A UAV radome side fold back connecting mechanism

Abstract

The application provides a UAV radar cover lateral folding connection mechanism, comprising a hinge base assembly, an upper hinge assembly, a lower hinge assembly, a plurality of hinge shaft assemblies, a fuselage front frame, a radar cover ring frame assembly, a radar cover, a plurality of positioning pin seats and a limiting assembly. The application realizes the connection between the radar cover and the fuselage through two synchronous open motion chains, and the radar cover can be quickly and smoothly opened and closed laterally. The technical scheme of the application can solve the technical problems of the prior art, such as complex opening and closing operation process, long dismounting time and sealing scheme limited by the motion track of the radar cover.

Description

Technical Field

[0001] This invention belongs to the field of structural design technology, and in particular relates to a lateral folding connection mechanism for a drone radome. Background Technology

[0002] During ground testing, inspection, and maintenance of UAVs, the radome needs to be opened and closed frequently. Therefore, a mechanism that can stably and reliably connect the radome to the fuselage and is easy to operate is required.

[0003] Currently, the connection between the radome and the drone body is mostly achieved using bolts / nuts or hinges. The bolt / nut method connects the radome to the fuselage frame via a group of bolts around the perimeter. Disassembly and assembly require removing all bolts before the radome can be removed, making the process complex and time-consuming; the radome is also prone to damage during transport. The hinge method connects the fuselage and radome via hinges on the upper part of the fuselage frame. The radome rotates around a fixed axis, sealing the connection by compressing a sealing ring in the mating area. However, the width of this mating area is limited by the movement trajectory, resulting in poor sealing. After the radome is opened, it is locked in place by a diagonal brace. The entire process requires multiple people to operate. Summary of the Invention

[0004] This invention provides a lateral folding connection mechanism for a drone radome, which can at least solve one of the technical problems existing in the prior art.

[0005] The present invention provides a lateral folding connection mechanism for a drone radome, including a hinge base assembly, an upper hinge assembly, a lower hinge assembly, several hinge shaft assemblies, a fuselage front frame, a radome ring frame assembly, a radome, several positioning pins, and a limiting assembly.

[0006] The radar dome frame assembly includes a radar dome frame body and a radar dome frame upper connector, a radar dome frame lower connector, and several positioning pins disposed on the radar dome frame body; the radar dome frame body is sleeved inside the radar dome.

[0007] The hinge base assembly includes a hinge base body, an upper hinge base connector, a lower hinge base connector, and a hinge base limiting post. The hinge base body is disposed on the front frame of the fuselage, and the upper hinge base connector is disposed on the upper part of the hinge base body. The lower hinge base connector and the limiting post are disposed on the lower part of the hinge base body. The limiting post is used to contact the lower hinge root link when the radome is in the fully open state to limit the lower hinge root link. The limiting post is provided with a positioning pin hole, and the positioning pin hole of the limiting post matches the position of one of the positioning pins.

[0008] The upper hinge assembly includes an upper hinge root link, an upper hinge middle link, and an upper hinge end link; one end of the upper hinge root link is hinged to the upper connector of the hinge base via the hinge shaft assembly, and the other end is hinged to one end of the upper hinge middle link via the hinge shaft assembly; one end of the upper hinge end link is hinged to the other end of the upper hinge middle link via the hinge shaft assembly, and the other end is hinged to the upper connector of the radar dome frame via the hinge shaft assembly;

[0009] The lower hinge assembly includes a lower hinge root link, a lower hinge middle link, and a lower hinge end link; one end of the lower hinge root link is hinged to the lower connector of the hinge base via the hinge shaft assembly, and the other end is hinged to one end of the lower hinge middle link via the hinge shaft assembly; one end of the lower hinge end link is hinged to the other end of the lower hinge middle link via the hinge shaft assembly, and the other end is hinged to the lower connector of the radar dome frame via the hinge shaft assembly;

[0010] A number of positioning pin seats are provided on the front frame of the fuselage, and each positioning pin seat is provided with a positioning pin hole; the positioning pin hole of each positioning pin seat matches the position of the corresponding positioning pin; the closure of the radar dome is realized through the cooperation of the positioning pin hole of the hinge base limiting post, the positioning pin hole of each positioning pin seat and the corresponding positioning pin.

[0011] The limiting component is used to fix all movable parts within the connecting mechanism when the radar dome is in the fully open state, thereby limiting the position of the radar dome.

[0012] Preferably, the upper hinge assembly and the lower hinge assembly are arranged in parallel vertically, and their vertical projections in the vertical direction coincide.

[0013] Preferably, the upper hinge root link, the upper hinge end link, the lower hinge root link, and the lower hinge end link are all in the shape of an "I"; the upper hinge middle link and the lower hinge middle link are both in the shape of a "V".

[0014] Preferably, the limiting assembly includes two first limiting members and two second limiting members; when the connecting mechanism is in the fully open state, one of the first limiting members is fixedly connected to one side of the upper connector of the hinge base, the root connecting rod of the upper hinge, and the middle connecting rod of the upper hinge, respectively; the other first limiting member is fixedly connected to one side of the lower connector of the hinge base, the root connecting rod of the lower hinge, and the middle connecting rod of the lower hinge, respectively; one of the second limiting members is fixedly connected to the other side of the upper connector of the radome ring frame, the end connecting rod of the upper hinge, and the middle connecting rod of the upper hinge, respectively; the other second limiting member is fixedly connected to the other side of the lower connector of the radome ring frame, the end connecting rod of the lower hinge, and the middle connecting rod of the lower hinge, respectively.

[0015] Preferably, each hinge shaft assembly includes a hinge bolt, a bushing, a washer, a slotted nut, and a cotter pin; the bushing is sleeved on the outside of the hinge bolt, and the hinge bolt with the bushing sleeved is sequentially inserted into the corresponding hinge hole and the washer and then threadedly connected to the slotted nut; the cotter pin is disposed in the slot of the slotted nut and is threadedly connected to the hinge bolt.

[0016] Preferably, when the connecting mechanism is in the fully open state, the angle between the lower hinge root link and the front frame of the fuselage is in the range of 155-170°.

[0017] Preferably, when the connecting mechanism is in the fully open state, the angle between the plane where the radar dome port is located and the plane where the fuselage front frame is located is not less than 100°.

[0018] By applying the technical solution of this invention, the connection between the radome and the airframe is achieved through two synchronously moving open kinematic chains, allowing the radome to open and close quickly and smoothly in a lateral manner. Compared with existing technologies, the technical solution of this invention simplifies the opening and closing process of the UAV radome, shortens the time for radome assembly and disassembly, allows for operation by a single person, features a high degree of freedom in the entire stroke trajectory of the mechanism, does not interfere with the airframe structure, facilitates sealing design at the docking end, and offers a large opening angle and good openness. Attached Figure Description

[0019] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0020] Figure 1 This diagram illustrates a UAV radome lateral folding connection mechanism in the retracted position state, according to an embodiment of the present invention.

[0021] Figure 2 This diagram illustrates a UAV radome lateral retraction connection mechanism in the open-positioned state, according to an embodiment of the present invention.

[0022] Figure 3 A schematic diagram of a hinge base and several locating pins provided according to an embodiment of the present invention is shown, which are installed on the front frame of the fuselage.

[0023] Figure 4 A schematic diagram of the structure of an upper hinge assembly according to an embodiment of the present invention is shown;

[0024] Figure 5 A schematic diagram of the structure of a lower hinge assembly according to an embodiment of the present invention is shown;

[0025] Figure 6 A schematic diagram of a hinge shaft assembly according to an embodiment of the present invention is shown;

[0026] Figure 7 A schematic diagram of the structure of a radome and a radome ring assembly provided according to an embodiment of the present invention is shown;

[0027] Figure 8 A schematic diagram of the installation state of a limiting component provided according to an embodiment of the present invention is shown.

[0028] The above figures include the following reference numerals:

[0029] 1. Hinge base assembly; 2. Upper hinge assembly; 3. Lower hinge assembly; 4. Hinge shaft assembly; 5. Front frame of fuselage; 6. Radar radome ring frame assembly; 7. Radar radome; 8. Positioning pin seat; 9. Limiting assembly; 1-1. Upper connector of hinge base; 1-2. Lower connector of hinge base; 1-3. Limiting post of hinge base; 2-1. Root connecting rod of upper hinge; 2-2. Middle connecting rod of upper hinge; 2-3. End connecting rod of upper hinge; 3-1. Root connecting rod of lower hinge; 3-2. Middle connecting rod of lower hinge; 3-3. End connecting rod of lower hinge; 4-1. Hinge bolt; 4-2. Bushing; 4-3. Washer; 4-4. Slotted nut; 4-5. Cotter pin; 6-1. Upper connector of radome ring frame; 6-2. Lower connector of radome ring frame; 6-3. Positioning pin; 9-1. First limiting component; 9-2. Second limiting component. Detailed Implementation

[0030] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0032] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0033] like Figures 1-8 As shown, the present invention provides a lateral folding connection mechanism for a drone radome, including a hinge base assembly 1, an upper hinge assembly 2, a lower hinge assembly 3, several hinge shaft assemblies 4, a fuselage front frame 5, a radome ring frame assembly 6, a radome 7, several positioning pin seats 8, and a limiting assembly 9.

[0034] The radar radome frame assembly 6 includes a radar radome frame body and a radar radome frame upper connector 6-1, a radar radome frame lower connector 6-2, and a plurality of positioning pins 6-3 disposed on the radar radome frame body; the radar radome frame body is sleeved inside the radar radome 7.

[0035] The hinge base assembly 1 includes a hinge base body, an upper hinge base connector 1-1, a lower hinge base connector 1-2, and a hinge base limiting post 1-3. The hinge base body is fixed to the front frame 5 of the fuselage by bolts. The upper hinge base connector 1-1 is located on the upper part of the hinge base body. The lower hinge base connector 1-2 and the limiting post 1-3 are located on the lower part of the hinge base body. The limiting post 1-3 is used to contact the lower hinge root link 3-1 when the radar dome 7 is in the fully open state, so as to limit the lower hinge root link 3-1. The limiting post 1-3 is provided with a positioning pin hole, and the positioning pin hole of the limiting post 1-3 matches the position of one of the positioning pins 6-3.

[0036] The upper hinge assembly 2 includes an upper hinge root link 2-1, an upper hinge middle link 2-2, and an upper hinge end link 2-3; one end of the upper hinge root link 2-1 is hinged to the upper connector 1-1 of the hinge base through the hinge shaft assembly 4, and the other end is hinged to one end of the upper hinge middle link 2-2 through the hinge shaft assembly 4; one end of the upper hinge end link 2-3 is hinged to the other end of the upper hinge middle link 2-2 through the hinge shaft assembly 4, and the other end is hinged to the upper connector 6-1 of the radar dome frame through the hinge shaft assembly 4;

[0037] The lower hinge assembly 3 includes a lower hinge root link 3-1, a lower hinge middle link 3-2, and a lower hinge end link 3-3. One end of the lower hinge root link 3-1 is hinged to the lower connector 1-2 of the hinge base via the hinge shaft assembly 4, and the other end is hinged to one end of the lower hinge middle link 3-2 via the hinge shaft assembly 4. One end of the lower hinge end link 3-3 is hinged to the other end of the lower hinge middle link 3-2 via the hinge shaft assembly 4, and the other end is hinged to the lower connector 6-2 of the radar dome frame via the hinge shaft assembly 4.

[0038] Several positioning pin seats 8 are fixed to the front frame 5 of the fuselage by riveting, and each positioning pin seat 8 is provided with a positioning pin hole; the positioning pin hole of each positioning pin seat 8 matches the position of the corresponding positioning pin 6-3; the closure of the radar cover 7 is realized by the cooperation of the positioning pin holes of the hinge base limiting post 1-3, the positioning pin holes of each positioning pin seat 8 and the corresponding positioning pin 6-3.

[0039] The limiting component 9 is used to fix all movable parts in the connecting mechanism when the radar dome 7 is in the fully open state, so as to limit the radar dome 7.

[0040] In this embodiment, the hinge base 1, the radar dome frame 6, and the positioning pin seat 8 require tooling for positioning during assembly. Furthermore, all components of the connecting mechanism are located inside the machine body, with no protruding aerodynamic surfaces.

[0041] According to one embodiment of the present invention, the upper hinge assembly 2 and the lower hinge assembly 3 are two sets of open kinematic chains, arranged in parallel vertically, and their vertical projections in the vertical direction coincide. That is, the link lengths and hinge projection positions of the two sets of hinge assemblies are consistent, thereby ensuring that the upper hinge assembly 2 and the lower hinge assembly 3 move synchronously throughout all movements of the radar dome 7.

[0042] According to one embodiment of the present invention, the upper hinge root link 2-1, the upper hinge end link 2-3, the lower hinge root link 3-1, and the lower hinge end link 3-3 are all in the shape of an "I"; the upper hinge middle link 2-2 and the lower hinge middle link 3-2 are both in the shape of a "V".

[0043] According to one embodiment of the present invention, the limiting assembly 9 includes two first limiting members 9-1 and two second limiting members 9-2. When the connecting mechanism is in the fully open state, one of the first limiting members 9-1 is fixedly connected to one side of the upper connector 1-1 of the hinge base, the root connecting rod 2-1 of the upper hinge, and the middle connecting rod 2-2 of the upper hinge, respectively; the other first limiting member 9-1 is fixedly connected to one side of the lower connector 1-2 of the hinge base, the root connecting rod 3-1 of the lower hinge, and the middle connecting rod 3-2 of the lower hinge, respectively. One of the second limiting members 9-2 is fixedly connected to the other side of the upper connector 6-1 of the radome ring frame, the end connecting rod 2-3 of the upper hinge, and the middle connecting rod 2-2 of the upper hinge, respectively; the other second limiting member 9-2 is fixedly connected to the other side of the lower connector 6-2 of the radome ring frame, the end connecting rod 3-3 of the lower hinge, and the middle connecting rod 3-2 of the lower hinge, respectively. In other words, the limiting assembly 9 restricts the movement of the entire mechanism through pin connections.

[0044] According to one embodiment of the present invention, each hinge shaft assembly 4 includes a hinge bolt 4-1, a bushing 4-2, a washer 4-3, a slotted nut 4-4, and a cotter pin 4-5; the bushing 4-2 is sleeved on the outside of the hinge bolt 4-1, and the hinge bolt 4-1 with the bushing 4-2 sleeved on it is sequentially inserted into the corresponding hinge hole and the washer 4-3 and then threadedly connected to the slotted nut 4-4; the cotter pin 4-5 is disposed in the slot of the slotted nut 4-4 and is threadedly connected to the hinge bolt 4-1.

[0045] According to one embodiment of the present invention, when the connecting mechanism is in the fully open state, the angle between the lower hinge root link 3-1 and the front frame 5 of the fuselage is in the range of 155-170°.

[0046] According to one embodiment of the present invention, when the connecting mechanism is in the fully open state, the angle between the plane containing the port of the radome 7 and the plane containing the front frame 5 of the fuselage is not less than 100°. That is, the fully open angle of the radome 7 is not less than 100°.

[0047] To gain a further understanding of the present invention, the following description is provided in conjunction with... Figures 1-8 The working principle of the UAV radome lateral folding connection mechanism of the present invention will be described in detail below:

[0048] When the radome 7 is in the retracted position, the upper hinge assembly 2 and the lower hinge assembly 3 are folded and stored inside the radar compartment (i.e., within the space enclosed by the radome 7 and the front frame 5 of the fuselage). The positioning pins 6-3 on the radome ring frame 6 cooperate with the positioning pin seat 8 and the hinge base limiting post 1-3.

[0049] When radar dome 7 is opened, it first moves along the fuselage heading ( Figure 3 Pull out the radome 7 in a vertical outward direction. The positioning pins 6-3 on the radome ring frame 6 will retract from the positioning pin seats 8 and the hinge base limiting posts 1-3. After all the positioning pins 6-3 have completely retracted from the pin holes of the positioning pin seats 8 and the hinge base limiting posts 1-3, push the radome 7 to move horizontally relative to the front frame 5 of the fuselage. Figure 2 The combined motion of translation within the plane of the upper hinge assembly 2 and rotation around the vertical axis (the axis of the hinge axis assembly 4) continues until the connecting mechanism is in the fully open state.

[0050] At this point, the opening process of the radar dome 7 ends, and the lower hinge root link 3-1 rotates to a position where it forms a 160° angle with the front frame 5 of the fuselage; and its side contacts the side of the limiting post 1-3, preventing it from rotating excessively and squeezing the front frame 5 of the fuselage.

[0051] With the radar dome 7 fully open, the upper hinge assembly 2 and the lower hinge assembly 3 are locked in place using the limiting component 9, and the fully open angle of the radar dome 7 is not less than 100°.

[0052] When the radar dome 7 is closed, the limiting component 9 is removed, the position lock of the upper hinge component 2 and the lower hinge component 3 is released, and then the reverse motion of the radar dome 7 opening process is performed.

[0053] When the radome ring 6 is closed to near the front end of the fuselage end frame 5, adjust the relative position of the radome ring 6 and the fuselage end frame 5, and push the radome 6 in along the fuselage heading. The positioning pins 6-3 on the radome ring 6 engage with the corresponding pin holes on the positioning pin seat 8 and the hinge base limit post 1-3. The radome 7 is sleeved on the outside of the front fuselage frame 5. The positioning pins 6-3 bear the shear force between the radome 7 and the fuselage. The closing process of the radome 7 is completed.

[0054] In summary, the present invention provides a lateral folding connection mechanism for a UAV radome, which has the following advantages compared with the prior art:

[0055] (1) The mechanism is simple in composition. It connects the radome to the body through two synchronously moving open kinematic chains. The radome can be opened and closed quickly and smoothly in the side.

[0056] (2) The organization has simplified the process of opening the radome of the UAV, shortened the time for disassembling and assembling the radome, and can complete the operation by a single person;

[0057] (3) The mechanism has a high degree of freedom in its motion trajectory, does not interfere with the body structure, is conducive to sealing the docking end, has a large opening angle, and good openness.

[0058] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0059] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0060] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A lateral folding connection mechanism for a drone radome, characterized in that, Includes hinge base assembly (1), upper hinge assembly (2), lower hinge assembly (3), several hinge shaft assemblies (4), fuselage front frame (5), radome ring frame assembly (6), radome (7), several positioning pin seats (8), and limit assembly (9); The radar dome frame assembly (6) includes a radar dome frame body and a radar dome upper connector (6-1), a radar dome lower connector (6-2), and several positioning pins (6-3) disposed on the radar dome frame body; the radar dome frame body is sleeved inside the radar dome (7); The hinge base assembly (1) includes a hinge base body, an upper hinge base connector (1-1), a lower hinge base connector (1-2), and a hinge base limiting post (1-3). The hinge base body is disposed on the front frame (5) of the fuselage. The upper hinge base connector (1-1) is disposed on the upper part of the hinge base body. The lower hinge base connector (1-2) and the limiting post (1-3) are disposed on the lower part of the hinge base body. The limiting post (1-3) is used to contact the lower hinge root link (3-1) when the radar dome (7) is in the fully open state, so as to limit the lower hinge root link (3-1). The limiting post (1-3) is provided with a positioning pin hole, and the positioning pin hole of the limiting post (1-3) matches the position of one of the positioning pins (6-3). The upper hinge assembly (2) includes an upper hinge root link (2-1), an upper hinge middle link (2-2), and an upper hinge end link (2-3); one end of the upper hinge root link (2-1) is hinged to the upper connector (1-1) of the hinge base through the hinge shaft assembly (4), and the other end is hinged to one end of the upper hinge middle link (2-2) through the hinge shaft assembly (4); one end of the upper hinge end link (2-3) is hinged to the other end of the upper hinge middle link (2-2) through the hinge shaft assembly (4), and the other end is hinged to the upper connector (6-1) of the radar dome frame through the hinge shaft assembly (4); The lower hinge assembly (3) includes a lower hinge root link (3-1), a lower hinge middle link (3-2), and a lower hinge end link (3-3). One end of the lower hinge root link (3-1) is hinged to the lower connector (1-2) of the hinge base through the hinge shaft assembly (4), and the other end is hinged to one end of the lower hinge middle link (3-2) through the hinge shaft assembly (4). One end of the lower hinge end link (3-3) is hinged to the other end of the lower hinge middle link (3-2) through the hinge shaft assembly (4), and the other end is hinged to the lower connector (6-2) of the radar dome frame through the hinge shaft assembly (4). A number of positioning pin seats (8) are provided on the front frame (5) of the fuselage, and each positioning pin seat (8) is provided with a positioning pin hole; the positioning pin hole of each positioning pin seat (8) matches the position of the corresponding positioning pin (6-3); the closure of the radar dome (7) is realized by the cooperation of the positioning pin hole of the hinge base limiting post (1-3), the positioning pin hole of each positioning pin seat (8) and the corresponding positioning pin (6-3); The limiting component (9) is used to fix all movable parts in the connecting mechanism when the radar dome (7) is in the fully open state, so as to limit the radar dome (7).

2. The connecting mechanism according to claim 1, characterized in that, The upper hinge assembly (2) and the lower hinge assembly (3) are arranged in parallel vertically, and their vertical projections along the vertical direction coincide.

3. The connecting mechanism according to claim 1 or 2, characterized in that, The upper hinge root link (2-1), the upper hinge end link (2-3), the lower hinge root link (3-1), and the lower hinge end link (3-3) are all in the shape of an "I"; the upper hinge middle link (2-2) and the lower hinge middle link (3-2) are both in the shape of a "V".

4. The connecting mechanism according to any one of claims 1-3, characterized in that, The limiting component (9) includes two first limiting members (9-1) and two second limiting members (9-2); when the connecting mechanism is in the fully open state, one of the first limiting members (9-1) is fixedly connected to one side of the upper connector (1-1) of the hinge base, the root connecting rod (2-1) of the upper hinge, and the middle connecting rod (2-2) of the upper hinge, respectively; the other first limiting member (9-1) is fixedly connected to the lower connector (1-2) of the hinge base and the root connecting rod of the lower hinge, respectively. (3-1) and one side of the connecting rod (3-2) in the lower hinge are fixedly connected. One of the second limiting members (9-2) is fixedly connected to the other side of the upper connector (6-1) of the radar dome frame, the connecting rod (2-3) at the upper hinge end, and the connecting rod (2-2) in the upper hinge, respectively. The other second limiting member (9-2) is fixedly connected to the other side of the lower connector (6-2) of the radar dome frame, the connecting rod (3-3) at the lower hinge end, and the connecting rod (3-2) in the lower hinge, respectively.

5. The connecting mechanism according to claim 1, characterized in that, Each of the hinge shaft assemblies (4) includes a hinge bolt (4-1), a bushing (4-2), a washer (4-3), a slotted nut (4-4), and a cotter pin (4-5). The bushing (4-2) is sleeved on the outside of the hinge bolt (4-1). The hinge bolt (4-1) with the bushing (4-2) sleeved on it is inserted into the corresponding hinge hole and the washer (4-3) in sequence and then threadedly connected to the slotted nut (4-4). The cotter pin (4-5) is set in the slot of the slotted nut (4-4) and threadedly connected to the hinge bolt (4-1).

6. The connecting mechanism according to claim 1, characterized in that, When the connecting mechanism is in the fully open state, the angle between the lower hinge root link (3-1) and the front frame (5) of the fuselage is 155-170°.

7. The connecting mechanism according to claim 1, characterized in that, When the connecting mechanism is in the fully open state, the angle between the plane where the radar dome (7) port is located and the plane where the fuselage front frame (5) is located is not less than 100°.

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