Anti-unmanned aerial vehicle rocket engine secondary ignition system
Through the design of the secondary ignition system of the rocket engine, the combined ignition method of primary and secondary ignition is used to solve the problem of insufficient flight distance in the existing technology, and the effective interception ability at a relatively high distance is achieved. Simple and reliable structure.
Patent Information
- Application Number
- CN202421334115.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-12
- Publication Date
- 2025-01-10
- Estimated Expiration
- 2034-06-12
AI Technical Summary
Existing anti-drone rocket engines lack flight distances at higher and longer distances, making it difficult to effectively intercept targets.
The rocket engine's secondary ignition system is adopted, through a combination of primary ignition and secondary ignition, and the sliding piston and resin support are used to achieve step by step ignition of rocket propellant and extend the rocket's flight distance.
It effectively improves the flight distance of the rocket, enhances its interception ability when hitting far and higher targets, and has a simple and reliable structure.
Smart Images
Figure CN222333914U_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of anti-UAV technology, and in particular to a two-stage ignition system for an anti-UAV rocket engine. Background Art
[0002] With the development of science and technology, drones have been widely used in various occasions in life, but in some cases the use of drones will affect public safety. In addition, drones have been used in large numbers in modern wars and have caused considerable losses. Therefore, a large number of scientific researchers have gradually shifted their attention to the research of anti-drone equipment.
[0003] Some researchers have applied rocket-related technologies to anti-UAV equipment, but there is still a gap in this research field. Existing research using rockets basically uses a rocket engine structure with one-stage ignition, but when the target is at a high and long distance, the flight distance of a rocket ignited once is not enough, making it difficult to intercept the target.
[0004] Therefore, in order to increase the flight distance of the rocket, combined with the structural characteristics of the rocket engine, the utility model provides an anti-UAV rocket engine two-stage ignition system. Utility Model Content
[0005] In order to improve the problem of insufficient interception distance, the present application provides an anti-UAV rocket engine two-stage ignition system.
[0006] The present application provides an anti-UAV rocket engine two-stage ignition system that adopts the following technical solution:
[0007] A two-stage ignition system for an anti-UAV rocket engine, characterized in that it includes a launch chamber, a rocket body, a body functional chamber, a sliding piston, a resin support, and a sabot; wherein the rocket body is installed in the launch chamber, the body functional chamber is connected to the bottom of the rocket body, the sabot is connected to the launch chamber and is located below the body functional chamber, a primary primer is arranged in the sabot, a secondary primer is arranged in the body functional chamber, the sliding piston and the resin support are arranged in the body functional chamber, the sliding piston can slide relative to the body functional chamber, a piston propellant is arranged between the sliding piston and the primary primer, the resin support is located between the sliding piston and the secondary primer, the rocket body is provided with a rocket propellant, the rocket propellant is arranged close to the secondary primer, and a guide hole is opened on the sabot for a firing pin to pass through and contact the primary primer.
[0008] Optionally, the rocket body functional compartment is connected to the rocket body by threads.
[0009] Optionally, a copper cap for a primary primer and a lower ignition platform are provided in the cartridge case, the primary primer is installed in the copper cap for the primary primer, and one end of the lower ignition platform extends into the copper cap for the primary primer to press the primary primer.
[0010] Optionally, the lower ignition platform is threadedly connected to the spring support.
[0011] Optionally, the arrow body functional compartment is equipped with an upper ignition platform and a secondary primer copper cap, the secondary primer is installed in the secondary primer copper cap, and one end of the upper ignition platform extends into the secondary primer copper cap to press the secondary primer.
[0012] Optionally, the upper ignition platform is functionally threadedly connected to the arrow body.
[0013] When the firing pin hits the copper cap for the primary primer and ignites the primary primer of the primary ignition system, it ignites the piston propellant in the secondary ignition system. The piston propellant provides thrust for the sliding piston so that the rocket can achieve a certain distance of sliding segment. While the rocket is gliding, the front end of the sliding piston hits the copper cap for the secondary primer of the secondary ignition system, igniting the secondary primer and igniting the rocket propellant to make it fly.
[0014] To sum up, the present application includes at least one of the following beneficial technical effects: the anti-UAV rocket engine two-stage ignition system proposed in the utility model can save rocket energy, effectively increase the flight distance of the rocket, and has a more positive effect in attacking and intercepting higher and longer-distance targets. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 This is a schematic diagram of the overall structure of a two-stage ignition system for an anti-UAV rocket engine according to the utility model;
[0016] Figure 2 This is a cross-sectional view of the overall installation structure of a second-stage ignition system for an anti-UAV rocket engine of the utility model;
[0017] Figure 3 It is a partial cross-sectional view of the internal installation structure of a secondary ignition system of an anti-UAV rocket engine of the utility model;
[0018] Figure 4 This is a cross-sectional view of the overall structure of a two-stage ignition system for an anti-UAV rocket engine after the first stage ignition of the utility model;
[0019] Figure 5 This is a cross-sectional view of the parts of the rocket body functional compartment of the secondary ignition system of an anti-UAV rocket engine of the utility model;
[0020] Reference numerals:
[0021] 1. Rocket body; 2. Copper cap for secondary primer; 31. Primary primer; 32. Secondary primer; 41. Lower ignition platform; 42. Upper ignition platform; 5. Rocket body functional compartment; 51. First connecting part; 52. First annular step; 53. Second connecting part; 54. Second annular step; 55. Inner cavity; 6. Resin support; 7. Sliding piston; 8. Butt support; 9. Copper cap for primary primer; 10. Piston propellant; 11. Firing pin; 12. Launch compartment; 13. Rocket propellant. DETAILED DESCRIPTION
[0022] The following is combined with Figure 1-5 This application is described in further detail.
[0023] See also Figure 1 and Figure 2 A secondary ignition system for an anti-UAV rocket engine includes a rocket body 1, a copper cap for a secondary primer 2, a primer 3, a ignition platform 4, a body functional compartment 5, a resin support 6, a sliding piston 7, a sabot 8, a copper cap for a primary primer 9, a piston propellant 10, a firing pin 11, a launch compartment 12, and a rocket propellant 13. The interior of the rocket body 1 is a cavity structure, and the bottom is open. An internal thread is provided at the bottom opening position, and one end of the body functional compartment 5 extends through the opening into the cavity and is threadedly connected to the rocket body 1 and closes the opening. The rocket propellant 13 is installed in the cavity of the rocket body 1.
[0024] The body functional compartment 5 is threadedly connected to the rocket body 1. Specifically, the body functional compartment 5 includes a first connecting portion 51, a first annular step 52, a second connecting portion 53 and a second annular step 54 fixed in sequence, wherein the outer wall of the first connecting portion 51 is provided with an external thread, which cooperates with the internal thread at the opening. The first annular step 52 abuts against the bottom of the rocket body 1. The body functional compartment 5 has an inner cavity 55 with two ends through, and the inner cavity 55 is a stepped cylindrical cavity.
[0025] The rocket body 1 is located in the launch chamber 12, the sabot 8 is fixedly connected to the flange edge at the bottom of the launch chamber 12, the front end boss of the sabot 8 is embedded in the rocket body functional chamber 5, and a guide hole is opened in the center of the sabot 8, and the guide hole also has a stepped hole structure.
[0026] See also Figure 3 The primary primer 31 in the primary ignition system is installed in the copper cap 9 for the primary primer, and the copper cap 9 for the primary primer 31 is installed in the countersunk hole of the sabot 8. The lower ignition platform 41 is connected to the sabot 8 by threads, and one end of the lower ignition platform 41 presses the primary primer 31. Specifically, the lower ignition platform 41 has a central hole, an external thread is opened on the side wall, and an internal thread is opened on one end of the guide hole close to the rocket body 1, so that the lower ignition platform 41 is threadedly connected to the sabot 8.
[0027] See also Figure 3 , Figure 4 and Figure 5 The secondary primer 32 in the secondary ignition system is installed in the secondary primer copper cap 2, and the secondary primer copper cap 2 is installed in the inner cavity of the arrow body functional compartment 5. The upper ignition platform 42 is connected to the arrow body functional compartment 5 through a thread. The specific connection method can refer to the connection between the lower ignition platform 41 and the cartridge case 8.
[0028] When the firing pin 11 hits into the copper cap 9 for the primary primer through the guide hole at the rear side of the cartridge case 8, the primary primer 31 is ignited, and the piston propellant 10 is ignited through the central through hole of the lower ignition platform 41.
[0029] The piston propellant 10 is installed in the cavity of the sliding piston 7, and the sliding piston 7 is installed in the inner cavity of the rocket body functional chamber 5, and its rear end face is against the front end face of the boss of the cartridge case 8. The resin support 6 is installed at the front end of the sliding piston 7, which plays the role of installing the resin support 6 and providing a certain movement stroke for the sliding piston 7. The resin support 6 is similar to a cylindrical structure with two ends through. When the piston propellant 10 is ignited, the rocket as a whole will slide forward a certain distance by the impact force to separate from the launch chamber 12 and the cartridge case 8. At the same time, the sliding piston 7 is impacted and crushes the resin support 6 forward. The front end boss of the sliding piston 7 hits the copper cap 2 for the secondary primer, ignites the secondary primer 32, and ignites the rocket propellant 13 through the central through hole of the ignition table 4, and the rocket obtains the flight power.
[0030] The anti-UAV rocket engine two-stage ignition system proposed in the utility model can effectively increase the flight distance of the rocket, while also having the advantages of a simple and reliable rocket engine structure, and has a very positive effect when attacking and intercepting targets that are farther and higher.
[0031] In the description of the present utility model, it should be understood that the terms "upper", "lower", "left", "right", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, as well as a specific direction structure and operation, and therefore, cannot be understood as a limitation on the present utility model. 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 utility model, unless otherwise specified, "multiple" means two or more.
[0032] 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 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.
[0033] The above description is only an embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made by using the contents of the specification and drawings of the present invention, 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 two-stage ignition system for an anti-UAV rocket engine, characterized in that: The invention comprises a launching chamber (12), a rocket body (1), a body functional chamber (5), a sliding piston (7), a resin support (6), and a sabot (8); wherein the rocket body (1) is installed in the launching chamber (12), the body functional chamber (5) is connected to the bottom of the rocket body (1), the sabot (8) is connected to the launching chamber (12) and is located below the body functional chamber (5), a primary primer (31) is arranged in the sabot (8), a secondary primer (32) is arranged in the body functional chamber (5), the sliding piston (7) and the resin support (6) is arranged in the rocket body functional chamber (5), the sliding piston (7) can slide relative to the rocket body functional chamber (5), a piston propellant (10) is arranged between the sliding piston (7) and the primary primer (31), the resin support (6) is located between the sliding piston (7) and the secondary primer (32), the rocket body (1) is provided with a rocket propellant (13), the rocket propellant (13) is arranged close to the secondary primer (32), and the cartridge case (8) is provided with a guide hole for the firing pin (11) to pass through and contact the primary primer (31).
2. The anti-UAV rocket engine two-stage ignition system according to claim 1, characterized in that: The rocket body functional compartment (5) is connected to the rocket body (1) via threads.
3. The anti-UAV rocket engine two-stage ignition system according to claim 1 is characterized in that: A copper cap for a primary primer (9) and a lower ignition platform (41) are arranged in the cartridge holder (8); the primary primer (31) is installed in the copper cap for the primary primer (9); one end of the lower ignition platform (41) extends into the copper cap for the primary primer (9) to press the primary primer (31).
4. The anti-UAV rocket engine two-stage ignition system according to claim 3 is characterized in that: The lower ignition platform (41) is threadedly connected to the spring support (8).
5. The anti-UAV rocket engine two-stage ignition system according to claim 1 is characterized in that: The arrow body functional chamber (5) is equipped with an upper ignition platform (42) and a secondary primer copper cap (2), the secondary primer (32) is installed in the secondary primer copper cap (2), and one end of the upper ignition platform (42) extends into the secondary primer copper cap (2) to press the secondary primer (32).
6. The anti-UAV rocket engine two-stage ignition system according to claim 5, characterized in that: The upper ignition platform (42) is threadedly connected to the arrow body functional compartment (5).