A composite pod device for airborne multi-meteorological-element measurement

Abstract

A kind of composite pod device of airborne multi-meteorological element measurement, it is related to meteorological field, including composite pod and mounting rack, the inside of the mounting rack is also equipped with intermediate frame, the inside fixedly equipped with composite pod, the inside of the mounting rack is also transversely provided with fixed plate, shock-absorbing control component and auxiliary shock-absorbing component are equipped on the fixed plate, the shock-absorbing control component is also connected with the top of intermediate frame by linkage column.The present application integrates meteorological measuring unit on composite pod, can monitor multiple meteorological elements simultaneously, realizes the synchronous acquisition to the weather condition of operation airspace, provides reliable data support for weather modification decision;Secondly, through vibration sensor real-time monitoring environment, the first electric cylinder and linkage electric cylinder are dynamically allocated by master control system to work cooperatively, so that shock-absorbing characteristics are always optimally matched with current flight state, whether in smooth or strong turbulence, can provide best protection for composite pod, reduces equipment failure, prolongs the service life of composite pod.

Description

Technical Field

[0001] This invention relates to the field of meteorological monitoring, and in particular to a composite pod device for airborne measurement of multiple meteorological elements. Background Technology

[0002] In the field of weather modification, it is necessary to measure meteorological elements in designated airspace. Catalysts can only be spread by smoke generators or aircraft when these meteorological elements meet the conditions for weather modification operations.

[0003] Currently, meteorological element detection for weather modification mainly relies on lidar to measure wind and clouds in the sky, and microwave radiometers to measure water vapor content in the sky. These devices are bulky and heavy, difficult to move, and are only used as base-level equipment. Relevant parameters are calculated through inversion, resulting in poor timeliness. Furthermore, existing measurements of single meteorological elements cannot reflect the dynamic changes in upper-air meteorological conditions in real time, making it difficult to meet the real-time and accuracy requirements of weather modification operations. Secondly, in airborne environments, equipment is often subjected to strong vibrations and airflow impacts. Existing devices lack efficient vibration reduction and adaptive stabilization mechanisms, which can easily lead to large measurement errors, shortened equipment lifespan, difficult installation, high maintenance costs, and poor stability under complex meteorological conditions. Summary of the Invention

[0004] To address the aforementioned problems, the present invention employs the following technical solution:

[0005] A composite pod device for airborne multi-meteorological element measurement, mounted on the bottom of an aircraft, includes a composite pod and a mounting frame. An intermediate frame is also installed inside the mounting frame, and the composite pod is fixedly mounted inside the intermediate frame. The outer walls of both sides of the intermediate frame are fixedly connected to the inner walls of the mounting frame via several first springs. A fixing plate is also laterally arranged inside the mounting frame, and a vibration damping control component and an auxiliary vibration damping component are mounted on the fixing plate. The vibration damping control component is also connected to the top of the intermediate frame via a linkage column. The vibration damping control component includes a first electric cylinder, which is fixedly installed at the top of the inner part of the mounting frame. The telescopic end of the first electric cylinder is fixedly connected to a contact head. Sliding plates are symmetrically arranged on the fixing plate via first guide blocks, and a first slot is formed on one side of the contact head relative to each sliding plate. The fixed plate is also movably mounted with a portal-shaped seat, which is located below the two sliding plates. A top rod is also installed inside the portal-shaped seat, and a vertical connecting rod is fixedly installed at the bottom of the portal-shaped seat. The vertical connecting rod is also movably connected to the intermediate frame. The linkage column is also connected to the fixed plate via an auxiliary shock-absorbing component. The composite pod has a hollow internal structure. A meteorological measurement unit is also fixedly mounted on the composite pod. The output end of the meteorological measurement unit is electrically connected to a circuit board. The circuit board integrates a central control system and is located inside the composite pod. The circuit board also partially encloses an airbag. A vibration sensor is also fixedly mounted on the mounting frame. The vibration sensor is also signal-connected to a shock-absorbing control component, which can adaptively adjust the external environment of the composite pod in real time.

[0006] Preferably, the meteorological measurement unit includes a five-hole pitot tube, a cloud radar, an infrared sensor, a temperature and humidity sensor, an attitude monitoring module, a liquid water sensor, and a freezing rain sensor. The five-hole pitot tube is used to monitor the magnitude and direction of atmospheric velocity, the cloud radar is used to monitor cloud thickness, the infrared sensor is used to monitor cloud concentration, the temperature and humidity sensor is used to monitor atmospheric temperature and humidity, the attitude monitoring module is used to monitor the aircraft's pitch, heading angle, and speed, and the liquid water sensor and freezing rain sensor are used to monitor the liquid water content and supercooled water content in the atmosphere, respectively.

[0007] Preferably, a connecting column is fixedly installed on the top of the mounting frame, the connecting column is movably connected to the connecting block at the bottom of the aircraft, a support wheel is installed on the inner bottom of the intermediate frame, the support wheel is in contact with the surface of the composite pod, and an arc-shaped clamp can be adjusted on the two inner side walls of the intermediate frame.

[0008] Preferably, movable rods are also fixedly installed on both sides of the fixed plate. Each movable rod partially extends into the hanger frame, and a second spring is also fitted on the movable rod, with the second spring located between the outer side of the fixed plate and the inner side of the hanger frame.

[0009] Preferably, a guide rod is fixedly connected to the far end of each sliding plate. The guide rod passes through a second guide block, which is fixedly mounted on a fixed plate. A return spring is also fitted on the guide rod, and the return spring is located between the far end of the sliding plate and the second guide block.

[0010] Preferably, the sliding plate has a second slot relative to the direction of the gantry seat, and the sliding plate is also provided with an oblique sliding groove. A slider is movably mounted in the oblique sliding groove, and the slider is also fixedly connected to the linkage component. The linkage component is also fixedly connected to the auxiliary shock absorption component.

[0011] Preferably, the linkage component includes a drive plate, which is fixedly connected to the slider and located on the upper surface of the sliding plate. The drive plate is also arranged parallel to the fixed plate. The bottom of the drive plate is also fixedly connected to the telescopic end of the linkage electric cylinder, and the bottom of the linkage electric cylinder is also fixed to the top of the linkage column.

[0012] Preferably, two limiting plates are symmetrically fixed on the fixed plate, and each limiting plate is located on the upper part of the drive plate.

[0013] Preferably, the auxiliary shock absorption assembly includes an auxiliary link, a retaining ring is fixedly provided at the distal end of the auxiliary link, the retaining ring is also fixedly connected to an auxiliary spring, the other end of the auxiliary spring is also fixedly connected to a stabilizing plate, and the stabilizing plate is also fixedly mounted on a fixed plate.

[0014] The beneficial effects of this invention are as follows:

[0015] This invention integrates a meteorological measurement unit into the composite pod, enabling simultaneous monitoring of multiple meteorological elements and synchronous acquisition of meteorological conditions in the operational airspace. This provides unified and reliable data support for decision-making in weather modification operations. Secondly, this invention uses vibration sensors to monitor the environment in real time, and the central control system dynamically coordinates the coordinated operation of the first electric cylinder and the linkage electric cylinder, ensuring that the vibration reduction characteristics are always optimally matched with the current flight state. Whether in stable cruise or strong turbulence, this provides the best protection for the composite pod, significantly reducing the equipment failure rate and extending the service life of the composite pod. Attached Figure Description

[0016] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0017] Figure 2 This is a three-dimensional structural schematic diagram of the present invention from another perspective;

[0018] Figure 3 for Figure 2 Enlarged structural diagram of section A in the middle;

[0019] Figure 4 This is a front view structural diagram of the present invention;

[0020] Figure 5 for Figure 4 Enlarged structural diagram of section B in the middle;

[0021] Figure 6 This is a side view of the structure of the present invention;

[0022] Figure 7 This is a cross-sectional structural diagram of the present invention;

[0023] Figure 8 This is a schematic diagram illustrating the operation of the invention mounted on an aircraft wing;

[0024] Figure 9 This is a schematic diagram of the invention mounted on the fuselage.

[0025] In the diagram: Composite pod 1, mounting frame 2, intermediate frame 3, first spring 4, fixing plate 5, shock absorption control assembly 6, auxiliary shock absorption assembly 7, linkage column 8, first electric cylinder 60, contact head 61, first guide block 62, sliding plate 63, first slot 64, portal seat 65, top rod 66, vertical connecting rod 67, guide rod 68, second guide block 69, return spring 690, second slot 691, inclined slide 692, slider 693, linkage assembly 694, drive plate 6940, linkage electric cylinder 694 1. Limiting plate 6942, meteorological measurement unit 9, circuit board 10, main control system 11, airbag 12, vibration sensor 13, five-hole pitot tube 90, wave cloud radar 91, infrared sensor 92, temperature and humidity sensor 93, attitude monitoring module 94, liquid water sensor 95, freezing rain sensor 96, connecting column 14, connecting block 15, support wheel 16, arc-shaped clamp 17, moving rod 18, second spring 19, preload spring 20, auxiliary connecting rod 70, retaining ring 71, auxiliary spring 72, and stabilizing plate 73. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0027] In the description of this invention, it should be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and 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 this invention. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0028] Example 1:

[0029] See appendix Figure 1-9 A composite pod device for measuring multiple meteorological elements on air is mounted on the bottom of an aircraft, specifically on the wing of the aircraft. Figure 8 As shown, or the belly of the aircraft, such as Figure 9As shown, the specific mounting can be configured according to actual conditions, including a composite pod 1 and a mounting frame 2. The mounting frame 2 is also equipped with an intermediate frame 3, and the composite pod 1 is fixedly mounted inside the intermediate frame 3. The principle of this invention is as follows: The aircraft is equipped with an automatic deployment device. During flight, the meteorological measurement unit 9 on the composite pod collects data in real time and transmits it to the central control system 11 on the circuit board 10. During this process, the vibration sensor 13 monitors the vibration intensity and frequency of the mounting frame 2 in real time. Based on the vibration data, the central control system 11 dynamically adjusts the buffer state between the intermediate frame 3 and the composite pod 1 through the vibration damping control component 6. Through the vibration damping control component 6, the vibration energy is absorbed and dissipated step by step, maintaining the relative stability of the composite pod 1, which can adapt to different external environments, and realizing the protection of the composite pod 1, especially the meteorological measurement unit 9, making the operation more stable. The outer walls on both sides of the intermediate frame 3 are also fixedly connected to the inner walls of the mounting frame 2 by several first springs 4. The first springs 4 absorb low-frequency vibrations and impacts during flight through elastic deformation, which is equivalent to achieving preliminary mechanical isolation between the composite pod 1 and the aircraft. This kind of shock absorption is a passive buffer. The mounting frame 2 also has a horizontally arranged fixing plate 5 inside. The fixing plate 5 is equipped with a shock absorption control component 6 and an auxiliary shock absorption component 7. The shock absorption control component 6 is also connected to the top of the intermediate frame 3 through a linkage column 8. The shock absorption control component 6 includes a first electric cylinder 60, which is fixedly installed at the top of the inside of the mounting frame 2. The telescopic end of the first electric cylinder 60 is fixedly connected to a contact head 61. The fixing plate 5 also has sliding plates 63 symmetrically arranged through first guide blocks 62. The contact head 61 also has a first slot 64 on one side of each sliding plate 63. The fixing plate 5 also has The movable gate-shaped seat 65 is located below the two sliding plates 63. The gate-shaped seat 65 is also equipped with a top rod 66 inside, and a vertical connecting rod 67 is fixedly installed at the bottom of the gate-shaped seat 65. A pre-tension spring 20 is also installed on the vertical connecting rod 67. The vertical connecting rod 67 is also movably connected to the intermediate frame 3. The linkage column 8 is also connected to the fixed plate 5 through the auxiliary shock absorption component 7. The shock absorption control component 6 is an active shock absorption control. The interior of the composite pod 1 is a hollow structure. A meteorological measurement unit 9 is also fixedly installed on the composite pod 1. The output end of the meteorological measurement unit 9 is electrically connected to the circuit board 10. The circuit board 10 integrates a central control system 11. The central control system 11 dynamically coordinates the first electric cylinder 60 (to deal with low-frequency large-amplitude vibration) and the linkage electric cylinder 6941 (to deal with high-frequency small-amplitude vibration) to work together, so that the shock absorption characteristics are always optimally matched with the current flight state. The circuit board 10 is located inside the composite pod 1, and the circuit board 10 also partially covers the airbag 12. The mounting frame 2 is also fixedly equipped with a vibration sensor 13, which is also connected to the vibration damping control component 6. The vibration damping control component 6 can adaptively adjust the external environment of the composite pod 1 in real time.

[0030] Before understanding the principle of this invention, it is necessary to understand that low-frequency vibrations usually have a large amplitude but a low frequency, such as the swaying caused by aircraft maneuvers or gradual changes in airflow, while high-frequency vibrations have a small amplitude but a high frequency, such as the rapid shaking caused by engine vibration or turbulence. Different coping strategies are needed for these two types of vibrations. For low-frequency vibrations, due to the large amplitude, a larger displacement is required to absorb energy and prevent the composite pod 1 from shaking as a whole.

[0031] The following describes the working principle of the vibration damping control component 6 at low frequencies:

[0032] When vibration sensor 13 detects a continuous, low-frequency, large-amplitude signal from the pylon 2 (such as during aircraft turning, climbing, or encountering stable airflow disturbance), the first electric cylinder 60 is activated, i.e., the contact head 61 presses down. During the pressing process, the first slot 64 gradually approaches the end of the sliding plate 63 until the end of the sliding plate 63 extends into the first slot 64. During this process, the sliding plate 63 begins to move horizontally closer, and the return spring 690 is in an extended state. At this time, the slider 693 of the inclined slide groove 692 will drive the linkage component 694 to extend, i.e., the drive plate 6940 moves upward. During this process, the portal seat 65 will press down, and the vertical connecting rod 67 will compress the preload spring 20. At this time, the intermediate frame 3 is pulled downward, the preload force of the first spring 4 increases, and the swing amplitude of the composite pod 1 is mechanically constrained. Figure 5 As shown, at this time, the auxiliary damping component 7 provides an additional elastic connection between the fixed plate 5 and the linkage column 8, absorbing micro-vibrations, and the low-frequency swing amplitude of the composite pod 1 will be significantly reduced.

[0033] For high-frequency vibrations with small amplitudes, a rapid response is required to reduce the vibration transmitted to composite pod 1.

[0034] The following describes the working principle of the vibration damping control component 6 at high frequencies:

[0035] Vibration sensor 13 detects a vibration signal and transmits it to the main control system 11. The main control system 11 determines that it is a high-frequency micro-amplitude vibration. At this time, the linkage electric cylinder 6941 is activated and retracted. The drive plate 6940 drives the slider 693 to move rapidly and slightly within the inclined slide groove 692. During this process, the sliding plate 63 moves horizontally outward until the second slot 691 is relative to the root of the portal seat 65 (the root facing upward). At this time, the preload spring 20 is in a stretched state, which is equivalent to generating a high-frequency damping effect, reducing the impact of high-frequency vibration. During this process, the auxiliary damping component 7 absorbs high-frequency energy, and the retaining ring 71 and the auxiliary connecting rod 70 form a flexible limit to avoid resonance.

[0036] See Figure 2 and Figure 6The meteorological measurement unit 9 includes a five-hole pitot tube 90, a cloud radar 91, an infrared sensor 92, a temperature and humidity sensor 93, an attitude monitoring module 94, a liquid water sensor 95, and a freezing rain sensor 96. The five-hole pitot tube 90 is used to monitor the magnitude and direction of atmospheric velocity. The cloud radar 91 is used to monitor cloud thickness. The infrared sensor 92 is used to monitor cloud concentration. The temperature and humidity sensor 93 is used to monitor atmospheric temperature and humidity. The attitude monitoring module 94 is used to monitor the aircraft's pitch, heading angle, and speed. The liquid water sensor 95 and the freezing rain sensor 96 are used to monitor the liquid water content and supercooled water content in the atmosphere, respectively. The five-hole pitot tube 90, cloud radar 91, infrared sensor 92, temperature and humidity sensor 93, attitude monitoring module 94, liquid water sensor 95, and freezing rain sensor 96 can transmit the monitored data to the central control system 11, which can calculate the cold cloud seeding assessment value Z1 and the warm cloud seeding assessment value Z2, respectively.

[0037] The calculation formulas are as follows:

[0038] Z1 ;

[0039] Z2 ;

[0040] in: cloud thickness %. Temperature (%), LNC subcooled water content (%), W wind speed.

[0041] The above technical solution allows for the calculation and evaluation of values ​​under different conditions, providing operators with simple judgments to immediately decide whether to initiate the seeding process, thus reducing the technical requirements for operators. It can also be directly linked to automatic seeding equipment to achieve automatic calculation and seeding of the catalyst.

[0042] See Figure 1 and Figure 4 The top of the mounting frame 2 is also fixedly provided with a connecting column 14, which is movably connected to the connecting block 15 at the bottom of the aircraft. The connecting column 14 and the connecting block 15 can be different models. The bottom inner side of the intermediate frame 3 is also equipped with a support wheel 16, which contacts the surface of the composite pod 1. The two inner side walls of the intermediate frame 3 can also be adjusted with arc-shaped clamps 17.

[0043] Through the above technical solution, the mounting frame 2 is connected to the connecting block 15 on the aircraft through the standardized connecting column 14, which enables the pod to switch quickly between different types of aircraft or UAVs, greatly improving the equipment deployment efficiency and platform adaptability. Secondly, the support wheel 16 forms a rolling support, while the arc-shaped clamp 17 forms a flexible clamp and can be automatically adjusted to adapt to different composite pods 1. Together, they form a non-rigid constraint, which can prevent the composite pod from undergoing slight displacement due to temperature changes, material deformation, or stress, thus avoiding damage to the internal structure due to stress concentration.

[0044] See Figure 1 Movable rods 18 are fixedly installed on both sides of the fixed plate 5. Each movable rod 18 extends partially into the hanger 2. A second spring 19 is also fitted on the movable rod 18, and the second spring 19 is located between the outer side of the fixed plate 5 and the inner side of the hanger 2.

[0045] With this technical solution, regardless of low or high frequency, the second spring 19 suppresses the lateral sway of the fixed plate 5 itself, providing a stable working platform for the vibration control component 6 and the auxiliary vibration damping component 7. If the fixed plate 5 itself swings violently during vibration, it will cause the entire active vibration damping control logic to fail, or even cause mechanical interference.

[0046] See Figure 5 Each sliding plate 63 is further connected to a guide rod 68 at its distal end. The guide rod 68 passes through a second guide block 69, which is fixedly mounted on the fixed plate 5. The second guide block 69 acts as a guide seat. A return spring 690 is also fitted onto the guide rod 68, located between the distal end of the sliding plate 63 and the second guide block 69. The guide rod 68 and the second guide block 69 form a set of high-precision sliding bearings, which strictly constrain the sliding plate 63 to move only along a preset straight trajectory, completely eliminating possible deflection, warping, or jamming of the sliding plate 63 during movement. The return spring 690 itself is also a damping element. When the system is subjected to high-frequency micro-vibration, a small high-frequency relative motion tendency will occur between the guide rod 68 and the second guide block 69. The return spring 690 can quickly absorb this energy, preventing it from being converted into dry friction or impact noise between the sliding plate 63 and the first guide block 62, thus reducing mechanical wear and vibration noise.

[0047] See Figure 2 and Figure 5The sliding plate 63 has a second slot 691 in the direction of the portal seat 65. The two ends of the portal seat 65 will be engaged in the second slot 691 in a timely manner. When the two ends of the portal seat 65 are inserted, the sliding plate 63 will stop moving. The sliding plate 63 is also provided with an inclined sliding groove 692. A slider 693 is movably installed in the inclined sliding groove 692. The slider 693 is also fixedly connected to the linkage component 694. The linkage component 694 is also fixedly connected to the auxiliary shock absorption component 7.

[0048] See Figure 3 and Figure 5 The linkage component 694 includes a drive plate 6940, which is fixedly connected to the slider 693 and located on the upper surface of the sliding plate 63. The bottom of the drive plate 6940 is also fixedly connected to the telescopic end of the linkage cylinder 6941, and the bottom of the linkage cylinder 6941 is also fixed to the top of the linkage column 8. The linkage cylinder 6941 can change the reference height of the drive plate 6940, thereby presetting the position of the slider 693 in the inclined slide groove 692, which is a key node.

[0049] Through the above technical solution, the linkage electric cylinder 6941 installed on the top of the linkage column 8 is directly commanded by the main control system 11. The system can adjust the drive plate 6940 by adjusting the linkage electric cylinder 6941 according to the real-time feedback of the vibration sensor 13, thereby instantly changing the equivalent lever ratio or pre-tightening state of the sliding plate 63 and optimizing the dynamic characteristics of the system.

[0050] Specifically, when the linkage electric cylinder 6941 is activated, its telescopic end extends, causing the drive plate 6940 to approach the limit plate 6942. During this process, the slider 693 moves towards the limit plate 6942 via the inclined slide groove 692. At this time, the sliding plate 63 moves towards the contact head 61 under the action of the return spring 690 until the end of the sliding plate 63 extends into the first slot 64. During this process, the portal seat 65 compresses the pre-tension spring 20. At this time, the intermediate frame 3 is pulled downward, the pre-tension force of the first spring 4 increases, and the swing amplitude of the composite pod 1 is mechanically constrained.

[0051] Two limiting plates 6942 are symmetrically fixed on the fixed plate 5, and each limiting plate 6942 is located above the drive plate 6940. When the drive plate 6940 moves under the drive of the linkage electric cylinder 6941, its stroke is mechanically protected by the upper limiting plate 6942 to prevent the mechanism from failing to function due to over-adjustment in extreme cases.

[0052] See Figure 3The auxiliary shock absorption component 7 includes an auxiliary connecting rod 70. A retaining ring 71 is fixedly installed at the distal end of the auxiliary connecting rod 70. The retaining ring 71 is also fixedly connected to an auxiliary spring 72. The other end of the auxiliary spring 72 is also fixedly connected to a stabilizing plate 73. The stabilizing plate 73 is also fixedly installed on a fixed plate 5. The auxiliary shock absorption component 7 provides an additional elastic connection between the fixed plate 5 and the linkage column 8, absorbing micro-vibrations and reducing the swing amplitude of the composite pod 1.

[0053] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention in any other way. Any person skilled in the art may make changes or modifications to the above-disclosed technical content to create equivalent embodiments that can be applied to other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the protection scope of the present invention.

Claims

1. A composite pod device for airborne multi-meteorological element measurement, mounted on the bottom of an aircraft, characterized in that, The system includes a composite pod and a mounting frame. An intermediate frame is also installed inside the mounting frame, and the composite pod is fixedly installed inside the intermediate frame. The outer walls of both sides of the intermediate frame are fixedly connected to the inner walls of the mounting frame via several first springs. A horizontally arranged fixing plate is also installed inside the mounting frame. A shock absorption control assembly and an auxiliary shock absorption assembly are installed on the fixing plate. The shock absorption control assembly is connected to the top of the intermediate frame via a linkage column. The shock absorption control assembly includes a first electric cylinder, which is fixedly installed at the top of the mounting frame. The telescopic end of the first electric cylinder is fixedly connected to a contact head. Sliding plates are symmetrically arranged on the fixing plate via first guide blocks. A first slot is formed on one side of each sliding plate relative to the contact head. The fixing plate also... The device features a portal-shaped base located below two sliding plates. A top rod is installed inside the portal-shaped base, and a vertical connecting rod is fixedly mounted at its bottom. A pre-tension spring is mounted on the vertical connecting rod, which is movably connected to an intermediate frame. A linkage column is connected to a fixed plate via an auxiliary shock-absorbing assembly. The composite pod has a hollow interior and is equipped with a fixed meteorological measurement unit. The output of the meteorological measurement unit is electrically connected to a circuit board, which integrates a central control system. The circuit board is located inside the composite pod and partially encloses an airbag. A vibration sensor is fixedly mounted on the mounting frame and is signal-connected to the shock-absorbing control assembly.

2. The composite pod device for airborne multi-meteorological element measurement according to claim 1, characterized in that, The meteorological measurement unit includes a five-hole pitot tube, a cloud radar, an infrared sensor, a temperature and humidity sensor, an attitude monitoring module, a liquid water sensor, and a freezing rain sensor. The five-hole pitot tube is used to monitor the magnitude and direction of atmospheric velocity, the cloud radar is used to monitor cloud thickness, the infrared sensor is used to monitor cloud concentration, the temperature and humidity sensor is used to monitor atmospheric temperature and humidity, the attitude monitoring module is used to monitor the aircraft's pitch, heading angle, and speed, and the liquid water sensor and freezing rain sensor are used to monitor the liquid water content and supercooled water content in the atmosphere, respectively.

3. The composite pod device for airborne multi-meteorological element measurement according to claim 1, characterized in that, A connecting column is fixedly installed on the top of the pylon, and the connecting column is movably connected to the connecting block at the bottom of the aircraft. A support wheel is also installed on the bottom inner side of the intermediate frame, and the support wheel contacts the surface of the composite pod. Arc-shaped clamps can also be adjusted on the two inner side walls of the intermediate frame.

4. The composite pod device for airborne multi-meteorological element measurement according to claim 1, characterized in that, Movable rods are also fixedly installed on both sides of the fixed plate. Each movable rod partially extends into the hanger frame, and a second spring is also fitted on the movable rod. The second spring is located between the outer side of the fixed plate and the inner side of the hanger frame.

5. The composite pod device for airborne multi-meteorological element measurement according to claim 1, characterized in that, Each sliding plate is also fixedly connected to a guide rod at its distal end. The guide rod passes through a second guide block, which is fixedly mounted on a fixed plate. A return spring is also fitted on the guide rod, which is located between the distal end of the sliding plate and the second guide block.

6. The composite pod device for airborne multi-meteorological element measurement according to claim 1, characterized in that, The sliding plate has a second slot relative to the direction of the gantry seat. The sliding plate is also provided with an oblique sliding groove. A slider is movably mounted in the oblique sliding groove. The slider is also fixedly connected to the linkage component. The linkage component is also fixedly connected to the auxiliary shock absorption component.

7. The composite pod device for airborne multi-meteorological element measurement according to claim 6, characterized in that, The linkage component includes a drive plate, which is fixedly connected to the slider and located on the upper surface of the sliding plate. The drive plate is parallel to the fixed plate, and the bottom of the drive plate is also fixedly connected to the telescopic end of the linkage electric cylinder. The bottom of the linkage electric cylinder is also fixed to the top of the linkage column.

8. The composite pod device for airborne multi-meteorological element measurement according to claim 7, characterized in that, Two limiting plates are symmetrically fixed on the fixed plate, and each limiting plate is located on the upper part of the drive plate.

9. The composite pod device for airborne multi-meteorological element measurement according to claim 1, characterized in that, The auxiliary shock absorption assembly includes an auxiliary connecting rod, with a retaining ring fixedly installed at the distal end of the auxiliary connecting rod. The retaining ring is also fixedly connected to an auxiliary spring, and the other end of the auxiliary spring is also fixedly connected to a stabilizing plate. The stabilizing plate is also fixedly mounted on a fixed plate.

Images