Rocket tail traction movable structure applied to anti-unmanned aerial vehicle

Abstract

The utility model relates to the technical field of anti-unmanned aerial vehicles, and particularly discloses a rocket tail traction movable structure applied to anti-unmanned aerial vehicles, which comprises a rocket body, a rocket engine, an engine base, an ignition head, an electronic igniter, a movable traction hanging ring and a traction rope, the rocket engine is installed in the engine base, the ignition head is installed in the rocket engine and controlled by the electronic igniter, a groove is formed in the engine base, the movable traction hanging ring is rotatably installed in the groove, and the traction rope is connected with the movable traction hanging ring. The rocket can have the stable traction function, the requirement for the thrust and guidance capacity of the rocket is small, the safety and reliability of rocket operation are high, the rocket can efficiently complete traction operation, and the task of intercepting the unmanned aerial vehicle is completed.

Description

Technical Field

[0001] The present application relates to the technical field of anti-UAV, and in particular to a rocket tail traction movable structure used for anti-UAV. Background Art

[0002] With the development of related hardware and software, drone technology has been widely used in transportation, observation and other aspects, and illegal flights have occurred frequently; drones have also appeared in large numbers on the battlefield, and anti-drone technology has become a popular research direction.

[0003] Anti-UAV technology mainly consists of non-contact radio interference and contact mechanical attack. In the contact type, anti-UAV capture net technology often uses drones to drag, which has a small interception area and a low success rate; and uses rockets to tow the capture net to intercept the target drone over a large area.

[0004] The military anti-UAV hose-towing rocket-driven capture net interception technology uses side traction and a fixed structure, which will have a significant impact on the rocket guidance accuracy. The rocket has high thrust and high-precision self-stabilizing guidance requirements, and is prone to loss of control during flight, making the anti-UAV operation ineffective. The pilot rocket traction structure is complex and has a high failure rate.

[0005] Therefore, in order to solve the above problems, it is necessary to provide a rocket tail traction activity structure used for anti-UAV, which can stably tow the capture net while stabilizing the flight to complete the task of capturing the UAV. Utility Model Content

[0006] In order to improve the problem of complex structure, the present application provides a rocket tail traction movable structure used for anti-UAV.

[0007] The present application provides a rocket tail traction movable structure for anti-UAV use, which adopts the following technical solution:

[0008] A rocket tail traction movable structure used for anti-UAV, characterized in that it includes a rocket body, a rocket engine, an engine base, an ignition head, an electronic igniter, a movable traction ring, and a traction rope, wherein the engine base is fixed on the rocket body, the rocket engine is installed in the engine base, the ignition head is installed in the rocket engine and controlled by the electronic igniter, the engine base is provided with a groove, the movable traction ring is rotatably installed in the groove, and the traction rope is connected to the movable traction ring.

[0009] Optionally, the engine base is provided with a notch, the notch is communicated with the groove, and the traction rope is connected to the traction object after passing through the notch.

[0010] Optionally, the rocket body is hollow inside and has an internal thread, and the engine base has an external thread which is threadably connected to the rocket body.

[0011] Optionally, a pin hole is provided on the engine base, and a cylindrical pin is installed on the movable traction lifting ring. The cylindrical pin is inserted into the pin hole and rotates to cooperate with the pin hole.

[0012] Optionally, the engine base has a mounting cavity, and the rocket engine is embedded in the mounting cavity of the engine base.

[0013] Optionally, the length of the rocket engine is the same as the length of the mounting cavity of the engine base.

[0014] In summary, the present application includes at least one of the following beneficial technical effects: (1) The utility model can enable the rocket to have a stable traction function, has a simple structure, and is easy to produce and install.

[0015] (2) The movable traction lifting ring of the utility model has low requirements on rocket thrust and guidance capabilities and has wide applicability.

[0016] (3) The utility model discloses a rocket tail traction movable structure for anti-UAV, wherein the movable traction ring is hidden in the groove of the engine base, and the traction rope is arranged in the notch of the groove, which saves space and launch quality and does not affect the normal launch of the rocket. The safety and reliability of rocket operation are improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is an overall schematic diagram of a rocket tail traction activity structure used for anti-UAV in the utility model;

[0018] Figure 2 This is a cross-sectional view of a rocket tail traction activity structure used for anti-UAV in the utility model;

[0019] Figure 3 This is a bottom view of a rocket tail traction movable structure used for anti-UAV in the utility model;

[0020] Figure 4 This is a schematic diagram of an engine base of a rocket tail traction movable structure used for anti-UAV in the utility model;

[0021] Figure 5 The utility model is a schematic diagram of an active traction ring of a rocket tail traction active structure used for anti-UAV.

[0022] Figure numerals: 1. rocket body; 2. tail fin stabilizing rudder; 3. rocket engine; 4. engine base; 41. first seat body; 42. second seat body; 421. groove; 422. pin hole; 423. notch; 5. ignition head; 6. electronic igniter; 7. movable traction ring; 8. cylindrical pin; 9. traction rope; 10. traction object. DETAILED DESCRIPTION

[0023] The following is combined with Figure 1-5 This application is described in further detail.

[0024] A rocket tail traction movable structure used for anti-UAV, such as Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, it includes a rocket body 1, a tail stabilizing rudder 2, a rocket engine 3, an engine base 4, an ignition head 5, an electronic igniter control 6, a movable traction ring 7, a cylindrical pin 8, a traction rope 9 and a traction object 10.

[0025] like Figure 1 As shown, the rocket body 1 is fixedly connected to the tail stabilizing rudder 2. The bottom of the rocket body 1 is hollow and has an internal thread, such as Figure 2 and 4 As shown, the engine base 4 includes a first base body 41 and a second base body 42, the first base body 41 and the second base body 42 are integrally formed, and the outer diameter of the first base body 41 is smaller than the outer diameter of the second base body 42. The side wall of the first base body 41 is provided with an external thread, the engine base 4 is threadedly connected to the rocket body 1 through the first base body 41, and the second base body 42 is located outside the rocket body 1 and abuts against the end of the rocket body 1. The engine base 4 has an installation cavity, and the installation cavity extends from the end surface of the second base body 42 to the first base body 41 but does not penetrate the first base body 41. The rocket engine 3 is embedded in the installation cavity of the engine base 4, and the length of the rocket engine 3 is the same as the length of the installation cavity of the engine base 4.

[0026] The rocket engine 3 is provided with an ignition chamber, and the ignition head 5 penetrates into the ignition chamber of the rocket engine 3. A groove 421 is provided at the bottom of the second base 42, and the groove 421 is an annular groove, and a notch 423 is provided on the side wall of the second base 42, and the notch 423 is connected with the groove 421. The movable traction ring 7 is placed in the groove 421, and cylindrical pins 8 are fixedly installed at both ends of the movable traction ring 7, and a pin hole 422 corresponding to the cylindrical pin 8 is provided on the second base 42, and the cylindrical pin 8 is inserted into the pin hole 422 so that the movable traction ring 7 can rotate around the cylindrical pin 8. The traction rope 9 is hung on the movable traction ring 7, extends through the notch 423, and is connected to the traction object 10.

[0027] The electronic igniter 6 is electrically connected or signal-connected to the ignition head. When the rocket is working, the electronic igniter 6 sends an ignition signal, the ignition head 5 is excited, the rocket engine 2 is operated, and the rocket is launched.

[0028] The implementation principle of the rocket tail traction movable structure used for anti-UAV in the embodiment of the present application is as follows: the movable traction ring 7 and the cylindrical pin 8 are rotatable, and the movable traction ring 7 rotates around the cylindrical pin 8 under the action of the traction rope 9 and comes out of the groove of the engine base 4. The traction rope 9 naturally keeps consistent with the pressure center of the rocket engine 3 nozzle under the action of thrust and gravity. After a certain period of launch, the traction work of the traction object 10 is completed. The structure is simple and the traction is stable.

[0029] In the description of the present invention, it should be understood that the terms "upper", "lower", "left", "right", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, and a specific direction structure and operation, and therefore, cannot be understood as a limitation on the present invention. In addition, "first" and "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", etc. should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] The above descriptions are merely embodiments of the present invention and are not intended to limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made using the contents of the present invention specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A rocket tail traction movable structure used for anti-UAV, characterized by: The invention comprises a rocket body (1), a rocket engine (3), an engine base (4), an ignition head (5), an electronic igniter (6), a movable traction ring (7), and a traction rope (9), wherein the engine base (4) is fixed on the rocket body (1), the rocket engine (3) is installed in the engine base (4), the ignition head (5) is installed in the rocket engine (3) and is controlled by the electronic igniter (6), the engine base (4) is provided with a groove (421), the movable traction ring is rotatably installed in the groove (421), and the traction rope (9) is connected to the movable traction ring (7).

2. The rocket tail traction movable structure used for anti-UAV according to claim 1 is characterized in that: The engine base (4) is provided with a notch (423), the notch (423) is communicated with the groove (421), and the traction rope (9) is connected to the traction object (10) after passing through the notch (423).

3. The rocket tail traction movable structure used for anti-UAV according to claim 1 is characterized in that: The rocket body (1) is hollow inside and is provided with an internal thread, and the engine base (4) is provided with an external thread and is threadably connected to the rocket body (1).

4. The rocket tail traction movable structure used for anti-UAV according to claim 1 is characterized in that: The engine base (4) is provided with a pin hole (422), the movable traction lifting ring (7) is provided with a cylindrical pin (8), and the cylindrical pin (8) is inserted into the pin hole (422) and rotatably matched with the pin hole (422).

5. The rocket tail traction movable structure used for anti-UAV according to claim 1 is characterized in that: The engine base (4) has a mounting cavity therein, and the rocket engine (3) is embedded in the mounting cavity of the engine base (4).

6. The rocket tail traction movable structure used for anti-UAV according to claim 5 is characterized in that: The length of the rocket engine (3) is the same as the length of the installation cavity of the engine base (4).

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