A water-air dual-purpose unmanned aerial vehicle joint device

Abstract

The present invention discloses a joint device for a dual-purpose water-air unmanned aerial vehicle, which comprises: a cabin shell, rubber, a joint assembly and a flange cover, wherein the outer side wall of the cabin shell is provided with a receiving hole; a sealing rubber is filled and arranged in the receiving hole; the joint assembly is located in the receiving hole, and the joint assembly is partially arranged in the sealing rubber; the flange cover is detachably sealed and connected to the outer side wall of the cabin shell, and the flange cover is arranged on the receiving hole. The present application can improve the watertightness, operability and convenience of use of the dual-purpose water-air unmanned aerial vehicle.

Description

Technical Field

[0001] The invention relates to the technical field of a cross-medium water-air dual-purpose unmanned aerial vehicle, and in particular to a water-air dual-purpose unmanned aerial vehicle connector device. Background Art

[0002] Cross-media dual-purpose water-air unmanned aerial vehicle is a kind of vehicle that can adaptively realize motion transition and continuous existence between two different fluid media, water and air, and can autonomously and continuously navigate and perform specific tasks in the two media. Cross-media dual-purpose water-air unmanned aerial vehicle combines the advantages of traditional drones and traditional underwater robots and integrates innovation, with a wider range of application areas and use value. Cross-media dual-purpose water-air unmanned aerial vehicle is the key area and direction of future aircraft development, and there is no mature cross-media dual-purpose water-air unmanned aerial vehicle in the market, which has good development prospects and competitive advantages.

[0003] Rotor-type cross-medium water-air dual-purpose unmanned aerial vehicle has become an important research direction of cross-medium unmanned aerial vehicle due to its flexibility and no restrictions on take-off and landing sites. Its energy system-related components and power system-related components, airborne equipment systems need to be connected by cables, and the energy system needs to be charged, and the airborne equipment system needs to be powered on and off. At present, how to realize the integration of energy system and airborne equipment system lines to facilitate interaction with the outside world under the design requirements of ensuring the water tightness, pressure resistance and low resistance of the cross-medium water-air dual-purpose unmanned aerial vehicle is a key issue of the underwater sealing water-air dual-purpose unmanned aerial vehicle connector device of the cross-medium unmanned aerial vehicle. The cables of the energy system and the airborne equipment system of the water-air dual-purpose unmanned aerial vehicle in the prior art are usually arranged inside the cabin of the unmanned aerial vehicle. When the energy system needs to be charged and the airborne equipment system needs to be powered on and off, the upper and lower cabins of the unmanned aerial vehicle need to be disassembled to expose the cables, so as to facilitate the operation of the cables to charge the energy system or power on and off the airborne equipment system. The operation is cumbersome and multiple disassembly will affect the sealing of the unmanned aerial vehicle. Summary of the invention

[0004] Based on this, it is necessary to provide a water-air dual-purpose unmanned aerial vehicle connector device that is easy to operate and does not affect the sealing of the unmanned aerial vehicle.

[0005] A water-air dual-purpose unmanned aerial vehicle connector device, comprising:

[0006] A cabin shell, wherein an outer side wall of the cabin shell is provided with a receiving hole;

[0007] A sealing rubber is filled in the receiving hole;

[0008] A joint assembly is located in the receiving hole, and the joint assembly is partially disposed in the sealing rubber, the sealing rubber is used to fix the joint assembly, and the joint assembly is used to connect the energy system, the power system and the airborne equipment system of the water-air dual-purpose unmanned aerial vehicle; and

[0009] The flange cover is detachably and hermetically connected to the outer side wall of the cabin shell, and the flange cover is arranged on the accommodating hole.

[0010] Optionally, the connector assembly includes a plurality of cables, the plurality of cables are spaced apart in the accommodating hole, and the plurality of cables are partially disposed in the sealing rubber, and each of the cables is respectively connected to an energy system, a power system and an onboard equipment system of the dap-air unmanned aerial vehicle.

[0011] Optionally, the cable includes a male cable head and a female cable head, the male cable head portion is inserted into the sealing rubber, the female cable head portion is inserted into the sealing rubber, and the male cable head and the female cable head can be close to or away from each other to achieve docking or separation of the male cable head and the female cable head.

[0012] Optionally, the dual-purpose water-air unmanned aerial vehicle joint device also includes a first sealing component, which is arranged between the cabin shell and the flange cover, and the first sealing component is used to achieve sealing between the cabin shell and the flange cover in a first direction.

[0013] Optionally, the first sealing assembly includes a first rubber ring and a first mounting groove. The cabin shell is provided with a first mounting groove, the first mounting groove is arranged around the accommodating hole, one end of the first rubber ring is arranged in the first mounting groove, and the other end of the first rubber ring is used to abut against the flange cover, and the side of the first rubber ring is also used to abut against the flange cover to achieve sealing of the cabin shell and the flange cover in a first direction.

[0014] Optionally, the dual-purpose water-air unmanned aerial vehicle joint device also includes a second sealing component, which is spaced apart from the first sealing component, and is arranged between the cabin shell and the flange cover, and the second sealing component is used to achieve sealing between the cabin shell and the flange cover in a second direction, and the second direction is perpendicular to the first direction.

[0015] Optionally, the second sealing assembly includes a second rubber ring and a second mounting groove. The cabin shell is provided with a second mounting groove, the second mounting groove is spaced apart from the first mounting groove, the second mounting groove is arranged around the first mounting groove, one end of the second rubber ring is arranged in the second mounting groove, and the other end of the second rubber ring is used to abut against the flange cover to achieve sealing of the cabin shell and the flange cover in the second direction.

[0016] Optionally, the flange cover includes a base plate portion and an arc portion, the base plate portion is arranged on the outer side wall of the cabin shell, the base plate portion is arranged around the accommodating hole, the arc portion is covered above the accommodating hole, the arc portion is arranged in the middle of the base plate portion, and the base plate portion and the arc portion are connected by an arc transition.

[0017] Optionally, the dual-purpose water-air unmanned aerial vehicle connector device also includes a fixing member, the base plate portion is provided with a first fixing hole, the cabin shell is provided with a second fixing hole, the first fixing hole and the second fixing hole are arranged correspondingly, and the fixing member is used to pass through the first fixing hole and the second fixing hole in sequence to achieve a fixed connection between the cabin shell and the base plate portion.

[0018] Optionally, the number of the fixing member, the first fixing hole and the second fixing hole are all multiple, the multiple first fixing holes are arranged around the circumference of the base plate portion, and the multiple second fixing holes are arranged around the cabin shell.

[0019] The present application provides a joint device for a dual-purpose water and air unmanned aerial vehicle, which integrates relevant components of the energy system, relevant components of the power system and cable groups of the airborne equipment system of the unmanned aerial vehicle into a joint assembly, and opens a receiving hole on the outer wall of the cabin shell, and the receiving hole is filled with rubber, and then the joint assembly is partially arranged in the rubber, and then is covered on the receiving hole through a flange cover, and the flange cover is sealed with the outer wall of the cabin shell. When it is necessary to charge the energy system or to power on and off the airborne equipment system, it is only necessary to remove the flange cover from the cabin shell to perform relevant operations on the joint assembly. Compared with the prior art that requires disassembly of the upper and lower cabins of the unmanned aerial vehicle, the present application can improve the watertightness, operability and ease of use of the dual-purpose water and air unmanned aerial vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0021] Figure 1 This is a schematic structural diagram of a joint device for a dual-purpose water-air unmanned aerial vehicle in one embodiment;

[0022] Figure 2 is a schematic structural diagram of a cabin shell in an embodiment;

[0023] Figure 3 This is a schematic diagram of the combined structure of the cabin shell, rubber and joint assembly in one embodiment;

[0024] Figure 4 This is a schematic diagram of the structure of a flange cover in one embodiment;

[0025] Figure 5 is a structural schematic diagram of a joint device in another perspective in one embodiment;

[0026] Figure 6 for Figure 5 Section view at AA;

[0027] Figure 7 for Figure 6 Schematic diagram of the enlarged structure at point B.

[0028] 1. Cabin shell; 11. Accommodation hole; 12. Second fixing hole; 2. Sealing rubber; 3. Joint assembly; 31. Cable; 311. Cable male end; 312. Cable female end; 4. Flange cover; 41. Base plate portion; 411. First fixing hole; 42. Arc portion; 43. Supporting portion; 5. First sealing assembly; 51. First rubber ring; 52. First mounting groove; 6. Second sealing assembly; 61. Second rubber ring; 62. Second mounting groove; 7. Fixing piece.

[0029] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work are within the scope of protection of the present invention.

[0031] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0032] In addition, the descriptions of "first", "second", etc. in the present invention are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, "and / or" in the full text includes three solutions. Taking A and / or B as an example, it includes technical solution A, technical solution B, and technical solution that satisfies both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0033] refer to Figures 1 to 4 The present application provides a joint device for a dual-purpose water and air unmanned aerial vehicle, which includes a cabin shell 1, a sealing rubber 2, a joint assembly 3 and a flange cover 4. The outer wall of the cabin shell 1 is provided with a receiving hole 11; the sealing rubber 2 is filled and arranged in the receiving hole 11; the joint assembly 3 is located in the receiving hole 11, and the joint assembly 3 is partially arranged in the sealing rubber 2. The joint assembly 3 is used to connect the energy system, power system and airborne equipment system of the dual-purpose water and air unmanned aerial vehicle; the sealing rubber 2 is used to fix the joint assembly 3; the flange cover 4 is detachably and sealedly connected to the outer wall of the cabin shell 1, and the flange cover 4 is covered on the receiving hole 11.

[0034] The present application provides a joint device for a dual-purpose water and air unmanned aerial vehicle, by grouping and integrating relevant components of the energy system, relevant components of the power system and cables 31 of the airborne equipment system of the unmanned aerial vehicle into a joint assembly 3, and opening a receiving hole 11 on the outer wall of the cabin shell 1, and the receiving hole 11 is filled with a sealing rubber 2, and then the joint assembly 3 is partially arranged in the sealing rubber 2, and then covered on the receiving hole 11 through a flange cover 4, and the flange cover 4 is sealed with the outer wall of the cabin shell 1. When it is necessary to charge the energy system or to power on and off the airborne equipment system, it is only necessary to remove the flange cover 4 from the cabin shell 1 to perform relevant operations on the joint assembly 3. Compared with the prior art that requires disassembly of the upper and lower cabins of the unmanned aerial vehicle, the present application can improve the watertightness, operability and ease of use of the dual-purpose water and air unmanned aerial vehicle.

[0035] Specifically, the cabin shell is the cabin outer shell of the water-air dual-purpose unmanned aerial vehicle.

[0036] The connector assembly 3 includes a plurality of cables 31, which are arranged at intervals in the receiving hole 11, and the plurality of cables 31 are respectively partially arranged in the sealing rubber 2, and each cable 31 is respectively connected to the energy system, power system and airborne equipment system of the water-air dual-purpose unmanned aerial vehicle. The present application centralizes the cables 31 between the energy system-related components, the power system-related components and the airborne equipment system to facilitate the power supply and discharge of the energy system.

[0037] In this embodiment, the sealing rubber 2 is a watertight rubber. Furthermore, the sealing rubber 2 is a watertight combing rubber, which can fix the cable 31 and facilitate marking the position of the cable 31.

[0038] In this embodiment, the connector assembly 3 includes three cables 31, and the three cables 31 are respectively connected to the energy system, the power system and the airborne equipment system of the dual-purpose water-air unmanned aerial vehicle.

[0039] The cable 31 includes a cable male head 311 and a cable female head 312. The cable male head 311 is partially inserted into the sealing rubber 2, and the cable female head 312 is partially inserted into the sealing rubber 2. The cable male head 311 and the cable female head 312 can be close to or away from each other to achieve docking or separation of the cable male head 311 and the cable female head 312.

[0040] refer to Figures 5 to 7 The water-air dual-purpose unmanned aerial vehicle joint device also includes a first sealing component 5 and a second sealing component 6. The first sealing component 5 and the second sealing component 6 are both arranged between the cabin shell 1 and the flange cover 4. The first sealing component 5 is used to achieve sealing between the cabin shell 1 and the flange cover 4 in a first direction, and the second sealing component 6 is used to achieve sealing between the cabin shell 1 and the flange cover 4 in a second direction, and the second direction is perpendicular to the first direction.

[0041] Specifically, the first direction is the axial direction of the nacelle shell 1 , and the second direction is the radial direction of the nacelle shell 1 . Furthermore, the radial direction of the nacelle shell 1 is a direction parallel to the upper surface direction of the nacelle shell 1 .

[0042] refer to Figure 4 and Figure 6 The flange cover 4 includes a base plate portion 41, an arc portion 42 and a supporting portion 43. The base plate portion 41 is arranged on the outer side wall of the cabin shell 1, the base plate portion 41 is arranged around the accommodating hole 11, the arc portion 42 is covered above the accommodating hole 11, the arc portion 42 is arranged in the middle of the base plate portion 41, the supporting portion 43 is arranged below the arc portion 42, and the supporting portion 43 is arranged around the arc portion 42. The base plate portion 41 and the arc portion 42 are connected in an arc transition, and the arc portion 42 is streamlined.

[0043] Specifically, the abutting portion 43 is annular, and one end of the abutting portion 43 away from the arc portion 42 extends into the accommodating hole 11 to abut against the sealing rubber 2 .

[0044] Specifically, the arc portion 42 and the base plate portion 41 adopt R10 smooth rounded transition, and the flange cover 4 is a streamlined structure. Under the same conditions, the underwater coefficient of the arc portion 42 of the present application is 0.005, which is much smaller than the hemispherical (dome) drag coefficient of 0.015 and the cylindrical drag coefficient of 1.2, and can greatly reduce the fuselage drag of the cross-medium water-air dual-purpose unmanned aerial vehicle.

[0045] refer to Figure 6 and Figure 7 The first sealing assembly 5 includes a first rubber ring 51 and a first mounting groove 52, and the second sealing assembly 6 includes a second rubber ring 61 and a second mounting groove 62. The outer wall of the cabin shell 1 is provided with a first mounting groove 52 and a second mounting groove 62 at intervals. The first mounting groove 52 is arranged around the accommodating hole 11. One end of the first rubber ring 51 is arranged in the first mounting groove 52, and the other end of the first rubber ring 51 protrudes from the first mounting groove 52 and is used to abut against the base plate portion 41. The side of the first rubber ring 51 away from the second rubber ring 61 is also used to abut against the abutting portion 43 to achieve sealing of the cabin shell 1 and the flange cover 4 in the first direction. The second mounting groove 62 is arranged around the first mounting groove 52, one end of the second rubber ring 61 is arranged in the second mounting groove 62, and the other end of the second rubber ring 61 protrudes from the second mounting groove 62 and is used to abut against the base plate portion 41 to achieve sealing of the cabin shell 1 and the flange cover 4 in the second direction.

[0046] Specifically, the first rubber ring 51 and the second rubber ring 61 are both watertight O-type rubber rings. The specifications of the first rubber ring 51 are 2×52 mm, the specifications of the second rubber ring 61 are 2×60 mm, the first installation groove 52 and the second installation groove 62 are both rectangular grooves, the first installation groove 52 matches the first rubber ring 51, and the second installation groove 62 matches the second rubber ring 61.

[0047] The first installation groove 52 and the second installation groove 62 are both rectangular grooves, suitable for dynamic sealing and static sealing. At the same time, the first rubber ring 51 and the second rubber ring 61 are combined and use axial and radial combined sealing. The flange cover 4 is used to provide pressure to compress the first rubber ring 51 and the second rubber ring 61. After being compressed, the first rubber ring 51 and the second rubber ring 61 always tend to restore the original cross-section, generating a self-compression force effect. When the first rubber ring 51 and the second rubber ring 61 are respectively installed in the first installation groove 52 and the second installation groove 62, the contact stress distribution can be approximately described by a parabola:

[0048]

[0049] Where S is the contact width, σ max —Maximum contact stress

[0050] The compression rate W of the first installation groove 52 or the second installation groove 62 is usually calculated using the following empirical formula:

[0051]

[0052] Wherein D0 is the cross-sectional diameter of the first mounting groove 52 or the second mounting groove 62 in a free state, and h is the distance between the bottom of the first mounting groove 52 or the second mounting groove 62 and the sealing surface (i.e., the cross-sectional height of the first rubber ring 51 and the second rubber ring 61 after compression).

[0053] The first rubber ring 51 and the second rubber ring 61 can have a longer service life when the compression rate does not exceed 15%-20% of the original cross section.

[0054] In summary, after relevant calculations and structural design, the flange cover 4 provides pressure to control the compression rate of the first rubber ring 51 and the second rubber ring 61 to 17%. At the same time, a small amount of silicone grease is applied to the first rubber ring 51 and the second rubber ring 61 to compensate for the insufficient smoothness of the sealing surface of the first rubber ring 51 and the second rubber ring 61 and to play a lubricating role.

[0055] refer to Figures 1 to 4 The water-air dual-purpose unmanned aerial vehicle connector device also includes a fixing member 7, a first fixing hole 411 is provided on the base plate portion 41, and a second fixing hole 12 is provided on the cabin shell 1. The first fixing hole 411 and the second fixing hole 12 are arranged correspondingly, and the fixing member 7 is used to sequentially pass through the first fixing hole 411 and the second fixing hole 12 to achieve a fixed connection between the cabin shell 1 and the base plate portion 41. The number of the fixing member 7, the first fixing hole 411, and the second fixing hole 12 are all multiple, and the multiple first fixing holes 411 are arranged around the circumference of the base plate portion 41, and the multiple second fixing holes 12 are arranged around the cabin shell 1.

[0056] Specifically, the fixing member 7 is an M5 fastening screw, and the first fixing hole 411 and the second fixing hole 12 are M5 fastening threaded holes.

[0057] The joint device of the present application also has the characteristic of good pressure resistance, and the wall thickness of the flange cover 4 is determined by performing pressure resistance design on the flange cover 4 .

[0058] The specific operation is to determine the relevant environmental parameters according to the working environment and mission requirements of the cross-medium water-air dual-purpose unmanned aerial vehicle, the working depth range h∈[0,50]m, the seawater density ρ∈[1.02,1.07]g / cm 3 , gravitational acceleration g∈[9.780,9.832]m / s 2 , atmospheric pressure p 大气=1.01325×10 5 pa, so the maximum working pressure p of the cross-medium water-air dual-purpose unmanned aerial vehicle can be obtained max =ρ max g max h max +p 大气 =6.27337×10 5 pa, considering possible material defects, calculation formula errors, ultra-deep and overpressure in operation and other unsafe factors, the pressure hull subjected to external pressure should be designed and calculated according to the calculated pressure, which is taken as 1.5 times the maximum working pressure, so the calculated pressure P j =1.5p max =9.410055×10 5 pa.

[0059] According to the design requirements of the cross-medium water-air dual-purpose unmanned aerial vehicle, the cabin material is determined to be transparent photosensitive resin, and then the basic material parameter tensile strength (tensile strength) σ b ∈[44×10 6 ,62×10 6 ]pa.

[0060] When a spherical pressure shell (spherical shell) is subjected to uniform external pressure, it can maintain its spherical shape and be uniformly compressed. At this time, the uniform mid-surface compressive stress is Where P is the uniform external pressure; R is the radius of the mid-surface of the spherical shell; and t is the thickness of the spherical shell. Considering the requirements for safe operation, the shell plate stress σ is The obtained spherical shell plate stress σ should satisfy: σ≤0.85σ s , σ s is the yield strength of the material, and transparent photosensitive resin is a brittle material, so σ b Minimum value instead of σ s The ellipsoidal shell is calibrated with an equivalent radius R d As the radius of the spherical shell, Where D0 is the inner diameter of the ellipsoid, D1 is the outer diameter of the ellipsoid, and H is the depth of the ellipsoid. According to the above content, the minimum wall thickness of the cross-medium water-air dual-purpose unmanned aerial vehicle is theoretically calculated and determined, and the maximum value is taken as the overall wall thickness of the cabin.

[0061] The flange cover 4 is approximated as an ellipsoidal shell, and the minimum thickness of the shell calculated according to the above analysis is: min =1.2830mm.

[0062] Considering that the internal pressure of the joint device is approximately equal to the atmospheric pressure p 大气 =1.01325×10 5 pa is much smaller than the external pressure (maximum working pressure) p of the joint device max =ρmax g max h max +p 大气 =6.27337×10 5 pa, no internal pressure resistance test is performed here.

[0063] The steps of using the water-air dual-purpose unmanned aerial vehicle connector of the present application include:

[0064] When the cross-media water-air dual-purpose unmanned aerial vehicle is about to perform a mission, first connect the corresponding male ends of the cables 31 with the female ends of the cables 31 to start the cross-media water-air dual-purpose unmanned aerial vehicle. After manual debugging and inspection, install the first rubber ring 51 to the corresponding first mounting groove 52 of the cabin shell 1, and install the second rubber ring 61 to the second mounting groove 62. Finally, fasten the flange cover 4 to the cabin shell 1 through threads to complete the installation. The cross-media water-air dual-purpose unmanned aerial vehicle can perform related tasks normally. When the cross-media water-air dual-purpose unmanned aerial vehicle completes its mission and flies back, first remove the flange cover 4, then remove the first rubber ring 51 and the second rubber ring 61 from the corresponding first mounting groove 52 and the second mounting groove 62 of the cabin shell 1 respectively, then disconnect the corresponding cable male heads and cable female heads to shut down the cross-media water-air dual-purpose unmanned aerial vehicle, and finally charge the energy system of the cross-media water-air dual-purpose unmanned aerial vehicle through the cable 31 corresponding to the energy system, or perform other operations on the cross-media water-air dual-purpose unmanned aerial vehicle.

[0065] The above are only preferred embodiments of the present invention, and are not intended to limit the patent scope of the present invention. All equivalent structural changes made using the contents of the present invention's specification and drawings, or directly / indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A dual-purpose water and air unmanned aerial vehicle joint device, characterized in that: include: A cabin shell, wherein an outer side wall of the cabin shell is provided with a receiving hole; A sealing rubber is filled in the receiving hole; A connector assembly is located in the receiving hole, and the connector assembly is partially arranged in the sealing rubber, the sealing rubber is used to fix the connector assembly, and the connector assembly is used to connect the energy system, power system and airborne equipment system of the dual-purpose water and air unmanned aerial vehicle. The connector assembly includes a plurality of cables, and the plurality of cables are arranged in the receiving hole at intervals, and the plurality of cables are respectively partially arranged in the sealing rubber, and each of the cables is respectively connected to the energy system, power system and airborne equipment system of the dual-purpose water and air unmanned aerial vehicle; the cable includes a cable male head and a cable female head, the cable male head is partially inserted in the sealing rubber, and the cable female head is partially inserted in the sealing rubber, and the cable male head and the cable female head can be close to or away from each other to achieve the docking or separation of the cable male head and the cable female head; A flange cover is detachably sealed and connected to the outer side wall of the cabin shell, and the flange cover is arranged on the receiving hole; the flange cover includes a base plate portion and an arc portion, the base plate portion is arranged on the outer side wall of the cabin shell, the base plate portion is arranged around the receiving hole, the arc portion is arranged above the receiving hole, the arc portion is arranged in the middle of the base plate portion, and the base plate portion and the arc portion are connected in an arc transition; The dual-purpose water-air unmanned aerial vehicle connector device also includes a first sealing component, which is arranged between the cabin shell and the flange cover, and the first sealing component is used to achieve sealing between the cabin shell and the flange cover in a first direction; the dual-purpose water-air unmanned aerial vehicle connector device also includes a second sealing component, which is spaced apart from the first sealing component, and the second sealing component is arranged between the cabin shell and the flange cover, and the second sealing component is used to achieve sealing between the cabin shell and the flange cover in a second direction, and the second direction is perpendicular to the first direction.

2. The water-air dual-purpose unmanned aerial vehicle connector device according to claim 1, characterized in that: The first sealing assembly includes a first rubber ring and a first mounting groove. The cabin shell is provided with a first mounting groove, and the first mounting groove is arranged around the accommodating hole. One end of the first rubber ring is arranged in the first mounting groove, and the other end of the first rubber ring is used to abut against the flange cover. The side surface of the first rubber ring is also used to abut against the flange cover to achieve sealing of the cabin shell and the flange cover in a first direction.

3. The water-air dual-purpose unmanned aerial vehicle connector device according to claim 2, characterized in that: The second sealing assembly includes a second rubber ring and a second mounting groove. The cabin shell is provided with a second mounting groove. The second mounting groove is spaced apart from the first mounting groove and is arranged around the first mounting groove. One end of the second rubber ring is arranged in the second mounting groove, and the other end of the second rubber ring is used to abut against the flange cover to achieve sealing of the cabin shell and the flange cover in the second direction.

4. The water-air dual-purpose unmanned aerial vehicle connector device according to claim 1, characterized in that: The dual-purpose water-air unmanned aerial vehicle connector device also includes a fixing member, the base plate portion is provided with a first fixing hole, the cabin shell is provided with a second fixing hole, the first fixing hole and the second fixing hole are arranged correspondingly, and the fixing member is used to pass through the first fixing hole and the second fixing hole in sequence to achieve a fixed connection between the cabin shell and the base plate portion.

5. The water-air dual-purpose unmanned aerial vehicle connector device according to claim 4, characterized in that: The number of the fixing member, the first fixing hole and the second fixing hole are all multiple, the multiple first fixing holes are arranged around the circumference of the base plate portion, and the multiple second fixing holes are arranged around the cabin shell.

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