Rocket launch unmanned aerial vehicle connector plug-in mechanism

Abstract

The application belongs to the field of unmanned aerial vehicle launching and provides a connector plugging and unplugging mechanism based on rocket launching of unmanned aerial vehicle, which comprises a box body, a four-bar linkage and a connector plug; the box body is installed at the top of a launching box; the bottom of the box body is provided with the connector plug which can be plugged out and is used for plugging and cooperating with the connector of the unmanned aerial vehicle; the four-bar linkage is installed in the box body and the top of the connector plug is connected with the four-bar linkage; when the connector plug is used for launching the unmanned aerial vehicle, the connector plug is pushed to rise by the movement of the four-bar linkage, so as to be separated from the connector; the connector plugging and unplugging mechanism is integrated in the launching box, the influence of the rocket tail flame can be avoided, the connector plug is unplugged when it moves synchronously with the unmanned aerial vehicle, the connector is prevented from being pulled, and the stability and reliability of the plugging and unplugging action are improved.

Description

Technical Field

[0001] This invention belongs to the field of drone launch, specifically relating to a connector disconnection mechanism for drones launched from rockets. Background Technology

[0002] With the widespread application of drones in the military field, rapid launch and takeoff have become crucial factors in gaining battlefield initiative. Rocket-assisted launch is a key method for achieving rapid drone takeoff. The drone and launch container are connected via a connector for drone status monitoring and control. The drone has a connector socket, while the launch container has a drone plug. During the process of the booster rocket ejecting the drone from the launch container, the connector plug and socket need to reliably separate, ensuring that the connector plug on the launch container is not ablated by the booster rocket's exhaust plume.

[0003] The existing connector disconnection mechanism cannot completely isolate the connector plug on the launch box from the booster rocket exhaust plume, and the connector plug is at risk of being burned. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a connector de-energizing mechanism for rocket-launched unmanned aerial vehicles (UAVs) to solve the problems in the prior art. The technical solution adopted by this invention is as follows: A connector insertion / disconnection mechanism for rocket-launched unmanned aerial vehicles includes a housing, a four-bar linkage, and a connector plug; The housing is installed at the top inside the launch box, and the bottom of the housing is provided with a connector plug that can be inserted through. The connector plug is used to connect to the connector of the UAV. The four-bar linkage is installed inside the housing, and the top of the connector plug is connected to the four-bar linkage. When the drone is launched, the connector plug is pushed up by the movement of the four-bar linkage, thereby detaching from the connector.

[0005] Furthermore, it also includes a plug mounting base, which is disposed within the housing, on which the connector plug is mounted, and the plug mounting base is connected to the four-bar linkage.

[0006] Furthermore, the four-bar linkage includes four parallel rods, the tops of which are rotatably connected to the top of the housing, and the bottoms of which are rotatably connected to the plug mounting base.

[0007] Furthermore, the bottom of the housing is provided with a hollow portion for the connector plug to move through, and the connector plug extends through the hollow portion.

[0008] Furthermore, it also includes connecting rods, sliders, push rods, and switch baffles; One end of the plug mounting base is rotatably connected to one end of the connecting rod, and the other end of the connecting rod is movably connected to the slider, which is slidably connected to the bottom of the housing. The slider is rotatably connected to one end of the two push rods, the other end of the two push rods is rotatably connected to one end of the two switch baffles, and the other end of the two switch baffles is rotatably connected to the bottom of the box. When the plug mounting base moves, it pushes the slider to move via the connecting rod. When the slider moves, it pushes the two push rods to rotate, causing the two switch baffles to close or open. When the two switch baffles are closed, they block the hollow part. When the two switch baffles are open, they open the hollow part.

[0009] Furthermore, the slider is mounted on an electric guide rail.

[0010] Furthermore, the connector plug includes a retaining base, a plug, a spring, and a limiting pin; The top surface of the plug mounting base is fixedly connected to the fixing base, which is a hollow structure. The plug is slidably disposed within the hollow structure. The bottom of the plug protrudes from the fixing base and is used to connect to the connector. The side of the plug is fixedly connected to the limiting pin. The side of the fixing base is provided with a notch for the limiting pin to move. The limiting pin is fixedly connected to the top of the spring, and the bottom of the spring is fixedly connected to the top surface of the plug mounting base.

[0011] The present invention has the following beneficial effects: The present invention integrates the connector disengagement mechanism into the launch box, and can avoid the influence of rocket exhaust flame. The connector plug disengages when it moves synchronously with the UAV, avoiding connector pulling and improving the stability and reliability of the disengagement action. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the overall structure; Figure 2 This is a schematic diagram of the disengagement mechanism. Figure 1 ; Figure 3 This is a schematic diagram of the disengagement mechanism. Figure 2 ; Figure 4 This is a schematic diagram of the disengagement mechanism. Figure 3 In the diagram, the upper diagram shows the switch baffle when it is open, and the lower diagram shows the switch baffle when it is closed. Figure 5 This is a schematic diagram of a connector plug. Detailed Implementation

[0013] The following will be based on embodiments of the present invention. Figures 1-5The technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Unless otherwise specified, the technical means used in the embodiments are conventional means well known to those skilled in the art.

[0014] like Figure 1 A connector insertion / disconnection mechanism for rocket-launched unmanned aerial vehicles includes a housing 1, a four-bar linkage 2, and a connector plug. The housing 1 is installed at the top inside the launch box, and the bottom of the housing 1 is provided with a connector plug that can be inserted through. The connector plug is used to connect to the connector of the UAV. The four-bar linkage 2 is installed inside the housing 1. The top of the connector plug is connected to the four-bar linkage 2. When the drone is launched, the connector plug is pushed up by the movement of the four-bar linkage 2, thereby detaching from the connector.

[0015] During the rocket-assisted launch of the UAV of this invention, the four-bar linkage 2 is triggered. The upward movement of the four-bar linkage 2 causes the connector plug to move forward and rise, separating the connector plug from the UAV's connector and completing the disengagement action. The connector plug can be matched to the launch speed of the UAV. The housing 1 of this invention provides a protective space for the disengagement mechanism, avoiding the influence of the rocket's exhaust plume.

[0016] This invention integrates the connector disengagement mechanism into the launch box, and can avoid the influence of rocket exhaust flame. The connector plug disengages when it moves synchronously with the UAV, avoiding connector pulling and improving the stability and reliability of the disengagement action.

[0017] like Figures 2-4 The present invention also includes a plug mounting base 3, which is disposed inside the housing 1. The connector plug is mounted on the plug mounting base 3, and the plug mounting base 3 is connected to the four-bar linkage 2.

[0018] Furthermore, the four-bar linkage 2 includes four parallel rods, the tops of which are rotatably connected to the top of the housing 1, and the bottoms of which are rotatably connected to the plug mounting base 3.

[0019] The four rods are divided into two groups and symmetrically distributed on both sides of the plug mounting base 3. The top of each rod is hinged to the top of the housing 1 through a hinge shaft, and the bottom is hinged to the top surface of the plug mounting base 3 through a hinge shaft, forming two sets of symmetrical parallelogram linkage structures. In the ready-to-launch state, the four rods are set vertically, the plug mounting base 3 is in the low position, and the connector plug is inserted into the connector. When disengaging, the four rods rotate upward around the top hinge point in sync, driving the plug mounting base 3 to move forward and rise, so that the connector plug is separated from the UAV connector, completing the disengagement action.

[0020] Furthermore, the bottom of the housing 1 is provided with a hollow portion for the connector plug to move through, and the connector plug passes through the hollow portion. The hollow portion has an oblong hole structure, which serves to constrain the direction of movement of the connector plug.

[0021] Furthermore, it also includes a connecting rod 4, a slider 5, a push rod 6, and a switch baffle 7; One end of the plug mounting base 3 is rotatably connected to one end of the connecting rod 4, and the other end of the connecting rod 4 is movably connected to the slider 5. The slider 5 is slidably connected to the bottom of the box 1. The slider 5 is rotatably connected to one end of the two push rods 6, the other end of the two push rods 6 is rotatably connected to one end of the two switch baffles 7, and the other end of the two switch baffles 7 is rotatably connected to the bottom of the box 1. When the plug mounting base 3 moves, it pushes the slider 5 to move via the connecting rod 4. When the slider 5 moves, it pushes the two push rods 6 to rotate, causing the two switch baffles 7 to close or open. When the two switch baffles 7 are closed, they block the hollow part. When the two switch baffles 7 are open, they open the hollow part.

[0022] In the ready-to-launch state, the plug mounting base 3 is in the low position and protrudes from the hollow part. The connector plug is inserted into the connector, and the switch baffle 7 unfolds to both sides, fully opening the hollow part at the bottom of the housing 1. The connector plug protrudes from the hollow part. During the insertion and removal process, the plug mounting base 3 rises, pushing the slider 5 to slide through the connecting rod 4. When the slider 5 slides, it drives the two push rods 6 to rotate towards the center. The push rods 6 push the two switch baffles 7 to rotate around the end hinge point towards the center. When the plug mounting base 3 rises to the highest position and the connector plug is fully retracted into the housing 1, the two switch baffles 7 are fully closed, blocking the hollow part at the bottom of the housing 1. The closing protection function of the switch baffles can block the exhaust flame outside the housing 1 and avoid the influence of the exhaust flame.

[0023] Furthermore, the slider 5 is mounted on the electric guide rail 9.

[0024] During the insertion and removal process, the electric guide rail 9 starts synchronously. In coordination with the movement of the drone, the slider 5 moves under the action of the electric guide rail 9 and the connecting rod 4. The stroke of the electric guide rail 9 is long enough to allow the connector plug to rise to the highest position, above the hollow part, to prevent the switch baffle 7 from failing to close completely.

[0025] like Figure 5 The connector plug includes a fixing base 10, a plug 12, a spring 8, and a limiting pin 11; The top surface of the plug mounting base 3 is fixedly connected to the fixing base 10. The fixing base 10 has a hollow structure. The plug 12 is slidably disposed in the hollow structure. The bottom of the plug 12 protrudes from the fixing base 10 and is used to connect to the connector. The side of the plug 12 is fixedly connected to the limiting pin 11. The side of the fixing base 10 is provided with a notch for the limiting pin 11 to move. The limiting pin 11 is fixedly connected to the top of the spring 8. The bottom of the spring 8 is fixedly connected to the top surface of the plug mounting base 3.

[0026] The connector plug is a floating buffer type connector plug. The fixing base 10 provides radial limiting and sliding guidance for the plug 12, and the plug 12 can slide axially along the hollow structure of the fixing base 10. The spring 8 provides axial preload and buffer force for the plug 12. The preload during insertion can ensure that the plug 12 is tightly connected to the connector. Multiple springs 8 can be provided.

[0027] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Any modifications, alterations, substitutions, or variations made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A connector insertion / disconnection mechanism for rocket-launched unmanned aerial vehicles, characterized in that, It includes a housing (1), a four-bar linkage (2), and a connector plug; The box (1) is installed at the top inside the launch box, and the bottom of the box (1) is provided with a connector plug that can be inserted. The connector plug is used to connect to the connector of the UAV. The four-bar linkage (2) is installed inside the housing (1). The top of the connector plug is connected to the four-bar linkage (2). When the UAV is launched, the connector plug is pushed up by the movement of the four-bar linkage (2), thereby detaching from the connector.

2. The connector insertion / disconnection mechanism for a rocket-launched unmanned aerial vehicle according to claim 1, characterized in that, It also includes a plug mounting base (3), which is disposed inside the housing (1), on which the connector plug is mounted, and the plug mounting base (3) is connected to the four-bar linkage (2).

3. The coupling / disengagement mechanism for a rocket-launched unmanned aerial vehicle (UAV) connector according to claim 2, characterized in that, The four-bar linkage (2) includes four parallel rods, the tops of the four rods are rotatably connected to the top of the box (1), and the bottoms of the four rods are rotatably connected to the plug mounting base (3).

4. The unplugging / plugging mechanism for a rocket-launched unmanned aerial vehicle connector according to claim 2, characterized in that, The bottom of the housing (1) is provided with a hollow portion for the connector plug to move through, and the connector plug passes through the hollow portion.

5. The connector de-energizing mechanism for rocket-launched unmanned aerial vehicles according to claim 2, characterized in that, It also includes a connecting rod (4), a slider (5), a push rod (6), and a switch baffle (7); One end of the plug mounting base (3) is rotatably connected to one end of the connecting rod (4), and the other end of the connecting rod (4) is movably connected to the slider (5). The slider (5) is slidably connected to the bottom of the box (1). The slider (5) is rotatably connected to one end of the two push rods (6), the other end of the two push rods (6) is rotatably connected to one end of the two switch baffles (7), and the other end of the two switch baffles (7) is rotatably connected to the bottom of the box (1). When the plug mounting base (3) moves, it pushes the slider (5) to move through the connecting rod (4). The slider (5) is used to push the two push rods (6) to rotate when it moves, so that the two switch baffles (7) close or open. When the two switch baffles (7) are closed, they block the hollow part. When the two switch baffles (7) are open, they open the hollow part.

6. The connector de-energizing mechanism for rocket-launched unmanned aerial vehicles according to claim 5, characterized in that, The slider (5) is mounted on the electric guide rail (9).

7. The connector insertion / disconnection mechanism for a rocket-launched unmanned aerial vehicle according to claim 2, characterized in that, The connector plug includes a fixing base (10), a plug (12), a spring (8), and a limiting pin (11). The top surface of the plug mounting base (3) is fixedly connected to the fixing base (10). The fixing base (10) is a hollow structure. The plug (12) is slidably disposed in the hollow structure. The bottom of the plug (12) protrudes from the fixing base (10) and is used to connect to the connector. The side of the plug (12) is fixedly connected to the limiting pin (11). The side of the fixing base (10) is provided with a notch for the limiting pin (11) to move. The limiting pin (11) is fixedly connected to the top of the spring (8). The bottom of the spring (8) is fixedly connected to the top surface of the plug mounting base (3).

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