A flying pod system for personnel transfer between sea and land

Abstract

This invention provides a flying pod system for transferring personnel between land and sea, comprising, from top to bottom, a rotorcraft, a lifting cable, and a pod; the two ends of the lifting cable are connected to the rotorcraft and the pod, respectively; the pod includes: a main load-bearing space frame, which has a dome-shaped appearance that expands outward in the middle and converges vertically, serving as the interior of the pod for accommodating the object to be transferred; a sealing structure, disposed on the surface area enclosed by the main load-bearing space frame, for sealing the pod; a lifting point mechanism, mounted on the upper part of the pod's interior, including a rotating buffer mechanism and an elastic buffer mechanism connected sequentially from top to bottom, with the lifting cable connected to the top of the rotating buffer mechanism; and a load-bearing suspension mechanism, mounted on the middle part of the pod's interior, for supporting the object to be transferred and mitigating the transmission of impact loads to the object.

Description

Technical Field

[0001] This invention relates to the field of personnel transfer and emergency rescue equipment technology, and in particular to a flying pod system for personnel transfer by sea and land. Background Technology

[0002] Currently, there is a real demand for rapid personnel transfer equipment in scenarios such as offshore oil and gas platform operations, wind farm maintenance, pilot boarding, urban high-altitude rescue, and mountain emergency rescue. In existing technologies, offshore oil and gas platforms mostly use cranes in conjunction with open-type personnel baskets for personnel transfer, while offshore wind power platforms often use maintenance vessels for boarding, and pilots typically use rope ladders for transfer. In onshore rescue scenarios, personnel transfer in complex terrain or high-altitude locations mainly relies on helicopter transfers or manual access. These traditional methods generally suffer from insufficient safety assurance capabilities, limited operational windows, and limited applicability when operating in harsh environments, complex terrain, or when emergency response requirements are high.

[0003] Most existing hoisting devices are designed for crane or conventional low-speed hoisting conditions, and typically lack configuration optimization for the downwash environment of rotorcraft. When used for rotorcraft hoisting, the hoisting device is prone to high-frequency vibration and attitude disturbances under the combined effects of downwash, crosswinds, and sling sway, affecting transport stability, personnel comfort, and safety margins. Meanwhile, the buffer structures of existing hoisting devices are usually quite simple; in the event of a hard landing or side impact, the impact load is directly transferred to the occupants, making it difficult to provide effective cushioning protection. Furthermore, most hoisting devices use open or semi-open structures, making it difficult to simultaneously address windproof, rainproof, fall protection, and emergency protection requirements in specific environments, and they cannot freely switch between land and sea scenarios.

[0004] Therefore, it is necessary to propose a flying pod system suitable for personnel transfer between land and sea to improve the stable operation, buffer protection and environmental adaptability of rotorcraft during the lifting process, so as to meet the safety, rapid response and comfort of personnel transfer in multiple scenarios.

[0005] It should be noted that the information disclosed in the background section above is only for understanding the background of this application, and therefore may include information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0006] To overcome the shortcomings of existing technologies, this invention provides a flying pod system for personnel transfer at sea and land, enabling stable, safe, and comfortable transfer of personnel or goods in various environments.

[0007] The present invention adopts the following technical solution: A flying pod system for transferring personnel between land and sea includes, from top to bottom: a rotorcraft, a lifting cable, and a pod; the upper end of the lifting cable is connected to the rotorcraft, and the lower end of the lifting cable is connected to the pod; the pod includes: a main load-bearing space frame, which has a dome-shaped appearance that expands outward in the middle and converges at the top and bottom, the interior of the main load-bearing space frame serving as the interior of the pod for accommodating the object to be transferred; a sealing structure, disposed on the surface area enclosed by the main load-bearing space frame, for sealing the pod; a lifting point mechanism, mounted on the upper part of the interior of the pod, including a rotating buffer mechanism for mitigating the transmission of torsional torque and an elastic buffer mechanism for buffering vertical impact, connected sequentially from top to bottom, the top of the rotating buffer mechanism being connected to the lifting cable; and a load-bearing suspension mechanism, mounted on the middle part of the interior of the pod, for carrying the object to be transferred and mitigating the transmission of impact loads to the object to be transferred.

[0008] The present invention has the following beneficial effects: This invention, through a dome-shaped configuration design with outward expansion in the middle and convergence at the top and bottom of the main load-bearing space frame, combined with a multi-stage buffering mechanism including a rotating buffer mechanism and an elastic buffer mechanism in the hoisting point mechanism, as well as the independent buffering function of the load-bearing suspension mechanism, effectively alleviates vibration transmission and impact loads during the hoisting of rotorcraft, thereby improving the stability and comfort of the transport. Specifically, it has the following advantages: (1) Excellent aerodynamic performance: The main load-bearing space frame of the present invention has a dome configuration that expands outward in the middle and converges upward and downward, which is beneficial to improving the aerodynamic adaptability of the pod under the lifting conditions of rotorcraft.

[0009] (2) Ultimate impact resistance: In the preferred scheme, by setting collision protection components on the outside of the main load-bearing space frame and combining them with the load-bearing suspension mechanism set inside the pod, a graded buffer structure can be further formed to better absorb the impact load generated by the hard landing or lateral impact of the pod.

[0010] (3) Decoupling design of lifting point: The lifting point mechanism is equipped with a rotary buffer mechanism and an elastic buffer mechanism. In the preferred scheme, a damping unit is also provided, which helps to reduce the vibration transmission between the rotorcraft and the pod and to alleviate the tension peak when the lifting cable suddenly tightens. In the preferred scheme, the angular contact ball bearing design of the rotary buffer mechanism effectively blocks the transmission of torsional torque and reduces the attitude disturbance of the pod.

[0011] (4) Protection and adaptability: The sealed structure fully covers the outer surface of the pod, ensuring its sealing performance in various environments. In the preferred embodiment, the pod's protection and adaptability in complex marine and land environments can be improved by combining it with buoyancy supply devices, auxiliary operating components, etc.

[0012] This invention significantly improves the stability, safety, and environmental adaptability of the flight pod system through the synergistic effect of structural optimization and multi-level buffering mechanisms, meeting the high standards required for personnel and material transfer. It can be applied to offshore personnel transfer scenarios such as offshore oil and gas platform operations, offshore wind farm operation and maintenance, and navigation pilot boarding, as well as onshore personnel transfer scenarios such as onshore wind farm operation and maintenance, urban high-altitude rescue, mountain emergency rescue, and scenic spot sightseeing. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall flight pod system of the present invention.

[0014] Figure 2 This is a structural schematic diagram of the main load-bearing space frame of the present invention.

[0015] Figure 3 This is a schematic diagram of the bottom frame of the present invention.

[0016] Figure 4a This is a three-dimensional schematic diagram of the entire pod of the present invention.

[0017] Figure 4b This is a schematic diagram of the internal structure of the pod; Figure 5 This is a schematic diagram of the collision protection component of the present invention.

[0018] Figure 6a This is a structural schematic diagram of the lifting point mechanism of the present invention.

[0019] Figure 6b This is an exploded structural diagram of the lifting point mechanism of the present invention.

[0020] Figure 7 This is a structural schematic diagram of the load-bearing suspension mechanism of the present invention.

[0021] Figure 8 This is a schematic diagram of the bottom buffer layer of the present invention.

[0022] Figure 9 This is an aerodynamic simulation test diagram of the pod shape of the present invention. Detailed Implementation

[0023] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0024] It should be noted that the accompanying drawings are simplified and use non-precise proportions, intended only to facilitate and clarify the explanation of the embodiments of the present invention. Please refer to the accompanying drawings for a clearer understanding of the objectives, features, and advantages of the present invention. It should be understood that the structures, proportions, sizes, etc., depicted in the accompanying drawings are merely for illustrative purposes and to aid those skilled in the art, and are not intended to limit the implementation of the present invention. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to size, without affecting the effects and objectives of the present invention, should still fall within the scope of the technical content disclosed in the present invention.

[0025] It should be noted that the terms "upper", "lower", "top", "bottom", "external", and "internal" in this embodiment are used to illustrate the orientation or positional relationship shown in the accompanying drawings and specific embodiments. They are only used as a reference for the illustration and description of the present invention and are not intended to specify a particular orientation or position that the structure or component must have, nor are they limiting conditions of the present invention.

[0026] It should be noted that the term "connection" should be interpreted broadly. For example, when a component is said to be "connected to" another component, it can be directly connected to the other component or indirectly connected to it.

[0027] like Figures 1 to 8 As shown, a flying pod system for transporting personnel by sea and land includes, from top to bottom, a rotorcraft 1, a lifting cable 2, and a pod 3, wherein the pod 3 is suspended below the rotorcraft 1 by the lifting cable 2.

[0028] The pod 3 includes a main load-bearing space frame, a sealing structure 15, a lifting point mechanism 13, and a load-bearing suspension mechanism 14. The main load-bearing space frame has a square dome shape with rounded corners, expanding outwards in the middle and converging upwards and downwards. The interior of the main load-bearing space frame serves as the interior of the pod 3, used to accommodate objects to be transferred, such as personnel and supplies. The sealing structure 15 is located on the surface area enclosed by the main load-bearing space frame and is used to seal the pod 3. The lifting point mechanism 13 is mounted on the upper part of the interior of the pod 3. The lifting point mechanism 13 includes a rotary buffer mechanism for mitigating the transmission of torsional torque and an elastic buffer mechanism for buffering vertical impact, connected sequentially from top to bottom. The top of the rotary buffer mechanism is connected to a lifting cable 2. The connection between the top of the lifting point mechanism 13 and the lifting cable 2 is used to achieve the suspension connection between the pod 3 and the rotorcraft 1 and to mitigate the transmission of high-frequency vibrations. The load-bearing suspension mechanism 14 is located below the lifting point mechanism 13 and is mounted in the middle of the interior of the pod 3. It is used to carry the object to be transferred and to reduce the transmission of impact load to the object to be transferred.

[0029] like Figure 2 , Figure 3 , 4b As shown, preferably, the main load-bearing space frame includes a top ring frame 4, multiple meridional spokes 5, latitudinal spokes 6, a bottom frame 7, and a mounting column 12; the bottom frame 7 is a planar frame, including an inner ring 9, radial beams 10, and an outer ring 11 from the inside out, the inner ring 9 being connected to the outer ring 11 through multiple radial beams 10; the upper ends of the multiple meridional spokes 5 are connected to the top ring frame 4, and the lower ends are connected to the connection node between the radial beams 10 and the outer ring 11; the meridional spokes 5 are composed of an arc-shaped upper section, a middle section (preferably a straight section), and an arc-shaped lower section, so that the pod sequentially forms an upper dome region, a middle vertical region, and a lower convergent region along the direction of the downwash airflow, allowing the downwash airflow to smoothly transition along the outer periphery of the pod, delaying boundary layer separation and reducing the low-pressure wake region at the tail, thereby reducing vertical aerodynamic drag and reducing the additional tension of the lifting cable during the lifting process. The latitudinal spokes 6 have two loops, which are connected to the longitudinal spokes 5 along the circumference of the main load-bearing space frame. One loop of the latitudinal spokes 6 is connected to the transition between the upper section and the middle section of the arc, and the other loop of the latitudinal spokes 6 is connected to the transition between the middle section and the lower section of the arc. There are at least four mounting posts 12, such as an even number like 4, 6, or 8. In this embodiment, there are eight mounting posts 12, which are located in the center of the interior of the pod 3. The top of the mounting post 12 is connected to the connection node between the upper end of the radial spoke 5 and the top ring frame 4, and the bottom of the mounting post 12 is connected to the connection node between the radial beam 10 and the inner ring 9. The lifting point mechanism 13 and the load-bearing suspension mechanism 14 are installed on the mounting posts 12. Specifically, the load-bearing suspension mechanism 14 is mounted in the central part of the interior of the pod 3, the lifting point mechanism 13 is located in the area enclosed by the eight mounting posts 12, and the load-bearing suspension mechanism 14 is located outside the area enclosed by the eight mounting posts 12.

[0030] Preferably, the main load-bearing space frame is made of hollow profiles with a weather-resistant coating on the outer surface to improve durability under harsh environments such as strong light and salt spray. More preferably, the main load-bearing space frame is made of aluminum alloy or carbon fiber composite material.

[0031] like Figure 4aAs shown, preferably, the sealing structure 15 includes, from top to bottom: an upper frame inter-frame sealing plate 16, a middle frame inter-frame sealing assembly 17, a lower frame inter-frame sealing plate 18, and a bottom sealing plate 19; the upper frame inter-frame sealing plate 16 is used to seal the upper part of the main load-bearing space frame (mainly the area formed by the arc-shaped upper section of the radial spokes 5), the middle frame inter-frame sealing assembly 17 is used to seal the middle part of the main load-bearing space frame (mainly the area formed by the middle section of the radial spokes 5), and the lower frame inter-frame sealing plate 18 is used to seal the lower part of the main load-bearing space frame (mainly the area formed by the arc-shaped upper section of the radial spokes 5). (If the area is formed by the arc-shaped lower section of the radial spokes 5), the bottom sealing plate 19 is used to seal the bottom of the main load-bearing space frame (mainly sealing the bottom frame 7); the middle frame sealing assembly 17 includes a hatch 33 located in the middle of the main load-bearing space frame and a collision protection assembly 20. At least one hatch 33 is provided in the middle opening area of ​​the main load-bearing space frame, and the collision protection assembly 20 is provided in the middle opening area where no hatch 33 is provided. The collision protection assembly 20 serves as both a sealing plate and has the function of preventing puncture and lateral impact. The hatch 33 can be, for example, a double swing door. Double swing doors have conventional structures such as gas exchange holes, mechanical interlocks, and self-locking devices, and emergency opening handles can be provided on both the inner and outer sides of the hatch 33. Preferably, the upper frame sealing plate 16, the lower frame sealing plate 18, and the bottom sealing plate 19 are made of polycarbonate.

[0032] like Figure 5 As shown, preferably, the collision protection component 20 is detachably connected to the outer side of the main load-bearing space frame, and the collision protection component 20 includes an inner buffer layer 21 and an outer rigid wear-resistant shell 22. For example, the collision protection component 20 can be quickly connected to the main load-bearing space frame via a latch. More preferably, the outer surface of the collision protection component 20 is also provided with reflective markings. Preferably, the inner buffer layer 21 of the collision protection component 20 is made of ethylene-vinyl acetate copolymer (EVA) or artificial cartilage foam biomimetic material (ACF); the outer rigid wear-resistant shell 22 is made of high-density polyethylene (HDPE) or sandwich composite board.

[0033] like Figure 6a and 6bAs shown, preferably, the rotary buffer mechanism in the lifting point mechanism 13 includes a hook 23, a central shaft 24 with a trapezoidal shoulder, an angular contact ball bearing 25, and an upper end plate anti-reverse sleeve 26. The hook 23 is connected to the top of the central shaft 24, and the angular contact ball bearing 25 is interference-fitted onto the central shaft 24. The outer ring of the angular contact ball bearing 25 is fixedly connected to the upper end of the upper end plate anti-reverse sleeve 26, and the angular contact ball bearing 25 is located inside the upper end plate anti-reverse sleeve 26. The lower end of the upper end plate anti-reverse sleeve 26 is connected to the elastic buffer mechanism, and the lower end of the upper end plate anti-reverse sleeve 26 is sealed, which improves the protection of the ball bearing 25 and ensures its long-term reliability and sealing. The angular contact ball bearing 25 is used to prevent torque transmission. Preferably, there is at least one pair of angular contact ball bearings (the number of angular contact ball bearings is preferably an even number), for example, one pair (2), two pairs (4), etc., to better transfer axial loads. Preferably, a buffer sealing strip is provided on the upper surface of the upper end plate anti-reverse cylinder 26 or the lower surface of the top ring frame 4. When the pod 3 is lifted, under the action of tension, the upper surface of the upper end plate anti-reverse cylinder 26 is stopped by the top ring frame 4, and the upper surface of the upper end plate anti-reverse cylinder 26 and the lower surface of the top ring frame 4 are sealed by the buffer sealing strip.

[0034] like Figure 6a and 6b As shown, preferably, the elastic buffer mechanism in the suspension point mechanism 13 includes a spring seat 27, multiple sets of springs 28 (in this embodiment, four sets of springs 28 are arranged circumferentially), a guide mechanism 29 (the guide mechanism 29 limits the springs 28; in this embodiment, the guide mechanism is a guide rod, and the springs 28 are sleeved on the guide rod), and a middle end plate 30; the lower end of the upper end plate anti-reverse cylinder 26 is connected to one end of the spring 28 through the spring seat 27, the inside of the spring 28 is limited by the guide mechanism 29, and the other end of the spring 28 is connected to the middle end plate 30; the lower end of the guide mechanism 29 is connected to the middle end plate 30, and the upper end is free.

[0035] like Figure 6a and 6b As shown, preferably, the suspension point mechanism 13 further includes a damping unit for dissipating impact energy connected to the elastic buffer mechanism. The damping unit includes a damper 31 and a lower end plate 32. The damper 31 is fixed between the middle end plate 30 and the lower end plate 32. The lower end plate 32 is fixedly connected to the mounting column 12.

[0036] The bottom of the suspension point mechanism 13 is mounted on the mounting column 12. When the damping unit is not connected below the elastic buffer mechanism of the suspension point mechanism 13, the middle end plate 30 is fixedly connected to the mounting column 12. When the damping unit is connected below the elastic buffer mechanism of the suspension point mechanism 13, the middle end plate 30 is not connected to the mounting column 12, and the lower end plate 32 is fixedly connected to the mounting column 12.

[0037] Preferably, there are multiple dampers 31, such as hydraulic dampers, arranged in an X-shaped cross pattern so that damping force can be applied in the XYZ directions. However, this is not the only option. In other embodiments, the multiple dampers 31 can also be arranged vertically in parallel.

[0038] In the preferred embodiment described above, the lifting point mechanism 13 can be simplified to a spring unit or spring-damping unit that does not transmit torsion. The vibration frequency of the lifting point mechanism 13 avoids the vibrations generated by the operation of the rotorcraft 1's wings (40-300Hz), the vibrations caused by the wind pressure of the downwash airflow of the rotorcraft 1 (0-1Hz), the swing frequency of the lifting cable 2 (<0.3Hz), and the first-order modal frequency (30Hz) of the main load-bearing space frame of the pod. Preferably, the stiffness of the spring 28 is selected between 480-960 N / mm, and the vibration frequency of the lifting point mechanism 13 is 4.42-6.26Hz. Figure 7 As shown, preferably, the load-bearing suspension mechanism 14 includes an upper support frame 34, a lower support frame 35, a guide column 36, a sliding sleeve 37, a load-bearing platform 38, a load-bearing part 39, and a support spring 40; the upper support frame 34 and the lower support frame 35 are fixed to the hanging column 12. In this embodiment, both the upper support frame 34 and the lower support frame 35 are annular frames, and the inner ring of the annular frame is fixed to the outer surface of the hanging column 12 (i.e., after fixing, the hanging column 12 is located inside the annular frame). The guide column 36 connects the upper support frame 34 and the lower support frame 35, and the sliding sleeve 37 is sleeved on the guide column 36 and connected to the load-bearing platform 38. The support unit 39 is mounted on the support platform 38 and is used to directly support the object to be transferred. The support spring 40 is sleeved on the guide post 36 and located between the sliding sleeve 37 and the lower support frame 35. The entire assembly consisting of the support platform 38, the support unit 39, and the sliding sleeve 37 can move up and down on the guide post 36, buffering the impact load transmitted to the object to be transferred under the action of the support spring 40. Preferably, the support unit 39 is detachably mounted on the support platform 38 to select different structures according to the actual transfer situation and the object to be transferred. For example, when the object to be transferred is a sea or land personnel, the support unit 39 can be a seat or a transport stretcher.

[0039] Preferably, in the load-bearing suspension mechanism 14, the overall vibration frequency of the sliding sleeve 37, the load-bearing platform 38, the load-bearing part 39, and the support spring 40 is 2-3 Hz. This overall vibration frequency avoids the vibrations generated by the rotorcraft 1's wing operation (40-300 Hz), the vibrations caused by the downwash air pressure of the rotorcraft 1 (0-1 Hz), the swing frequency of the lifting cable 2 (<0.3 Hz), the first-order modal frequency of the pod's main load-bearing space frame (30 Hz), and the vibration frequency of the lifting point mechanism (4.42-6.26 Hz). Figure 4a and 8 As shown, preferably, it also includes a buoyancy providing device 41 and a bottom buffer layer 42 of the pod. The buoyancy providing device 41 is a buoyancy cylinder or closed-cell foam, arranged inside the pod 3; the bottom buffer layer 42 is arranged on the outer bottom surface of the bottom frame 7. The buoyancy providing device 41 can improve the floating protection capability under specific working conditions. Preferably, the buoyancy providing device 41 is arranged circumferentially between two rings of weft spokes 6 along the main load-bearing space frame, and the bottom of the buoyancy providing device 41 is at a predetermined height from the bottom of the pod 3, for example, 0.3m from the bottom of the pod 3. Preferably, the bottom buffer layer 42 can be streamlined in shape, and the main material of the bottom buffer layer 42 can be ethylene-vinyl acetate copolymer material or artificial cartilage foam biomimetic material, and is covered with a high-density polyethylene shell.

[0040] Preferably, the gondola 3 further includes the following auxiliary operating components: an emergency light installed inside the gondola 3, for example, below the hoisting mechanism 13, for nighttime work or emergency rescue; a handle 8 installed inside and / or outside the gondola 3, for example, the internal handle can be used to secure passengers, and the external handle can be used to grip or attach additional flotation devices; a tow rope 43 laid on the outer bottom surface of the gondola 3 for ground support personnel to tow and position; and a visual waterproof positioning device installed on the outer bottom surface of the gondola 3 for operators to visualize the take-off and landing process in the gondola 3.

[0041] In this embodiment of the invention, the flight pod system is used by a rotorcraft 1 to suspend the pod 3 via a lifting cable 2 for personnel transfer. During the lifting process, the lifting point mechanism 13 is used to mitigate the transmission of high-frequency vibrations; when the pod 3 experiences a landing impact or lateral collision, the collision protection component 20 and the load-bearing suspension mechanism 14 buffer the impact load; when in a marine environment, the sealing structure 15 and the buoyancy providing device 41 can improve the protective capability and environmental adaptability of the pod 3.

[0042] like Figure 9 As shown, taking pod 3 with a length, width, and height of 2m as an example, a CFD aerodynamic simulation analysis is performed on the shape of pod 3. The Reynolds number is Re = 1.3692 × 10⁻⁶ m.5 Under a vertical uniform inflow (inflow velocity of 1 m / s), using the Reynolds-averaged Navier-Stokes (RANS) calculation model, the average drag coefficient under implicit unsteady-state conditions is 0.32, and the root mean square coefficient is 0.018, indicating that the pod exhibits excellent aerodynamic characteristics of low drag and high stability under given operating conditions.

[0043] The above description provides a further detailed explanation of the present invention in conjunction with specific / preferred embodiments, and it should not be construed that the specific implementation of the present invention is limited to these descriptions. For those skilled in the art, various substitutions or modifications can be made to these described embodiments without departing from the concept of the present invention, and all such substitutions or modifications should be considered within the scope of protection of the present invention. In the description of this specification, the reference to terms such as "an embodiment," "some embodiments," "preferred embodiment," "example," "specific example," or "some examples," etc., indicates that the specific features, structures, materials, or characteristics described in connection with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any suitable manner in one or more embodiments or examples. Without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification and the features of different embodiments or examples. Although the embodiments of the present invention and their advantages have been described in detail, it should be understood that various changes, substitutions, and modifications can be made herein without departing from the scope of protection of the patent application.

Claims

1. A flying pod system for personnel transfer between sea and land, characterized in that, From top to bottom, it includes: a rotorcraft (1), a lifting cable (2), and a pod (3); the upper end of the lifting cable (2) is connected to the rotorcraft (1), and the lower end of the lifting cable (2) is connected to the pod (3); the pod (3) includes: The main load-bearing space frame has a dome-shaped appearance that expands outward in the middle and converges at the top and bottom. The interior of the main load-bearing space frame serves as the interior of the pod (3) to accommodate the object to be transferred. A sealing structure (15) is provided on the surface area enclosed by the main load-bearing space frame to seal the pod (3). The hoisting mechanism (13) is mounted on the upper part of the interior of the pod, including a rotary buffer mechanism for mitigating the transmission of torsional torque and an elastic buffer mechanism for buffering vertical impact, which are connected sequentially from top to bottom. The top of the rotary buffer mechanism is connected to the hoisting cable (2). The load-bearing suspension mechanism (14) is mounted in the middle of the interior of the pod and is used to carry the object to be transferred and to reduce the transmission of impact load to the object to be transferred.

2. The flight pod system of claim 1, wherein, The main load-bearing space frame includes a top ring frame (4), multiple longitudinal spokes (5), latitudinal spokes (6), a bottom frame (7), and mounting columns (12). The bottom frame (7) is a planar frame, which includes an inner ring (9), multiple radial beams (10) and an outer ring (11) from the inside to the outside. The inner ring (9) is connected to the outer ring (11) through the radial beams (10). The upper ends of the multiple radial spokes (5) are connected to the top ring frame (4), and the lower ends are connected to the connection node between the radial beam (10) and the outer ring (11); the radial spokes (5) are composed of an arc-shaped upper section, a middle section and an arc-shaped lower section; The latitudinal spokes (6) have two rings, which are connected to the longitudinal spokes (5) along the circumference of the main load-bearing space frame. One ring of the latitudinal spokes (6) is connected to the transition between the upper arc section and the middle section, and the other ring of the latitudinal spokes (6) is connected to the transition between the middle section and the lower arc section. The lifting point mechanism (13) and the load-bearing suspension mechanism (14) are installed on the mounting column (12). There are at least 4 mounting columns (12), which are located in the center of the interior of the pod (3). The top of the mounting column (12) is connected to the connection node between the upper end of the radial spoke (5) and the top ring frame (4). The bottom of the mounting column (12) is connected to the connection node between the radial beam (10) and the inner ring (9).

3. The flying pod system of claim 1 or 2, wherein, The main load-bearing space frame is made of hollow profiles with a weather-resistant coating on the outer surface; the main load-bearing space frame is made of aluminum alloy or carbon fiber composite material.

4. The flight pod system of claim 1, wherein, The sealing structure (15) includes, from top to bottom, an upper frame inter-sealing plate (16), a middle frame inter-sealing assembly (17), a lower frame inter-sealing plate (18), and a bottom sealing plate (19); the middle frame inter-sealing assembly (17) includes a hatch (33) located in the middle of the main load-bearing space frame and a collision protection assembly (20); the collision protection assembly (20) is detachably connected to the outer side of the middle of the main load-bearing space frame and includes an inner buffer layer (21) and an outer rigid wear-resistant shell (22); preferably, the upper frame inter-sealing plate (16), the lower frame inter-sealing plate (18), and the bottom sealing plate (19) are made of polycarbonate.

5. The flight pod system of claim 1, wherein, The rotating buffer mechanism includes a hook (23), a central shaft (24) with a trapezoidal shoulder, an angular contact ball bearing (25), and an upper end plate anti-reverse sleeve (26); the hook (23) is connected to the top of the central shaft (24), and the central shaft (24) is interference-fitted with the angular contact ball bearing (25); the angular contact ball bearing (25) is located inside the upper end plate anti-reverse sleeve (26), and the outer ring of the angular contact ball bearing (25) is fixedly connected to the upper end of the upper end plate anti-reverse sleeve (26), and the lower end of the upper end plate anti-reverse sleeve (26) is connected to the elastic buffer mechanism.

6. The flight pod system of claim 5, wherein, The elastic buffer mechanism includes a spring seat (27), multiple sets of springs (28), a guide mechanism (29), and a middle end plate (30); the lower end of the upper end plate anti-reverse cylinder (26) is connected to one end of the multiple sets of springs (28) through the spring seat (27), the interior of the springs (28) is limited by the guide mechanism (29), and the other end of the multiple sets of springs (28) is connected to the middle end plate (30), and the lower end of the guide mechanism (29) is connected to the middle end plate (30).

7. The flight pod system of claim 6, wherein, The suspension point mechanism (13) further includes a damping unit for dissipating impact energy connected to the elastic buffer mechanism. The damping unit includes a damper (31) and a lower end plate (32). The damper (31) is fixed between the middle end plate (30) and the lower end plate (32). The lower end plate (32) is fixedly connected to the mounting column (12). Preferably, there are multiple dampers arranged in an X-shaped cross pattern.

8. The flight pod system according to claim 1, characterized in that, The load-bearing suspension mechanism (14) includes an upper support frame (34), a lower support frame (35), a guide column (36), a sliding sleeve (37), a load-bearing platform (38), a load-bearing part (39), and a support spring (40). The upper support frame (34) and the lower support frame (35) are fixed on the hanging column (12). The guide column (36) is connected between the upper support frame (34) and the lower support frame (35). The sliding sleeve (37) is sleeved on the guide column (36) and connected to the load-bearing platform (38). The load-bearing part (39) is connected to the load-bearing platform (38). The support spring (40) is sleeved on the guide column (36) and located between the sliding sleeve (37) and the lower support frame (35).

9. The flight pod system according to claim 1, characterized in that, It also includes a buoyancy supply device (41) and a bottom buffer layer (42) of the pod. The buoyancy supply device (41) is a buoyancy tube or closed-cell foam and is arranged inside the pod. The bottom buffer layer (42) is arranged on the outer bottom surface of the bottom frame (7).

10. The flight pod system according to claim 1, characterized in that, It also includes auxiliary operating components, which include at least one of the following: an emergency light located inside the pod, a handle (8) located inside and / or outside the pod, a tow rope (43) laid on the outer bottom surface of the pod, and a visual waterproof positioning device installed on the outer bottom surface of the pod.

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