US20220307806A1 - Bullet Stabilization in Subsonic Flight - Google Patents
Bullet Stabilization in Subsonic Flight Download PDFInfo
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- US20220307806A1 US20220307806A1 US17/590,885 US202217590885A US2022307806A1 US 20220307806 A1 US20220307806 A1 US 20220307806A1 US 202217590885 A US202217590885 A US 202217590885A US 2022307806 A1 US2022307806 A1 US 2022307806A1
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- bullet
- fins
- tail section
- cylindrical
- flight
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- 238000011105 stabilization Methods 0.000 title description 2
- 238000004519 manufacturing process Methods 0.000 claims abstract description 7
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 6
- 239000000463 material Substances 0.000 claims description 44
- 239000011162 core material Substances 0.000 claims description 20
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 14
- 229910052802 copper Inorganic materials 0.000 claims description 14
- 239000010949 copper Substances 0.000 claims description 14
- 238000000034 method Methods 0.000 claims description 12
- 238000010304 firing Methods 0.000 claims description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000011133 lead Substances 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 4
- 229910052721 tungsten Inorganic materials 0.000 claims description 4
- 239000010937 tungsten Substances 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 5
- 239000003380 propellant Substances 0.000 description 5
- 238000010276 construction Methods 0.000 description 3
- 238000005520 cutting process Methods 0.000 description 3
- 230000003466 anti-cipated effect Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
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- 238000003825 pressing Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
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- 239000000843 powder Substances 0.000 description 1
- 239000011343 solid material Substances 0.000 description 1
Images
Classifications
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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
- F42B10/10—Tail fins the fins being formed in the barrel by deformation or the projectile body
-
- 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
-
- 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
- F42B10/22—Projectiles of cannelured type
- F42B10/24—Projectiles of cannelured type with inclined grooves
-
- 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
- F42B10/26—Stabilising arrangements using spin
-
- 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
- F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material
- F42B12/74—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the core or solid body
-
- 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
- F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material
- F42B12/76—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the casing
- F42B12/78—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the casing of jackets for smallarm bullets ; Jacketed bullets or projectiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
- F42B30/02—Bullets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
- F42B5/02—Cartridges, i.e. cases with charge and missile
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
- F42B5/02—Cartridges, i.e. cases with charge and missile
- F42B5/067—Mounting or locking missiles in cartridge cases
Definitions
- Some embodiments relate to a bullet having features that stabilize it during subsonic flight.
- the bullet includes a nose section, a cylindrical midsection, a cylindrical tail section, and a concave base.
- the cylindrical tail section has a diameter greater than or equal to the diameter of the cylindrical midsection.
- the surface of the cylindrical tail section has a material hardness that is less than or equal to the material hardness of the surface of the cylindrical midsection. The material hardness of the surface of the cylindrical tail section is such that the cylindrical tail section is capable of being mechanically formed to include fins.
- the surface of the cylindrical midsection is one of copper or lead. In some embodiments, the surface of the cylindrical tail section is one of aluminum and lead. In some embodiments, the bullet also includes at least one core material, where the core material(s) is one of tungsten, steel, copper, or lead.
- Some embodiments relate to a bullet having features that stabilize it during subsonic flight, such as a parabolic nose, a cylindrical midsection, a secant ogive tail, and at least one helical fin protruding from the tail section.
- the radius of the helical fin(s) is less than or equal to the radius of the cylindrical midsection.
- the bullet has at least one jacket material, where the jacket material(s) is one of copper or lead. In some embodiments, the bullet has at least one core material, where the core material(s) is one of tungsten, steel, copper, or lead.
- Some embodiments relate to a method of stabilizing a bullet in subsonic flight.
- the method includes firing a bullet that includes a nose section, a cylindrical midsection, and a cylindrical tail section capable of forming fins.
- the method further includes forming fins in the cylindrical tail section.
- the fins are configured to impart angular momentum onto the bullet via the airflow over the fins during flight.
- the method further includes imparting angular momentum to the bullet via the airflow over the fins during flight.
- the fins are formed by the rifling of the barrel through which the bullet is fired. In some embodiments, the fins are formed by at least one blade inside the casing in which the bullet is loaded. In some embodiments, the fins are formed during manufacturing of the bullet.
- FIG. 1 a is a representation of a bullet with a soft tail section material capable of forming fins.
- FIG. 1 b is a representation of a bullet with a soft tail section material capable of forming fins after fins have been formed.
- FIG. 2 a is a representation of a bullet with a concave base capable of forming fins.
- FIG. 2 b is a representation of a bullet with a concave base capable of forming fins after fins have been formed.
- FIG. 3 is a representation of a bullet with a concave base and a soft tail section material capable of forming fins after fins have been formed.
- FIG. 4 is a representation of a bullet with a parabolic nose, cylindrical midsection, a secant ogive tail section, and a number of helical fins protruding from the tail section.
- FIG. 5 is a cross-section of a bullet with a concave base capable of forming fins assembled with a casing, propellant, and primer.
- FIG. 6 is a representation of a bullet with a soft tail section material capable of forming fins being pressed into a casing with a number of cutting features capable of cutting fins into the tail section of the bullet.
- FIG. 7 is a diagram of a method of stabilizing a bullet in subsonic flight.
- a solution to this problem may involve the use of helical fins on the bullet.
- the laminar air flow may pass over the bullet, and across the radial surface of the fins.
- the fluid flow will apply a force to the fins due to the fins' twist rate.
- a portion of the force aligned with the linear velocity vector of the bullet may act to slow the bullet.
- a portion of the force orthogonal to the linear velocity vector of the bullet may apply a moment to the bullet, causing it to maintain its spin.
- This may help alleviate some of the problems inherent in subsonic ballistics, such as, but not limited to, tumbling in flight, loss of impact energy, and the changes in both accuracy and precision of the firearm shots fired at subsonic speeds.
- the fins may be formed during the manufacturing of the bullet, and be rigidly affixed to the bullet. Conversely, in some embodiments the fins may be self-forming. In such an embodiment, the fins may be formed by the rifling of the barrel through which the bullet is fired, through a carving mechanism in the casing, or through any other forming means that will activate at some point after the manufacturing of the bullet.
- a bullet having self-forming fins may have a nose section 1 , a cylindrical midsection 2 , and a cylindrical tail section 3 .
- the nose section 1 is preferably parabolic, but may be hemispherical, a truncated cone, or any other appropriate geometry.
- the surface of the tail section 3 may be of a material having a material hardness less than the surface of the midsection 2 .
- the tail section 3 may be constructed of the same material as the midsection 2 , as long as the tail section does not have a material hardness greater than that of midsection. Further, the tail section 3 may have a diameter greater than or equal to the diameter of the midsection 2 .
- the fins may be formed as follows. When the bullet is fired, the bullet enters the barrel, and engages with the barrel rifling. When the tail section reaches the rifling, the extended diameter causes the tail section to fill the rifling more completely than the midsection. As the bullet travels down the barrel, the portion of the tail section filling the rifling will protrude, while the rest of the surface will be formed to the internal diameter of the barrel. This will cause helical fins 4 to be formed into the tail section of the bullet. Using a tail section of a softer material than the midsection enhances this forming effect, allowing the rifling to cut fins into the tail section while having little effect on the harder surface of the midsection.
- the tail section material may be a part of the core of the bullet.
- the nose and midsection may be formed from a jacket of a material having a higher material hardness than that of the core and/or tail section.
- the bullet may be manufactured with a copper jacket over a lead core.
- the core may then be formed such that the tail section contains a lip that extends beyond the diameter of the copper jacket.
- Other materials for the jacket and core are anticipated, and this disclosure is not so limited.
- the helical fins may have a larger impact on the flight stability of a bullet in subsonic flight than on one in supersonic flight. This is because subsonic flight is characterized by laminar flow. Thus the air travels smoothly over the length of the bullet, fully engaging with the fins, and imparting angular momentum to the bullet. Conversely, the air does not flow smoothly over a mach wave, and thus at supersonic speeds the air will not fully engage with the fins.
- a bullet having self-forming fins may have a nose 1 , a cylindrical midsection 2 , and concave base 5 .
- the fins may be formed as follows. When the bullet is fired, the expanding gas fills the concave base 5 , applying pressure radially against the wall of the concave portion. The portion of the pressure that aligns with the direction of the barrel causes the bullet to travel down the barrel. The portion of the pressure on the thinner side walls of the concave base attempts to expand the side walls. Once the bullet enters the barrel, this pressure expands the side walls into the barrel rifling, forming fins 4 with a twist equal to that of the rifling.
- the bullet may be made of a solid material, or be made of a jacketed core, or be constructed in any other manner common to the art. If the bullet has a jacket and core, then the jacket may extend rearwards towards the tail of the bullet beyond the core. For example, if the bullet has a copper jacket over a lead core, then the core may stop at the depth of the concavity, with sidewalls formed of the copper jacket. In this case, the fins 4 will be formed from the expanded copper. Other materials and constructions may be used, and this disclosure is not so limited.
- FIGS. 2 a and 2 b illustrate a relatively hemispherical concavity.
- other shapes such as paraboloids, cylinders, or other geometries, are anticipated, and this disclosure is not so limited.
- a bullet having self-forming fins may have a nose section 1 , a cylindrical midsection 2 , a cylindrical tail section 3 , and a concave base 5 .
- the surface of the tail section 3 may be of a material having a material hardness less than the surface of the midsection 2 .
- the tail section 3 may be constructed of the same material as the midsection 2 , as long as the tail section does not have a material hardness greater than that of midsection.
- the tail section 3 may have a diameter greater than or equal to the diameter of the midsection 2 .
- the fins are formed through a combination of the effects described above.
- the expanding gas in the chamber presses the thin sidewalls of the concavity 5 into the rifling, causing the material to fill the rifling more completely than that of the midsection 2 , or than that of a typical bullet.
- Using a softer material and/or larger diameter for the tail section 3 enhances this effect, providing for more efficient fin 4 formation.
- a bullet may have a nose section 6 , a cylindrical midsection 7 , a secant ogive tail section 8 , and helical fins 9 .
- the nose section 6 is preferably parabolic, but may be hemispherical, a truncated cone, or any other appropriate geometry. This nose geometry, combined with the secant ogive tail section 8 provides for more stable laminar flow over the length of the bullet. This, in turn, enhances the effectiveness of the helical fins 9 .
- the fins 9 may extend the full length of the tail section, or for any portion thereof. They may extend out to the diameter of the midsection 7 , or any fraction thereof.
- the twist of the fins 9 would preferably be timed to the twist of the rifling of the gun in which the bullet is to be used.
- the design of this embodiment enhances the flight stability of a bullet at subsonic speed as follows.
- the rifling of the barrel imparts angular momentum to the bullet, helping it to not tumble during flight.
- the streamline of the airflow will pass smoothly over the nose 6 , the midsection 7 , and upon reaching the tail section 8 will follow the narrowing curve of the tail. This will provide a large surface of air for the fins 9 to engage with.
- the fluid flow will apply a force to the fins due to the fins' twist rate. A portion of the force aligned with the linear velocity vector of the bullet will act to slow the bullet.
- a portion of the force orthogonal to the linear velocity vector of the bullet will apply a moment to the bullet, causing it to maintain its spin. Thus it causes the bullet to maintain its angular momentum over its entire flight. This in turn helps alleviate some of the problems inherent in subsonic ballistics, such as, but not limited to, tumbling in flight, loss of impact energy, and the changes in both accuracy and precision of the firearm shots fired at subsonic speeds.
- a bullet 10 as described above may be used with a suitable casing 11 . While a straight casing 11 is illustrated, any suitable casing may be used, such as a necked down casing.
- the casing may be characterized by a sidewall 12 that defines an interior chamber 13 for holding a propellant.
- the propellant may be smokeless powder, although other propellants may be used and this embodiment is not so limited.
- the casing 11 may include a primer pocket in the base for receiving a primer 14 .
- the ignition end of the primer 14 may be positioned such that, upon striking by the firing pin of a firearm, the flame from the primer 14 may ignite the propellant within the interior chamber 13 .
- a bullet 10 such as any of the novel designs described in this application, may be seated in the casing 11 , whereby it may be held in place at least partially by friction. While the bullet 10 is illustrated to have a concave base, any suitable bullet, such as those of FIG. 1, 2, 3 , or 4 , or any other suitable bullet, may be used and this disclosure is not so limited.
- a bullet with a self-forming stabilizing means may have such means formed in a way other than by the barrel rifling.
- a bullet 15 may be received in a casing 16 having at least one internal cutting blade 17 .
- the internal blades 17 may cut into the material of the tail section of the bullet 15 , forming helical grooves in the tail section.
- these grooves may help to stabilize the bullet in the same manner as the fins described above.
- the bullet 15 may be made using a copper jacket over a lead core. The lead core may form the tail section of the bullet 15 , such that the surface of the tail section is lead.
- the internal blades 17 press into the softer material of the lead, forming helical grooves.
- These grooves provide the same functionality as the fins described above, and may be viewed to form wide fins between the grooves.
- the bullet 15 is illustrated to have such a construction, any suitable bullet, such as those of FIG. 1, 2, 3 , or 4 , or any other suitable bullet, may be used and this disclosure is not so limited.
- a straight casing 16 is illustrated, any suitable casing may be used, such as a necked down casing.
- the internal blades 17 may be formed through a variety of means, and be of a variety of geometries and dimensions.
- the internal blades 17 may be attached to the inside of the casing 16 . Alternatively, they may be made from the material of the sidewall of the casing 16 . In such a situation, they may be pressed, crimped inwards, or formed through any other suitable means.
- the internal blades 17 may be narrow and sharp, as in a knife blade, such that they cut the material of the bullet 15 . Alternatively, they may be wider, such that they press the material of the bullet inwards. In such a case, they may be much wider than the gaps between them, whereby they form fins similar to those illustrated in FIGS.
- a method of stabilizing a bullet in subsonic flight is provided.
- a bullet may be fired through a means known to the art.
- fins may be formed in the tail section of the bullet. Such fins may be formed after firing the bullet, either by the rifling of the barrel, or by another means.
- step two 19 could also readily envision how step two 19 could be performed before step one 18 .
- the fins may be formed when the bullet is pressed into a casing, such as in the embodiment of FIG. 6 , or they may be formed through other suitable means wherein they are formed before firing the bullet but after manufacturing of the bullet.
- the fins may be formed during manufacturing of the bullet, such as in the embodiment of FIG. 4 .
- angular momentum is directional, conservation of momentum makes it difficult not only to change the amount of angular momentum in a system, but also its direction. In the present invention, this means that once angular momentum is imparted to the bullet in step three 20 , it becomes much more difficult to change the orientation of the bullet during flight. This helps protect against tumbling, and subsequently loss of impact energy, and the changes in both accuracy and precision of the firearm shots fired at subsonic speeds.
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Abstract
The present invention relates to increasing the flight stability of a bullet in subsonic flight. The bullet may incorporate features that impart additional angular momentum during flight. Helical fins may be configured such that laminar airflow over the bullet during flight causes the bullet to rotate, increasing the angular momentum of the bullet and stabilizing it during flight. The fins may be self-forming during the use of the bullet or may be formed during manufacturing.
Description
- This application claims the benefit of U.S. Provisional Application No. 63/165,226, filed Mar. 24, 2021, entitled “BULLET STABILIZATION IN SUBSONIC FLIGHT”, which is hereby incorporated by reference in its entirety.
- Bullets in subsonic flight struggle with tumbling and other issues that affect their accuracy. By employing certain measures that impart additional angular momentum to the bullet during flight, flight stability may be maintained during the entire flight of the bullet.
- Some embodiments relate to a bullet having features that stabilize it during subsonic flight. The bullet includes a nose section, a cylindrical midsection, a cylindrical tail section, and a concave base. The cylindrical tail section has a diameter greater than or equal to the diameter of the cylindrical midsection. Further, the surface of the cylindrical tail section has a material hardness that is less than or equal to the material hardness of the surface of the cylindrical midsection. The material hardness of the surface of the cylindrical tail section is such that the cylindrical tail section is capable of being mechanically formed to include fins.
- In some embodiments, the surface of the cylindrical midsection is one of copper or lead. In some embodiments, the surface of the cylindrical tail section is one of aluminum and lead. In some embodiments, the bullet also includes at least one core material, where the core material(s) is one of tungsten, steel, copper, or lead.
- Some embodiments relate to a bullet having features that stabilize it during subsonic flight, such as a parabolic nose, a cylindrical midsection, a secant ogive tail, and at least one helical fin protruding from the tail section. The radius of the helical fin(s) is less than or equal to the radius of the cylindrical midsection.
- In some embodiments, the bullet has at least one jacket material, where the jacket material(s) is one of copper or lead. In some embodiments, the bullet has at least one core material, where the core material(s) is one of tungsten, steel, copper, or lead.
- Some embodiments relate to a method of stabilizing a bullet in subsonic flight. The method includes firing a bullet that includes a nose section, a cylindrical midsection, and a cylindrical tail section capable of forming fins. The method further includes forming fins in the cylindrical tail section. The fins are configured to impart angular momentum onto the bullet via the airflow over the fins during flight. The method further includes imparting angular momentum to the bullet via the airflow over the fins during flight.
- In some embodiments, the fins are formed by the rifling of the barrel through which the bullet is fired. In some embodiments, the fins are formed by at least one blade inside the casing in which the bullet is loaded. In some embodiments, the fins are formed during manufacturing of the bullet.
-
FIG. 1a is a representation of a bullet with a soft tail section material capable of forming fins. -
FIG. 1b is a representation of a bullet with a soft tail section material capable of forming fins after fins have been formed. -
FIG. 2a is a representation of a bullet with a concave base capable of forming fins. -
FIG. 2b is a representation of a bullet with a concave base capable of forming fins after fins have been formed. -
FIG. 3 is a representation of a bullet with a concave base and a soft tail section material capable of forming fins after fins have been formed. -
FIG. 4 is a representation of a bullet with a parabolic nose, cylindrical midsection, a secant ogive tail section, and a number of helical fins protruding from the tail section. -
FIG. 5 is a cross-section of a bullet with a concave base capable of forming fins assembled with a casing, propellant, and primer. -
FIG. 6 is a representation of a bullet with a soft tail section material capable of forming fins being pressed into a casing with a number of cutting features capable of cutting fins into the tail section of the bullet. -
FIG. 7 is a diagram of a method of stabilizing a bullet in subsonic flight. - Most commercially available bullets are designed for supersonic flight speeds. As such, when they are fired at subsonic speeds, they may tumble during flight or exhibit other undesirable aerodynamic characteristics. Such problems are typically mitigated by the gyroscopic effect of the angular momentum imparted to the bullet by the rifling of the barrel it is fired through. However, the drag of the air over the bullet can cause a loss of this angular momentum, causing the bullet to lose flight stability.
- A solution to this problem may involve the use of helical fins on the bullet. During subsonic flight, the laminar air flow may pass over the bullet, and across the radial surface of the fins. As the air flows over the fins, the fluid flow will apply a force to the fins due to the fins' twist rate. A portion of the force aligned with the linear velocity vector of the bullet may act to slow the bullet. A portion of the force orthogonal to the linear velocity vector of the bullet may apply a moment to the bullet, causing it to maintain its spin. Thus it may cause the bullet to maintain its angular momentum over its entire flight. This in turn may help alleviate some of the problems inherent in subsonic ballistics, such as, but not limited to, tumbling in flight, loss of impact energy, and the changes in both accuracy and precision of the firearm shots fired at subsonic speeds.
- In some embodiments, the fins may be formed during the manufacturing of the bullet, and be rigidly affixed to the bullet. Conversely, in some embodiments the fins may be self-forming. In such an embodiment, the fins may be formed by the rifling of the barrel through which the bullet is fired, through a carving mechanism in the casing, or through any other forming means that will activate at some point after the manufacturing of the bullet.
- Referring to
FIGS. 1a and 1b , in one embodiment, a bullet having self-forming fins may have anose section 1, acylindrical midsection 2, and acylindrical tail section 3. Thenose section 1 is preferably parabolic, but may be hemispherical, a truncated cone, or any other appropriate geometry. The surface of thetail section 3 may be of a material having a material hardness less than the surface of themidsection 2. Alternatively, thetail section 3 may be constructed of the same material as themidsection 2, as long as the tail section does not have a material hardness greater than that of midsection. Further, thetail section 3 may have a diameter greater than or equal to the diameter of themidsection 2. - In an embodiment having a
tail section 3 that is softer and wider than themidsection 2, the fins may be formed as follows. When the bullet is fired, the bullet enters the barrel, and engages with the barrel rifling. When the tail section reaches the rifling, the extended diameter causes the tail section to fill the rifling more completely than the midsection. As the bullet travels down the barrel, the portion of the tail section filling the rifling will protrude, while the rest of the surface will be formed to the internal diameter of the barrel. This will causehelical fins 4 to be formed into the tail section of the bullet. Using a tail section of a softer material than the midsection enhances this forming effect, allowing the rifling to cut fins into the tail section while having little effect on the harder surface of the midsection. - In an embodiment as described above, the tail section material may be a part of the core of the bullet. The nose and midsection may be formed from a jacket of a material having a higher material hardness than that of the core and/or tail section. For example, the bullet may be manufactured with a copper jacket over a lead core. The core may then be formed such that the tail section contains a lip that extends beyond the diameter of the copper jacket. Other materials for the jacket and core are anticipated, and this disclosure is not so limited.
- Once formed, the helical fins may have a larger impact on the flight stability of a bullet in subsonic flight than on one in supersonic flight. This is because subsonic flight is characterized by laminar flow. Thus the air travels smoothly over the length of the bullet, fully engaging with the fins, and imparting angular momentum to the bullet. Conversely, the air does not flow smoothly over a mach wave, and thus at supersonic speeds the air will not fully engage with the fins.
- Referring to
FIGS. 2a and 2b , in another embodiment, a bullet having self-forming fins may have anose 1, acylindrical midsection 2, andconcave base 5. In this embodiment, the fins may be formed as follows. When the bullet is fired, the expanding gas fills theconcave base 5, applying pressure radially against the wall of the concave portion. The portion of the pressure that aligns with the direction of the barrel causes the bullet to travel down the barrel. The portion of the pressure on the thinner side walls of the concave base attempts to expand the side walls. Once the bullet enters the barrel, this pressure expands the side walls into the barrel rifling, formingfins 4 with a twist equal to that of the rifling. - In an embodiment described above, the bullet may be made of a solid material, or be made of a jacketed core, or be constructed in any other manner common to the art. If the bullet has a jacket and core, then the jacket may extend rearwards towards the tail of the bullet beyond the core. For example, if the bullet has a copper jacket over a lead core, then the core may stop at the depth of the concavity, with sidewalls formed of the copper jacket. In this case, the
fins 4 will be formed from the expanded copper. Other materials and constructions may be used, and this disclosure is not so limited. -
FIGS. 2a and 2b illustrate a relatively hemispherical concavity. However, other shapes, such as paraboloids, cylinders, or other geometries, are anticipated, and this disclosure is not so limited. - Referring to
FIG. 3 , in another embodiment, a bullet having self-forming fins may have anose section 1, acylindrical midsection 2, acylindrical tail section 3, and aconcave base 5. The surface of thetail section 3 may be of a material having a material hardness less than the surface of themidsection 2. Alternatively, thetail section 3 may be constructed of the same material as themidsection 2, as long as the tail section does not have a material hardness greater than that of midsection. Further, thetail section 3 may have a diameter greater than or equal to the diameter of themidsection 2. - In such an embodiment, the fins are formed through a combination of the effects described above. When the bullet is fired, the expanding gas in the chamber presses the thin sidewalls of the
concavity 5 into the rifling, causing the material to fill the rifling more completely than that of themidsection 2, or than that of a typical bullet. Using a softer material and/or larger diameter for thetail section 3 enhances this effect, providing for moreefficient fin 4 formation. - Referring to
FIG. 4 , in another embodiment, a bullet may have anose section 6, acylindrical midsection 7, a secantogive tail section 8, andhelical fins 9. Thenose section 6 is preferably parabolic, but may be hemispherical, a truncated cone, or any other appropriate geometry. This nose geometry, combined with the secantogive tail section 8 provides for more stable laminar flow over the length of the bullet. This, in turn, enhances the effectiveness of thehelical fins 9. - The
fins 9 may extend the full length of the tail section, or for any portion thereof. They may extend out to the diameter of themidsection 7, or any fraction thereof. The twist of thefins 9 would preferably be timed to the twist of the rifling of the gun in which the bullet is to be used. - The design of this embodiment enhances the flight stability of a bullet at subsonic speed as follows. When the bullet is fired, the rifling of the barrel imparts angular momentum to the bullet, helping it to not tumble during flight. Once the bullet clears the end of the barrel and reaches clean air, the streamline of the airflow will pass smoothly over the
nose 6, themidsection 7, and upon reaching thetail section 8 will follow the narrowing curve of the tail. This will provide a large surface of air for thefins 9 to engage with. As the air flows over thefins 9, the fluid flow will apply a force to the fins due to the fins' twist rate. A portion of the force aligned with the linear velocity vector of the bullet will act to slow the bullet. A portion of the force orthogonal to the linear velocity vector of the bullet will apply a moment to the bullet, causing it to maintain its spin. Thus it causes the bullet to maintain its angular momentum over its entire flight. This in turn helps alleviate some of the problems inherent in subsonic ballistics, such as, but not limited to, tumbling in flight, loss of impact energy, and the changes in both accuracy and precision of the firearm shots fired at subsonic speeds. - Referring to
FIG. 5 , in an embodiment, abullet 10 as described above may be used with asuitable casing 11. While astraight casing 11 is illustrated, any suitable casing may be used, such as a necked down casing. The casing may be characterized by asidewall 12 that defines aninterior chamber 13 for holding a propellant. In some embodiments, the propellant may be smokeless powder, although other propellants may be used and this embodiment is not so limited. Thecasing 11 may include a primer pocket in the base for receiving aprimer 14. The ignition end of theprimer 14 may be positioned such that, upon striking by the firing pin of a firearm, the flame from theprimer 14 may ignite the propellant within theinterior chamber 13. Abullet 10, such as any of the novel designs described in this application, may be seated in thecasing 11, whereby it may be held in place at least partially by friction. While thebullet 10 is illustrated to have a concave base, any suitable bullet, such as those ofFIG. 1, 2, 3 , or 4, or any other suitable bullet, may be used and this disclosure is not so limited. - In another embodiment, a bullet with a self-forming stabilizing means may have such means formed in a way other than by the barrel rifling. For example, referring to
FIG. 6 , abullet 15 may be received in acasing 16 having at least oneinternal cutting blade 17. When thebullet 15 is pressed into thecasing 16, theinternal blades 17 may cut into the material of the tail section of thebullet 15, forming helical grooves in the tail section. Upon firing thebullet 15, these grooves may help to stabilize the bullet in the same manner as the fins described above. For example, thebullet 15 may be made using a copper jacket over a lead core. The lead core may form the tail section of thebullet 15, such that the surface of the tail section is lead. By pressing thebullet 15 into thecasing 16 during loading, theinternal blades 17 press into the softer material of the lead, forming helical grooves. These grooves provide the same functionality as the fins described above, and may be viewed to form wide fins between the grooves. While thebullet 15 is illustrated to have such a construction, any suitable bullet, such as those ofFIG. 1, 2, 3 , or 4, or any other suitable bullet, may be used and this disclosure is not so limited. Further, while astraight casing 16 is illustrated, any suitable casing may be used, such as a necked down casing. - The
internal blades 17 may be formed through a variety of means, and be of a variety of geometries and dimensions. Theinternal blades 17 may be attached to the inside of thecasing 16. Alternatively, they may be made from the material of the sidewall of thecasing 16. In such a situation, they may be pressed, crimped inwards, or formed through any other suitable means. Theinternal blades 17 may be narrow and sharp, as in a knife blade, such that they cut the material of thebullet 15. Alternatively, they may be wider, such that they press the material of the bullet inwards. In such a case, they may be much wider than the gaps between them, whereby they form fins similar to those illustrated inFIGS. 1b, 2b , 3, and 4. So, while narrow,triangular blades 17 are illustrated,internal blades 17 having any of the geometries described, or any other suitable geometry, may also be utilized, and this disclosure is not so limited. - Referring to
FIG. 7 , a method of stabilizing a bullet in subsonic flight is provided. In step one 18, a bullet may be fired through a means known to the art. In step two 19, fins may be formed in the tail section of the bullet. Such fins may be formed after firing the bullet, either by the rifling of the barrel, or by another means. One skilled in the art could also readily envision how step two 19 could be performed before step one 18. In such a case, the fins may be formed when the bullet is pressed into a casing, such as in the embodiment ofFIG. 6 , or they may be formed through other suitable means wherein they are formed before firing the bullet but after manufacturing of the bullet. Alternatively, the fins may be formed during manufacturing of the bullet, such as in the embodiment ofFIG. 4 . Once the fins are formed and the bullet is in flight, in step three 20, the airflow over the fins may impart angular momentum to the bullet. - Because angular momentum is directional, conservation of momentum makes it difficult not only to change the amount of angular momentum in a system, but also its direction. In the present invention, this means that once angular momentum is imparted to the bullet in step three 20, it becomes much more difficult to change the orientation of the bullet during flight. This helps protect against tumbling, and subsequently loss of impact energy, and the changes in both accuracy and precision of the firearm shots fired at subsonic speeds.
- The invention here described of novel aerodynamics and construction has been shown to alleviate the problems inherent in subsonic ballistics, such as, but not limited to, tumbling in flight, loss of impact energy, as well as the changes in both accuracy and precision of the firearm shots fired at subsonic speeds. It is understood that the foregoing examples are merely illustrative of the present invention. Certain modifications of the articles and/or methods may be made and still achieve the objectives of the invention. Such modifications are contemplated as within the scope of the claimed invention.
Claims (14)
1. A bullet comprising:
a nose section;
a cylindrical midsection having a first diameter, wherein a surface of the cylindrical midsection is a first material having a first material hardness;
a cylindrical tail section having a second diameter, wherein the second diameter is greater than or equal to the first diameter, and wherein a surface of the cylindrical tail section is a second material having a second material hardness;
a concave base; and
wherein the second material hardness is less than or equal to the first material hardness, and wherein the second material hardness is such that the second material is capable of being mechanically formed into fins.
2. The bullet of claim 1 , wherein the first material is selected from the group consisting of copper and lead.
3. The bullet of claim 2 , wherein the second material is selected from the group consisting of aluminum and lead.
4. The bullet of any claim 3 , further comprising at least one core material.
5. The bullet of claim 4 , wherein the at least one core material is selected from the group consisting of tungsten, steel, copper, and lead.
6. A bullet comprising:
a parabolic nose;
a cylindrical midsection having a first radius;
a secant ogive tail;
at least one helical fin protruding from the secant ogive tail, wherein the at least one helical fin has a second radius less than or equal to the first radius, and wherein the at least one helical fin has a twist approximately equal to that of a standard barrel rifling.
7. The bullet of claim 6 , further comprising at least one jacket material.
8. The bullet of claim 7 , wherein the at least one jacket material is selected from the group consisting of copper and lead.
9. The bullet of claim 8 , further comprising at least one core material.
10. The bullet of claim 9 , wherein the at least one core material is selected from the group consisting of tungsten, steel, copper, and lead.
11. A method of stabilizing a bullet in subsonic flight, the method comprising:
firing a bullet comprising a nose section, a cylindrical midsection of a first material and a first diameter, and a cylindrical tail section of a second material and a second diameter;
forming fins in the cylindrical tail section of the bullet, wherein the fins are configured to impart angular momentum to the bullet via airflow over the fins during flight;
imparting angular momentum to the bullet via the airflow over the fins during flight.
12. The method of claim 11 , wherein the fins are formed by a rifling of a barrel through which the bullet is fired.
13. The method of claim 11 , wherein the fins are formed by at least one blade inside a casing in which the bullet is loaded.
14. The method of claim 11 , wherein the fins are formed during manufacturing of the bullet.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
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US17/590,885 US20220307806A1 (en) | 2021-03-24 | 2022-02-02 | Bullet Stabilization in Subsonic Flight |
US18/097,520 US20230384068A1 (en) | 2021-03-24 | 2023-01-17 | Bullet Stabilization in Subsonic Flight |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US202163165226P | 2021-03-24 | 2021-03-24 | |
US17/590,885 US20220307806A1 (en) | 2021-03-24 | 2022-02-02 | Bullet Stabilization in Subsonic Flight |
Related Child Applications (1)
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US18/097,520 Division US20230384068A1 (en) | 2021-03-24 | 2023-01-17 | Bullet Stabilization in Subsonic Flight |
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US20220307806A1 true US20220307806A1 (en) | 2022-09-29 |
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US17/590,885 Abandoned US20220307806A1 (en) | 2021-03-24 | 2022-02-02 | Bullet Stabilization in Subsonic Flight |
US18/097,520 Pending US20230384068A1 (en) | 2021-03-24 | 2023-01-17 | Bullet Stabilization in Subsonic Flight |
Family Applications After (1)
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US18/097,520 Pending US20230384068A1 (en) | 2021-03-24 | 2023-01-17 | Bullet Stabilization in Subsonic Flight |
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Also Published As
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US20230384068A1 (en) | 2023-11-30 |
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