquid used to suppress low-frequency large-scale disturbances; the annular cabin fixing ring is located at the outermost side of the gradient annular liquid vibration damping cabin to protect the gradient annular liquid vibration damping cabin from damage, and three connecting arm fixing blocks are arranged in an annular shape in equal parts above the annular cabin fixing ring to fix the three connecting arms; the front end of the connecting arm is integrally formed with the load-bearing shell, and the middle is connected to the upper end of the vibration damping spring; the load-bearing shell is provided with a circular hole, the diameter of the circular hole is slightly larger than the diameter of the lock tube, and the lower end of the vibration damping spring is connected to the vibration damping spring loading plate.

[0005] Furthermore, there are three vertical vibration reduction cabins, which are arranged in an equilateral triangle with the center of gravity of the shooting device as the geometric center. They are connected to the equipment base through a bracket, including a spiral guide plate, a vertical cabin body, a fixing ring, a base and a connecting top cover; the spiral guide plate is perpendicular to the inside of the vertical cabin body, and the pitch gradually decreases from top to bottom. The inclination angle of the guide plate transitions from 60° to 30° from top to bottom, forming a tapered spiral channel; when the equipment vibrates, vibration energy is input, and the liquid on the top of the vertical vibration reduction cabin generates slight turbulence, and the flow path is extended through the spiral guide plate, and the energy is dissipated through viscous shear.

[0006] Furthermore, the lateral supplementary cabin includes an inert gas chamber, a PID air pressure regulating controller, a connecting hose, a gas guiding tube, a liquid compensation port, a support frame, a conventional tube and a connecting hose protection plate; both ends of the inert gas chamber are connected to the conventional tube through flanges; the PID air pressure regulating controller is connected to the conventional tube through the connecting hose, and is connected to the vertical vibration reduction cabin through the gas guiding tube; the liquid compensation port is connected to the gradient annular liquid vibration reduction cabin, and the bottom liquid in the gradient annular liquid vibration reduction cabin can flow into the vertical vibration reduction cabin through the liquid compensation port.

[0007] Furthermore, the double self-locking device includes a main lock tongue, a lock tube, a ball hole, a lock groove, a guide groove, a lock tongue extension body, a secondary lock tongue limiting groove, an equipment mounting plate, an equipment mounting hole, a top ball block, a magnetic groove, a multi-stage secondary lock tongue, a secondary lock tongue cap, a main lock tongue fixing buckle, a small cam, a large cam and a fixed steel ball; the main lock tongue is installed in the bearing shell, the main lock tongue fixing buckle cooperates with the annular lock groove provided on the main lock tongue, and the main lock tongue is fixed by installing the main lock tongue fixing buckle; the main lock tongue root is provided with a straight The lock tongue extension body has a diameter smaller than that of the main lock tongue, and three auxiliary lock tongue limiting grooves are evenly opened along the circumferential direction of the lock tongue extension body. The bottom of the lock tongue extension body is fixedly connected to an equipment mounting plate; the equipment mounting plate is provided with an equipment mounting hole for installing related equipment; the main lock tongue fixing buckle is composed of a small cam and a large cam, and the lock groove is evenly provided with three guide grooves along the circumferential direction. The small cam can pass through the guide groove. When the main lock tongue fixing buckle is rotated, the large cam can be stuck in the lock groove, thereby completing the locking of the main lock tongue.

[0008] Furthermore, the lock tube is installed in the carrier shell through the circular hole on the carrier shell. Two ball holes are symmetrically opened on the top of the lock tube, and their inner diameters are slightly larger than the outer diameters of the multi-stage auxiliary lock tongues, so that the multi-stage auxiliary lock tongues can move smoothly inside the lock tube. The multi-stage auxiliary lock tongues are placed inside the lock tube, and there are two matching top ball blocks and two magnetic slots, which are cross-distributed at the top of the multi-stage auxiliary lock tongues; the function of the top ball blocks is to push some fixed steel balls out of the lock tube, so that they are stuck on the carrier shell, thereby achieving the fixation of the lock tube; the magnetic slots are used to suck the fixed steel balls back into the lock tube to complete the unlocking operation; the outer contour of the auxiliary lock tongue cap is circular, and a three-dimensional three-pronged pattern is designed inside it, with the angle between the three prongs being 120 degrees. The multi-stage auxiliary lock tongues are fixed at the intersection of the three prongs.

[0009] Furthermore, a method for measuring the thickness of polar ice sheets using laser ranging-assisted airborne radar comprises the following steps: Step S1: The laser ranging module emits a laser pulse to the surface of the ice sheet, based on the round-trip time and the speed of the laser in the air. Calculate the vertical distance from the flight platform to the ice surface , the formula is: ; Step S2: Use the aerial radar module to transmit electromagnetic waves to the ice sheet and synchronously record the reflection time difference of the ice-bedrock water interface ; in is the total radar echo time, is the total time the radar wave spends in the air; is the speed of radar waves in air; Step S3: Invert surface snow density using laser echo intensity , dynamic correction of ice wave velocity : in, is the basic value of ice wave velocity, is the reference density, is the density-wave velocity correction factor; Step S4: Jitter error caused by vibration , to compensate for the radar time difference: Among them, the gradient annular liquid vibration damping cabin is used to suppress the vibration of the flight platform, and the jitter error ; Step S5: Fuse the compensated radar data with the laser elevation data and output the ice thickness : Furthermore, the dynamic correction of ice wave velocity Inversion of surface snow density from medium laser echo intensity The mapping relationship is established through calibration experiments, and the density-wave velocity correction coefficient The value of is determined by fitting the density-wave velocity correlation curve of the ice core sample.

[0010] Compared with the existing technology, the present invention provides a device and method for measuring the thickness of polar ice sheets using laser ranging-assisted aviation radar, which has the following beneficial effects: 1. Wideband vibration synergistic attenuation with a gradient annular liquid damping capsule: Through a density-viscosity gradient design with three liquid layers (high, medium, and low), this design achieves full coverage of both high and low frequencies, addressing sensor data offsets caused by flight platform vibration during polar aviation exploration. 2. Directed dissipation of high-frequency energy in the vertical vibration damping cabin: The spiral guide plate extends the liquid flow path, significantly improving the efficiency of high-frequency vibration energy dissipation; 3. Cross-modal precision fusion of laser ranging-assisted aerial radar measurement: By fusing laser ranging and millimeter-wave radar data, the target distance solution error is reduced, significantly improving the measurement accuracy compared to single radar. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 Schematic diagram of the overall structure of the vibration reduction device of the present invention; Figure 2 Schematic diagrams of the top structure and bottom structure of the vibration damping device of the present invention; Figure 3 A schematic diagram of the opening of the double self-locking device of the vibration damping device of the present invention; Figure 4This is a schematic structural diagram of the gradient annular liquid vibration damping cabin of the present invention; Figure 5 It is a structural schematic diagram of the vertical vibration reduction cabin of the present invention; Figure 6 This is a schematic structural diagram of the transverse supplementary compartment of the present invention; Figure 7 is a cross-sectional view of the double self-locking device of the present invention; Figure 8 It is a structural schematic diagram of the double self-locking device of the present invention; Figure 9 This is a schematic structural diagram of the key parts of the double self-locking device of the present invention; Figure 10 This is a schematic diagram of the effects of the laser ranging-assisted aviation radar measuring the thickness of the polar ice sheet before and after the present invention; In the picture: 1- Gradient annular liquid vibration reduction cabin 2- Vertical vibration reduction cabin 3- Horizontal supplementary cabin 4- Double self-locking device; 101- annular vibration damping cabin 102- top layer liquid 103- middle layer liquid 104- bottom layer liquid 105- annular cabin fixing ring 106- vibration damping spring 107- bearing shell 108- connecting arm fixing block 109- connecting arm 110- vibration damping spring loading plate; 201- spiral guide plate 202- vertical cabin body 203- fixing ring 204- base 205- connecting top cover; 301 - inert gas chamber 302 - PID air pressure regulating controller 303 - connecting hose 304 - gas guiding tube 305 - liquid compensation port 306 - support frame 307 - conventional tube 308 - connecting hose protection plate; 401 - Main lock tongue 402 - Lock tube 403 - Ball hole 404 - Lock slot 405 - Guide rail slot 406 - Lock tongue extension 407 - Auxiliary lock tongue limiting slot 408 - Equipment mounting plate 409 - Equipment mounting hole 410 - Top ball block 411 - Magnetic slot 412 - Multi-stage auxiliary lock tongue 413 - Auxiliary lock tongue cap 414 - Main lock tongue fixing buckle 415 - Small cam 416 - Large cam 417 - Fixed steel ball; DETAILED DESCRIPTION The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0012] The following is based on the attached Figure 1-10The present invention is described in detail as follows Figure 1 、 Figure 2 as well as Figure 3 As shown, a measuring device for measuring the thickness of polar ice sheets by laser ranging-assisted aerial radar of the present invention comprises a gradient annular liquid vibration reduction cabin 1, a vertical vibration reduction cabin 2, a transverse supplementary cabin 3 and a double self-locking device 4. The gradient annular liquid vibration reduction cabin 1 is located above the vertical vibration reduction cabin 2, and the double self-locking device 4 is supported by a connecting arm 109 in the middle, providing an installation platform for laser ranging equipment and aerial cameras; the transverse supplementary cabin 3 is located at the bottom of the entire device, and is filled with inert gas to adjust the pressure balance, thereby achieving coordinated offset of multi-directional vibrations between the gradient annular liquid vibration reduction cabin 1 and the vertical vibration reduction cabin 2.

[0013] Specific as Figure 4 As shown, the gradient annular liquid vibration damping cabin 1 includes an annular vibration damping cabin body 101, a top layer of liquid 102, a middle layer of liquid 103, a bottom layer of liquid 104, an annular cabin body fixing ring 105, a vibration damping spring 106, a bearing shell 107, a connecting arm fixing block 108, a connecting arm 109 and a vibration damping spring loading plate 110; the gradient annular liquid vibration damping cabin 1 includes an annular vibration damping cabin body 101, which is annular and filled with a top layer of liquid 102, a middle layer of liquid 103 and a bottom layer of liquid 104; the top layer of liquid 102 is a low-density and high-fluidity liquid used to absorb high-frequency micro-amplitude vibrations; the middle layer of liquid 103 is a medium-density liquid , to cope with medium-frequency vibrations; the bottom liquid 104 is a high-density viscous liquid, which suppresses low-frequency large disturbances; the annular cabin fixing ring 105 is located at the outermost side of the gradient annular liquid vibration damping cabin 1 to protect the gradient annular liquid vibration damping cabin 1 from damage, and three connecting arm fixing blocks 108 are arranged in an annular shape in equal parts above the annular cabin fixing ring 105 to fix three connecting arms 109; the front end of the connecting arm 109 is integrally formed with the supporting shell 107, and the middle is connected to the upper end of the vibration damping spring 106; the supporting shell 107 is provided with a circular hole, the diameter of the circular hole is slightly larger than the diameter of the lock tube 402, and the lower end of the vibration damping spring 106 is connected to the vibration damping spring loading plate 110.

[0014] Specific as Figure 5 As shown, there are three vertical vibration reduction cabins 2. The three vertical vibration reduction cabins 2 are arranged in an equilateral triangle with the center of gravity of the shooting device as the geometric center. They are connected to the equipment base through a bracket, including a spiral guide plate 201, a vertical cabin body 202, a fixing ring 203, a base 204 and a connecting top cover 205; the spiral guide plate 201 is perpendicular to the interior of the vertical cabin body 202, and the pitch gradually decreases from top to bottom. The inclination angle of the guide plate transitions from 60° to 30° from top to bottom, forming a tapered spiral channel; when the equipment vibrates and vibration energy is input, the liquid on the top of the vertical vibration reduction cabin 2 generates slight turbulence, and the flow path is extended through the spiral guide plate 201, and the energy is dissipated through viscous shear.

[0015] Specific as Figure 6 As shown, the lateral supplementary cabin 3 includes an inert gas chamber 301, a PID air pressure regulating controller 302, a connecting hose 303, an air guiding tube 304, a liquid compensation port 305, a support frame 306, a conventional tube 307 and a connecting hose protection plate 308; both ends of the inert gas chamber 301 are connected to the conventional tube 307 through flanges; the PID air pressure regulating controller 302 is in communication with the conventional tube 307 through the connecting hose 303, and is in communication with the vertical vibration reduction cabin 2 through the air guiding tube 304; the liquid compensation port 305 is in communication with the gradient annular liquid vibration reduction cabin 1, and the bottom liquid 104 in the gradient annular liquid vibration reduction cabin 1 can flow into the vertical vibration reduction cabin 2 through the liquid compensation port 305.

[0016] Specific as Figure 7 and Figure 8 As shown, the double self-locking device 4 includes a main lock tongue 401, a lock tube 402, a ball hole 403, a lock groove 404, a guide groove 405, a lock tongue extension body 406, an auxiliary lock tongue limiting groove 407, an equipment mounting plate 408, an equipment mounting hole 409, a top ball block 410, a magnetic groove 411, a multi-stage auxiliary lock tongue 412, an auxiliary lock tongue cap 413, a main lock tongue fixing buckle 414, a small cam 415, a large cam 416 and a fixed steel ball 417; the main lock tongue 401 is installed in the bearing shell 107, the main lock tongue fixing buckle 414 cooperates with the annular lock groove 404 provided on the main lock tongue 401, and the main lock tongue 401 is fixed by installing the main lock tongue fixing buckle 414; the main lock A lock tongue extension body 406 with a diameter smaller than the main lock tongue 401 is provided at the root of the tongue 401, and three auxiliary lock tongue limiting grooves 407 are evenly provided along the circumferential direction of the lock tongue extension body 406, and an equipment mounting plate 408 is fixedly connected to the bottom of the lock tongue extension body 406; the equipment mounting plate 408 is provided with an equipment mounting hole 409 for installing related equipment; the main lock tongue fixing buckle 414 is composed of a small cam 415 and a large cam 416, and the lock slot 404 is evenly provided with three guide grooves 405 along the circumferential direction. The small cam 415 can pass through the guide groove 405. When the main lock tongue fixing buckle 414 is rotated, the large cam 416 can be stuck in the lock slot 404, thereby completing the locking of the main lock tongue 401.

[0017] Specific as Figure 9As shown, the lock tube 402 is installed in the carrier shell 107 through the circular hole on the carrier shell 107. Two ball holes 403 are symmetrically opened on the top of the lock tube 402. The inner diameter of the ball holes is slightly larger than the outer diameter of the multi-stage auxiliary lock tongue 412, so that the multi-stage auxiliary lock tongue 412 can move smoothly inside the lock tube 402. The multi-stage auxiliary lock tongue 412 is placed inside the lock tube 402, and there are two matching top ball blocks 410 and magnetic slots 411, which are cross-distributed at the top of the multi-stage auxiliary lock tongue 412; the function of the top ball block 410 is to push part of the fixed steel ball 417 out of the lock tube 402, so that it is stuck on the supporting shell 107, thereby achieving the fixation of the lock tube 402; the magnetic slot 411 is used to suck the fixed steel ball 417 back into the lock tube 402 to complete the unlocking operation; the outer contour of the auxiliary lock tongue cap 413 is circular, and a three-dimensional three-pronged pattern is designed inside it, with an angle between the three forks of 120 degrees, and the multi-stage auxiliary lock tongue 412 is fixed at the intersection of the three forks.

[0018] A measuring method for a device for measuring the thickness of a polar ice sheet using a laser ranging-assisted aviation radar, characterized by comprising the following steps: Step S1: Laser pulses are emitted to the ice sheet surface through the laser ranging module, based on the round-trip time and the speed of the laser in air Calculate the vertical distance from the flight platform to the ice surface , the formula is: Step S2: Use the aerial radar module to transmit electromagnetic waves to the ice sheet and synchronously record the reflection time difference of the ice-bedrock water interface ; in is the total radar echo time, is the total time the radar wave spends in the air; is the speed of radar waves in air; Step S3: Invert surface snow density using laser echo intensity , dynamic correction of ice wave velocity : in, is the basic value of ice wave velocity, is the reference density, is the density-wave velocity correction factor; Step S4: Jitter error caused by vibration , to compensate for the radar time difference: Among them, the gradient annular liquid vibration reduction cabin 1 and the vertical vibration reduction cabin 2 are used to suppress the vibration of the flight platform, and the jitter error ; Step S5: Fuse the compensated radar data with the laser elevation data and output the ice thickness : Dynamically corrected ice wave velocity Inversion of surface snow density from medium laser echo intensity The mapping relationship is established through calibration experiments, and the density-wave velocity correction coefficient The value of is determined by fitting the density-wave velocity correlation curve of the ice core sample.

[0019] Specific as Figure 10 As shown, after installing the vibration reduction device, the measurement effect is significantly improved, and the surveying and mapping data are outputted coherently. Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A measuring device for measuring the thickness of polar ice sheets using laser ranging-assisted aviation radar, comprising a gradient annular liquid vibration damping cabin (1), a vertical vibration damping cabin (2), a transverse supplementary cabin (3), and a double self-locking device (4), wherein the gradient annular liquid vibration damping cabin (1) is located above the vertical vibration damping cabin (2), and the double self-locking device (4) is supported in the middle by a connecting arm (109), providing an installation platform for laser ranging equipment and an aviation camera; the transverse supplementary cabin (3) is located at the bottom of the entire device, and is filled with inert gas to adjust the pressure balance, thereby achieving coordinated offsetting of multi-directional vibrations of the gradient annular liquid vibration damping cabin (1) and the vertical vibration damping cabin (2).

2. The device for measuring polar ice sheet thickness using laser ranging-assisted aviation radar according to claim 1, characterized in that: The gradient annular liquid vibration damping cabin (1) comprises an annular vibration damping cabin body (101), a top layer of liquid (102), a middle layer of liquid (103), a bottom layer of liquid (104), an annular cabin body fixing ring (105), a vibration damping spring (106), a bearing shell (107), a connecting arm fixing block (108), a connecting arm (109) and a vibration damping spring loading plate (110); the gradient annular liquid vibration damping cabin (110) comprises an annular vibration damping cabin body (101) filled with a top layer of liquid (102), a middle layer of liquid (103) and a bottom layer of liquid (104); the top layer of liquid (102) is a low-density, high-fluidity liquid used to absorb high-frequency micro-amplitude vibrations; the middle layer of liquid (103) is a medium-density, high-fluidity liquid used to absorb high-frequency micro-amplitude vibrations; Liquid, to cope with medium-frequency vibration; the bottom liquid (104) is a high-density viscous liquid, which suppresses low-frequency large-scale disturbances; the annular cabin fixing ring (105) is located at the outermost side of the gradient annular liquid vibration damping cabin (1), protecting the gradient annular liquid vibration damping cabin (1) from being damaged, and three connecting arm fixing blocks (108) are arranged in an annular shape in equal parts above the annular cabin fixing ring (105) to fix three connecting arms (109); the front end of the connecting arm (109) is integrally formed with the bearing shell (107), and the middle is connected to the upper end of the vibration damping spring (106); the bearing shell (107) is opened with a circular hole, the diameter of the circular hole is slightly larger than the diameter of the lock tube (402), and the lower end of the vibration damping spring (106) is connected to the vibration damping spring loading plate (110).

3. The device for measuring polar ice sheet thickness using laser ranging-assisted aviation radar according to claim 1, characterized in that: There are three vertical vibration reduction cabins (2). The three vertical vibration reduction cabins (2) are arranged in an equilateral triangle with the center of gravity of the shooting device as the geometric center. They are connected to the device base through a bracket and include a spiral guide plate (201), a vertical cabin body (202), a fixing ring (203), a base (204) and a connecting top cover (205). The spiral guide plate (201) is perpendicular to the interior of the vertical cabin body (202), and the pitch gradually decreases from the top to the bottom. The guide plate inclination angle transitions from 60° to 30° from top to bottom, forming a gradually contracting spiral channel. When the device vibrates and vibration energy is input, the liquid at the top of the vertical vibration reduction cabin (2) generates a slight turbulence, and the flow path is extended through the spiral guide plate (201), and the energy is dissipated through viscous shear.

4. The device for measuring polar ice sheet thickness using laser ranging-assisted aviation radar according to claim 1, characterized in that: The lateral supplementary cabin (3) comprises an inert gas chamber (301), a PID air pressure regulating controller (302), a connecting hose (303), a gas guiding tube (304), a liquid compensation port (305), a support frame (306), a conventional tube (307), and a connecting hose protection plate (308); both ends of the inert gas chamber (301) are connected to the conventional tube (307) via flanges; the PID air pressure regulating controller (302) is in communication with the conventional tube (307) via the connecting hose (303), and is in communication with the vertical vibration reduction cabin (2) via the gas guiding tube (304); the liquid compensation port (305) is in communication with the gradient annular liquid vibration reduction cabin (1), and the bottom liquid (104) in the gradient annular liquid vibration reduction cabin (1) can flow into the vertical vibration reduction cabin (2) via the liquid compensation port (305).

5. The device for measuring polar ice sheet thickness using laser ranging-assisted aviation radar according to claim 1, characterized in that: The double self-locking device (4) comprises a main lock tongue (401), a lock tube (402), a ball hole (403), a lock groove (404), a guide groove (405), a lock tongue extension body (406), a secondary lock tongue limiting groove (407), an equipment mounting plate (408), an equipment mounting hole (409), a top ball block (410), a magnetic groove (411), a multi-stage secondary lock tongue (412), a secondary lock tongue cap (413), a main lock tongue fixing buckle (414), a small cam (415), a large cam (416) and a fixed steel ball (417); the main lock tongue (401) is installed in the bearing shell (107), the main lock tongue fixing buckle (414) cooperates with the annular lock groove (404) provided on the main lock tongue (401), and the main lock tongue (401) is fixed by installing the main lock tongue fixing buckle (414); The main lock tongue (401) is provided with a lock tongue extension body (406) having a diameter smaller than that of the main lock tongue (401) at its root, and three auxiliary lock tongue limiting grooves (407) are evenly provided along the circumferential direction of the lock tongue extension body (406), and a device mounting plate (408) is fixedly connected to the bottom of the lock tongue extension body (406); the device mounting plate (408) is provided with a device mounting hole (409) for installing relevant equipment; the main lock tongue fixing buckle (414) is composed of a small cam (415) and a large cam (416), and the lock slot (404) is evenly provided with three guide grooves (405) along the circumferential direction, the small cam (415) can pass through the guide groove (405), and when the main lock tongue fixing buckle (414) is rotated, the large cam (416) can be stuck in the lock slot (404), thereby completing the locking of the main lock tongue (401).

6. The device for measuring polar ice sheet thickness using laser ranging-assisted aviation radar according to claim 5, characterized in that: The lock tube (402) is installed in the carrier shell (107) through the circular hole on the carrier shell (107). Two ball holes (403) are symmetrically opened on the top of the lock tube (402). The inner diameter of the ball holes is slightly larger than the outer diameter of the multi-stage auxiliary lock tongue (412), so that the multi-stage auxiliary lock tongue (412) can move smoothly inside the lock tube (402). The multi-stage auxiliary lock tongue (412) is placed inside the lock tube (402). There are two top ball blocks (410) and two magnetic slots (411) that match the multi-stage auxiliary lock tongue (412). They are cross-distributed on the multi-stage auxiliary lock tongue (412). The top of the lock tube (402) is provided with a top ball block (410); the function of the top ball block (410) is to push part of the fixed steel ball (417) out of the lock tube (402) so that the fixed steel ball (417) is stuck on the bearing shell (107), thereby achieving the fixation of the lock tube (402); the magnetic groove (411) is used to suck the fixed steel ball (417) back into the lock tube (402) to complete the unlocking operation; the outer contour of the auxiliary lock tongue cap (413) is circular, and a three-dimensional three-pronged pattern is designed inside the auxiliary lock tongue cap (413), with the angle between the three forks being 120 degrees, and the multi-stage auxiliary lock tongue (412) is fixed at the intersection of the three forks.

7. The measuring method according to any one of claims 1 to 6, characterized in that: The steps include: Step S1: Laser pulses are emitted to the ice sheet surface through the laser ranging module, based on the round-trip time and the speed of the laser in air Calculate the vertical distance from the flight platform to the ice surface , the formula is: ； Step S2: Use the aerial radar module to transmit electromagnetic waves to the ice sheet and synchronously record the reflection time difference of the ice-bedrock water interface ; in is the total radar echo time, is the total time the radar wave spends in the air; is the speed of radar waves in air; Step S3: Invert surface snow density using laser echo intensity , dynamic correction of ice wave velocity : in, is the basic value of ice wave velocity, is the reference density, is the density-wave velocity correction factor; Step S4: Jitter error caused by vibration , to compensate for the radar time difference: Among them, due to the use of gradient annular liquid vibration reduction cabin (1) and vertical vibration reduction cabin (2) to suppress the vibration of the flight platform, the jitter error ; Step S5: Fuse the compensated radar data with the laser elevation data and output the ice thickness : 。 8. The measuring method according to claim 7, wherein: Dynamic correction of ice wave velocity Inversion of surface snow density from medium laser echo intensity The mapping relationship is established through calibration experiments, and the density-wave velocity correction coefficient The value of is determined by fitting the density-wave velocity correlation curve of the ice core sample.

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