EP3117177B1 - Patrone mit induzierter instabilität bei einem voreingestellten bereich - Google Patents

Patrone mit induzierter instabilität bei einem voreingestellten bereich Download PDF

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Publication number
EP3117177B1
EP3117177B1 EP15800253.5A EP15800253A EP3117177B1 EP 3117177 B1 EP3117177 B1 EP 3117177B1 EP 15800253 A EP15800253 A EP 15800253A EP 3117177 B1 EP3117177 B1 EP 3117177B1
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EP
European Patent Office
Prior art keywords
projectile
liquid
void
flight
solid
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EP15800253.5A
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English (en)
French (fr)
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EP3117177A4 (de
EP3117177A2 (de
Inventor
Kevin Michael Sullivan
Marcelo Eduardo MARTINEZ
Nicolas Horacio Bruno
Roy Kelly
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Nostromo Holdings LLC
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Nostromo Holdings LLC
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Priority claimed from PCT/US2015/019570 external-priority patent/WO2015183371A2/en
Publication of EP3117177A2 publication Critical patent/EP3117177A2/de
Publication of EP3117177A4 publication Critical patent/EP3117177A4/de
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B8/00—Practice or training ammunition
    • F42B8/02—Cartridges
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding

Definitions

  • SDZs The Surface Danger Zones
  • SRTP's Short Range Training Projectiles
  • SRTA Short Range Training Ammunition
  • SRTPs Short Range Training Projectiles
  • Patent No. 4,128,060 to Gawlick Patent No. 4,140,061 to Campoli
  • Patent No. 4,911,080 to Leeker Patent No. 5,001,986 to Meister .
  • All of these patents describe methods for modifying air-flow over the projectile body, thereby shortening the projectile's flight path.
  • European Patent Pub. No. 0,036,232 A1 to DeBrant discloses designs for SRTPs where the outer surface undergoes changes after set-back that induce an aero-ballistic drag that shortens the flight path of the ammunition. Most of these disclosed methodologies induce a linear increase in aero-ballistic drag and yaw after barrel exit.
  • a principal objective of the present invention is to provide a training ammunition cartridge where the flight path of its projectile initially matches the flight path of a reference projectile and subsequently loses stable flight characteristics, thus shortening the maximum range of the projectile.
  • the shortened maximum range can reduce the Surface Danger Zone both at the end and aside of the firing range.
  • the projectiles according to the invention are designed to initially exhibit a very close match to reference (e.g. ball) war-shot ammunition but, at a point in the training projectile's ballistic path, the liquid and, if present, the solid material in the void induces a combination of forces that quickly destabilize the projectiles' flight.
  • reference e.g. ball
  • the SRTP's allow militaries and/or private range owners to establish training ranges on smaller parcels of land. This, in turn, allows militaries to convert land previously set aside for surface danger zones to re-utilize, and/or repurpose the land set aside for small caliber shooting to train with larger weapons.
  • the AMC Pamphlet pp. 701-165 states: "For a heavy projectile filled with a comparatively small mass of liquid, the stability of problems reduces the problem of calculating the Eigen frequencies (of the liquid) and associated residues.”
  • the void geometry of the SRTA projectile induces forces on the projectile accentuating spin decay and yaw. It is also possible to configure the geometry to shift the center of gravity of the projectile to further accentuate the projectile's yaw amplitude and frequency, thereby further degrading the flight stability.
  • the selection of the void geometry identifies what design equations to utilize in predicting both stable flight and the projectile's transition to unstable flight.
  • liquids generally exhibit nine hundred times more resistance to motion when compared to that of a gas. Liquids may also exhibit a resonance that can influence objects in flight. Prior work has shown that configurations with of a projectile's liquid filled void often had an infinite set of initial boundary conditions and projectiles have frequently been troublesomely susceptible to picking up resonances which have imparted un-predictable forces that act on the projectile in flight.
  • a projectile's gyroscopic stability is achieved by optimizing the mass rotating around center of gravity and the axis of rotation.
  • a designer can, in selecting materials and geometry, shift the solid mass in a projectile to further reduce a training projectile's gyroscopic stability, further shortening its range.
  • the U.S. Army Material Command (AMC) Pamphlet 706-165 published in April 1969 and approved for release to the public in January 1972, provides an authoritative overview of the challenges associated with designing liquid filled projectiles.
  • the opening paragraph states "the problem of the unpredictable behavior of liquid-filled projectiles in flight has been known to designers for a long time.”
  • This AMC Pamphlet was published to assist Army ammunition designers in producing ammunition with payloads such as white phosphorus that, under certain conditions, could liquefy and create flight instability.
  • the AMC Pamphlet 706-165 further notes the challenge in establishing repeatable initial boundary conditions for a projectile containing a liquid.
  • the present invention allows a designer (1) to use the Miles equation to identify a liquid-filled projectile that will initially have stable flight and where forces in the projectile subsequently destabilize the flight, or (2) to firmly establish the initial boundary conditions of barrel exit by using a material that transitions from solid to liquid after set-back.
  • the change from a solid to liquid may be accomplished either by a heat-induced phase change or by the use of a Non-Newtonian liquid or dilatant.
  • the use of a Non-Newtonian liquid or dilatant does not form part of the invention as defined in claim 1.
  • the liquid in the void induces forces that destabilize the projectile's flight after an initial match period with a reference projectile.
  • the material contained in the void is a solid when it transits the barrel.
  • This solid does not retain resonance frequencies as are generally induced in liquids and which are known to be detrimental when liquid-filled ammunition exits the barrel. According to the invention, however, the material rapidly liquefies after barrel exit and, interacting with the void geometry and solid projectile body, reliably increases the yaw amplitude and frequency of the projectile. This approach provides the basis for a unique design of the projectile, causing it to become unstable in flight.
  • a selected liquid may induce desired or undesired instability when the Eigen frequency falls near the natural frequency of the liquid or nutation frequency.
  • a selected liquid may introduce a stabilizing damping effect.
  • the selection of a liquid should allow the projectile exiting the barrel to have degrees of freedom and velocities that match the desired reference projectile.
  • the present invention comprises a projectile containing a void and a select material contained in the void.
  • the material is a solid at set-back that liquefies after set-back and muzzle (barrel) exit.
  • the liquefied material initiates a combination of forces that induce instability in the projectile.
  • the instability is created after a short period of stable flight where the projectile flight path closely matches the path of a reference projectile.
  • internal geometry and characteristics of the void create friction between the liquid and solid. Properly coupled together, void geometry, liquid-solid forces and imparted resonance increase a projectile's yaw amplitude and retard the projectile's rotational frequency which, in combination, destabilize the projectile.
  • the fluid must act as a Non-Newtonian fluid under the high g-forces of acceleration.
  • Many materials that exhibit normal flow liquid characteristics under nominal conditions exhibit Non-Newtonian characteristics under the high-g forces induced at acceleration.
  • certain liquids that exhibit Non-Newtonian characteristics under g-loads may no longer exhibit Newtonian characteristics. Amplification of a liquid's natural frequency is precluded, and risks associated with associated perturbations are eliminated and initial barrel exit conditions are normalized.
  • Rheopectic liquids become more viscous when shaken, agitated or stressed.
  • Bingham plastics behave as a solid in low stress environments but exhibit viscosity under stressed conditions.
  • Shear thickening liquids exhibit increasing viscosities with increased shear stress.
  • Shear thinning liquids exhibit decreased viscosity as the shear stress is decreased.
  • Thixotropic liquids become less viscous when shaken, agitated or otherwise stressed. Dilatant or shear thickening behavior is typically observed in fluids with a high concentration of small, solid particulate suspended within a liquid.
  • dilatants then transition to a solid-like condition when a greater shear stress or force is applied.
  • dilatant materials become very rigid.
  • the projectile can utilize the heat imparted to its driving band as it progresses through the barrel and/or it can harvest heat from the pyrotechnic propellant, transferring the heat to the material in the void.
  • the resulting increase in temperature flows from the driving band and the propellant through the projectile body into the void.
  • the heated material in the void undergoes a phase change from solid to liquid.
  • the liquefied material in the void induces forces on the projectile in flight.
  • high velocity projectiles may harvest heat in flight in the vicinity of the nose. It is well known that air friction encountered by high velocity projectiles in flight transfers significant heat into the projectile s nose assembly. Therefore, in certain configurations, in is advantageous to locate a void with a liquid in the void harvesting the friction heat to induce a phase change in the material housed in the void.
  • the void can be filled with a non-Newtonian fluid which acts as a solid when exposed to high acceleration forces but exhibits the characteristics of a normal liquid in a reduced acceleration environment.
  • a non-Newtonian fluid which acts as a solid when exposed to high acceleration forces but exhibits the characteristics of a normal liquid in a reduced acceleration environment.
  • the high G-forces acting on the non-Newtonian fluid cause the fluid to act as a solid mass.
  • the non-Newtonian material acts as a liquid. This allows the design to establish a fixed set of barrel exit conditions that closely match those of a reference projectile and subsequently induce instability that shortens the projectiles flight path. In setting repeatable boundary conditions and matching the exterior form of a ball projectile, a good initial match to a ball projectile is achieved.
  • Cylindrical cavities are useful when producing ammunition since most projectiles have a basic cylindrical form with the cylinder capped by a conical nose. Forming processes for cup-shaped forms have long been a cost-effective method of metal forming in ammunition manufacture. Therefore, it is practical to produce cylindrical voids during ammunition production.
  • Stewartson's equations published in 1959, provided mathematical solutions to induce instability when a liquid is housed in a cylindrical cavity. The set of equations allows designers to design ammunition that induces predictable instability.
  • Karpov's publication of " Dynamics of Liquid Filled Shell: Resonances in Modified Cylindrical Cavities” was published in 1966 and added to this body of work.
  • non-symmetric cavities While the equations for non-symmetric cavities have less confirmatory experimentation, the basic formulas provide for a method to construct voids the induce forces to destabilize the projectile upon liquefaction of the void material.
  • a non-symmetric cavity may be designed to quickly shift the center of gravity away from the axis of rotation.
  • the designer can modify the internal geometry and surface of the void to induce either laminar or non-laminar flow of the liquid in the void. This flow increases liquid-to-solid friction, reducing the projectile's spin rate and increasing the instability in an SRTP.
  • center of gravity shifts after a short period of free flight.
  • Center of gravity shifts off-center from the axis of rotation, accentuate yaw amplitude and degrade the projectile's flight stability.
  • Suspending a dense solid in a lower density material that liquefies after set-back allows a designer the ability to shift the center of gravity of the projectile, thus inducing increased yaw.
  • Embodiments of the present invention provide for a projectile that has an excellent ballistic match (flight path) with respect to reference ammunition for the initial stage of free flight. After a set period of transit, a liquefied material in the SRTPs void imparts forces on the projectile that rapidly degrade the SRTP's flight characteristics thus shortening the projectile's maximum range.
  • Figure 1 illustrates the effective range of a reference projectile and the maximum range of this projectile.
  • Figure 2 illustrates a location along a flight path where instability is induced, shortening the maximum range of a projectile.
  • Figure 3 further illustrates the resulting ballistic match distance where a SRTP matches a reference ammunition.
  • FIG 4 illustrates how Surface Danger Zones (SDZs) are calculated, requiring military and range owners to set aside land adjacent ranges to prevent personal injury or death.
  • SDZs are extended beyond the range of the ammunition to provide for an additional buffer due to ricochet danger, and metrological and geodesic factors that extend the possible flight path of ammunition in certain circumstances.
  • a reduction in the maximum range of a projectile has a corresponding reduction in the required SDZ that must be established surrounding a range.
  • Figure 5 depicts a known aero-ballistic de-spinning projectile, together with publicly released performance data.
  • This approach is the current prevailing technical approach to produce small caliber Short Range Training Ammunition (SRTA).
  • SRTA Short Range Training Ammunition
  • This approach requires the manufacturer to carve or form a de-spin vane on the nose of the projectile.
  • the vanes may interfere with weapon function.
  • Figure 6 depicts the forces induced on a projectile with a liquid fill. According to the invention a projectile designer may adjust these forces to induce instability in the projectile and provide for a trajectory with a good ballistic match and, thereafter, with a quickly encountering instability, thus shortening the range.
  • Figure 7 depicts US Army test results showing spin decay rates induced on a 20mm projectile containing a liquid cavity.
  • Figure 8 depicts the sheer force effect of fluids.
  • Figure 9 depicts a simple thermal model of the transfer of heat into a projectile.
  • the projectile When traversing in a barrel, the projectile is heated by the hot, expanding propellant gases at the base of the projectile and is also heated by the mechanical friction of the driving band's engagement with the inner diameter of the barrel. Additionally, when a high velocity projectile exits the barrel and enters free flight the air-flow over the projectile's nose and outer surface generates friction forces that heat the projectile s nose cap. In all cases, the heat generated by friction passes through the projectile body, driving band and nose cap to the void to induce a solid-to-liquid change in the void material.
  • Figure 10 depicts a cylindrical cavity along the center of spin of a projectile, illustrating how the driving band is positioned to conduct the flow of heat to cause a change in the material.
  • Figure 11 depicts a cylindrical cavity in a projectile containing a material of the type used in the present invention.
  • Figure 12 depicts a spheroidal cavity containing a material of the type used in the present invention.
  • a designer using a spheroidal cavity can utilize Greenhill's calculations to induce rapid instability where the frequency of rotation of the projectile corresponds to the natural frequency of the liquid in the void.
  • Figure 13 depicts partially and a fully filled voids in four different projectiles.
  • Figure 13 depicts a liquid-filled, symmetric void in a projectile in three stages of flight.
  • Figures 14 to 18 depict projectiles with both symmetric and non-symmetric voids having a solid mass that is released by a phase change in the surrounding material in the void.
  • This material fixes the position of the solid mass at set-back and at successive times during flight, illustrating the solid mass's movement from a location at the center of spin to an offset location. The movement of the mass from the centerline axial position induces increases yaw that destabilizes the projectile's flight.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (4)

  1. Übungsmunitionspatrone, die ein an einem Patronengehäuse montiertes Projektil mit einem pyrotechnischen Treibmittel umfasst, wobei das Projektil einen Projektilkörper mit einer geeigneten Strukturintegrität aufweist, um Rückstoßkräfte auszuhalten, die ausgeübt werden, wenn das Projektil aus einer Pistole abgefeuert wird, wobei der Projektilkörper wenigstens eine Kammer aufweist, die einen Hohlraum bildet, wobei der Hohlraum ein Material enthält, das sich nach dem Rückstoß und nachdem das Projektil aus einem Lauf der Pistole ausgetreten ist, von einem Festkörper in eine Flüssigkeit umwandelt, wobei der Hohlraum so konfiguriert ist, dass das darin enthaltene flüssige Material Kräfte und Drehmomente induzieren kann, die nach einer Zeitspanne eines stabilen ballistischen Flugs das Projektil destabilisieren und seinen Flug abkürzen,
    dadurch gekennzeichnet, dass sich das Material, das in dem Hohlraum enthalten ist, bei Erreichen einer erhöhten Temperatur über einer Lagerungs- und Betriebstemperatur der Munitionspatrone von einem Festkörper in eine Flüssigkeit umwandelt.
  2. Munitionspatrone nach Anspruch 1, wobei das Material beim Umwandeln von einem Festkörper in eine Flüssigkeit in dem Hohlraum strömt und wobei die kombinierten Kräfte einer Reibung, die durch die Flüssigkeit, die an der inneren Hohlraumgrenzfläche wirkt, und die Eigenschwingung der Flüssigkeit mitgeteilt werden, eine Erhöhung der Gieramplitude des Projektils induzieren, wodurch die maximale Flugweite des Projektils verkürzt wird.
  3. Übungsmunitionspatrone, die ein an einem Patronengehäuse montiertes Projektil mit einem pyrotechnischen Treibmittel umfasst, wobei das Projektil einen Projektilkörper mit einer geeigneten Strukturintegrität aufweist, um Rückstoßkräfte auszuhalten, die ausgeübt werden, wenn das Projektil aus einer Pistole abgefeuert wird, wobei der Projektilkörper wenigstens eine Kammer aufweist, die einen Hohlraum bildet und eine feste Masse enthält, die freigegeben wird, um ihre Position nach dem Rückstoß und nachdem das Projektil aus einem Lauf der Pistole ausgetreten ist, zu verlagern, wobei der Hohlraum so konfiguriert ist, dass die Masse bei einer Verlagerung Kräfte und Drehmomente induzieren kann, die nach einer Zeitspanne eines stabilen ballistischen Flugs das Projektil destabilisieren und seinen Flug abkürzen;
    dadurch gekennzeichnet, dass sie ferner ein flüssiges Material umfasst, das in dem Hohlraum enthalten ist, und wobei die Masse ihre Position in dem Projektilkörper verlagert und durch das flüssige Material strömt, wodurch der Masseschwerpunkt des Projektils, wenn es nach dem Rückstoß freigegeben wird, verändert wird,
    wobei eine Bewegungsgeschwindigkeit der festen Masse durch einen Widerstand, der durch das flüssige Material mitgeteilt wird, gedämpft und verlangsamt wird.
  4. Munitionspatrone nach einem der vorhergehenden Ansprüche, wobei der Projektilkörper aus einem zerbrechlichen Material gefertigt ist, das einen Rückstoß und einen Flug überlebt, jedoch bei einem Aufprall zerbricht, wodurch ein Querschläger verhindert wird.
EP15800253.5A 2014-03-10 2015-03-10 Patrone mit induzierter instabilität bei einem voreingestellten bereich Active EP3117177B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201461950270P 2014-03-10 2014-03-10
PCT/US2015/019570 WO2015183371A2 (en) 2014-03-10 2015-03-10 Ammunition cartridge with induced instability at a pre-set range

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EP3117177A2 EP3117177A2 (de) 2017-01-18
EP3117177A4 EP3117177A4 (de) 2018-03-14
EP3117177B1 true EP3117177B1 (de) 2019-08-07

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3872438A1 (de) * 2020-02-27 2021-09-01 Albert Gaide Munitionskartusche

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4241660A (en) * 1978-10-03 1980-12-30 The United States Of America As Represented By The Secretary Of The Army Projectile
FR2717258B1 (fr) * 1994-03-08 1997-04-18 Denis Jean Pierre Cartouche à projectile de portée limitée.
DE202012010484U1 (de) * 2012-10-30 2012-11-16 Jork Meyer Geschoss mit verringertem Penetrationsvermögen

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3872438A1 (de) * 2020-02-27 2021-09-01 Albert Gaide Munitionskartusche
WO2021170633A1 (en) * 2020-02-27 2021-09-02 Albert Gaide Ammunition cartridge

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DK3117177T3 (da) 2019-11-11
EP3117177A4 (de) 2018-03-14
EP3117177A2 (de) 2017-01-18

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