CN112781448A - Anti-submarine missile based on water inlet buffer device and control method - Google Patents
Anti-submarine missile based on water inlet buffer device and control method Download PDFInfo
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- CN112781448A CN112781448A CN202011605742.9A CN202011605742A CN112781448A CN 112781448 A CN112781448 A CN 112781448A CN 202011605742 A CN202011605742 A CN 202011605742A CN 112781448 A CN112781448 A CN 112781448A
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- missile
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
- F42B10/668—Injection of a fluid, e.g. a propellant, into the gas shear in a nozzle or in the boundary layer at the outer surface of a missile, e.g. to create a shock wave in a supersonic flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B17/00—Rocket torpedoes, i.e. missiles provided with separate propulsion means for movement through air and through water
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- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses an anti-submarine missile based on an underwater buffer device and a control method, wherein the generation principle of a supercavity is applied in a two-way manner, a tail propelling device is used for pushing a missile body to achieve cavitation speed, and a head cavitator is used for jetting reverse jet flow to ensure that a water surface is cavitated in advance before the missile body arrives, so that the missile body is in a complete and stable supercavity in the whole underwater entering process, direct slamming with water is avoided, and an effective buffer effect is provided for the whole missile body structure; because the projectile body reaches the cavitation speed before entering water, compared with the reverse jet flow ejected by the head cavitator, the projectile body can meet the head cavitation purpose without being ejected at too high speed, namely, the projectile body does not need to provide larger energy for the cavitator; the thermoelectric conversion module is applied, so that the problem of overheating of the power device is solved, the redundant and useless energy can be stored and reused, and the energy cost is saved.
Description
Technical Field
The invention belongs to the technical field of missile structure protection and motion drag reduction, and particularly relates to an anti-submarine missile based on an underwater buffer device and a control method.
Background
In recent years, with the continuous development of the strong military career of our country, the national defense strength is continuously improved, and the weapon equipment equipped by the military is more advanced. Particularly, the characteristics of high generation speed and large demand of naval equipment in various military varieties are reflected more obviously since the strong national strategy of the ocean is put forward in China. The importance of anti-missile in many weaponry is always self-evident. As the anti-submarine missile has greater operational advantages on submarines, countries in the world compete to develop the weapon on the basis of the research results of the existing missiles and torpedoes. The traditional anti-diving missile consists of a missile body, a warhead, a power device, a guidance device, a power supply and a speed reducing umbrella, wherein the speed reducing umbrella is arranged to prevent the missile body from deforming and destabilizing due to strong slamming with fluid in the high-speed water entering process, so that the fighting capacity is lost. If the strength of the structural material of the projectile body is simply improved or an additional protective layer is added on the surface of the projectile body, the cost is higher. The battlefield situation changes instantly, the hitting target is more quickly and accurately taught, the water entering is controlled in the traditional mode of decelerating before entering the water, the hitting capacity and the killing capacity of the missile are greatly reduced, the opportunity of avoiding and counterdirecting enemies is given, and the warplanes are more likely to be missed. From the development trend, the stability of the structure of an important part in the process of the projectile entering water can be ensured on the premise of no deceleration, and the method is a key development direction for improving the combat efficiency.
Disclosure of Invention
Aiming at the defects of the existing water entry protection technology of the anti-submarine missile, the invention aims to overcome the defects that the slamming effect is relieved at the cost of speed reduction, or buffer equipment with high energy consumption, large mass and more occupied space is installed in the prior art, and provides the water entry buffer device which is based on the thrust vector technology and combines thermoelectric materials with the supercavity technology, has good buffer protection performance and strong self-adaptive capacity, can save energy consumption, ensures energy recycling, and improves the stability and the service life of a system.
An anti-submarine missile based on an underwater buffer device comprises a missile body (3), a propelling device, a tail gas integration module and a head cavitator; the propulsion device comprises a vector thruster (1); the tail gas integration module comprises a gas guide pipeline, a gas storage cavity (7) and an electronic pressure regulating valve; the head cavitator comprises a gas jet orifice (10) and a pressure sensor (11);
the gas storage cavity (7) is arranged inside the projectile body (3) and communicated with a gas jet opening (10) arranged at the head of the projectile body (3) through a spray pipe (9); one end of the air guide pipeline is arranged near the vector propeller (1), and the other end of the air guide pipeline is communicated with the air storage cavity (7) and is used for conveying the vector propeller (1) to the air storage cavity (7); an electronic pressure regulating valve is arranged in the air guide pipeline; an electronic pressure regulating valve is arranged at the joint of the gas storage cavity (7) and the spray pipe (9);
the pressure sensor (11) is arranged at the gas jet opening (10).
Further, the three-stage TEG thermoelectric conversion module is arranged inside the projectile body (3), wherein the hot conversion end (301) is close to the vector thruster (1) at the tail of the projectile body (3), and the cold conversion end (302) is far away from the vector thruster (1); when temperature difference occurs between the thermal conversion hot end (301) and the thermal conversion cold end (302), energy is generated, the energy is converted into electric energy, and the electric energy is used for supplying power for the head cavitator and the tail gas integration module.
Furthermore, a fairing (8) is arranged on the outer side of the projectile body (3).
Furthermore, the propulsion device also comprises a guidance system (2) for regulating and controlling the jet pipe jet angle of the vector propeller (1).
Preferably, the number of the air guide pipes is at least 2, and the air guide pipes are symmetrically arranged on the inner wall of the projectile body (3).
Further, the system comprises a circuit system (12) and a control device (6); the circuit system (12) transmits a pressure value signal of the pressure sensor (11) to the control equipment (6); the control device (6) controls the connection part of the air storage cavity (7) and the spray pipe (9) to be provided with a switch of the electronic pressure regulating valve according to the pressure value.
A method of controlling an anti-submarine missile, comprising:
when the projectile body (3) flies to a set water inlet area, the jet angle of the jet pipe of the vector propeller (1) is regulated and controlled, and the projectile body (3) is regulated to be in a vertical water inlet state;
the vector thruster (1) is controlled to increase the propelling power, so as to ensure that the projectile body (3) reaches the cavitation speed in a short time;
when an electronic pressure regulating valve in the air guide pipeline reaches a threshold value, the pipeline is opened, the air guide pipeline collects tail gas of the vector propeller (1), and the tail gas is transported into the air storage cavity (7) for storage;
when the pressure value detected by the pressure sensor (11) reaches a set value, an electronic pressure regulating valve is arranged at the joint of the opened gas storage cavity (7) and the spray pipe (9), and the tail gas is sprayed out from the gas jet orifice (10) to jet to the water surface.
The invention has the following beneficial effects:
the invention carries out bidirectional application on the generation principle of the supercavity, and not only leads the tail propelling device to push the projectile body to reach the cavitation speed, but also leads the head cavitator to jet reverse jet flow, so that the water surface is cavitated in advance before the projectile body arrives, thereby ensuring that the projectile body is in a complete and stable supercavity in the whole water entering process, avoiding direct slamming with water and providing effective buffer action for the whole projectile body structure;
because the projectile body reaches the cavitation speed before entering water, compared with the reverse jet flow ejected by the head cavitator, the projectile body can meet the head cavitation purpose without being ejected at too high speed, namely, the projectile body does not need to provide larger energy for the cavitator;
a large number of researches show that the projectile enters water at different angles under the same condition, the impact is minimum when the projectile slams vertically to the water surface, and the upper impact limit of the projectile entering the water can be effectively reduced by using a thrust vector technology;
the thermoelectric conversion module is applied, so that the problem of overheating of the power device is solved, the redundant and useless energy can be stored and reused, and the energy cost is saved; the thermoelectric material has small volume, light weight, no environmental pollution, no noise in the working process, little interference on the working environment in the projectile body, long service life and recyclability;
the tail gas generated by the propeller is fully utilized and provided for the head cavitator to jet the reverse jet, so that the structure does not need a high-pressure gas cylinder necessary for the traditional cavitator, the occupied space is saved, the structure weight is reduced, the water is easier to gasify due to the high-temperature tail gas jet, and more stable cavitation can be formed compared with the traditional cavitator.
Drawings
FIG. 1 is a schematic longitudinal sectional view of the apparatus of the present invention;
the system comprises a vector thruster 1, a vector thruster 2, a guidance system 3, a projectile body 301, a hot point conversion hot end 302, a thermoelectric conversion cold end 401, a guidance pipeline 402, electronic pressure regulating valves 501 and 502, a control device 6, a gas storage cavity 7, a fairing 8, a spray pipe 9, a gas jet opening 10, a pressure sensor 11 and a circuit system 12.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention discloses an anti-submarine missile based on an underwater buffer device, and particularly relates to the fields of missile structure protection and motion drag reduction. The anti-submarine missile provided by the invention comprises a missile body 3, a propelling device, a three-stage TEG thermoelectric conversion module, a tail gas integration module and a small-sized head cavitator. The propulsion device comprises a vector propeller 1 and a computer guidance system 2; the three-stage TEG thermoelectric conversion module comprises a thermoelectric conversion end and a control device 6; the tail gas integration module comprises gas guide pipelines 401 and 402, a gas storage cavity 7 and electronic pressure regulating valves 501 and 502; the head-compact cavitator comprises a fairing 8, a nozzle 9, a gas jet orifice 10 and a pressure sensor 11.
In order to reuse a large amount of heat energy generated by the vector propeller in the action process, one end of the three-stage TEG thermoelectric conversion module is arranged near the heat source propulsion device, so that the propeller can absorb heat in time when working, a huge temperature difference is formed between the thermoelectric conversion module and the other end of the thermoelectric conversion module, and small-scale power generation is carried out by utilizing the Seebeck effect of a thermoelectric material; the gas guide pipeline of the tail gas integration module is connected with the projectile tail propeller through an electronic pressure regulating valve, and energy is supplied from the other end of the thermoelectric conversion module through a circuit; the nozzle of the small-sized head cavitator is connected with the gas storage cavity of the tail gas integration module through a gas guide pipeline, and the pressure sensor at the front end of the head controls when the jet flow is sprayed out from the gas jet opening.
When the projectile body 3 flies to the set water entering area, the computer guidance system 2 regulates and controls the jet angle of the jet pipe of the vector propeller 1, and the projectile body is adjusted to be in a vertical water entering state.
The vector propeller 1 instantly increases the propelling power to ensure that the projectile body reaches the cavitation speed in a short time, and meanwhile, the thermoelectric module starts to work to rapidly store a large amount of heat energy and convert the heat energy into electric energy to be supplied to the cavitation device and the tail gas integration module;
when the electronic pressure regulating valves 501 and 502 reach the threshold value, the pipelines are opened, and the tail gas integration module collects tail gas of the vector propeller 1 through the gas guide pipelines 401 and 402 and transports the tail gas to the gas storage cavity 7 for storage;
the small-sized head cavitator ejects reverse jet from the gas ejection opening 10 to be jetted to the water surface when the projectile body 3 is about to enter water, and further splits the water surface to form a supercavitation interlayer;
the projectile body enters water at a high speed in the complete and stable supercavitation interlayer, and the projectile body is prevented from directly slamming with the water.
The invention will be further described with reference to the accompanying drawings in which:
referring to fig. 1, an anti-diving missile water-entering buffering device combining thermoelectric materials and a supercavitation technology comprises a power part, an internal energy storage and transportation part and a buffering part.
A power part: the vector propeller 1 is controlled by a computer guidance system 2, and the jet direction and the output power of the jet pipe are adjusted at the right time through a set algorithm program.
An internal energy storage transport portion: constitute by tertiary TEG thermoelectric conversion module and partial tail gas integration module, thermoelectric conversion end 301 is settled near power device for absorb unnecessary heat, and thermoelectric conversion end 302 is settled and is used for giving controlgear 6 and cavitator energy supply in the middle of the projectile body structure, and gas pipeline 401 and gas pipeline 402 paste the shell case inner wall and lay, intercommunication tail gas jet orifice and gas storage chamber 7, and the pipeline afterbody is close to collection port position and installs electronic pressure regulating valve 501.
A buffer part: constitute by the small-size cavitator of head and partial tail gas integration module, spray tube 9 links to each other with gas storage chamber 7, change signal with the external pressure value is transmitted for controlgear 6 through circuitry 12 by pressure sensor 11, and then give the electronic pressure regulating valve 502 of gas storage chamber 7 front end corresponding switching instruction by the program that has set up in advance, ensure that tail gas can be from gas jet port 10 blowout when needs, radome fairing 8 covers in the warhead outside for preventing that the cavitator is whole to receive the influence of harmful factors such as pneumatic heating and acoustic oscillation.
When the projectile flies to the set water entering area, the computer guidance system 2 regulates and controls the jet angle of the jet pipe of the vector propeller 1 to adjust the projectile to be in a vertical water entering state. At the moment, the injection power is increased, the temperature near the power device is rapidly increased, a great temperature difference is formed between the thermoelectric conversion end 301 and the thermoelectric conversion end 302, the thermoelectric conversion module starts to work, the heat energy is converted into electric energy for storage, the circuit system 12 supplies energy to the cavitator and the tail gas integration module, the electronic pressure regulating valve 501 receives a control signal and is opened, and the gas guide pipeline 401 and the gas guide pipeline 402 collect the tail gas at the same time and transmit the tail gas to the gas storage cavity 7.
As the projectile approaches the water surface, its velocity also reaches the cavitation velocity. At this moment, the pressure sensor 11 transmits the external environment pressure change signal to the control device 6, the algorithm program gives an opening instruction to the electronic pressure regulating valve 502, then the tail gas in the gas storage cavity 7 is extruded and sprayed out from the gas jet port 10 along the spray pipe 9, the reverse jet has a great spraying speed relative to the water surface, the water surface is split, and the water surface is cavitated in advance when not in contact with the projectile body. Therefore, the projectile body is always isolated from water by a complete and stable supercavity interlayer in the whole high-speed water entering process, the direct slamming of the structure and the water is avoided, and the projectile body structure is protected by the buffering and resistance reducing effect.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. An anti-submarine missile based on an underwater buffer device is characterized by comprising an missile body (3), a propelling device, a tail gas integration module and a head cavitator; the propulsion device comprises a vector thruster (1); the tail gas integration module comprises a gas guide pipeline, a gas storage cavity (7) and an electronic pressure regulating valve; the head cavitator comprises a gas jet orifice (10) and a pressure sensor (11);
the gas storage cavity (7) is arranged inside the projectile body (3) and communicated with a gas jet opening (10) arranged at the head of the projectile body (3) through a spray pipe (9); one end of the air guide pipeline is arranged near the vector propeller (1), and the other end of the air guide pipeline is communicated with the air storage cavity (7) and is used for conveying the vector propeller (1) to the air storage cavity (7); an electronic pressure regulating valve is arranged in the air guide pipeline; an electronic pressure regulating valve is arranged at the joint of the gas storage cavity (7) and the spray pipe (9);
the pressure sensor (11) is arranged at the gas jet opening (10).
2. The anti-submarine missile based on the water-inlet buffer device as claimed in claim 1, further comprising a three-stage TEG thermoelectric conversion module arranged inside the missile body (3), wherein the hot conversion end (301) is close to the vector thruster (1) at the tail of the missile body (3), and the cold conversion end (302) is far away from the vector thruster (1); when temperature difference occurs between the thermal conversion hot end (301) and the thermal conversion cold end (302), energy is generated, the energy is converted into electric energy, and the electric energy is used for supplying power for the head cavitator and the tail gas integration module.
3. An anti-submarine missile based on an underwater buffer device according to claim 1, wherein a fairing (8) is arranged outside the missile body (3).
4. An anti-submarine missile based on an incoming water buffer as claimed in claim 1 wherein the propulsion means further comprises a guidance system (2) for regulating the nozzle jet angle of the vector thruster (1).
5. An anti-submarine missile based on an incoming water buffer device according to claim 1, wherein the number of air guide pipelines is at least 2, and the air guide pipelines are symmetrically arranged on the inner wall of the missile body (3).
6. An anti-submarine missile based on an incoming water buffer as claimed in claim 1 further comprising circuitry (12) and control equipment (6); the circuit system (12) transmits a pressure value signal of the pressure sensor (11) to the control equipment (6); the control device (6) controls the connection part of the air storage cavity (7) and the spray pipe (9) to be provided with a switch of the electronic pressure regulating valve according to the pressure value.
7. A method of controlling an anti-submarine missile according to claim 1, comprising:
when the projectile body (3) flies to a set water inlet area, the jet angle of the jet pipe of the vector propeller (1) is regulated and controlled, and the projectile body (3) is regulated to be in a vertical water inlet state;
the vector thruster (1) is controlled to increase the propelling power, so as to ensure that the projectile body (3) reaches the cavitation speed in a short time;
when an electronic pressure regulating valve in the air guide pipeline reaches a threshold value, the pipeline is opened, the air guide pipeline collects tail gas of the vector propeller (1), and the tail gas is transported into the air storage cavity (7) for storage;
when the pressure value detected by the pressure sensor (11) reaches a set value, an electronic pressure regulating valve is arranged at the joint of the opened gas storage cavity (7) and the spray pipe (9), and the tail gas is sprayed out from the gas jet orifice (10) to jet to the water surface.
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| CN202011605742.9A CN112781448A (en) | 2020-12-29 | 2020-12-29 | Anti-submarine missile based on water inlet buffer device and control method |
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| CN202011605742.9A CN112781448A (en) | 2020-12-29 | 2020-12-29 | Anti-submarine missile based on water inlet buffer device and control method |
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| CN113879451A (en) * | 2021-10-29 | 2022-01-04 | 大连理工大学 | Combined disc type cavitation structure for underwater navigation of navigation body |
| CN113932664A (en) * | 2021-10-29 | 2022-01-14 | 大连理工大学 | Self-rotating water-entering buffering device of cavitator |
| CN113932663A (en) * | 2021-10-29 | 2022-01-14 | 大连理工大学 | Reverse air injection load-reducing device |
| CN113955055A (en) * | 2021-10-29 | 2022-01-21 | 大连理工大学 | Composite load-reducing device for navigation body |
| CN114001601A (en) * | 2021-10-14 | 2022-02-01 | 哈尔滨工程大学 | Ventilation load reduction and posture adjustment device for high-speed cross-medium water inlet and adjustment method thereof |
| CN114013614A (en) * | 2021-10-29 | 2022-02-08 | 大连理工大学 | Gas multichannel cyclic utilization's compound buffer of jet-propelled income water |
| CN114013557A (en) * | 2021-10-29 | 2022-02-08 | 大连理工大学 | Cavity body air-compression type water-entering combined load-reducing device |
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| CN114013557B (en) * | 2021-10-29 | 2022-12-09 | 大连理工大学 | Cavity body air-compression type water-entering combined load-reducing device |
| CN113932663B (en) * | 2021-10-29 | 2022-12-09 | 大连理工大学 | Reverse air injection load-reducing device |
| WO2023072200A1 (en) * | 2021-10-29 | 2023-05-04 | 大连理工大学 | Combined disc-type cavitation structure for underwater navigation of navigation body |
| CN113879451B (en) * | 2021-10-29 | 2023-10-31 | 大连理工大学 | Combined disc type cavitation structure for underwater navigation of navigation body |
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Application publication date: 20210511 |
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