Segmented self-destruction device for rocket engine

Abstract

The invention discloses a segmented self-destruction device for a rocket engine, and relates to the technical field of artificial precipitation hail suppression rockets. The segmented self-destruction device comprises a connecting ring, a casting barrel, a first self-destruction body, separation powder, a second self-destruction body and an engine igniter. The segmented self-destruction device is a rotary body with a hole in the middle. The first self-destruction body comprises a first self-destruction body end cover, a second self-destruction body end cover, a delay tube protective sleeve, a fire propagation delay tube, an explosion propagation delay tube and a self-destruction explosive; the second self-destruction body comprises a third self-destruction body end cover, a fourth self-destruction body end cover and self-destruction medicine; sealing rings are placed in grooves of the self-destruction body and the second self-destruction body, and then the grooves are stuffed into the casting cylinder; the segmented self-destruction device is adopted as the self-destruction device of the rain enhancement and hail suppression rocket, engine assemblies can be exploded into small fragments to fall on the ground through a special working mode of the segmented self-destruction device, the mass of the fragments is not larger than 100 g, all the assemblies can be self-destructed reliably, and damage of rocket body wreckage to personnel, buildings, farmlands, livestock and the like can be effectively reduced.

Description

Technical Field

[0001] The invention relates to the technical field of artificial rainfall enhancement and hail prevention rockets, in particular to a rocket engine segmented self-destruction device. Background Art

[0002] my country is a country with severe water shortage and frequent meteorological disasters. Artificial weather modification is one of the important means of disaster prevention and mitigation in meteorological science and technology. Rain-making and hail-prevention rockets have many advantages, such as large amount of catalyst, high nucleation rate, high launch altitude, and easy operation. Therefore, they have been rapidly promoted and applied throughout the country. The BL series rockets are typical representatives of traditional explosive self-destruction rain-making and hail-prevention rockets. The BL series rockets have three self-destruction bodies concentrated in the middle of the rocket body as a safe landing device. When the self-destruction device is working, the three self-destruction bodies move to the head, middle and tail of the rocket body respectively under the action of gunpowder gas, and then the pyrotechnics in the three self-destruction bodies explode simultaneously. Due to the reliability of the ignition mechanism and the residual powder in the solid propellant combustion, the three self-destruction bodies often hardly move or are hindered during the movement and cannot move to the predetermined position, resulting in the head and tail of the rocket body cannot be blown up and fall as large pieces of debris, causing damage to personnel, buildings, farmland, livestock, etc. Traditional explosive self-destructive rain-increasing and hail-prevention rockets use pyrotechnic delay tubes as delay devices. During the rocket launch phase, all pyrotechnic delay tubes are ignited at the same time, and different lengths of delay charges burn for different times to control the catalyst spreading and self-destruction time. Due to the influence of raw material production, processing technology, assembly process, etc., the delay time of the delay charge has a large deviation and is unreliable. At the same time, the three-stage self-destruction body serves as a safe landing device. When the self-destruction device is working, the three-stage self-destruction body moves to the head, middle and tail of the rocket body respectively under the action of gunpowder gas, and then the pyrotechnics in the three-stage self-destruction body explodes simultaneously. Due to the reliability of the ignition mechanism and the residual powder of the solid propellant burning, the three-stage self-destruction body often hardly moves or is hindered during the movement and cannot move to the predetermined position, resulting in the head and tail of the rocket body cannot be blown up and fall as large pieces of debris, causing damage to personnel, buildings, farmland, livestock, etc. In view of the above problems, the inventor proposes a rocket engine segmented self-destruction device to solve the above problems. Summary of the invention

[0003] In order to solve the above-mentioned problems, the object of the present invention is to provide a rocket engine segmented self-destruction device.

[0004] In order to solve the above technical problems, the present invention adopts the following technical solutions: a rocket engine segmented self-destruction device, the segmented self-destruction device comprises a connecting ring, a projectile tube, a first self-destruction body, a separation charge, a second self-destruction body and an engine ignition device, and the segmented self-destruction device is a rotating body with a hole in the middle; The first self-destruct body comprises a first self-destruct body end cover, a second self-destruct body end cover, a delay tube protective sleeve, a ignition delay tube, a detonation delay tube and a self-destruct charge; The second self-destruct body comprises a third self-destruct body end cap, a fourth self-destruct body end cap and a self-destruct medicine; Sealing rings are placed in the grooves of the first self-destruction body and the second self-destruction body and then inserted into the projectile tube.

[0005] Preferably, the first self-destruct body end cap, the second self-destruct body end cap, the third self-destruct body end cap and the fourth self-destruct body end cap are all connected to the first self-destruct body and the second self-destruct body by gluing.

[0006] Preferably, the segmented self-destruction device ignites the separation charge through the ignition delay tube to separate the first self-destruction body from the second self-destruction body, and places them at the front end and the rear end of the engine respectively. After a certain period of time, the first self-destruction body and the second self-destruction body are ignited through the explosion delay tube, and the first self-destruction body and the second self-destruction body explode the rocket engine to form fragments with a mass not exceeding 100g.

[0007] Preferably, an isolation sheathing pad is glued to one end of the engine ignition tool close to the fourth self-destruct body end cover, and a rubber elastic pad is glued to one end of the engine ignition tool away from the fourth self-destruct body end cover, and the rubber elastic pad fixes the wire of the engine ignition tool passing through the central through hole.

[0008] Preferably, the ignition delay tube and the detonation delay tube are both designed to be redundant.

[0009] Compared with the prior art, the present invention has the following beneficial effects: In the present invention, a segmented self-destruction device is adopted as a self-destruction device for a rain-enhancing and hail-preventing rocket. Through its special working mode, the engine components can be exploded into small fragments that fall to the ground, and the mass of the fragments is no more than 100g. Each component can self-destruct reliably, and the damage caused by the rocket body debris to personnel, buildings, farmland, livestock, etc. can be effectively reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0011] Figure 1 It is a schematic diagram of the structure of the present invention.

[0012] In the figure: 1, first self-destruct body end cover; 2, ejection tube; 3, first self-destruct body; 4, second self-destruct body end cover; 5, separation charge; 6, third self-destruct body end cover; 7, second self-destruct body; 8, fourth self-destruct body end cover; 9, isolation coating pad; 10, engine ignition device; 11, rubber spring pad; 12, connecting ring; 13, sealing ring; 14, delay tube protective sleeve; 15, ignition delay tube; 16, explosion delay tube. DETAILED DESCRIPTION

[0013] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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.

[0014] Example: Figure 1 As shown, the present invention provides a rocket engine segmented self-destruction device, which includes a connecting ring 12, a projectile tube 2, a first self-destruction body 3, a separation charge 5, a second self-destruction body 7 and an engine ignition device 10. The segmented self-destruction device is a rotating body with a hole in the middle; The first self-destruct body 3 includes a first self-destruct body end cover 1, a second self-destruct body end cover 4, a delay tube protective sleeve 14, a fire transmission delay tube 15, a detonation transmission delay tube 16 and a self-destruct charge; The second self-destruct body 7 includes a third self-destruct body end cap 6, a fourth self-destruct body end cap 8 and a self-destruct medicine; The sealing rings 13 are placed in the grooves of the first self-destruction body 3 and the second self-destruction body 7 and then inserted into the projectile tube 2.

[0015] The first self-destruct body end cover 1 , the second self-destruct body end cover 4 , the third self-destruct body end cover 6 and the fourth self-destruct body end cover 8 are all connected to the first self-destruct body 3 and the second self-destruct body 7 by gluing.

[0016] The segmented self-destruction device ignites the separation charge 5 through the ignition delay tube 15, separates the first self-destruction body 3 from the second self-destruction body 7, and places them at the front end and the rear end of the engine respectively. After a certain period of time, the first self-destruction body 3 and the second self-destruction body 7 are ignited through the explosion delay tube 16, and the first self-destruction body 3 and the second self-destruction body 7 explode the rocket engine to form fragments with a mass not greater than 100g.

[0017] An isolation covering pad 9 is glued to one end of the engine ignition device 10 close to the fourth self-destruct body end cover 8, and a rubber elastic pad 11 is glued to one end of the engine ignition device 10 away from the fourth self-destruct body end cover 8. The rubber elastic pad 11 fixes the wire of the engine ignition device 10 passing through the central through hole.

[0018] The ignition delay tube 15 and the explosion delay tube 16 are both designed to be redundant.

[0019] Working principle: When in use, first, the self-destruct body ejection ignition device ejects the segmented self-destruct device to the tail section of the engine, and then the fire transmission delay tube 15 works. After a certain delay time, the separation charge 5 is ignited to separate the first self-destruct body 3 from the second self-destruct body 7. The first self-destruct body 3 is ejected upward to the front end of the engine, and the second self-destruct body 7 remains in the tail section of the engine. Finally, the explosion transmission delay tube 16 works. After a certain delay time, the first self-destruct body 3 and the second self-destruct body 7 are ignited. At this time, the segmented self-destruct device explodes the engine components into fragments, and the fragments are no more than 100g and fall to the ground.

[0020] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A rocket engine segmented self-destruction device, characterized in that: The segmented self-destruct device comprises a connecting ring (12), a projectile tube (2), a first self-destruct body (3), a separation charge (5), a second self-destruct body (7) and an engine ignition device (10); the segmented self-destruct device is a rotating body with a hole in the middle; The first self-destruct body (3) comprises a first self-destruct body end cover (1), a second self-destruct body end cover (4), a delay tube protective sleeve (14), a ignition delay tube (15), a detonation delay tube (16) and a self-destruct charge; The second self-destruct body (7) comprises a third self-destruct body end cap (6), a fourth self-destruct body end cap (8) and a self-destruct medicine; A sealing ring (13) is placed in the grooves of the first self-destruction body (3) and the second self-destruction body (7), and then inserted into the projectile tube (2).

2. A rocket engine segmented self-destruction device as claimed in claim 1, characterized in that: The first self-destruct body end cover (1), the second self-destruct body end cover (4), the third self-destruct body end cover (6) and the fourth self-destruct body end cover (8) are all connected to the first self-destruct body (3) and the second self-destruct body (7) by gluing.

3. A rocket engine segmented self-destruction device as claimed in claim 1, characterized in that: The segmented self-destruction device ignites the separation charge (5) through the ignition delay tube (15), separates the first self-destruction body (3) and the second self-destruction body (7), and places them at the front end and the rear end of the engine respectively. After a certain period of time, the first self-destruction body (3) and the second self-destruction body (7) are ignited through the explosion delay tube (16), and the rocket engine is exploded by the first self-destruction body (3) and the second self-destruction body (7) to form fragments with a mass of no more than 100g.

4. A rocket engine segmented self-destruction device as claimed in claim 1, characterized in that: An isolation covering pad (9) is glued to one end of the engine ignition tool (10) close to the fourth self-destruct body end cover (8), and a rubber elastic pad (11) is glued to one end of the engine ignition tool (10) away from the fourth self-destruct body end cover (8), wherein the rubber elastic pad (11) fixes the wire of the engine ignition tool (10) passing through the central through hole.

5. A rocket engine segmented self-destruction device as claimed in claim 1, characterized in that: The ignition delay tube (15) and the explosion delay tube (16) are both designed to be redundant.

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