Electric opening and closing mounting cabin and water-air dual-purpose UAV

Abstract

The present invention relates to an electrically openable and closable mounting cabin and a dual-purpose water and air drone, wherein the electrically openable and closable mounting cabin comprises a cabin door, an airbag cabin, a hinge assembly, a motor and an airbag. The airbag cabin has an airbag cabin body, and the hinge assembly has an upper hinge and a lower hinge, wherein the upper hinge is attached to the airbag cabin body, and the lower hinge is attached to the cabin door, and the cabin door can be pivoted relative to the airbag cabin body through the hinge assembly. The motor has an output shaft, and the output shaft is coupled to the cabin door. The airbag is arranged in an inner cavity formed by the airbag cabin body and the cabin door. The motor is configured to drive the output shaft to rotate when the airbag expands to drive the cabin door to pivot in an opening direction; and to drive the output shaft to rotate when the airbag contracts to drive the cabin door to pivot in a closing direction to close the cabin door. In the electrically openable and closable mounting cabin provided by the present invention, the rotation of the output shaft of the motor is synchronized with the expansion or contraction of the airbag, and the motor combined with the hinge assembly can improve the reliability of the opening and closing of the cabin door.

Description

Technical Field

[0001] The present invention mainly relates to an electrically openable and closable mounting cabin, and more particularly, to an electrically openable and closable mounting cabin for a rotor cantilever of a dual-purpose water and air UAV and a dual-purpose water and air UAV provided with the mounting cabin. Background Art

[0002] Dual-purpose drones are new unmanned aerial vehicles that can cross the interface between water and air multiple times and can continue to navigate and be reused. Dual-purpose drones have the ability to dive underwater, cross water and air, and cruise in the air, and have broad application prospects in the fields of sea and air communications, search and rescue, and underwater equipment maintenance.

[0003] In a quad-rotor dual-purpose water-air drone, the quad-rotor is used to generate lift during the water-air crossing process to pull the drone from the water surface into the air. In this process, since the dual-purpose water-air drone floats on the water surface and there is a large amount of water in the fuselage, the quad-rotor needs to overcome not only the weight of the aircraft itself but also the weight of a large amount of additional water during the upward pulling process, which brings great challenges to the quad-rotor. In addition, this process will also greatly consume battery power and shorten the execution time of the quad-rotor dual-purpose water-air aircraft in tasks such as underwater diving and aerial cruising. At the same time, when the dual-purpose water-air drone stays on the water surface to perform the water-air crossing conversion, the propeller of the quad-rotor is close to the water surface. Once the fuselage is unstable during the crossing process, the propeller is likely to hit the water surface, causing damage to the propeller. Therefore, during the conversion process from diving to air flight, the drone needs to float on the water surface and keep the quad-rotor above the water surface at a certain height. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides an electrically openable and closable mounting cabin and a water-air dyadic UAV having the mounting cabin.

[0005] In a first aspect, the present invention provides an electrically openable and closable cargo compartment, comprising: a compartment door, an airbag compartment, a hinge assembly, a motor, and an airbag. The airbag compartment has an airbag compartment body, and the hinge assembly has an upper hinge and a lower hinge, the upper hinge is attached to the airbag compartment body, and the lower hinge is attached to the compartment door, and the compartment door can pivot relative to the airbag compartment body through the hinge assembly. The motor has an output shaft, and the output shaft is coupled to the compartment door. The airbag is arranged in an inner cavity formed by the airbag compartment body and the compartment door. The motor is configured to drive the output shaft to rotate in a first direction when the airbag is inflated to drive the compartment door to pivot in an opening direction, and to drive the output shaft to rotate in a second direction or continue to rotate in the first direction when the airbag is deflated to drive the compartment door to pivot in a closing direction to close the compartment door.

[0006] Specifically, the cargo compartment includes a connecting rod assembly, the output shaft is coupled to the cabin door via the connecting rod assembly, one end of the connecting rod assembly is attached to the output shaft, and the other end of the connecting rod assembly is attached to the cabin door.

[0007] Preferably, the motor is configured as an electric steering gear. The connecting rod assembly includes a first connecting rod, a second connecting rod and a support, one end of the first connecting rod is fixedly connected to the output shaft, the other end of the first connecting rod is pivotally connected to one end of the second connecting rod, the other end of the second connecting rod is pivotally connected to one end of the support, and the other end of the support is fixedly connected to the cabin door.

[0008] Specifically, the hatch extends longitudinally, and supports are respectively arranged at both ends of the inner side of the hatch, and a longitudinally extending shaft is arranged on the inner side of the hatch, and the shaft is fixed to the support. The shaft is passed through the other end of the second connecting rod so that the second connecting rod can pivot relative to the support.

[0009] Specifically, there are two doors and four hinge assemblies, and the four hinge assemblies are respectively arranged at the front and rear sides of the two doors.

[0010] Furthermore, the head and tail of the electrically openable and closeable mounting cabin are provided with fairing heads respectively, and an electric servo is provided between each fairing head and the airbag cabin, the electric servo at the head controls the opening and closing of one of the two cabin doors, and the electric servo at the tail controls the opening and closing of the other of the two cabin doors. Preferably, the cabin door, the airbag cabin and the fairing head are all made of nylon carbon fiber material.

[0011] Preferably, a communication hole is provided on the top of the airbag module body, and the communication hole is configured to connect the airbag fluid to the air source.

[0012] Preferably, the airbag compartment is provided with a rib plate and a connecting block, the rib plate extending longitudinally outside the top of the airbag compartment body; the connecting block includes a first part and a second part that are detachably connected, the first part is fixedly connected to the rib plate, and a connecting hole is formed between the first part and the second part.

[0013] In a second aspect, the present invention provides a dual-purpose water and air UAV having a rotor arm. The dual-purpose water and air UAV is also provided with a preferred electric opening and closing mounting cabin of the above-mentioned first aspect, and the rotor arm is connected to the electric opening and closing mounting cabin through the connecting hole of the connecting block.

[0014] Features and advantages of the present disclosure include:

[0015] The electrically openable and closable mounting cabin provided by the present invention connects the cabin door to the airbag cabin through a hinge assembly. The rotation of the output shaft of the motor is synchronized with the expansion or contraction of the airbag. The motor combined with the hinge assembly can improve the reliability of the opening and closing of the cabin door, and is suitable for meeting the needs of different degrees of opening of the cabin door, thereby meeting the needs of amphibious water and air drones for different buoyancy. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1 It is a structural schematic diagram of the electrically opened and closed mounting cabin provided by the present invention;

[0018] Figure 2 yes Figure 1 Schematic diagram of the stowage bay shown with the fairing head, hinge assembly and hatch removed;

[0019] Figure 3 It is a schematic diagram of the structure of the motor, connecting rod assembly and hatch of the mount cabin;

[0020] Figure 4 It is a schematic diagram of the structure of the hinge assembly of the mounting compartment;

[0021] Figure 5 This is a schematic diagram of the door of the mount bay in a closed state;

[0022] Figure 6 This is a schematic diagram of the mount bay door in an open state.

[0023] Description of reference numerals:

[0024] 100-mounting compartment, 10-airbag compartment, 11-connecting hole, 12-airbag compartment body, 14-ring body, 16-mounting groove, 18-rib plate, 20-hinge assembly, 21-upper hinge, 22-lower hinge, 24-hinge rod, 25-hinge rod cover, 26-mounting hole, 30-connecting block, 32-first part, 34-second part, 36-connecting hole, 40-motor, 42-output shaft, 50-connecting rod assembly, 52-first connecting rod, 54-second connecting rod, 101-hatch door, 102-airbag, 104-shaft rod, 105-support, 106-fairing head, 107-isolation plate. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present disclosure to clearly and completely describe the technical solutions in the embodiments of the present disclosure. Obviously, the described embodiments are only part of the embodiments of the present disclosure, not all of the embodiments. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present disclosure.

[0026] The present invention provides an electrically opened and closed mounting compartment 100, which can be detachably connected to the rotor arm of a dual-purpose water and air UAV. The mounting compartment is provided with an openable and closable door, and an airbag and a motor are provided inside the mounting compartment. When the airbag is inflated, the motor drives the door to open, so that the airbag can protrude from the mounting compartment, providing buoyancy for the UAV in the water so that the rotor propeller of the UAV is at a certain distance from the water surface for easy take-off from the water surface; when the airbag is deflated, the motor drives the door to close, the airbag retracts into the mounting compartment, and the door is closed, so that the airbag can be stored conveniently.

[0027] See also Figures 1 to 4 The electrically opened and closed cargo compartment 100 includes an airbag compartment 10, a hinge assembly 20, a door 101, a motor 40 and an airbag 102. The airbag compartment 10 and the door 101 are connected by the hinge assembly 20 to form a shell of the cargo compartment 100, and the airbag 102 is arranged in the inner cavity of the shell (the inner cavity formed by the airbag compartment 10 and the door 101).

[0028] Specifically, see Figure 1 , Figure 2 and Figure 3 The airbag cabin 10 has a longitudinally extending arc-shaped airbag cabin body 12, and the cabin door 101 is configured as a longitudinally extending arc-shaped plate. The cabin door 101 is pivotally connected to the airbag cabin body 12 through a hinge assembly 20. The airbag cabin body 12 and the cabin door 101 can be configured as a longitudinally extending cylindrical structure, and the cross-section of the structure can be elliptical, circular, etc., which is conducive to reducing the flight resistance of the drone. In some embodiments, see Figure 5 The airbag cabin body 12 and the hatch 101 form a cylindrical structure with a circular cross section. One or two hatches 101 can be provided. In a preferred embodiment, two hatches 101 are provided on the lower side of the airbag cabin body 12 and are arranged opposite to each other.

[0029] The drone is provided with an air source (e.g., a gas cylinder), which can provide gas for the airbag 102, and the airbag 102 and the air source can be fluidically connected through a tube. In some embodiments, a connecting hole 11 is provided on the top of the airbag cabin body 12, and the connecting hole 11 is fluidically connected to the airbag 102, and one end of the tube can be connected to the connecting hole 11. In other embodiments, one end of the tube is connected to the airbag 102, and the tube extends through the connecting hole 11. The airbag 102 can be inflated or deflated through the connecting hole 11.

[0030] The airbag 102 may be configured to be a long strip airbag extending longitudinally after deflation. In some embodiments, the airbag 102 is bonded to the top of the inner side of the airbag compartment 10, such as the top inner wall of the airbag compartment body 12. In some embodiments, the airbag 102 is made of elastic material, which will facilitate the airbag to return to the mounting compartment 100 after shrinking.

[0031] See also Figure 4The hinge assembly 20 includes an upper hinge 21, a lower hinge 22 and a hinge rod 24, and the upper hinge 21 and the lower hinge 22 are pivotally connected to the hinge rod 24. The upper hinge 21 is connected to the airbag cabin body 12, and the lower hinge 22 is connected to the cabin door 101. The upper hinge 21 and the lower hinge 22 are configured to have an arc-shaped plate-like portion extending in the longitudinal direction, and the arc-shaped plate-like portion of the upper hinge 21 is attached to the airbag cabin body 12, for example, attached to the inner side or the outer side of the arc-shaped plate-like portion, and the arc-shaped plate-like portion of the lower hinge 22 is attached to the cabin door 101. The arc-shaped plate-like portions of the upper hinge 21 and the lower hinge 22 are respectively provided with mounting holes 26, and the airbag cabin body 12 and the cabin door 101 are also provided with corresponding holes. The upper hinge 21 and the airbag cabin body 12, and the lower hinge 22 and the cabin door 101 are respectively fixedly connected by bolts or rivets.

[0032] One end of the hinge rod 24 is provided with a limiting boss. In some embodiments, the hinge assembly 20 further includes a hinge rod cover 25, which is provided at the other end of the hinge rod 24. The limiting boss of the hinge rod 24 and the hinge rod cover 25 are used to limit the longitudinal movement of the upper hinge 21 and the lower hinge 22 provided on the hinge rod 24 and prevent them from loosening and falling off, so that the hinge assembly 20 remains as a whole. Figure 2 The airbag cabin body 12 is provided with a mounting groove 16, and the hatch 101 is also provided with a corresponding mounting opening. The mounting groove 16 of the airbag cabin body 12 and the mounting opening of the hatch 101 are used to accommodate the middle part of the hinge assembly 20 (except the arc-shaped plate-shaped part).

[0033] Please continue to see Figure 1 , Figure 2 and Figure 3 In some embodiments, a hinge assembly 20 is provided at both ends of each hatch 101, that is, the mounting compartment 100 is provided with four hinge assemblies 20. The upper hinge 21 of the hinge assembly 20 is fixedly connected to the airbag compartment body 12, and the lower hinge 22 is connected to the hatch 101.

[0034] The airbag cabin 10 also includes a ring body 14 disposed at both ends of the airbag cabin body 12, and the mounting cabin 100 includes a fairing head 104, and two fairing heads 104 are respectively connected to the ring body 14. The fairing head 104, the airbag cabin 10, and the door 101 form a complete shell, and the airbag cabin 10 has a fluid shape, which is conducive to reducing the flight resistance of the drone. The fairing head 104, the airbag cabin 10, and the door 101 can be made of nylon carbon fiber (for example, by 3D printing), which not only meets the strength requirements of the mounting cabin 10, but also greatly reduces its weight.

[0035] See also Figure 2In some embodiments, the airbag capsule 10 further includes a rib plate 18, which extends longitudinally outside the top of the airbag capsule body 12, extending from the head end to the tail end of the airbag capsule body 12. The provision of the rib plate 18 helps to strengthen the strength of the airbag capsule 10.

[0036] The mount bay 100 further includes a connection block 30 disposed on the airbag bay 10, and the connection block 30 is used to connect the mount bay 100 to the rotor arm of the drone. Specifically, the connection block 30 can be configured as a lifting lug, and the connection block 30 is disposed on the rib plate 18. More specifically, the connection block 30 includes a first portion 32 and a second portion 34 that are detachably connected, wherein the first portion 32 is fixedly connected to the rib plate 18, a connection hole 36 is formed between the first portion 32 and the second portion 34, and the first portion 32 and the second portion 34 are connected by bolts or the like. When the mount bay 100 is connected to the rotor arm of the drone, the rotor arm extends through the connection hole 36.

[0037] Test Figure 2 and Figure 3 , an isolation plate 107 is provided between the airbag compartment 10 and the fairing head 106, and the motor 40 is embedded in the isolation plate 107. On the one hand, the isolation plate 107 provides mounting support for the motor 40, and on the other hand, it stops the airbag 102 from entering the fairing head 106. In some embodiments, the mounting compartment 100 is not provided with an isolation plate 107, and the motor 40 can be fixed to a bracket provided in the mounting compartment 100. The motor 40 has an output shaft 42, and the output shaft 42 is coupled to the hatch 101. The motor 40 can drive the output shaft 42 to rotate in two directions, clockwise and counterclockwise, wherein one of the clockwise and counterclockwise directions is a first direction, and the other is a second direction. The motor 40 has a waterproof function and can operate underwater. According to a preferred embodiment of the present invention, the motor 40 is a servo motor.

[0038] More specifically, the motor 40 is configured as an electric servo. In some embodiments, the electric servo receives instructions from the flight control system to drive the output shaft 42 to reciprocate between two angles, where each angle corresponds to a position. For example, the output shaft 42 rotates in a first direction, and when it rotates from the first angle to the second angle, the door 101 is fully opened; the output shaft 42 rotates in a second direction, and when it returns from the second angle to the first angle, the door 101 is fully closed. In some embodiments, the electric servo can control the output shaft 42 to rotate to any angle between the two angles, and rotate to different angles to adjust the degree of opening of the door 101, thereby meeting the space occupation requirements of the airbag 102 with different inflation degrees, and finally meeting the different buoyancy requirements of the drone in different scenarios.

[0039] In some preferred embodiments, the mounting compartment 100 includes a connecting rod assembly 50, and the output shaft 42 is coupled to the door 101 via the connecting rod assembly 50. One end of the connecting rod assembly 50 is attached to the output shaft 42 of the electric servo, and the other end of the connecting rod assembly 50 is attached to the door 101. When the output shaft 42 of the electric servo rotates, the connecting rod assembly 50 can be driven to move, and the door 101 is directly driven by the connecting rod assembly 50 to open or close in a pivoting manner with the cooperation of the hinge assembly 20. The connecting rod assembly 50 can convert the torque of the output shaft 42 into a push-pull force to open or close the door 101. The power assembly composed of the electric servo and the connecting rod assembly 50 has a simple structure and reliable operation.

[0040] The connecting rod assembly 50 includes a plurality of connecting rods. In some embodiments, the connecting rod assembly 50 includes a first connecting rod 52, a second connecting rod 54 and a third connecting rod (support 105), and the three connecting rods are pivotally connected in sequence. One end of the first connecting rod 52 is fixedly connected to the output shaft 42, the other end of the first connecting rod 52 is pivotally connected to one end of the second connecting rod 54, the other end of the second connecting rod 54 is pivotally connected to one end of the support 105, and the other end of the support 105 is fixed to the cabin door 101. The rotation angle of the cabin door 101 around the hinge rod 24 can be set as needed, which can be achieved by adjusting the length of the three connecting rods. In some embodiments, the range of the rotation angle of the cabin door 101 around the hinge rod 24 is 45° to 90°; in some embodiments, the rotation angle can be greater than 90°. The three connecting rods provided in the connecting rod assembly 50 can not only make the cabin door 101 rotate at a larger angle, but also be beneficial to stable operation.

[0041] Furthermore, a shaft 104 is provided on the inner side of the hatch 101, and the shaft 104 is fixedly connected to the support 105, and the other end of the second connecting rod 54 is pivotally connected to the support 105 through the shaft 104. Specifically, a shaft hole is provided on the other end of the second connecting rod 54, and the shaft 104 is passed through the shaft hole. Figure 3 , supports 105 are provided at both ends of the hatch 101, and the shaft 104 extends longitudinally to both ends of the hatch 101 and is fixedly connected to the two supports 105. Therefore, the driving force received by the shaft 104 can be transmitted to the two supports 105, so that the hatch 101 is subjected to force at the head and tail, which is conducive to the opening and closing of the hatch 101.

[0042] More specifically, in a preferred embodiment, the cargo compartment 100 has two doors 101, and electric servos are respectively provided between the fairing heads 106 at the head and tail of the cargo compartment 100 and the airbag compartment 10, that is, the isolation plate 107 at the head and the isolation plate 107 at the tail are respectively provided with electric servos, and the electric servo at the head controls the opening and closing of one of the two doors 101, and the electric servo at the tail controls the opening and closing of the other of the two doors 101.

[0043] Alternatively, in some embodiments, the electric servo receives the command of the flight control to drive the output shaft 42 to rotate in the first direction or the second direction for one circle, so that the opening and closing state of the cabin door 101 is cycled once. For example, when the output shaft 42 is at the first angle (first position), the cabin door 101 is completely closed; when the output shaft 42 rotates in the first direction, when it rotates from the first angle (first position) to the second angle (second position), the cabin door 101 is completely opened; the output shaft 42 continues to rotate in the first direction, when it returns from the second angle to the first angle, the cabin door 101 is completely closed. The connecting rod assembly 50 is specifically a crank rocker mechanism, which includes a crank, a connecting rod and a rocker. One end of the crank is attached to the output shaft 42, and the rocker near one end of the connecting rod is attached to the cabin door 101. The rotation of the output shaft 42 drives the rocker to do reciprocating swinging motion, thereby realizing the opening and closing of the cabin door 101.

[0044] The present invention also provides a drone provided with the aforementioned mounting cabin 100, the drone is provided with a gas cylinder, the gas cylinder provides a gas source for the airbag 101, and the gas cylinder is in fluid communication with the airbag 101. The mounting cabin 100 is connected to the rotor arm of the drone through a connecting block 30. Specifically, the rotor arm passes through the connecting hole 36 of the connecting block 30, and the first part 32 and the second part 34 of the connecting block 30 are connected by bolts. The drone can be provided with one or more mounting cabins 100 according to actual needs.

[0045] Figure 5 and Figure 6 The hatch 101 of the mounting compartment 100 is shown in a closed or open state. Figure 5 , the airbag 102 is not inflated, and the output shaft 42 of the electric servo and the connecting rod assembly 50 rotate to a closed angle position of the hatch 101. When the drone receives a floating command in the water, the gas cylinder starts to inflate the airbag 102. Figure 6 , the electric servo executes the command to open the cabin, the output shaft 42 and the connecting rod assembly 50 of the electric servo rotate to a position where the cabin door 101 is at a certain opening angle, and the inflated airbag 102 protrudes from the mounting cabin, providing buoyancy for the drone. When the drone floats to a certain distance from the water surface to ensure that the propeller does not beat on the water surface, the drone can take off from the water surface, thereby achieving the two-medium crossing of the drone. After the drone takes off from the water surface to a certain height, it starts to deflate the airbag 102, and the gas in the airbag 102 can return to the gas cylinder. At this time, the electric servo executes the command to close the cabin, and the output shaft 42 and the connecting rod assembly 50 of the electric servo rotate to pivot the cabin door 101 in the closing direction. At the same time, the airbag 102 gradually returns to the cabin, and finally the cabin door 101 is closed.

[0046] The mounting compartment 100 connects the door 101 to the airbag compartment 10 through the hinge assembly 20. The rotation of the output shaft 42 of the electric servo can be synchronized with the expansion or contraction of the airbag 102. The electric servo combined with the hinge assembly 20 can improve the reliability of the opening and closing of the door 101, and is suitable for meeting the needs of different degrees of opening of the door, thereby meeting the needs of the dual-purpose air-water UAV for different buoyancy. The mounting compartment 100 uses a simple mechanical structure to realize the switching of the drone in different states of the air and underwater buoyancy device, meeting the buoyancy requirements of the dual-purpose air-water UAV in different states. In addition, the mounting compartment can effectively simplify the layout of the drone structure, reduce the weight of the drone structure, and increase the overall design space of the drone. Providing buoyancy for the drone through the mounting compartment 100 has the advantages of simple control method and low process complexity, which can greatly reduce the weight and cost of the existing dual-purpose air-water UAV power device.

[0047] The above are only several embodiments of the present disclosure. Those skilled in the art may make various changes or modifications to the embodiments of the present disclosure based on the contents disclosed in the application documents without departing from the spirit and scope of the present disclosure.

Claims

1. An electrically openable and closable mounting cabin for a dual-purpose air-water UAV, wherein the dual-purpose air-water UAV has a rotor propeller, and the electrically openable and closable mounting cabin is detachably connected to the rotor arm of the dual-purpose air-water UAV, characterized in that: include: Hatch door (101); An airbag capsule (10), wherein the airbag capsule (10) has an airbag capsule body (12) extending longitudinally; Two hatches (101) extending longitudinally, the two hatches (101) being arranged opposite to each other on the lower side of the airbag cabin body (12), the two hatches and the airbag cabin body being configured into a longitudinally extending cylindrical structure; Four hinge assemblies (20), each hatch (101) is connected to the airbag cabin body (12) via two hinge assemblies (20); each hinge assembly (20) has an upper hinge (21) and a lower hinge (22), the upper hinge (21) is attached to the airbag cabin body (12), and the lower hinge (22) is attached to the hatch (101), and each hatch (101) can pivot relative to the airbag cabin body (12) via the two hinge assemblies (20); two motors (40), each motor (40) having an output shaft (42), the output shaft (42) being coupled to a hatch (101); and An airbag (102), the airbag (102) being arranged in an inner cavity formed by the airbag cabin body (12) and the two cabin doors (101); Each motor (40) is constructed such that: during the process of the amphibious aerial drone transforming from submerged flight to aerial flight, when the airbag (102) is inflated, the output shaft (42) is driven to rotate in a first direction to drive the coupled door (101) to pivot in an opening direction, and the inflated airbag (102) provides buoyancy for the amphibious aerial drone so that the rotor propeller is above the water surface by a certain distance; after the amphibious aerial drone is launched, when the airbag (102) is deflated, the output shaft (42) is driven to rotate in a second direction or continue to rotate in the first direction to drive the door (101) to pivot in a closing direction, and the deflated airbag (102) returns to the inner cavity.

2. The electrically openable and closable mounting bay according to claim 1, characterized in that: It comprises two connecting rod assemblies (50), each output shaft (42) is coupled to the cabin door (101) via a connecting rod assembly (50), one end of each connecting rod assembly (50) is attached to one output shaft (42), and the other end of each connecting rod assembly (50) is attached to one cabin door (101).

3. The electrically openable and closable mounting bay according to claim 2, characterized in that: The motor (40) is configured as an electric steering gear; The connecting rod assembly (50) comprises a first connecting rod (52), a second connecting rod (54) and a support (105); One end of the first connecting rod (52) is fixedly connected to an output shaft (42), the other end of the first connecting rod (52) is pivotally connected to one end of the second connecting rod (54), the other end of the second connecting rod (54) is pivotally connected to one end of the support (105), and the other end of the support (105) is fixedly connected to a cabin door (101).

4. The electrically openable and closable mounting bay according to claim 3, characterized in that: The supports (105) are respectively provided at both ends of the inner side of the hatch (101), and a longitudinally extending shaft (104) is provided on the inner side of the hatch (101), and the shaft (104) is fixed to the supports (105); The shaft rod (104) is passed through the other end of the corresponding second connecting rod (54) so ​​that the corresponding second connecting rod (54) can pivot relative to the coupled support (105).

5. The electrically openable and closable mounting bay according to claim 3, characterized in that: The four hinge assemblies (20) are respectively arranged at the front and rear sides of the two cabin doors (101).

6. The electrically openable and closable mounting bay according to claim 5, characterized in that: The head and tail of the electrically openable and closeable mounting cabin are respectively provided with fairing heads (106), each of the fairing heads (106) is provided with the electric servo, the electric servo at the head controls the opening and closing of one of the two cabin doors (101), and the electric servo at the tail controls the opening and closing of the other of the two cabin doors (101).

7. The electrically openable and closable mounting bay according to claim 6, characterized in that: The cabin door (101), the airbag cabin (10) and the fairing head (106) are all made of nylon carbon fiber material.

8. The electrically openable and closable mounting bay according to claim 1, characterized in that: A communication hole (11) is provided on the top of the airbag cabin body (12), and the communication hole (11) is configured to connect the airbag (102) fluid to an air source.

9. The electrically openable and closable loading bay according to any one of claims 1 to 8, characterized in that: The airbag compartment (10) is provided with a rib plate (18) and a connecting block (30); The rib plate (18) extends longitudinally outside the top of the airbag cabin body (12); The connecting block (30) comprises a first part (32) and a second part (34) which are detachably connected, the first part (32) being fixedly connected to the rib plate (18), and a connecting hole (36) being formed between the first part (32) and the second part (34).

10. A dual-purpose air-water drone having a rotor arm, characterized in that: The dual-purpose water-air UAV is also provided with the electrically openable and closable mounting compartment as claimed in claim 9, and the rotor support arm is connected to the electrically openable and closable mounting compartment via the connecting hole (36) of the connecting block (30).

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