CN109186373B - Kinetic energy type Cheng Fangbao grenade - Google Patents
Kinetic energy type Cheng Fangbao grenade Download PDFInfo
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- CN109186373B CN109186373B CN201811283783.3A CN201811283783A CN109186373B CN 109186373 B CN109186373 B CN 109186373B CN 201811283783 A CN201811283783 A CN 201811283783A CN 109186373 B CN109186373 B CN 109186373B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/46—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing gases, vapours, powders or chemically-reactive substances
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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
- F42B10/04—Stabilising arrangements using fixed fins
- F42B10/06—Tail fins
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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
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
- F42B12/22—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction
- F42B12/24—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction with grooves, recesses or other wall weakenings
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (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 a kinetic energy type Cheng Fangbao grenade, which comprises a kinetic energy striking part, a connecting seat, a propelling part and a transmitting part, wherein the kinetic energy striking part is connected with the propelling part through the connecting seat, the propelling part and the transmitting part are fixed through gluing, the kinetic energy striking part comprises a kinetic energy projectile, a detonation tube, a rubber guard plate, OC stimulating powder and a firing pin, the propelling part comprises a delay tube, a propellant, a fire cap, impact steel balls, a long-range spray tube and a projectile wing, and the transmitting part comprises a buffer, a projectile collector, a tail wing and a barrel jack. The invention is directed to the offshore maintenance, the handling of the group riot and the cleaning of the semi-closed space, has the dual effects of remote kinetic energy striking and stimulus dispersing, can better protect own combat power by twice propulsion and the effective range reaches 500 meters, realizes the non-fatal striking of the remote group or individual target, greatly flexibly and flexibly realizes the remote dispersing tactical of the riot fight, endows the automatic rifle with the non-fatal dispersing capability, and is the effective supplement of the traditional fatal weapon.
Description
Technical Field
The invention relates to the technical field of riot bullets, in particular to a kinetic energy type Cheng Fangbao-increased grenade.
Background
The traditional killing grenade is an ultra-caliber ammunition launched by a gun and a bullet or an empty package, and the initial speed is obtained by the action of gunpowder gas in the gun and the kinetic energy of the bullet, and is mainly used for dealing with a raw target, an armored target, a non-armored target and the like. The riot grenade is mainly used for temporarily disabling group or individual targets without generating permanent disability, and belongs to the category of non-lethal ammunition. Currently, non-lethal ammunition plays an important role in the tasks of army, armed police, public security, anti-terrorism, sudden handling, maintenance, maritime maintenance and the like, but the problems of shorter range, lower precision, single function and the like generally exist, and for the hand-throwing antiriot ammunition with shorter range, in order to achieve the expected tactical effect, the thrower has to approach criminal suspects or violent harassment crowds, so that the thrower is exposed to the attack range of the other party (such as attack of bricks, stones and glass bottles). The explosion proof ammunition of the gun is used for avoiding explosion accidents, is usually combustion ammunition, cannot form larger deterrence for long-distance targets, but explosion type non-lethal ammunition with larger deterrence, such as detonation ammunition and explosion accelerating ammunition, shortens throwing distance greatly by adopting a hand throwing mode, and has heavy potential safety hazards such as hand explosion and the like, so that the non-lethal ammunition cannot effectively cope with increasingly complex and variable anti-terrorism and stabile situations.
Antiriot ammunition is a type of non-lethal ammunition that has developed earlier, and is mainly used for preventing unclassified or dangerous behaviors without causing serious or fatal injury by transmitting enough striking force to a target so as to cause injury and pain. However, the explosion-proof kinetic energy bullet has a fatal weakness that short-distance kinetic energy is too large to cause disability and death, long-distance kinetic energy is too fast to decay, and an expected non-fatal injury effect is difficult to achieve, so that how to achieve long-distance non-fatal kinetic energy striking is a great difficulty puzzling academia, industrial departments and military and police departments.
Disclosure of Invention
The invention aims to provide a kinetic energy-increasing Cheng Fangbao grenade, which aims to solve the problem that the long-distance non-fatal kinetic energy striking is difficult to realize in the prior art.
In order to achieve the above purpose, the present invention provides the following technical solutions: the kinetic energy increases Cheng Fangbao rifle grenade, including kinetic energy striking portion, connecting seat, propulsion portion and launching unit, its characterized in that: the kinetic energy striking part and the propelling part are fixedly connected through the connecting seat, and the propelling part and the transmitting part are fixedly glued. The kinetic energy striking part is used for realizing the kinetic energy striking and stimulation dispersing of group or individual targets and comprises an axial kinetic energy projectile, a radial kinetic energy projectile, a T-shaped explosion-expanding tube, an explosion-expanding medicine, a high-temperature resistant rubber guard plate, a built-in stimulation powder cavity, OC stimulation powder and a built-in striking needle; the connecting seat comprises connecting seat internal threads; the propelling part is used for realizing secondary propelling and promoting the remodelling of non-fatal striking, and comprises a propelling part external thread, a secondary delay tube nozzle, a secondary delay tube, a secondary delay agent, a propellant cavity, a propellant cavity nozzle, a primary delay tube, a primary delay agent, a fire cap, a steel ball guide rail, an impact steel ball, a long-range spray pipe, a tail nozzle, a missile wing rotating shaft, a missile wing embedding part, a missile wing ferrule and a missile wing ferrule buckle; the launching part is used for starting the launching process and giving one-time propelling acceleration, and comprises a tail pipe, a buffer, a bullet collector, a tail fin, a gun barrel socket and a gauge rod jack.
Preferably, the axial kinetic energy pellets are rubber pellets with hemispherical front parts and cylindrical rear parts, the number of the axial kinetic energy pellets is 1, the radial kinetic energy pellets are 1/4 hollow cylinder rubber pellets, three layers of radial kinetic energy pellets are arranged between the axial kinetic energy pellets and the connecting seat, the number of the radial kinetic energy pellets on the same layer is 4, and the 4 radial kinetic energy pellets are distributed in a circumferential array along the central axis of the kinetic energy striking part.
Preferably, the upper part of the T-shaped explosion-expanding tube is a thin-wall cylinder with a cake-shaped opening at the axis of the lower end face, the lower part of the T-shaped explosion-expanding tube is a slender hollow cylinder, the upper cylinder and the lower cylinder are welded into a whole, the inner cavities are mutually communicated, the lower end part of the T-shaped explosion-expanding tube is propped against the upper surface of the connecting seat and is communicated with the secondary delay tube nozzle, the explosion-expanding agent is filled in the T-shaped explosion-expanding tube, the top surface of the upper part of the T-shaped explosion-expanding tube is provided with a top surface pressure relief hole, the side surface of the lower part of the T-shaped explosion-expanding tube is provided with a side surface pressure relief hole, the top surface pressure relief hole and the side surface pressure relief hole are sealed by hot melt adhesive before the T-shaped explosion-expanding tube is filled with the explosion-expanding agent, the top surface pressure relief hole and the side surface pressure relief hole are used for releasing gunpowder gas generated by the combustion of the T-shaped explosion-expanding tube, the T-expanding tube is externally wrapped with a high temperature resistant rubber guard plate, the high temperature resistant rubber guard plate is mainly used for isolating the ablation of high temperature gas sprayed out of the top surface pressure relief hole and the side surface pressure relief hole to axial kinetic energy pellets and radial kinetic energy pellets, the high temperature resistant rubber guard plate comprises a top rubber guard plate and side surface rubber guard plates, the number of the top rubber guard plate and the side surface rubber guard plates is 4, the 4 top rubber guard plates and the 4 side surface rubber guard plates are distributed in a circumferential array along the central axis of a T-shaped explosion-expanding tube, the 4 top rubber guard plates and the 4 side surface rubber guard plates are spliced by hot melt adhesive, the spliced whole body is the high temperature resistant rubber guard plate, the high temperature resistant rubber guard plate presents an inner hollow T-shaped cavity with the shape similar to that of the T-shaped explosion-expanding tube, the upper end surface of the high temperature resistant rubber guard plate is adhered with the axial kinetic energy pellets, the lower side wall is adhered with the radial kinetic energy pellets, the axial kinetic energy pellets are arranged between the top rubber guard plate and the top rubber guard plate, and the radial kinetic energy pellets and the side rubber guard plates are bonded through hot melt adhesives, and the axial kinetic energy pellets and the radial kinetic energy pellets, the single-layer radial kinetic energy pellets, the upper radial kinetic energy pellets and the lower radial kinetic energy pellets and the lowest radial kinetic energy pellets naturally abut against the upper surface of the connecting seat.
Preferably, the inside stimulus powder chamber that is provided with of radial kinetic energy pellet, built-in stimulus powder chamber is outside sphere, the cavity of inboard cylinder, built-in stimulus powder intracavity portion fills OC stimulus powder, built-in stimulus powder chamber includes outside sphere and inboard cylinder, outside sphere center department supports has built-in cylinder, inboard cylinder is by high temperature resistant fragile material preparation, inboard cylinder supports with T shape expansion tube outer wall, built-in cylinder includes tip, striking pin pole and concave spherical form striking pin base, built-in needle passes through concave spherical form striking pin base fixed connection in radial kinetic energy pellet inside, tip and striking pin pole are made by high strength metal material, concave spherical form striking pin base is made by hard rubber, concave spherical form striking pin base has certain buffer function, can ensure in ordinary storage, transportation etc. can not lead to the unexpected striking pin to smash inboard cylinder because of little vibration or rock, and unexpected release OC stimulus powder, and during normal transmission, radial kinetic energy pellet is realized to the inside cylinder is compressed to the inside spherical form striking pin base through concave spherical form striking pin base fixed connection in radial kinetic energy pellet, and the impact pin base is realized.
Preferably, the axial kinetic energy projectile, the T-shaped explosion tube, the connecting seat, the secondary delay tube, the propellant cavity, the primary delay tube, the steel ball guide rail and the central axis of the impact steel ball are mutually overlapped, the secondary delay tube is positioned in the outer thread of the propellant part, the outer thread of the propellant part is matched with the inner thread of the connecting seat, the kinetic energy striking part and the propellant part are firmly connected, the nozzle of the secondary delay tube is communicated with the bottom of the T-shaped explosion tube, the secondary delay medicine is filled in the secondary delay tube, the lower side of the secondary delay tube is communicated with the propellant cavity, the propellant cavity is filled with propellant, the lower end face of the propellant cavity is provided with a propellant cavity nozzle, the propellant cavity nozzle is communicated with the long-range nozzle, the tail of the long-range nozzle is a tail nozzle, the propellant cavity, the long-range nozzle and the tail nozzle are coaxial, the number of the 4 groups of the propellant cavity nozzle, the long-range nozzle and the tail nozzle are distributed in a circumferential array along the central axis of the propellant cavity, the long-range nozzle is greatly increased in the combustion distance, and the secondary combustion distance of the fuel gas is greatly increased, so that the secondary combustion distance of the fuel gas is greatly increased; the axis of the lower end surface of the propellant cavity is provided with a hole communicated with a nozzle of a primary delay tube, primary delay medicine is filled in the primary delay tube, a fire cap is riveted in the lower end opening of the primary delay tube, the lower side of the primary delay tube is provided with a steel ball guide rail, the lower end opening of the steel ball guide rail is wrapped with impact steel balls, the outer surface of the rear part of the propelling part is connected with missile wings through missile wing rotating shafts, the number of the missile wings is 4, the 4 missile wings are distributed in a circumferential array along the central axis of the propulsion part, the missile wings are folded at the missile wing embedded part when not in use and fixed through missile wing ferrules, the missile wing ferrules are clamped through missile wing ferrule buckles, before firing, the missile wing ferrule is removed, the missile wing is rotated anticlockwise along the missile wing rotating shaft to form a 90-degree opening angle, and the missile wing is used for endowing flight stability in the secondary propulsion process.
Preferably, the delay time of the secondary delay tube is 4s, and the secondary propulsion distance is 400 meters; the delay time of the primary delay pipe is 1s, and the primary propulsion distance is 100 meters; the secondary delay tube nozzle, the propellant cavity nozzle, the primary delay tube nozzle and the tail nozzle are sealed by hot melt adhesives.
Preferably, the diameter of the impact steel ball is slightly larger than the inner diameter of the steel ball guide rail, so that the condition that the impact steel ball accidentally fires the fire cap can not occur under small impact load in the links of normal storage, transportation and the like, and meanwhile, the impact steel ball is affected by the impact force during normal emission, can be rapidly extruded into the steel ball guide rail, and completes high-speed firing of the fire cap.
Preferably, the tail pipe includes tail pipe bonding department, tail pipe bonding department is the preceding terminal surface of tail pipe, propulsion portion and emission portion are fixed through the hot melt adhesive bonding department, tail pipe inner chamber front portion is provided with the buffer, the buffer upside is supported and is leaned on the impact steel ball, the buffer downside is supported and is leaned on there is the bullet collector, tail pipe inner chamber rear portion is the barrel jack, the barrel jack is used for inserting automatic rifle barrel, tail pipe rear portion surface riveting has the fin, the quantity of fin is 4, 4 fins are circumference array distribution along the axis of tail pipe, fin staggers 45 angles with the missile wing of relevant position, the fin is used for giving the flight stability of once advancing the in-process, 2 of 4 fins are provided with the ruler jack, the ruler jack is used for inserting the ruler.
Preferably, the bullet collector is made of aluminum alloy, deforms under the impact of a bullet when shooting, and extrudes the buffer, and the shooting part is acted by the thrust of gun barrel gunpowder gas and the impact kinetic energy of the bullet to realize one-time propulsion; and the propellant in the propellant cavity is combusted to generate high-temperature fuel gas for backward injection boosting, so that secondary propulsion is realized.
Preferably, the high-temperature fuel gas sprayed from the tail nozzle ablates the hot melt adhesive at the bonding part of the tail pipe to force the emitting part to separate from the propelling part, thereby effectively reducing the weight of the projectile body in secondary propelling.
Compared with the prior art, the invention has the following advantages:
1. the invention has novel and scientific design, small and exquisite flexibility and reasonable structure;
2. the invention realizes primary propulsion (flight distance is 100 meters) through the flight kinetic energy of the bullet of the automatic rifle bullet and the gas thrust of gunpowder at the muzzle, and realizes secondary propulsion (flight distance is 400 meters) through the gas injection of the propellant, thereby realizing the target of expected remote non-fatal kinetic energy striking, being remote striking and dispersing equipment, being a tactical of remote anti-riot and dispersing with great flexibility, being applicable to the sudden, anti-terrorist and maintenance tasks of offshore right-keeping, group riot event disposal, semi-closed space cleaning and the like;
3. the invention can effectively avoid close-range conflict, can timely restrain further deterioration of the situation in the group riot event, solve conflict in the sprouting state and furthest protect own combat force; the invention endows the automatic rifle with non-lethal expelling capability, is an effective supplement to the traditional lethal weapon, and is an effective combination of the lethal weapon and the non-lethal weapon;
4. the invention has the double functions of kinetic energy striking and tear forcing and dispersing, the kinetic energy pellets are processed and manufactured by adopting rubber materials, so that excessive damage can be avoided, and meanwhile, the design of forward single pellets and lateral multiple pellets can realize large-scale surface striking; meanwhile, the striking precision of the invention can be further improved by adopting the double-layer stabilizing device of the tail wing and the missile wing and adding the function of the gauge.
In conclusion, the invention has novel design, ingenious structure and convenient use, adopts the vacuum package of the aluminum plastic bag, is then filled into the plastic cylindrical bullet barrel, is convenient for long-time storage, ensures the transportation safety, can realize long-distance and high-precision kinetic energy striking and stimulation dispersing, effectively solves the problems of short range, low precision and single function of the active anti-riot bullet, has certain strategic significance, and can promote new tactical tactics.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
fig. 2 is a schematic structural view of a kinetic energy striking part 1 in the present invention;
FIG. 3 is a perspective view of a T-shaped explosion tube 1-3 according to the present invention;
FIG. 4 is a perspective view of a high temperature resistant rubber shield 1-5 of the present invention;
FIG. 5 is a perspective view of the internal stimulation powder chambers 1-6 of the present invention;
FIG. 6 is a perspective view of the present invention with the pins 1-8;
fig. 7 is a schematic structural view of the propulsion part 3 in the present invention;
FIG. 8 is a schematic view of the folding state of the missile wing 3-16 according to the present invention;
fig. 9 is a schematic structural view of the emitting portion 4 in the present invention.
In the figure: 1. 1-1 parts of kinetic energy striking part, 1-2 parts of axial kinetic energy projectile, 1-3 parts of radial kinetic energy projectile, 1-3 parts of T-shaped explosion tube, 1-3-1 parts of top surface pressure relief hole, 1-3-2 parts of side surface pressure relief hole, 1-4 parts of explosion-relieving medicine, 1-5 parts of high temperature resistant rubber guard plate, 1-5-1 parts of top rubber guard plate, 1-5-2 parts of side surface rubber guard plate, 1-6 parts of built-in stimulation powder cavity, 1-6-1 parts of outside spherical surface, 1-6-2 parts of inner cylindrical surface, 1-7 parts of OC stimulation powder, 1-8 parts of built-in firing pin, 1-8-1 parts of firing pin tip, 1-8-2 parts of firing pin rod, 1-8-3 parts of concave spherical firing pin base, 2 parts of connecting seat, 2-1, 2 parts of connecting seat internal screw threads, 3 parts of propelling part, 3-1, a propulsion part external thread, 3-2, a secondary delay tube nozzle, 3-3, a secondary delay tube, 3-4, a secondary delay agent, 3-5, a propellant cavity, 3-6, a propellant, 3-7, a propellant cavity nozzle, 3-8, a primary delay tube nozzle, 3-9, a primary delay tube, 3-10, a primary delay agent, 3-11, a fire cap, 3-12, a steel ball guide rail, 3-13, an impact steel ball, 3-14, a long-range nozzle, 3-15, a tail nozzle, 3-16, a missile wing, 3-17, a missile wing rotating shaft, 3-18, a missile wing embedding part, 3-19, a missile wing ferrule, 3-20, a missile wing ferrule buckle, 4, a transmitting part, 4-1, tail pipe, 4-1-1, tail pipe bonding part, 4-2, buffer, 4-3, bullet collector, 4-4, fin, 4-5, gun barrel jack, 4-6, gauge jack.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1-9, the present invention provides a technical solution: kinetic energy increases Cheng Fangbao rifle grenade, including kinetic energy striking portion 1, connecting seat 2, propulsion portion 3 and launching unit 4, its characterized in that: the kinetic energy striking part 1 and the propelling part 3 are fixedly connected through the connecting seat 2, and the propelling part 3 and the transmitting part 4 are fixedly glued. The kinetic energy striking part 1 is used for realizing the kinetic energy striking and stimulation dispersing of a group or individual target, and the kinetic energy striking part 1 comprises an axial kinetic energy projectile 1-1, a radial kinetic energy projectile 1-2, a T-shaped explosion-expanding tube 1-3, an explosion-expanding medicine 1-4, a high-temperature resistant rubber guard plate 1-5, a built-in stimulation powder cavity 1-6, OC stimulation powder 1-7 and a built-in striking needle 1-8; the connecting seat 2 comprises a connecting seat internal thread 2-1; the propulsion part 3 is used for realizing secondary propulsion and promoting remodelling of non-fatal striking, and the propulsion part 3 comprises a propulsion part external thread 3-1, a secondary delay tube nozzle 3-2, a secondary delay tube 3-3, a secondary delay agent 3-4, a propellant cavity 3-5, a propellant 3-6, a propellant cavity nozzle 3-7, a primary delay tube nozzle 3-8, a primary delay tube 3-9, a primary delay agent 3-10, a fire cap 3-11, a steel ball guide rail 3-12, an impact steel ball 3-13, a long-range spray tube 3-14, a tail nozzle 3-15, a missile wing 3-16, a missile wing rotating shaft 3-17, a missile wing filling part 3-18, a missile wing ferrule 3-19 and a missile wing ferrule buckle 3-20; the launching part 4 is used for starting the launching process and giving one-time propelling acceleration, and the launching part 4 comprises a tail pipe 4-1, a buffer 4-2, a bullet collector 4-3, a tail fin 4-4, a gun barrel socket 4-5 and a gauge jack 4-6.
Referring to fig. 1 and 2, the axial kinetic energy pellets 1-1 are rubber pellets with hemispherical front parts and cylindrical rear parts, and the number of the rubber pellets is 1; the radial kinetic energy pellets 1-2 are 1/4 hollow cylinder rubber pellets, three layers of radial kinetic energy pellets 1-2 are arranged between the axial kinetic energy pellets 1-1 and the connecting seat 2, the number of the radial kinetic energy pellets 1-2 on the same layer is 4, and the 4 radial kinetic energy pellets 1-2 are distributed in a circumferential array along the central axis of the kinetic energy striking part 1.
In this embodiment, an axial kinetic energy projectile 1-1 with larger mass is designed to achieve accurate kinetic energy striking of a long-distance important target, while a plurality of radial kinetic energy projectiles 1-2 are designed to achieve large-range kinetic energy striking, so that surface dispersion can be achieved while accidental injury is reduced.
Referring to fig. 1, 2, 3 and 4, the upper part of the T-shaped explosion-expanding tube 1-3 is a thin-walled cylinder with a cake-shaped opening at the axle center of the lower end surface, the lower part of the T-shaped explosion-expanding tube 1-3 is a slender hollow cylinder, the upper cylinder and the lower cylinder are welded into a whole, the inner cavities are mutually communicated, the lower end part of the T-shaped explosion-expanding tube 1-3 abuts against the upper surface of the connecting seat 2 and is communicated with the secondary delay tube nozzle 3-2, the inside of the T-shaped explosion-expanding tube 1-3 is filled with an explosion-expanding agent 1-4, the top surface of the upper part of the T-shaped explosion-expanding tube 1-3 is provided with a top surface pressure relief hole 1-3-1, the side surface of the lower side surface of the T-shaped explosion-expanding tube 1-3 is provided with a side surface pressure relief hole 1-3-2, the top surface pressure relief hole 1-3-1 and the side surface pressure relief hole 1-3-2 are sealed by hot melt adhesive before the T-shaped explosion-expanding tube 1-3 is filled with the explosion-expanding agent 1-4, the top surface pressure relief hole 1-3-1 and the side surface pressure relief hole 1-3-2 are used for releasing gunpowder gas generated by the combustion of the explosion-expanding agent 1-4, the T-shaped explosion-expanding tube 1-3 is externally wrapped with a high temperature resistant rubber protection plate 1-5, the high temperature resistant rubber protection plate 1-5 is mainly used for isolating the high temperature gas sprayed by the top surface pressure relief hole 1-3-1 and the side surface pressure relief hole 1-3-2 from ablating the axial kinetic energy pellets 1-1 and the radial kinetic energy pellets 1-2, the high temperature resistant rubber protection plate 1-5 comprises a top rubber protection plate 1-5-1 and a side surface rubber protection plate 1-5-2, the number of the top rubber guard plates 1-5-1 and the side rubber guard plates 1-5-2 is 4, the 4 top rubber guard plates 1-5-1 and the side rubber guard plates 1-5-2 are distributed in a circumferential array along the central axis of the T-shaped explosion-expanding tube 1-3, the 4 top rubber guard plates 1-5-1 and the 4 side rubber guard plates 1-5-2 are spliced by hot melt adhesive, the spliced whole is the high temperature resistant rubber guard plates 1-5, the high temperature resistant rubber guard plates 1-5 present an inner hollow T-shaped cavity similar to the shape of the T-shaped explosion-expanding tube 1-3, the high-temperature resistant rubber guard plate 1-5 is characterized in that an axial kinetic energy pellet 1-1 is adhered to the upper end face of the high-temperature resistant rubber guard plate 1-5, a radial kinetic energy pellet 1-2 is adhered to the lower side wall of the high-temperature resistant rubber guard plate, the axial kinetic energy pellet 1-1 is adhered to the top rubber guard plate 1-5-1, the radial kinetic energy pellet 1-2 is adhered to the side surface rubber guard plate 1-5-2 through hot melt adhesives, and the axial kinetic energy pellet 1-1 and the radial kinetic energy pellet 1-2, the single-layer radial kinetic energy pellet 1-2, the upper radial kinetic energy pellet 1-2 and the lower radial kinetic energy pellet 1-2 and the upper surface of the connecting seat 2 are all naturally abutted against each other.
Referring to fig. 1, 2, 5 and 6, the radial kinetic energy projectile 1-2 is internally provided with a built-in stimulating powder cavity 1-6, the built-in stimulating powder cavity 1-6 is a cavity with an outer spherical surface and an inner cylindrical surface, OC stimulating powder 1-7 is filled in the built-in stimulating powder cavity 1-6, the built-in stimulating powder cavity 1-6 comprises an outer spherical surface 1-6-1 and an inner cylindrical surface 1-6-2, an inner firing pin 1-8 is abutted against the center of the outer spherical surface 1-6-1, the inner cylindrical surface 1-6-2 is made of a high-temperature-resistant fragile material, the inner cylindrical surface 1-6-2 is abutted against the outer wall of the T-shaped explosion tube 1-3, the built-in firing pin 1-8 comprises a firing pin head 1-8-1, a firing pin rod 1-8-2 and a concave spherical firing pin base 1-8-3, the built-in firing pin 1-8 is fixedly connected inside the radial kinetic energy projectile 1-2 through the concave spherical firing pin base 1-8-3, the firing pin head 1-8-1 and the firing pin rod 1-8-2 are made of high-strength metal materials, the concave spherical firing pin base 1-8-3 is made of hard rubber, the concave spherical firing pin base 1-8-3 has a certain buffering function, the condition that the inner cylindrical surface 1-6-2 is accidentally broken by the firing pin 1-8 due to small vibration or shaking in normal storage, transportation and other tasks can be ensured, the OC stimulating powder 1-7 is accidentally released, and in normal emission, when the radial kinetic energy projectile 1-2 impacts a preset target, the concave spherical firing pin base 1-8-3 is compressed under force, so that the firing pin rod 1-8-2 drives the firing pin head 1-8-1 to punch the outer spherical surface 1-6-1 and further break the inner cylindrical surface 1-6-2, and the OC stimulation powder 1-7 is sprayed rapidly.
In other embodiments, the striking tip 1-8-1 may be placed inside the internal stimulation powder chamber 1-6, and this design may further enhance the safety of the present invention, so that the striking tip 1-8-1 will crush the inner cylindrical surface 1-6-2 unless the striking tip 1-8-1 is subjected to a sufficiently large impact force from the radially-moving projectile 1-2, and the striking tip 1-8-1 will only move repeatedly inside the internal stimulation powder chamber 1-6.
Referring to fig. 1, 7 and 8, the axial kinetic energy projectile 1-1, the T-shaped explosion tube 1-3, the connecting seat 2, the secondary delay tube 3-3, the propellant cavity 3-5, the primary delay tube 3-9, the steel ball guide rail 3-12 and the impact steel ball 3-13 are mutually overlapped, the secondary delay tube 3-3 is positioned in the external screw thread 3-1 of the propelling part, the external screw thread 3-1 of the propelling part is mutually matched with the internal screw thread 2-1 of the connecting seat to firmly connect the kinetic energy striking part 1 and the propelling part 3, the secondary delay tube nozzle 3-2 is communicated with the bottom of the T-shaped explosion tube 1-3, the secondary delay medicine 3-4 is filled in the secondary delay tube 3-3, the lower side of the secondary delay tube 3-3 is communicated with the propellant cavity 3-5, the propellant cavity 3-5 is internally filled with propellant 3-6, the lower end surface of the propellant cavity 3-5 is provided with propellant cavity nozzles 3-7, the propellant cavity nozzles 3-7 are communicated with the long-range spray pipes 3-14, the tail parts of the long-range spray pipes 3-14 are tail nozzles 3-15, the propellant cavity nozzles 3-7, the long-range spray pipes 3-14 and the tail nozzles 3-15 are coaxial, the number of the propellant cavity nozzles 3-5 is 4, the 4 groups of propellant cavity nozzles 3-7, the long-range spray pipes 3-14 and the tail nozzles 3-15 are distributed in a circumferential array along the central axis of the propellant cavity 3-5, the acceleration distance of fuel gas generated by burning the propellant 3-6 is greatly increased by the long-range spray pipes 3-14, so that the fuel gas boosting force is also greatly improved, thereby effectively improving the flight distance of the secondary propulsion; the axis of the lower end surface of the propellant cavity 3-5 is provided with a hole communicated with a first-stage delay tube nozzle 3-8, the inside of the first-stage delay tube 3-9 is filled with a first-stage delay agent 3-10, a fire cap 3-11 is riveted in the lower end opening of the first-stage delay tube 3-9, the lower side of the first-stage delay tube 3-9 is provided with a steel ball guide rail 3-12, the lower end opening of the steel ball guide rail 3-12 is wrapped with an impact steel ball 3-13, the outer surface of the rear part of the propelling part 3 is connected with missile wings 3-16 through a missile wing rotating shaft 3-17, the number of the missile wings 3-16 is 4, the 4 missile wings 3-16 are distributed in a circumferential array along the central axis of the propulsion part 3, the missile wings 3-16 are folded at the missile wing embedded filling part 3-18 when not in use and fixed through the missile wing ferrules 3-19, the missile wing ferrules 3-19 are clamped through the missile wing ferrule buckles 3-20, before being launched, the missile wing ferrules 3-19 are taken down, the missile wings 3-16 are rotated anticlockwise to form a 90-degree opening angle along the missile wing rotating shaft 3-17, and the missile wings 3-16 are used for endowing flight stability in the secondary propulsion process.
In the embodiment, the delay time of the secondary delay tube 3-3 is 4s, and the secondary propulsion distance is 400 meters; the delay time of the primary delay tube 3-9 is 1s, and the primary propulsion distance is 100 meters; the secondary delay tube nozzle 3-2, the propellant cavity nozzle 3-7, the primary delay tube nozzle 3-8 and the tail nozzle 3-15 are all sealed by hot melt adhesives.
As shown in fig. 7, the diameter of the impact steel ball 3-13 is slightly larger than the inner diameter of the steel ball guide rail 3-12, so that the situation that the impact steel ball 3-13 accidentally fires the fire cap 3-11 can not occur under small impact load in the links of normal storage, transportation and the like, and meanwhile, the impact steel ball 3-13 is affected by impact force during normal emission, can be rapidly extruded into the steel ball guide rail 3-12, and completes high-speed firing of the fire cap 3-11.
Referring to fig. 1 and 9, the tail pipe 4-1 comprises a tail pipe bonding part 4-1-1, the tail pipe bonding part 4-1-1 is the front end face of the tail pipe 4-1, the propelling part 3 and the launching part 4 are fixed at the tail pipe bonding part 4-1-1 through hot melt adhesive, a buffer 4-2 is arranged at the front part of an inner cavity of the tail pipe 4-1, the upper side of the buffer 4-2 abuts against an impact steel ball 3-13, the lower side of the buffer 4-2 abuts against a bullet collector 4-3, the rear part of an inner cavity of the tail pipe 4-1 is provided with a barrel jack 4-5, the barrel jack 4-5 is used for being inserted into an automatic rifle barrel, tail fins 4-4 are riveted on the outer surface of the rear part of the tail pipe 4-1, the tail fins 4-4 are distributed in a circumferential array along the central axis of the tail pipe 4-1, the tail fins 4-4 are staggered by 45 degrees with wings 3-16 at corresponding positions, the tail fins 4-4 are used for giving a scale 4-6 in a one-time flight stability, and the scale 4-6 gauge jack is used for being inserted into the scale 4-6 gauge.
In this embodiment, the bullet collector 4-3 is made of aluminum alloy, deforms under the impact of a bullet when shooting, and extrudes the buffer 4-2, and the firing part 4 is subjected to the action of the thrust of gun barrel gunpowder gas and the impact kinetic energy of the bullet, so that one-time propulsion is realized; the propellant 3-6 in the propellant cavity 3-5 burns to generate high-temperature fuel gas to spray backwards for boosting, so that secondary propulsion is realized.
With reference to fig. 1 and 9, the hot melt adhesive at the bonding part 4-1-1 of the tail pipe is ablated by the high-temperature fuel gas sprayed from the tail nozzle 3-15, so that the emitting part 4 is forced to be separated from the pushing part 3, and the weight of the elastomer in secondary pushing is effectively reduced.
Working principle:
when the invention is used, firstly, the plastic packaging barrel is unscrewed, the elastomer wrapped with the aluminum plastic bag is taken out, the aluminum plastic bag is torn, the missile wing ferrule buckle 3-20 is pressed, the missile wing ferrule 3-19 is taken down, 4 missile wings 3-16 are rotated anticlockwise along the missile wing rotating shaft 3-17 to form an opening angle of 90 degrees, a gauge is inserted at the position of the gauge jack 4-6, the automatic rifle barrel is inserted into the gun barrel jack 4-5, the automatic rifle air vent is closed, the insurance is placed at a single shot position, a gauge notch is selected according to the target distance, the selected gauge notch, the highest point and the target three-point line of the invention are triggered, a trigger is launched, a live bullet is shot, the bullet head impacts the bullet collector 4-3 and is collected by the bullet collector 4-3, the invention is separated from the automatic rifle barrel by converting the thrust of gun barrel gunpowder gas and the flying kinetic energy of bullet warhead into the flying kinetic energy of the invention, the bullet collector 4-3 is forced to deform and squeeze the buffer 4-2, the buffer 4-2 is forced to strike the impact steel ball 3-13, the impact steel ball 3-13 is forced to be extruded into the steel ball guide rail 3-12, the impact steel ball 3-13 completes the high-speed firing of the fire cap 3-11, then the fire cap 3-11 ignites the primary delay powder 3-10 in the primary delay tube 3-9, after the delay time of 1s, the primary delay powder 3-10 ignites the propellant 3-6 in the propellant cavity 3-5, the propellant 3-6 is violently combusted to generate a large amount of high-temperature high-pressure gunpowder gas, the gunpowder gas ablates the hot melt adhesive in the nozzle 3-7 of the propellant cavity, the hot melt adhesive moves rapidly along the long-range nozzle 3-14, the tail nozzle 3-15 is ablated, the hot melt adhesive at the bonding position 4-1-1 of the tail pipe forces the launching part 4 to be separated from the pushing part 3, so that the flying weight of the invention is lightened, and the process is regarded as pushing the invention once, and the pushing distance is about 100 meters. The propellant gas generated by the combustion of the propellant 3-6 is sprayed out from the tail nozzle 3-15 at a high speed to realize the secondary pushing of the invention, the secondary pushing distance is about 400 meters, the gas generated by the combustion of the propellant 3-6 simultaneously ignites the secondary delay agent 3-4 in the secondary delay tube 3-3, the secondary delay agent 3-4 ablates the hot melt adhesive in the nozzle 3-2 of the secondary delay tube after the delay time of 4 seconds, the secondary delay tube 3-3 is forced to ignite at the nozzle 3-2 of the secondary delay tube, the expanding explosive 1-4 in the T-shaped expanding tube 1-3 is ignited, the expanding explosive 1-4 is violently combusted, the hot melt adhesive in the top surface pressure relief hole 1-3-1 and the side surface pressure relief hole 1-3-2 is ablated, the gunpowder fuel gas is sprayed out from the top pressure relief hole 1-3-1 and the side pressure relief hole 1-3-2 at a high speed, the heat of the fuel gas further melts the hot melt adhesive at the joint of the T-shaped explosion tube 1-3, the axial kinetic energy projectile 1-1 and the radial kinetic energy projectile 1-2 are caused to fly out at a high speed in an explosive manner towards a preset direction, a group or an individual target is impacted, kinetic energy striking is realized, in the impact process, the concave spherical striking needle base 1-8-3 is compressed under the stress, the striking needle rod 1-8-2 drives the striking needle tip 1-8-1 to punch the outer spherical surface 1-6-1, and then the inner cylindrical surface 1-6-2 is broken, so that the OC stimulating powder 1-7 is rapidly sprayed, and the stimulated and dispersed to the target group is realized. The tail wing 4-4 endows the invention with the stability of primary propelling flight, and the missile wing 3-16 endows the invention with the stability of secondary propelling flight, so that the invention can realize accurate kinetic energy striking and stimulus dispersion of groups or individual targets outside a shooting distance of 500 meters.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. Kinetic energy increases Cheng Fangbao rifle grenade, including kinetic energy striking portion (1), connecting seat (2), propulsion portion (3) and launching unit (4), its characterized in that: the dynamic energy striking part (1) and the propelling part (3) are fixedly connected through the connecting seat (2), the propelling part (3) and the transmitting part (4) are fixedly connected through gluing, the dynamic energy striking part (1) is used for realizing the dynamic energy striking and stimulation dispersion of a group or individual target, the dynamic energy striking part (1) comprises axial dynamic energy pellets (1-1), radial dynamic energy pellets (1-2), T-shaped explosion-expanding tubes (1-3), explosion-expanding drugs (1-4), high-temperature resistant rubber guard plates (1-5), built-in stimulation powder cavities (1-6), OC stimulation powder (1-7) and built-in firing pins (1-8), and the axial dynamic energy pellets (1-1) are rubber pellets with hemispherical front parts and cylindrical rear parts, and the number of the axial dynamic energy pellets is 1; the radial kinetic energy pellets (1-2) are 1/4 hollow cylinder rubber pellets, three layers of radial kinetic energy pellets (1-2) are arranged between the axial kinetic energy pellets (1-1) and the connecting seat (2), the number of the radial kinetic energy pellets (1-2) on the same layer is 4, and the 4 radial kinetic energy pellets (1-2) are distributed in a circumferential array along the central axis of the kinetic energy striking part (1); the upper part of the T-shaped explosion expansion pipe (1-3) is a thin-wall cylinder with a cake-shaped opening at the axis of the lower end face, the lower part of the T-shaped explosion expansion pipe (1-3) is a slender hollow cylinder, the upper cylinder and the lower cylinder are welded into a whole, the inner cavities are mutually communicated, the lower end part of the T-shaped explosion expansion pipe (1-3) abuts against the upper surface of the connecting seat (2) and is communicated with the secondary delay pipe nozzle (3-2), the explosion expansion medicine (1-4) is filled in the T-shaped explosion expansion pipe (1-3), the top surface pressure relief hole (1-3-1) is formed in the top surface of the upper part of the T-shaped explosion expansion pipe (1-3), the side surface pressure relief hole (1-3-2) is formed in the side surface of the lower part of the T-shaped explosion expansion pipe (1-3), the top surface pressure relief hole (1-3-1) and the side surface pressure relief hole (1-3-2) are used for releasing the high-temperature-resistant rubber (1-4) before the T-shaped explosion expansion pipe (1-3) is filled with the explosion expansion medicine (1-4), the top surface is used for wrapping the high-temperature resistant rubber (1-3) and the high-temperature resistant protection plate, the high temperature resistant rubber guard plate (1-5) is mainly used for isolating the ablation of high temperature gas sprayed out of the top surface pressure relief hole (1-3-1) and the side surface pressure relief hole (1-3-2) to the axial kinetic energy projectile (1-1) and the radial kinetic energy projectile (1-2), the high temperature resistant rubber guard plate (1-5) comprises a top rubber guard plate (1-5-1) and a side surface rubber guard plate (1-5-2), the number of the top rubber guard plate (1-5-1) and the side surface rubber guard plate (1-5-2) is 4, the 4 top rubber guard plates (1-5-1) and the 4 side surface rubber guard plates (1-5-2) are distributed in a circumferential array along the central axis of the T-shaped explosion expansion tube (1-3), the whole body after the splicing, namely the high temperature resistant rubber guard plate (1-5) is spliced, the high temperature resistant rubber guard plate (1-5) shows the appearance similar to the shape of the radial kinetic energy projectile (1-1) in the T-shaped explosion tube (1-3), the high temperature resistant rubber guard plate is adhered to the axial kinetic energy projectile (1-1) at the side surface of the side wall (1-1), the axial kinetic energy pellets (1-1) and the top rubber guard plate (1-5-1) and the radial kinetic energy pellets (1-2) and the side rubber guard plates (1-5-2) are bonded through hot melt adhesives, and the axial kinetic energy pellets (1-1) and the radial kinetic energy pellets (1-2), the single-layer radial kinetic energy pellets (1-2), the upper radial kinetic energy pellets (1-2) and the lower radial kinetic energy pellets (1-2) and the upper surface of the connecting seat (2) are naturally abutted; the radial kinetic energy projectile (1-2) is internally provided with an internal stimulation powder cavity (1-6), the internal stimulation powder cavity (1-6) is a cavity of an outer spherical surface and an inner cylindrical surface, OC stimulation powder (1-7) is filled in the internal stimulation powder cavity (1-6), the internal stimulation powder cavity (1-6) comprises an outer spherical surface (1-6-1) and an inner cylindrical surface (1-6-2), an internal firing pin (1-8) is abutted against the center of the outer spherical surface (1-6-1), the inner cylindrical surface (1-6-2) is made of a high-temperature-resistant fragile material, and the inner cylindrical surface (1-6-2) is abutted against the outer wall of the T-shaped explosion tube (1-3); the built-in firing pin (1-8) comprises a firing pin point (1-8-1), a firing pin rod (1-8-2) and a concave spherical firing pin base (1-8-3), the built-in firing pin (1-8) is fixedly connected inside a radial kinetic energy projectile (1-2) through the concave spherical firing pin base (1-8-3), the firing pin point (1-8-1) and the firing pin rod (1-8-2) are made of high-strength metal materials, the concave spherical firing pin base (1-8-3) is made of hard rubber, the concave spherical firing pin base (1-8-3) has a certain buffering function, the built-in firing pin (1-8) can not crush an inner cylindrical surface (1-6-2) due to small vibration or shaking in normal storage and transportation service, and the radial kinetic energy projectile (1-2) impacts a preset target when the concave spherical firing pin base (1-8-1) impacts the preset target, the concave spherical firing pin base (1-8-3) compresses the inner cylindrical surface (1-2) to force the firing pin (1-6-2), realizing the rapid spraying of OC stimulating powder (1-7);
the connecting seat (2) comprises connecting seat internal threads (2-1); the propulsion part (3) is used for realizing secondary propulsion and promoting remodelling of non-fatal striking, the propulsion part (3) comprises a propulsion part external thread (3-1), a secondary delay tube nozzle (3-2), a secondary delay tube (3-3), a secondary delay medicine (3-4), a propellant cavity (3-5), a propellant (3-6), a propellant cavity nozzle (3-7), a primary delay tube nozzle (3-8), a primary delay tube (3-9), a primary delay medicine (3-10), a fire cap (3-11), a steel ball guide rail (3-12), an impact steel ball (3-13), a long-range spray tube (3-14), a tail nozzle (3-15), a missile wing (3-16), a missile wing rotating shaft (3-17), a missile wing embedding part (3-18), a missile wing ferrule (3-19) and a missile wing ferrule (3-20); the axial kinetic energy projectile (1-1), the T-shaped explosion tube (1-3), the connecting seat (2), the secondary delay tube (3-3), the propellant cavity (3-5), the primary delay tube (3-9), the steel ball guide rail (3-12) and the central axis of the impact steel ball (3-13) are mutually overlapped, the secondary delay tube (3-3) is positioned in the outer thread (3-1) of the propellant cavity, the outer thread (3-1) of the propellant cavity is matched with the inner thread (2-1) of the connecting seat, the kinetic energy striking part (1) and the propellant cavity (3) are firmly connected, the secondary delay tube nozzle (3-2) is communicated with the bottom of the T-shaped explosion tube (1-3), the secondary delay tube (3-4) is filled in the secondary delay tube (3-3), the lower side of the secondary delay tube (3-3) is communicated with the propellant cavity (3-5), the propellant cavity (3-5) is filled with the propellant (3-6), the tail end face of the propellant cavity (3-5) is provided with a long-end face propellant nozzle (14), the propellant cavity nozzles (3-7), the long-range spray pipes (3-14) and the tail nozzles (3-15) are coaxial, the number of the propellant cavity nozzles is 4 groups, the 4 groups of propellant cavity nozzles (3-7), the long-range spray pipes (3-14) and the tail nozzles (3-15) are distributed in a circumferential array along the central axis of the propellant cavity (3-5), the acceleration distance of fuel gas generated by burning the propellant (3-6) is greatly increased by the long-range spray pipes (3-14), so that the fuel gas boosting force is also greatly improved, and the flight distance of secondary propulsion is effectively improved; the lower end surface of the propellant cavity (3-5) is provided with a hole communicated with a primary delay pipe nozzle (3-8), primary delay medicines (3-10) are filled in the primary delay pipe (3-9), a fire cap (3-11) is riveted in the lower port of the primary delay pipe (3-9), the lower side of the primary delay pipe (3-9) is provided with a steel ball guide rail (3-12), the lower port of the steel ball guide rail (3-12) is wrapped with an impact steel ball (3-13), the outer surface of the rear part of the propelling part (3) is connected with missile wings (3-16) through a missile wing rotating shaft (3-17), the number of the missile wings (3-16) is 4, the 4 missile wings (3-16) are distributed in a circumferential array along the central axis of the propelling part (3), the missile wings (3-16) are folded at a missile wing embedding part (3-18) when not in use, the missile wings (3-19) are fixed, the missile wings (3-19) are clamped by the missile wings (3-19) in a buckling way, the missile wings (3-20) are clamped by the missile wings (3-19) to rotate around the missile wings (3-20) along the rotating shaft (3-90), the missile wing (3-16) is used for endowing flight stability in the secondary propulsion process;
the launching part (4) is used for starting the launching process and giving one-time propelling acceleration, and the launching part (4) comprises a tail pipe (4-1), a buffer (4-2), a bullet collector (4-3), a tail fin (4-4), a gun barrel jack (4-5) and a gauge jack (4-6); the tail pipe (4-1) comprises a tail pipe bonding part (4-1-1), the tail pipe bonding part (4-1-1) is the front end face of the tail pipe (4-1), the propelling part (3) and the launching part (4) are fixed at the tail pipe bonding part (4-1-1) through hot melt adhesive, a buffer (4-2) is arranged at the front part of an inner cavity of the tail pipe (4-1), the upper side of the buffer (4-2) abuts against an impact steel ball (3-13), the lower side of the buffer (4-2) abuts against a bullet collector (4-3), the rear part of the inner cavity of the tail pipe (4-1) is provided with a barrel jack (4-5), the barrel jack (4-5) is used for being inserted into an automatic rifle barrel, the tail fins (4-4) are riveted on the outer surface of the rear part of the tail pipe (4-1), the tail fins (4-4) are distributed along the central axis of the tail pipe (4-1) in a circumferential array, the tail fins (4-4) are staggered with the corresponding positions (4-4) and the tail fins (4-4) are provided with the angle of the corresponding positions (4-4) in a 4-jack (4) in a certain angle, the gauge jack (4-6) is used for inserting a gauge.
2. The kinetic energy enhanced anti-riot grenade of claim 1, characterized by: the delay time of the secondary delay tube (3-3) is 4s, and the secondary propulsion distance is 400 meters; the delay time of the primary delay tube (3-9) is 1s, and the primary propulsion distance is 100 meters; the secondary delay tube nozzle (3-2), the propellant cavity nozzle (3-7), the primary delay tube nozzle (3-8) and the tail nozzle (3-15) are all sealed by hot melt adhesive.
3. The kinetic energy enhanced anti-riot grenade of claim 1, characterized by: the diameter of the impact steel ball (3-13) is slightly larger than the inner diameter of the steel ball guide rail (3-12), so that the situation that the impact steel ball (3-13) accidentally fires the fire cap (3-11) can not occur under a small impact load in normal storage and transportation links, and meanwhile, the impact steel ball (3-13) is affected by impact force during normal emission, can be rapidly extruded into the steel ball guide rail (3-12), and completes high-speed firing of the fire cap (3-11).
4. The kinetic energy enhanced anti-riot grenade of claim 1, characterized by: the bullet collector (4-3) is made of aluminum alloy, deforms under the impact of a bullet when shooting, and extrudes the buffer (4-2), and the shooting part (4) is subjected to the action of the gas thrust of gun barrel gunpowder and the impact kinetic energy of the bullet to realize one-time propulsion; the propellant (3-6) in the propellant cavity (3-5) burns to generate high-temperature fuel gas to spray backwards for boosting, so that secondary propulsion is realized.
5. The kinetic energy enhanced anti-riot grenade of claim 1, characterized by: the high-temperature fuel gas sprayed from the tail nozzle (3-15) ablates the hot melt adhesive at the bonding part (4-1-1) of the tail pipe to force the emitting part (4) to be separated from the pushing part (3), thereby effectively reducing the weight of the elastomer in secondary pushing.
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| CN201811283783.3A CN109186373B (en) | 2018-10-19 | 2018-10-19 | Kinetic energy type Cheng Fangbao grenade |
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| CN201811283783.3A CN109186373B (en) | 2018-10-19 | 2018-10-19 | Kinetic energy type Cheng Fangbao grenade |
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| CN110375595A (en) * | 2019-05-15 | 2019-10-25 | 中国人民解放军陆军工程大学 | A kind of jetting gun type explosively formed projectile ammunition |
| CN113899253B (en) * | 2021-10-09 | 2022-11-04 | 中国人民武装警察部队工程大学 | Composite anti-riot kinetic energy bullet of leading honeycomb warhead of super-caliber |
| CN114858009B (en) * | 2022-06-16 | 2023-11-14 | 中国人民武装警察部队工程大学 | Non-lethal kinetic energy projectile with better aerodynamic characteristics and without hard projectile body |
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| US6523478B1 (en) * | 2001-09-10 | 2003-02-25 | The United States Of America As Represented By The Secretary Of The Army | Rifle-launched non-lethal cargo dispenser |
| KR20150023171A (en) * | 2013-08-23 | 2015-03-05 | 주식회사 한화 | Rifle grenade using bullet trap |
| CN207132794U (en) * | 2017-08-15 | 2018-03-23 | 中国人民武装警察部队工程大学 | A kind of rifle hairdo kinetic energy Dyeing shell |
| CN108592710A (en) * | 2018-06-14 | 2018-09-28 | 中国人民武装警察部队工程大学 | Self-rotating stable type antiriot bomb based on smoothbore transmitting |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7930977B2 (en) * | 2007-02-26 | 2011-04-26 | Klein John M | Non-lethal projectile ammunition |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6523478B1 (en) * | 2001-09-10 | 2003-02-25 | The United States Of America As Represented By The Secretary Of The Army | Rifle-launched non-lethal cargo dispenser |
| KR20150023171A (en) * | 2013-08-23 | 2015-03-05 | 주식회사 한화 | Rifle grenade using bullet trap |
| CN207132794U (en) * | 2017-08-15 | 2018-03-23 | 中国人民武装警察部队工程大学 | A kind of rifle hairdo kinetic energy Dyeing shell |
| CN108592710A (en) * | 2018-06-14 | 2018-09-28 | 中国人民武装警察部队工程大学 | Self-rotating stable type antiriot bomb based on smoothbore transmitting |
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