A missile water exit load reduction and stabilization device based on supercavitation principle

Abstract

The present invention discloses a missile exit-water load reduction and stabilization device based on the supercavitation principle, belonging to the field of high-speed missile exit-water load reduction and stabilization. The present invention primarily comprises a top air jet device and a side air jet device. Multiple sets of side air jet devices are arranged equidistantly along the sides of the missile and around its circumference. The present invention utilizes a hydrolysis reaction of a reactant to generate a large amount of gas that envelops the missile head, thereby reducing the effects of uneven loads on the missile before exiting the water. This reduces the load and stabilizes the missile during exiting the water, improving the missile's accuracy in striking targets. The top and side air jet devices utilize the hydrolysis reaction of the reactant to envelop the missile head in gas, eliminating the need for cumbersome missile modification, resulting in low modification costs and no significant damage to the missile structure. Furthermore, the gas generated by the top and side air jet devices, in conjunction with each other, covers a large area of ​​the missile head at a high enveloping speed, improving the missile's adaptability to transient changes before exiting the water.

Description

Technical Field

[0001] The invention belongs to the field of load reduction and stabilization of missiles emerging from water at high speed, and relates to a load reduction and stabilization device for missiles emerging from water based on the supercavitation principle. Background Art

[0002] Supercavitation technology is a very effective drag reduction method for underwater vehicles. Currently, only a few countries are able to independently design this technology. Russia was the first to propose the concept of an underwater supercavitating vehicle (torpedo). By surrounding the torpedo in a cavity, the torpedo is isolated from the water, greatly reducing the resistance of the torpedo during underwater navigation. Based on this, the US DSG Technology Company, referring to the principles of Russia's "Shvart" supercavitating torpedo, has developed a new type of "multi-environmental ammunition". The supercavitation technology used allows the bullet to form a bubble around it after being fired underwater, reducing the resistance of the bullet in the water, making the bullet move faster in the water and losing less kinetic energy, thereby achieving the purpose of accurately shooting the target.

[0003] Although the above-mentioned supercavitation technology has been applied, the technical problem it solves is only to reduce the water resistance of underwater vehicles, torpedoes, underwater bullets and other devices. In addition, the implementation of supercavitation technology is difficult, the modification process of underwater vehicles is complicated, and the modification cost is too high.

[0004] Existing supercavitation technology has yet to publicly disclose a solution for reducing load and increasing stability during missile exit. As is well known, the missile exiting the water is a rapid, transient process. During this process, the missile experiences a massive impact load, causing uneven forces around the warhead, leading to pre-exit deflection and ultimately reducing the missile's accuracy. Therefore, achieving accurate strikes for submarine-launched missiles is a technical challenge that is of great concern to countries worldwide, and any country achieving significant progress in this area will attract global attention. Summary of the Invention

[0005] In response to the above technical problems, the main purpose of the present invention is to provide a load reduction and stabilization device for a missile emerging from water based on the supercavitation principle. Chambers for chemical reactions are respectively provided at the head and side of the missile. Before the missile emerges from water, a large amount of gas is generated by chemically reacting seawater with the reactants in the chamber. The gas then wraps the missile head therein, thereby isolating the missile head from water, effectively reducing the influence of uneven load on the missile before emerging from water, thereby achieving load reduction and stabilization during the missile emerging from water, and significantly improving the accuracy of the missile in striking targets.

[0006] The purpose of the present invention is achieved through the following technical solutions.

[0007] The present invention discloses a missile water-emergence load reduction and stabilization device based on the supercavitation principle, comprising a top jet device and a side jet device. The top jet device is positioned at the top of the missile warhead; the side jet devices are provided in multiple groups and are arranged equidistantly along the sides of the missile and around its circumference.

[0008] The top air-injection device comprises a top reaction chamber, a top exhaust pipe, a top water pipe, a top one-way valve, a top cap and a connecting frame.

[0009] The top reaction chamber is a hole opened on the top of the missile; the top exhaust pipe is connected to and communicates with the top reaction chamber; the top water pipe is connected to the reaction chamber and the outer wall of the missile, and a top one-way valve is provided on the top water pipe near the outer wall of the missile; the top cap is provided at the top position of the missile head and is connected to the missile head through four sets of connecting frames. The top cap has the same arc cross-section as the top of the missile, so as not to destroy the streamlined shape of the missile head, and a gap of 20-50mm is left between the top cap and the missile head.

[0010] The side jet device includes a side reaction chamber, a side exhaust pipe, a side water pipe, a water baffle, and a side one-way valve. The side reaction chamber is a hole opened on the side of the missile; the side exhaust pipe is connected to and communicates with the side reaction chamber; the side water pipe is connected to the side reaction chamber and the outer wall of the missile, and a side one-way valve is installed on the side water pipe near the outer wall of the missile; the inlet cross-section of the side exhaust pipe is circular, and the outlet cross-section is rectangular; the water baffle is a rectangular plate with the same cross-section as the outlet cross-section of the side exhaust pipe. The water baffle rotates with the outer wall of the missile via a rotating shaft. The water baffle can only be opened from the inside out, preventing external seawater from entering.

[0011] Aluminum carbonate reactant is filled in the top reaction chamber and the side reaction chamber respectively. Aluminum carbonate is an inorganic substance with the chemical formula Al2(CO3)3. It is powdery white small particles and is unstable. It decomposes in water to produce carbon dioxide gas. The hydrolysis chemical reaction formula is: Al2(CO3)3+3H2O=2Al(OH)3↓+3CO2↑.

[0012] The working method of the missile water-exit load reduction and stabilization device disclosed in the present invention is as follows:

[0013] When the missile is launched from a submarine, before it exits the water, the top jet device and the side jet device are started simultaneously, wherein the top one-way valve in the top jet device is opened, and seawater enters the top reaction chamber through the top water pipe, and the aluminum carbonate in the top reaction chamber undergoes a hydrolysis reaction to produce a large amount of carbon dioxide gas, which reaches the top of the warhead along the top exhaust pipe, and the gas diffuses outward evenly along the gap between the top cap and the missile head, gradually wrapping the upper part of the missile head.

[0014] The side one-way valve in the side jet device is opened, and seawater enters the side reaction chamber through the side water pipe. The aluminum carbonate in the side reaction chamber undergoes a hydrolysis reaction to produce a large amount of carbon dioxide gas. The carbon dioxide gas follows the side exhaust pipe to the water baffle, pushes the water baffle open and diffuses downward, gradually wrapping the lower half of the missile head.

[0015] The gas then wraps the missile head, thereby isolating the missile head from the water. By isolating the missile head from the water, the impact of uneven load on the missile before it emerges from the water is reduced, thereby achieving load reduction and stability increase during the missile's emergence from the water, and significantly improving the missile's accuracy in striking targets.

[0016] Beneficial effects:

[0017] 1. The present invention discloses a missile exiting water load reduction and stabilization device based on the supercavitation principle. The device utilizes the hydrolysis reaction of a reactant to generate a large amount of gas to wrap the missile head, thereby reducing the impact of uneven load on the missile before exiting the water, thereby achieving load reduction and stabilization during the missile exiting the water.

[0018] 2. The present invention discloses a missile exiting water load reduction and stabilization device based on the supercavitation principle, which is respectively provided with a top jet device and a side jet device, and the side jet devices can be arranged in one row and multiple groups or multiple rows and multiple groups according to actual conditions. With the top and side jet devices cooperating at the same time, the gas generated by the device can wrap the missile head in a larger area and at a faster speed, thereby improving the adaptability to the transient change process before the missile exits the water.

[0019] 3. The present invention discloses a missile water-emergence load reduction and stabilization device based on the supercavitation principle. The overall structure is simple, and there is no need for complicated modifications to the missile. The modification cost is low, and the device will not cause obvious or potential damage to the missile's appearance, structure, devices, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 Schematic diagram of the device of the present invention;

[0021] Figure 2 Schematic diagram of the top air-jet device of the present invention;

[0022] Figure 3 Schematic diagram of the side jet device of the present invention;

[0023] Figure 4 Schematic diagram of the side exhaust pipe structure of the present invention;

[0024] Figure 5 A schematic diagram of the position of the side exhaust pipe of the present invention installed on the missile head;

[0025] Figure 6 A schematic diagram of the top and side jet ejection devices of the present invention before the missile emerges from the water;

[0026] In the figure: 1 - top jet device, 101 - top reaction chamber, 102 - top exhaust pipe, 103 - top water pipe, 104 - top one-way valve, 105 - top cap, 106 - connecting frame, 2 - side jet device, 201 - side reaction chamber, 202 - side exhaust pipe, 203 - side water pipe, 204 - water baffle, 205 - side one-way valve. DETAILED DESCRIPTION

[0027] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments.

[0028] like Figure 1 As shown, the present embodiment discloses a missile water-emergence load reduction and stabilization device based on the supercavitation principle, comprising a top jet device 1 and a side jet device 2, wherein the top jet device 1 is arranged at the top of the missile warhead, that is, the front end of the missile; the side jet devices 2 are provided in multiple rows and groups, and only one group of side jet devices 2 in one row is shown in the figure. The side jet devices 2 can be arranged in multiple rows along the missile body direction according to actual conditions, and multiple groups can be evenly arranged around the missile body.

[0029] like Figure 2 As shown, the top gas injection device 1 includes a top reaction chamber 101, a top exhaust pipe 102, a top water pipe 103, a top one-way valve 104, a top cap 105 and a connecting frame 106.

[0030] The top reaction chamber 101 is a nearly spherical hole opened on the top of the missile; the top exhaust pipe 102 is connected to and communicates with the top reaction chamber 101; the top water pipe is used to connect and open the top reaction chamber 101 and the outer wall of the missile, and a top one-way valve 104 is set on the top water pipe 103 near the outer wall of the missile; the top one-way valve 104 only allows seawater to flow into the interior of the missile body in one direction; the top cap 105 is made of high-strength alloy steel, and the top cap 105 is set at the top position of the missile head and connected to the missile head through four groups of connecting frames, and the four groups of connecting frames 106 are arranged at 90° intervals around the missile body.

[0031] The top cap 105 has the same arc cross section as the missile top, so as not to destroy the streamline of the missile head, and a gap of 20-50 mm is left between the top cap 105 and the missile head.

[0032] like Figure 3As shown, the side jet device 2 includes a side reaction chamber 201, a side exhaust pipe 202, a side water pipe 203, a water retaining plate 204, and a side one-way valve 205. The side reaction chamber 201 is a hole opened on the side of the missile; the side exhaust pipe 202 is connected to and communicates with the side reaction chamber 201; the side water pipe 203 is connected to the side reaction chamber 201 and the outer wall of the missile, and a side one-way valve 205 is installed on the side water pipe 203 near the outer wall of the missile. The side one-way valve 205 only allows seawater to flow into the missile body in one direction.

[0033] like Figure 4 and Figure 5 As shown, the cross-section of the inlet end of the side exhaust pipe 202 is circular, and the cross-section of the outlet end is rectangular. The rectangular outlet design is conducive to increasing the lateral coverage area of ​​the ejected gas, thereby ensuring that the ejected gas wraps a larger area around the missile head and a faster wrapping speed.

[0034] The water baffle 204 is a rectangular plate with the same cross-section as the outlet end of the side exhaust pipe 202. The water baffle 204 rotates with the outer wall of the missile through a rotating shaft. The water baffle 204 can only be opened from the inside to the outside, and external seawater cannot enter.

[0035] Aluminum carbonate reactant is filled in the top reaction chamber 1 and the side reaction chamber 2 respectively. Aluminum carbonate is an inorganic substance with the chemical formula Al2(CO3)3. It is powdery white small particles and is unstable. It decomposes in water to produce carbon dioxide gas. The hydrolysis chemical reaction formula is: Al2(CO3)3+3H2O=2Al(OH)3↓+3CO2↑.

[0036] The working method of the missile water exit load reduction and stabilization device based on the supercavitation principle disclosed in this embodiment is as follows:

[0037] like Figure 6 As shown, when the missile is launched from a submarine, before it emerges from the water, the top jet device 1 and the side jet device 2 are started simultaneously, wherein the top one-way valve 104 in the top jet device 1 is opened, and seawater enters the top reaction chamber 101 through the top water pipe 103, and the aluminum carbonate in the top reaction chamber 101 undergoes a hydrolysis reaction to produce a large amount of carbon dioxide gas, which reaches the top of the warhead along the top exhaust pipe 102, and the gas diffuses outward evenly along the gap between the top cap 105 and the missile head, gradually wrapping the upper part of the missile head.

[0038] At the same time, the side one-way valve 205 in the side jet device 2 is opened, and seawater enters the side reaction chamber 201 through the side water pipe 203. The aluminum carbonate in the side reaction chamber 201 undergoes a hydrolysis reaction to produce a large amount of carbon dioxide gas. The carbon dioxide gas flows along the side exhaust pipe 202 to the water retaining plate 204, pushes the water retaining plate 204 open, and diffuses downward, gradually wrapping the lower half of the missile head.

[0039] With the cooperation of the top jet device 1 and the side jet device 2, the gas generated by the device can completely wrap the missile head, thereby isolating the missile head from the water, thereby effectively reducing the impact of uneven load on the missile before it emerges from the water, thereby achieving load reduction and stabilization during the missile's emergence from the water, and significantly improving the accuracy of the missile in striking the target.

[0040] The foregoing is merely a preferred embodiment of the present invention. The specific embodiments described herein are intended solely to explain the present invention and are not intended to limit the present invention. It should be noted that those skilled in the art may make various improvements and modifications without departing from the principles of the present invention, and such improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A missile water exit load reduction and stabilization device based on the supercavitation principle, characterized by: It includes a top jet device (1) and a side jet device (2); The top jetting device (1) comprises a top reaction chamber (101), a top exhaust pipe (102), a top water pipe (103), a top one-way valve (104), a top cap (105) and a connecting frame (106); The top reaction chamber (101) is a hole opened on the top of the missile; the top exhaust pipe (102) is connected to and communicates with the top reaction chamber (101); the top water pipe (103) is used to connect and open the top reaction chamber (101) and the outer wall of the missile, and a top one-way valve (104) is provided on the top water pipe (103) near the outer wall of the missile; The side jet device (2) comprises a side reaction chamber (201), a side exhaust pipe (202), a side water pipe (203), a water baffle (204) and a side one-way valve (205); The side reaction chamber (201) is a hole opened on the side of the missile; the side water pipe (203) is connected to the side reaction chamber (201) and the outer wall of the missile, and a side one-way valve (205) is provided on the side water pipe (203) near the outer wall of the missile; When the missile is launched from the submarine, before it leaves the water, the top jet device (1) and the side jet device (2) are started simultaneously, wherein the top one-way valve (104) in the top jet device (1) is opened, and seawater enters the top reaction chamber (101) through the top water pipe (103), and the aluminum carbonate in the top reaction chamber (101) undergoes a hydrolysis reaction to produce a large amount of carbon dioxide gas, which flows along the top exhaust pipe (102) to the top of the warhead, and the gas diffuses outward evenly along the gap between the top cap (105) and the missile head, gradually wrapping the upper part of the missile head.

2. A missile water-emergence load reduction and stabilization device based on the supercavitation principle according to claim 1, characterized in that: The top reaction chamber (101) and the side reaction chamber (201) are respectively filled with aluminum carbonate reactant.

3. The missile water-emergence load reduction and stabilization device based on the supercavitation principle according to claim 1, characterized in that: The inlet end cross-section of the side exhaust pipe (202) is circular, and the outlet end cross-section is rectangular.

4. The missile water-emergence load reduction and stabilization device based on the supercavitation principle according to claim 1, characterized in that: The material of the top cap (105) is high-strength alloy steel. The top cap (105) is arranged at the top end of the missile head and is connected to the missile head through four sets of connecting frames.

5. The missile water-emergence load reduction and stabilization device based on the supercavitation principle according to claim 4, characterized in that: The four groups of connecting frames (106) are arranged at intervals of 90° around the missile.

6. The missile water-emergence load reduction and stabilization device based on the supercavitation principle according to claim 4, characterized in that: The top cap (105) has the same arc cross section as the missile top, and a gap of 20-50 mm is left between the top cap (105) and the missile head.

7. A missile water-emergence load reduction and stabilization device based on the supercavitation principle according to claim 1, 2, 3, 4, 5 or 6, characterized in that: Before the water is discharged, the top jet device (1) and the side jet device (2) are started simultaneously, wherein the top one-way valve (104) in the top jet device (1) is opened, and seawater enters the top reaction chamber (101) through the top water pipe (103), and the aluminum carbonate in the top reaction chamber (101) undergoes a hydrolysis reaction to produce a large amount of carbon dioxide gas, and the carbon dioxide gas reaches the top of the warhead along the top exhaust pipe (102), and the gas is evenly diffused outward along the gap between the top cap (105) and the missile head, gradually wrapping the upper part of the missile head; The side one-way valve (205) in the side jet device (2) is opened, and seawater enters the side reaction chamber (201) through the side water pipe (203). Aluminum carbonate in the side reaction chamber (201) undergoes a hydrolysis reaction to produce a large amount of carbon dioxide gas. The carbon dioxide gas flows along the side exhaust pipe (202) to the water retaining plate (204), pushes the water retaining plate (204) open, and diffuses downward, gradually wrapping the lower half of the missile head. With the cooperation of the top jet device (1) and the side jet device (2), the gas generated by the device can completely wrap the missile head, thereby isolating the missile head from the water, thereby effectively reducing the influence of uneven load on the missile before it emerges from the water, and thus achieving load reduction and stability enhancement during the missile's emergence from the water.

Images