CN116753785A - Bullet warhead - Google Patents

Abstract

The application discloses a warhead modeling structure for firing a linear bore firearm, which is expected to smoothly connect the warhead with the warhead tail through a smooth cambered surface by changing the traditional warhead waist cylinder modeling structure on the premise of not changing the original firing conditions and keeping the original comprehensive kinetic energy of the warhead, and the warhead and tail cone modeling structure is increased, so that the whole warhead presents a spindle body modeling structure, the strength of weakening the negative air pressure of the warhead tail is realized, the possibility of generating air vortex on the surface of the warhead is eliminated, and the comprehensive flying performance of the warhead is consolidated. Through increasing the spiral wing at warhead, warhead afterbody, cut warhead ambient air flow at warhead flight in-process, realize the adjustment of both duty cycle to warhead rectilinear flight kinetic energy, axial rotation kinetic energy, under the prerequisite of a small amount of biggest flight distance of weakening warhead, strengthen the stability of warhead flight, increase the stable flight distance of warhead, thereby improve the effective range of warhead that receives stability restriction, increase the stopping power of warhead simultaneously, reach under the same emission condition, warhead flight distance is farther, flight stability is better, the stopping effect is stronger, possess bigger effective range.

Description

Bullet warhead

Technical Field

The application relates to the field of manufacturing of firearm bullets, in particular to a bullet shaping structure of a line bore firing.

Background

At present, the known line bore gun firing warhead breaks through the friction resistance between the warhead and the rifling through high-temperature high-pressure gas generated by gunpowder combustion at the moment of firing, the warhead is pushed out along the rifling with maximum pressure, the warhead rotates around the central axis of the gun bore (or the two default lines of which the central axis of the warhead is known to coincide) at high speed to fire the gun bore under the combined action of the high-temperature high-pressure gas and the rifling, the warhead simultaneously has two motion states of linear flight and axial rotation, the warhead obtains the maximum comprehensive kinetic energy at the moment of firing, the maximum comprehensive kinetic energy comprises the linear flight kinetic energy and the axial rotation kinetic energy, the maximum linear initial velocity and the maximum rotation initial velocity are obtained, the linear initial velocity directly influences the maximum firing range and the stopping capability of the warhead, and the rotation initial velocity directly influences the flight stability of the warhead, and the two factors jointly act to determine the effective firing range of the warhead.

What is needed for modern war long range killing is not the maximum range, but the effective range.

For convenience in description, the warhead is divided into a warhead head, a warhead waist and a warhead tail in sequence by taking the warhead launching direction as the front, wherein the highest part of the middle bulge of the warhead is defined as the warhead waist, and the two ends of the warhead are defined as the warhead and the warhead tail in sequence.

The warheads launched by the currently known breech guns have the following disadvantages: firstly, the linear flight performance is good, the stability performance is poor, the effective range is far smaller than the maximum range, and the effective range of most of the gun warheads only occupies 1/4, 1/5 or less of the maximum range. Due to the improvement of the gunpowder performance and the improvement of the air tightness of the warhead and the rifling, the initial speed of the warhead is greatly improved, the warhead has larger kinetic energy, the warhead still maintains high flying speed beyond the effective range, and even at the landing moment of the flying tail end, the warhead still maintains high flying speed, and the warhead has stronger stopping capability. These phenomena demonstrate that compared to the flight speed and distance, the flight stability is a short plate that limits the effective range of the warhead, the maximum kinetic energy obtained when the warhead is discharged is not optimized in supporting the linear flight and axial rotation of the warhead, the kinetic energy ratio supporting the rotation of the warhead is not enough, the kinetic energy maintaining the flight stability of the warhead is not enough, the flight stability of the warhead is lost too early in the flight process of the warhead, the stable flight distance of the warhead is shorter, thereby limiting the effective range of the warhead from being improved, and meanwhile, the warhead keeps higher flight speed at the flight end, has stronger stopping capability, and a part of kinetic energy is wasted in an ineffective way under the condition that the stopping kinetic energy is far greater than the actual requirement.

Secondly, the warhead modeling structure of the prior known line bore firearm is not optimized, the warhead waist part is mostly in a cylindrical structure, the cylindrical rear end of the warhead waist part is slightly taken as the warhead tail part, and the bottom surface of the warhead is a circular plane or a circular concave surface. The design leads to in the transmission process, warhead receives the atress face of high temperature high pressure gas pressure and keeps away from warhead center mass point, be unfavorable for the stability of control warhead flight, be unfavorable for high temperature high pressure gas kinetic energy to the warhead transmission, and at warhead flight in-process, the warhead afterbody air compensation route is convenient smooth inadequately, stronger air negative pressure area appears at the warhead afterbody, the resistance that the warhead flies has been increased, the vortex is produced more easily at the warhead afterbody, the air disturbance aggravates, thereby the stability of warhead flight has been destroyed, both weakened the flight speed and the distance of warhead, the accuracy of warhead flight direction has also been weakened simultaneously.

Thirdly, the technology for improving the effective range of the warhead is known at present, and the technology for improving the effective range of the warhead is considered from the aspect of increasing the initial speed of the warhead at present, and by improving the performance of gunpowder, increasing the dosage of gunpowder, improving the weight of the warhead, improving the air tightness of a firing chamber, increasing the pressure of firing gas in the chamber, lengthening the length of the firing chamber and prolonging the working time of the firing gas, so that the warhead obtains larger comprehensive kinetic energy, and obtains larger linear flight initial speed and axial rotation initial speed, thereby obtaining larger flight distance and larger effective range. The technical disadvantage is that in order to overcome the increased firing gas pressure, the structural strength of the gun chamber and the thickness and length of the gun chamber are necessarily increased, so that the weight of the gun and the bullet are increased, the material consumption is increased, the burden of soldiers is increased, the operation difficulties such as traction and transfer are increased, and the newly increased effective range is compared with the newly increased maximum range, which is only a small proportion. The warhead keeps higher flying speed at the flying end anyway, and under the condition that the stopping kinetic energy is far greater than the actual requirement, a part of kinetic energy is wasted anyway.

Disclosure of Invention

In view of the above-mentioned drawbacks and shortcomings in the prior art, it is desirable to provide a warhead for firing a wire-bore gun, in which the ratio of the linear flight kinetic energy and the axial rotation kinetic energy of the warhead is adjusted on the premise of keeping the original comprehensive kinetic energy of the warhead without changing the original firing conditions, the linear flight kinetic energy of the warhead is properly weakened to be converted into the axial rotation kinetic energy, and the stable flight distance of the warhead is increased on the premise of properly reducing the maximum firing range of the warhead, so that the effective firing range of the warhead is improved. The implementation method is that a conical structure is added at the tail part of the warhead, so that the existing warhead modeling structure without tail or with short tail is changed. Secondly, the existing warhead waist cylinder modeling structure is changed, the warhead tail and the conical surface radian of the warhead head are connected in sequence, smooth connection of the warhead and the warhead tail is realized through the smooth cambered surface, and the warhead integrally presents a spindle modeling structure. Thirdly, spiral wings are respectively added at the head part and the tail part of the warhead.

Technical characteristics of

The shape of the existing warhead is kept unchanged, the cylinder shape of the waist of the existing warhead is changed, the shape of the existing warhead without tail or with short tail is changed, the cone shape is added to the tail of the warhead, smooth transition from the warhead to the tail of the warhead is realized through a smooth cambered surface, and the whole warhead presents the shape of a spindle body. And a head spiral wing and a tail spiral wing which are consistent with the rotation direction of the rifling and the entanglement degree of the rifling at the tail end of the muzzle are respectively added at the head part and the tail part of the warhead.

The warhead spiral wings are gradually increased in height from the front end of the warhead, gradually reduced in height at the middle position of the warhead until the height of the rear end of the warhead is reduced to zero, and the two ends of the full-section spiral wings are short and high in middle, incline according to the rotation direction of the spiral wings, have the number of the spiral wings of more than or equal to three, and are evenly distributed on the surface of the warhead by taking the central line of the warhead as an axis and the like. The warhead and tail spiral wings are gradually increased in height from the front end of the warhead and tail, gradually reduced in height at the middle position of the warhead and tail until the tail end of the warhead and tail is reduced to zero, and the two ends of the full-section spiral wings are short and high in middle and incline according to the rotation direction of the spiral wings, wherein the number of the spiral wings is more than or equal to three, and the spiral wings are evenly distributed on the surface of the warhead and tail at equal angles by taking the central line of the warhead as an axis.

The helical wings at the front part of the warhead bear the air pressure in front of the warhead in the flying process, and the helical wings at the tail part of the warhead bear the pressure of high-temperature and high-pressure gas generated by burning gunpowder, wherein the pressure is far smaller than the pressure of the high-temperature and high-pressure gas generated by burning the gunpowder, so that the helical wings at the head part of the warhead have small thickness, and the thickness can be properly increased by adopting a sheet-shaped modeling structure according to the penetration force required by hitting a target. The spiral wing at the tail of the warhead has large thickness and adopts a prismatic modeling structure.

The head spiral wing has great weakening degree on the straight-line flying speed of the warhead and strong consolidation capability on the axial rotating speed of the warhead. The tail spiral wing has small weakening degree on the straight-line flying speed of the warhead and weak consolidation capability on the axial rotating speed of the warhead.

The waist of the warhead is the highest part of the middle bulge of the warhead, the surface of the waist of the warhead is a smooth cambered surface for connecting the warhead and the cone of the warhead tail, and the distance between each point on the cambered surface and the central axis of the warhead is larger than the radius between the positive lines of the gun bore. The distance between each point on the surfaces of the warhead and the warhead tail and the central axis of the warhead is smaller than the radius between the positive lines of the gun bore. The distance between each point on the spiral wing of the warhead head and the spiral wing of the tail and the central axis of the warhead is smaller than the radius between the positive lines of the gun bore. Therefore, in the process of bullet firing, only the waist of the bullet participates in friction between the female line and the male line of the gun chamber, the head and the tail of the bullet do not rub with the rifling, and the spiral wings of the head and the tail of the bullet do not rub with the rifling.

Advantageous effects

Through increasing warhead afterbody cone molding structure, form smooth cambered surface from warhead head to warhead afterbody, guide air current to smoothly flow from warhead to warhead afterbody, firstly more efficient filling warhead afterbody air negative pressure area reduces warhead afterbody air negative pressure intensity, reduces the kinetic energy consumption of warhead straight line flight. Secondly, the air vortex at the tail of the warhead is reduced, and the disturbance of tail air flow to the tail of the warhead is reduced. Third, strengthen the steering engine effect of warhead flight direction, consolidate the stability that warhead flies, overcome the warhead and roll the swing.

Through changing current warhead waist cylinder molding structure, connect warhead afterbody, warhead head conical surface radian in order to smooth cambered surface realizes the smooth connection of warhead head and afterbody, makes the warhead wholly present spindle molding structure, makes the warhead waist more be favorable to the air current to flow backward on the one hand, eliminates current warhead cone head and cylindricality waist junction, cylindricality waist and cone tail junction and produces the possibility of vortex, reduces the air current to warhead waist, warhead afterbody disturbance to overcome warhead waist air current to warhead rectilinear flight speed and axial rotation speed's consumption. On the other hand, the arc waist combines with the cone tail, so that the warhead receives the stress surface pushed by the emitted gas, the area is far larger than the circular plane or concave surface of the existing warhead, the stress surface moves forward, is closer to the waist of the warhead, approaches to or even exceeds the center mass point of the warhead or the gravity center of the warhead, and is more beneficial to controlling the directivity and stability of the warhead in flight.

On the one hand, the spiral wings of the warhead are added, corresponding rotational kinetic energy is generated by cutting airflow around the warhead in the flying process of the warhead, and on the premise of weakening the linear flying kinetic energy of the warhead in a proper amount, the axial rotational kinetic energy of the warhead is strengthened, the axial rotation of the warhead is consolidated, and the flying stability of the warhead is maintained. On the other hand, after the warhead hits the target object, stronger cutting effect is generated through the spiral wings of the warhead, and the stopping effect of the warhead is improved.

The spiral wings at the tail of the warhead are added, corresponding rotational kinetic energy is generated by cutting airflow around the tail of the warhead in the flying process of the warhead, and on the premise of weakening the kinetic energy of the linear flying of the warhead in proper quantity, the axial rotational kinetic energy of the warhead is enhanced, the axial rotation of the warhead is consolidated, and the flying stability of the warhead is maintained.

Drawings

The application will now be described in further detail with reference to the drawings and examples, it being understood that the specific examples described herein are intended to be illustrative only and are not limiting of the application.

FIG. 1 is a side view of a combined bullet and case of a bullet of the present application

FIG. 2 is a side view of a bullet of the present application

FIG. 3 is a side view of a bullet and rifling combination of the present application

FIG. 4 is a cross-sectional view of a bullet of a gun of the present application

FIG. 5 is a cross-sectional view of a bullet B-B of the bullet of the present application

FIG. 6 is a side view of three corresponding configurations of a bullet of the present application

FIG. 7 is a side view of a concave-convex structure of a helical wing of a bullet warhead according to the present application

The marks in the figure are as follows:

1. a cartridge case; 2. a bullet; 3. spiral wings at the tail of the warhead; 4. spiral wings at the head of the warhead; 5. the rotating track of the helical wing tip of the warhead; 6. the rotating track of the spiral wing tip at the tail of the warhead; 7. a warhead head; 8. a bullet waist; 9. the tail part of the warhead; 10. a bore male line; 11. a gun bore shade line; 12. central axis of gun bore

As shown in fig. 1: the application discloses a bullet shaping structure of a bullet, which takes the currently known line bore bullet firing technology as the background technology, is based on the existing line bore bullet firing technology, and is based on the premise of keeping the factors such as the current bullet material, the internal structure, the gunpowder combustion performance and the like unchanged, and optimizes and changes the bullet shaping structure.

As shown in fig. 2: according to the bullet shaping structure of the bullet, disclosed by the application, the existing bullet waist cylindrical shaping structure is changed by adding the bullet tail cone shaping structure, the radian of the bullet head and the bullet tail cone is connected in sequence, smooth connection of the bullet head and the bullet tail is realized by smooth cambered surfaces, the bullet integrally presents a spindle body shaping structure, and a smooth curved surface is formed from the bullet head to the bullet tail. And a head spiral wing and a tail spiral wing which are consistent with the rotation direction of the rifling and the entanglement degree of the rifling at the tail end of the muzzle are respectively added at the head part and the tail part of the warhead.

As shown in fig. 3: the application discloses a bullet shaping structure of a bullet, wherein the waist of the bullet is the highest part of the middle bulge of the bullet, the surface of the waist of the bullet is a smooth cambered surface for connecting the head of the bullet and the cone of the tail of the bullet, and the distance between each point on the cambered surface and the central axis of the bullet is larger than the radius between the male lines of the gun chamber. The distance between each point on the surfaces of the warhead and the warhead tail and the central axis of the warhead is smaller than the radius between the positive lines of the gun bore. The distance between each point on the wing tips of the head spiral wing and the tail spiral wing of the warhead and the central axis of the warhead is smaller than the radius between the positive lines of the gun chamber. Therefore, in the process of bullet firing, only the waist of the bullet participates in friction between the female line and the male line of the gun chamber, the head and the tail of the bullet do not rub with the rifling, and the spiral wings of the head and the tail of the bullet do not rub with the rifling.

As shown in fig. 4: according to the bullet shaping structure disclosed by the application, the spiral wings of the bullet head incline according to the rotation direction of the spiral wings, the number of the spiral wings is more than or equal to three, and the spiral wings are uniformly distributed on the surface of the bullet head by taking the central line of the bullet head as an axis line at equal angles. The helical wings of the warhead bear the air pressure in front of the warhead in the flying process, so the helical wings of the warhead have small thickness due to small pressure, and the helical wings of the warhead adopt a sheet-shaped structure, so the thickness can be properly increased according to the penetration force required by hitting a target.

As shown in fig. 5: according to the bullet shaping structure disclosed by the application, the spiral wings at the tail of the bullet incline according to the rotation direction of the spiral wings, the number of the spiral wings is more than or equal to three, and the spiral wings are uniformly distributed on the surface of the tail of the bullet by taking the central line of the bullet as an axis line at equal angles. The spiral wings at the tail of the warhead need to bear the pressure of high-temperature and high-pressure gas generated by the combustion of gunpowder, and the thickness of the spiral wings at the tail of the warhead is large due to the large pressure, and a prismatic structure is adopted.

As shown in fig. 6: the bullet head spiral wing can correspond to three different bullet head appearance structures of a pointed head, a garden head and a square head which are known at present, the height of the bullet head is gradually increased from the front end of the bullet head, the height of the bullet head at the middle position of the bullet head is gradually reduced until the height of the back end of the bullet head is reduced to zero, and the two ends of the full-section spiral wing are short and middle-high.

As shown in fig. 7: according to the bullet shaping structure disclosed by the application, the spiral wings of the bullet head and the spiral wings of the tail can adopt a convex prismatic shaping structure or a concave grooved shaping structure, the cutting airflow of the bullet head is strong, the effect of generating axial rotation kinetic energy is obvious, the stopping capacity after hitting a target is large, the possibility of scraping rifling exists, the cutting airflow of the bullet tail is weak, the effect of generating axial rotation kinetic energy is not obvious, the stopping capacity after hitting the target is small, the possibility of scraping the rifling does not exist, and compared with the adoption of the convex prismatic shaping structure, the bullet shaping structure is more beneficial.

In addition, for convenience of description, only the part related to the application is shown in the drawings, and it should be noted that embodiments of the present application and features in the embodiments may be combined with each other without conflict.

Description of the embodiments

As shown in figure 3, the bullet of the bullet disclosed by the application has the advantages that on the premise of not changing the currently known emission conditions, friction is generated between the waist of the bullet and the male and female threads of the gun chamber, axial rotation is generated under the action of the female threads, the conical surface of the tail of the bullet is used as a working surface for generating high-pressure and high-temperature gas by burning gunpowder, the bullet is pushed to be ejected along the gun chamber direction, and in the process, the spiral wings at the head and the tail of the bullet are not rubbed with the female threads.

Before the warhead goes out of the bore, the gunpowder burns to generate high-temperature and high-pressure gas to push the warhead, the friction resistance between the warhead and the rifling is overcome, the linear thrust is generated, simultaneously, the torsion opposite to the rifling direction is generated through the spiral wings at the tail part of the warhead, the torsion is far smaller than the friction force between the waist of the warhead and the rifling, and the rotary motion of the warhead before going out of the bore is generated through the friction force between the waist of the warhead and the rifling, so that the rotary direction same as the rifling is kept.

The bullet gets the maximum comprehensive kinetic energy at the moment of the bullet discharging, including the maximum linear flight kinetic energy and the maximum axial rotation kinetic energy, and the thrust of the high-temperature and high-pressure gas acting on the bullet disappears.

After the warhead is out of the chamber, the warhead keeps running by inertia. In the process, the spiral wings at the head and the tail of the warhead start working, corresponding axial rotation kinetic energy is generated by cutting airflow around the warhead, the axial rotation kinetic energy of the warhead is enhanced, the axial rotation of the warhead is consolidated, the flying stability of the warhead is maintained, and the stable flying distance of the warhead is increased on the premise of weakening the linear flying kinetic energy of the warhead by a proper amount.

The warhead hits the target object, and the warhead spiral wing and the tail spiral wing reduce the phenomenon of bouncing after the warhead hits the inclined plane by enhancing the flight stability of the warhead, and enhance the cutting effect of the warhead, and enhance the stopping capability of the warhead while maintaining the penetrating effect of the warhead.

Claims (5)

1. A warhead modeling structure for firing a breech gun is characterized in that a cone modeling structure is added at the tail of a warhead, the tail-free or short-tail modeling structure of the traditional warhead is changed, the cylindrical modeling structure of the waist of the traditional warhead is changed, the tail of the warhead and the radian of the conical surface of the head of the warhead are connected in sequence, the head of the warhead and the tail of the warhead are smoothly connected through smooth cambered surfaces, the whole warhead presents a spindle modeling structure, and a head spiral wing and a tail spiral wing which are consistent with the rifling rotation direction and the rifling entanglement degree at the tail end of a muzzle are respectively added at the head of the warhead and the tail of the warhead.

2. The structure according to claim 1, wherein the helical wings of the warhead are gradually increased in height from the front end of the warhead, gradually decreased in height from the middle position of the warhead to zero in height at the rear end of the warhead, and the helical wings are inclined in the rotation direction of the helical wings, and the number of the helical wings is equal to or greater than three, and are uniformly distributed on the surface of the warhead at equal angles with the central line of the warhead as the axis.

3. The structure according to claim 1, wherein the helical wings at the tail of the warhead are gradually increased in height from the front end of the tail of the warhead, gradually decreased in height from the middle position of the tail of the warhead until the tail end of the warhead is reduced to zero, and the helical wings at the whole section are short at the middle and are inclined according to the rotation direction of the helical wings, and the number of the helical wings is equal to or greater than three, and are uniformly distributed on the surface of the tail of the warhead at equal angles with the central line of the warhead as the axis.

4. The warhead modeling structure of a line bore firearm according to claim 1, wherein the warhead spiral wing bears the air pressure in front of the warhead in the flying process, the warhead tail spiral wing bears the pressure of high-temperature and high-pressure gas generated by the combustion of gunpowder, the pressure of the former is far smaller than the pressure of the latter, so the thickness of the warhead spiral wing is small, a sheet structure is adopted, the thickness can be increased according to the penetration force required for hitting a target, the thickness of the warhead tail spiral wing is large, and a prismatic structure is adopted.

5. The bullet shaping structure of a line bore firearm according to claim 1, wherein the bullet waist is the highest part of the middle bulge of the bullet, the surface of the bullet waist is a smooth cambered surface for connecting the bullet head and the bullet tail cone, the distance between each point on the cambered surface and the central axis of the bullet is larger than the radius between the positive lines of the firearm bore, the distance between each point on the surfaces of the bullet head and the bullet tail and the central axis of the bullet is smaller than the radius between the positive lines of the firearm bore, and the distance between each point on the tips of the spiral wings of the bullet head and the spiral wings of the tail and the central axis of the bullet is smaller than the radius between the positive lines of the firearm bore.