A one-way partition igniter for arming and igniting the base fuze of a single-soldier rocket

Abstract

The present invention discloses a one-way partition igniter for arming the base fuze of a single-soldier rocket projectile. Based on the original product design, the present invention modifies the bottom structural design of the nozzle component, adding a first boss and a second boss at the center of the blind hole at the bottom and upper surface of the nozzle, respectively. A less sensitive donor charge and a more sensitive acceptor charge are placed in the blind holes of the two bosses, respectively. High-temperature, high-pressure gas in the nozzle cavity ignites the donor charge, causing it to ignite and explode, generating a detonation wave. While the partition remains structurally intact, the wave penetrates the partition and triggers the acceptor charge, generating a weak detonation output, completing the ignition function required to arm the second safety of the base fuze facing it. Through the integrated design of the nozzle and partition, the present invention eliminates the potential risk of chamber or ballistic explosion caused by high-pressure gas from the rocket combustion chamber being introduced into the fuze cavity as a first arming environment, which could then act on the base fuze if a reliable seal is not ensured.

Description

Technical Field

[0001] The invention belongs to the field of pyrotechnics, and in particular relates to a one-way partition igniter for arming and igniting the base fuze of an individual rocket. Background Art

[0002] Individual rockets and mortar shells do not rotate, and their armor-piercing projectile base fuzes only have a recoil overload environment that can be used as a safety arming environment, making it difficult to meet redundant safety requirements. Some products have introduced high-pressure gas from the propellant or rocket combustion chamber directly into the inner cavity of the base fuze, resulting in over-bore or ballistic explosions due to unreliable sealing. Patent CN108613598A proposes a design solution using piezoelectric push-push technology to solve the problem of transmitting base pressure information to the fuze when the base structure is sealed. Diaphragm igniters are widely used in the aerospace field, but they are large in size and cannot guarantee that ignition will not be transmitted in the reverse direction. Therefore, there is a possibility that the overly sensitive diaphragm igniter charge may accidentally trigger the premature explosion of in-line charges such as rocket engine propellant or artillery shell propellant. Summary of the Invention

[0003] The present invention aims to provide a one-way diaphragm igniter for arming the base fuzes of individual rockets, missiles, and mortars. This provides an independent arming condition for the base fuzes of non-rotating projectiles such as individual rockets, missiles, and mortars, while also preventing the diaphragm igniter from accidentally firing and causing safety hazards. The present invention is also applicable to other non-rotating projectiles, providing a second arming condition for the base fuzes.

[0004] The technical solution for achieving the objectives of the present invention is: a one-way partition igniter for igniting the base fuze of an individual rocket projectile to arm the safety, comprising a base fuze, a projectile body, a paper gasket, a washer, an acceptor charge, a nozzle, a donor charge, rocket charge, and a combustion chamber. Based on the original or classic product design, the bottom structural design of the nozzle parts can be changed, and a first boss and a second boss are respectively added at the bottom and top centers of the middle partition of the nozzle. Insensitive donor charges of boron / potassium nitrate and more sensitive acceptor charges of lead nitride are respectively disposed in the blind holes of the two bosses. The donor charge of boron / potassium nitrate is ignited by high-temperature and high-pressure gas in the nozzle cavity, causing the donor charge to ignite and explode, generating a detonation wave. While the partition remains structurally intact, the donor charge penetrates the partition and triggers the acceptor charge of lead nitride, generating a weak detonation output, thereby completing the ignition function required to arm the second safety of the base fuze directly facing the corresponding one.

[0005] Compared with the prior art, the present invention has the following significant advantages: by changing the bottom structural design of the existing nozzle parts, the nozzle and the baffle body are integrated, so that the base fuze of non-rotating projectiles such as individual rockets, missiles and mortar shells can obtain an independent, safe and reliable safety arming environment, while also preventing the safety hazard of premature explosion caused by accidental ignition of the baffle igniter itself. The integrated design of the nozzle and the baffle body eliminates the connection between the baffle igniter body and the nozzle body, avoiding the safety problem of chamber explosion or ballistic explosion caused by the failure of the seal of the connection, which allows the high-temperature and high-pressure gas of the rocket engine combustion chamber or the propellant to penetrate into the fuze cavity and the warhead charge chamber.

[0006] The present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 The present invention is an axial cross-sectional view of a one-way partition igniter used for arming and igniting the base fuze of an individual rocket.

[0008] In the figure, 1 is the base fuze, 2 is the projectile body, 3 is the paper gasket, 4 is the gasket, 5 is the acceptor charge, 6 is the nozzle, 7 is the donor charge, 8 is the rocket charge, and 9 is the combustion chamber. DETAILED DESCRIPTION

[0009] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0010] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0011] In addition, the terms "first," "second," and so on, used in this disclosure are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, features specified as "first" or "second" may explicitly or implicitly include at least one of these features.

[0012] In the present invention, unless otherwise specified or limited, the terms "connection" and "fixation" should be understood in a broad sense. For example, "fixation" can refer to fixed connection, detachable connection, or integration; "connection" can refer to mechanical connection or electrical connection. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0013] The following will further introduce the specific implementation methods, as well as the technical difficulties and inventive points of this invention in combination with this design example.

[0014] Combine Figure 1 A one-way partition igniter for arming the base fuze of an individual rocket comprises a base fuze 1, a projectile body 2, a paper gasket 3, a gasket 4, an acceptor charge 5, a nozzle 6, a donor charge 7, a rocket charge 8, and a combustion chamber 9. The base fuze 1, nozzle 6, and combustion chamber 9 are arranged coaxially from top to bottom. The base fuze 1 is placed in the cavity of the projectile 2, and its bottom receives flame input; the upper and lower ends of the nozzle 6 are screwed to the projectile 2 and the combustion chamber 9 respectively, and the longitudinal section of the nozzle 6 is "H"-shaped. A first boss is provided at the center of the bottom surface of the middle partition of the nozzle 6, and a first blind hole is opened from bottom to top on the first boss. The donor charge 7 is arranged in the first blind hole. A second boss is provided at the center of the top surface of the middle partition of the nozzle 6, and a second blind hole is opened from top to bottom on the second boss. The acceptor charge 5 is arranged in the second blind hole; an annular groove is formed between the second boss and the top surface of the nozzle 6, the gasket 4 is located in the annular groove on the top surface of the nozzle 6, and the paper gasket 3 is placed at the bottom of the base fuze 1; the tubular rocket charge 8 is arranged on the inner wall surface of the combustion chamber 9, so that a cylindrical cavity is formed in the center of the combustion chamber 9.

[0015] Furthermore, the nozzle 6 has an H-shaped longitudinal section, the first boss is higher than the second boss, the first boss is 2-6 mm high, the second boss is 0.5-1.5 mm high, and the outer diameters of the first and second bosses are both 5-15 mm.

[0016] Furthermore, the thickness of the partition between the first blind hole and the second blind hole is 0.5-1.5 mm, and the diameters of the first blind hole and the second blind hole are both 4-14 mm.

[0017] Furthermore, the depths of the first blind hole and the second blind hole are both 1-3 mm, the shelled donor charge 7 just fills the first blind hole, and the shelled acceptor charge 5 just fills the second blind hole.

[0018] Furthermore, the donor charge 7 is an insensitive low-power explosive agent with a sensitivity no higher than tetryl, which allows for in-line use and ensures safety.

[0019] Furthermore, the donor charge 7 is boron / potassium nitrate ignition powder.

[0020] Furthermore, the acceptor charge 5 is a sensitive detonator with high detonation sensitivity and is easily triggered.

[0021] Furthermore, the acceptor charge 5 is lead nitride or a mixed explosive based on lead nitride.

[0022] Furthermore, the nozzle 6 serves as the main body of the partition igniter structure, that is, the partition igniter body and the nozzle 6 adopt an integrated structural design.

[0023] The working process of the one-way partition igniter: Assuming the safety of the rocket engine charge and its ignition system is guaranteed (not the main content of this invention), during launch, the rocket engine is operating, and the nozzle 6 cavity generates high-temperature and high-pressure gas, which in turn ignites the donor charge 7. The donor charge 7 ignites and explodes, generating a detonation wave. Assuming the partition remains structurally intact, the donor charge 7 penetrates the partition and triggers the lead nitride in the acceptor charge 5, producing a weak detonation output, completing the ignition function required to release the secondary safety of the base fuze 1 directly opposite it, such as igniting the relay tube at the bottom of the fuze. The boron / potassium nitrate in the donor charge 7 is sufficiently insensitive that it is generally believed to have no possibility of accidental ignition and explosion. While the lead nitride in the acceptor charge 5 is relatively sensitive, its accidental ignition is not sufficient to reversely trigger the less sensitive donor charge 7, the boron / potassium nitrate in the donor charge 7, achieving the one-way ignition function. The base fuze 1 is a flameproof fuze. Even if accidentally ignited by the acceptor charge 5, there will be no explosion or dangerous fragmentation output, thus ensuring the safety of the engine charge system and warhead.

Claims

1. A one-way partition igniter for arming the base fuze of a rocket projectile, characterized by: The invention comprises a base fuze (1), a projectile (2), a paper gasket (3), a gasket (4), an acceptor charge (5), a nozzle (6), a donor charge (7), a rocket charge (8), and a combustion chamber (9); the base fuze (1), the nozzle (6), and the combustion chamber (9) are coaxially arranged from top to bottom, the base fuze (1) is placed in the cavity of the projectile (2), and the bottom of the nozzle (6) receives the flame input; the upper end and the lower end of the nozzle (6) are respectively screwed to the projectile (2) and the combustion chamber (9); the longitudinal section of the nozzle (6) is "H" shaped, and the center of the bottom surface of the middle partition of the nozzle (6) is A first boss is provided, the first boss has a first blind hole from bottom to top, a donor charge (7) is arranged in the first blind hole, a second boss is provided at the center of the top surface of the middle partition of the nozzle (6), the second boss has a second blind hole from top to bottom, and a recipient charge (5) is arranged in the second blind hole; an annular groove is formed between the second boss and the top surface of the nozzle (6), a gasket (4) is located in the annular groove of the top surface of the nozzle (6), and a paper gasket (3) is placed at the bottom of the base fuze (1); a cylindrical rocket charge (8) is arranged on the inner wall surface of the combustion chamber (9), so that a cylindrical cavity is formed in the center of the combustion chamber (9).

2. The one-way partition igniter for arming the base fuze of a rocket projectile according to claim 1, characterized in that: The height of the first boss of the nozzle (6) is higher than that of the second boss, the height of the first boss is 2 to 6 mm; the height of the second boss is 0.5 to 1.5 mm; and the outer diameters of the first boss and the second boss are both 5 to 15 mm.

3. The one-way partition igniter for arming the base fuze of an individual rocket according to claim 2, characterized in that: The thickness of the partition between the first blind hole and the second blind hole is 0.5-1.5 mm, and the diameters of the first blind hole and the second blind hole are both 4-14 mm.

4. The one-way partition igniter for arming the base fuze of an individual rocket according to claim 3, characterized in that: The depths of the first blind hole and the second blind hole are both 1 to 3 mm. The donor charge (7) with a shell just fills the first blind hole, and the acceptor charge (5) with a shell just fills the second blind hole.

5. The one-way partition igniter for arming the base fuze of a rocket projectile according to claim 1, characterized in that: The donor charge (7) is an insensitive low-power explosive agent with a sensitivity not higher than that of tetryl, which allows for in-line use and ensures safety.

6. The one-way partition igniter for arming the base fuze of a rocket projectile according to claim 5, characterized in that: The donor charge (7) is a boron / potassium nitrate ignition charge.

7. The one-way partition igniter for arming the base fuze of an individual rocket according to claim 1, characterized in that: The acceptor charge (5) is a sensitive detonator with high detonation sensitivity and is easily triggered.

8. The one-way partition igniter for arming the base fuze of a rocket projectile according to claim 7, characterized in that: The acceptor charge (5) is lead nitride or a mixed explosive based on lead nitride.

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