US20130014667A1 - Propellant gas operation/initiation of a non-pyrotechnic projectile tracer - Google Patents
Propellant gas operation/initiation of a non-pyrotechnic projectile tracer Download PDFInfo
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- US20130014667A1 US20130014667A1 US13/444,743 US201213444743A US2013014667A1 US 20130014667 A1 US20130014667 A1 US 20130014667A1 US 201213444743 A US201213444743 A US 201213444743A US 2013014667 A1 US2013014667 A1 US 2013014667A1
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- Prior art keywords
- ampoule
- tracer
- projectile
- chemiluminescent
- cavity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000000700 radioactive tracer Substances 0.000 title claims abstract description 60
- 239000003380 propellant Substances 0.000 title abstract description 10
- 230000000977 initiatory effect Effects 0.000 title abstract description 4
- 239000003708 ampul Substances 0.000 claims abstract description 56
- 230000007246 mechanism Effects 0.000 claims description 5
- 230000005855 radiation Effects 0.000 claims description 4
- 239000000126 substance Substances 0.000 abstract description 7
- 239000007788 liquid Substances 0.000 abstract description 6
- 238000010304 firing Methods 0.000 description 7
- 239000007789 gas Substances 0.000 description 6
- 230000004913 activation Effects 0.000 description 5
- 230000001133 acceleration Effects 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 3
- NIOPZPCMRQGZCE-WEVVVXLNSA-N 2,4-dinitro-6-(octan-2-yl)phenyl (E)-but-2-enoate Chemical compound CCCCCCC(C)C1=CC([N+]([O-])=O)=CC([N+]([O-])=O)=C1OC(=O)\C=C\C NIOPZPCMRQGZCE-WEVVVXLNSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 239000012190 activator Substances 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 229910052594 sapphire Inorganic materials 0.000 description 2
- 239000010980 sapphire Substances 0.000 description 2
- 239000000565 sealant Substances 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 230000000638 stimulation Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 239000012780 transparent material Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/38—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of tracer type
- F42B12/382—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of tracer type emitting an electromagnetic radiation, e.g. laser beam or infrared emission
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/38—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of tracer type
Definitions
- the present invention is related to projectile tracer assemblies, and more particularly to non-pyrotechnic projectile tracer assemblies and related methods.
- Base-mounted tracers for gun-launched projectiles have traditionally been characterized by the use of pyrotechnic compounds that are ignited/initiated by the act of firing the projectile.
- the hot propellant gases come into contact with and ignite the tracer's pyrotechnic compounds.
- the tracer marks the projectile's trajectory by virtue of the combusting pyrotechnic tracer compound.
- tracers are pyrotechnic in nature, they present a potential fire hazard during employment, particularly on firing ranges during training operations. This issue is addressed by the use of non-pyrotechnic tracer elements such as liquid bi-chemical chemiluminescent elements (U.S. Pat. No. 6,990,905).
- chemiluminescent systems consist of two liquid chemicals that when brought together in intimate contact experience a reaction, the products of which are visible light and infrared energy. Initially, the two chemicals are kept separate by the use of special/frangible containers (transparent or equipped with a transparent section) positioned coaxially one inside the other.
- the rupturing of the container(s) is accomplished by subjecting the projectile to stimulation at the desired time of tracer activation, typically launch and/or target impact.
- Launch stimuli may be predicated upon acceleration (setback) of the projectile, spin-up of spin-stabilized projectiles in guns that are rifled, and deceleration (set forward) of the projectile as it emerges from the gun's barrel (ending acceleration) and encounters open air.
- These stimuli act upon designed mechanisms, such as inertia masses (US Patent Application Publication No. 2010/0175577), to rupture the container(s).
- Embodiments of the invention provide a non-pyrotechnic projectile tracer, such as an ammunition round with chemiluminescent tracer portion configured for propellant gas operation or initiation of the non-pyrotechnic tracer material upon firing.
- a non-pyrotechnic projectile tracer such as an ammunition round with chemiluminescent tracer portion configured for propellant gas operation or initiation of the non-pyrotechnic tracer material upon firing.
- FIG. 1 is a cross-sectional side view of a projectile having a tracer configured in accordance with embodiments of the disclosure.
- FIG. 2 is a cross-sectional side view of a projectile having a tracer with a piston-activator configured in accordance with embodiments of the disclosure.
- FIG. 3 is a cross-sectional side view of a small-caliber projectile having a tracer configured in accordance with embodiments of the disclosure.
- FIG. 1 is a cross-sectional side view of a projectile 100 having a tracer 110 configured in accordance with embodiments of the disclosure.
- the tracer 110 includes an outer cylindrical ampoule 112 positioned within a tracer cavity 114 .
- the outer ampoule 112 is non-frangible when the projectile is fired from a gun or other launching mechanism.
- the illustrated outer ampoule 112 has an open internally-threaded end 116 and an opposite closed end 118 with a pronounced protrusion 120 .
- the outer ampoule 112 is positioned on an aft end 122 of the projectile 100 such that the protrusion 120 on the outer ampoule 112 is bearing against a blind end 124 of the projectile tracer cavity 114 .
- the tracer 110 includes an externally threaded stepped closure 126 equipped with a central window 128 constructed of a rugged, high temperature resistant material, such as sapphire.
- the window 128 can be substantially transparent to visible and/or infrared radiation.
- the stepped closure 126 can have threads to match the outer ampoule 112 .
- the tracer 110 further includes an inner frangible cylindrical ampoule 130 positioned longitudinally within the outer ampoule 112 , the inner ampoule 130 having a first end 132 bearing against the outer ampoule protrusion 120 and a second end 134 opposite the first end 132 and proximate to the central window 128 .
- the outer ampoule 112 can contain a first chemiluminescent component and the inner ampoule 130 can contain a second chemiluminescent component.
- the tracer 110 can further include an externally threaded capture ring 136 (threaded to match the designated projectile interface) whose central hole can permit a smooth sliding fit with the stepped closure 126 .
- the capture ring 136 can include an internal sliding seal that bears upon the smaller diameter section of the stepped closure 126 .
- the entire outer ampoule 112 is sized to be a sliding fit in the projectile's tracer cavity 114 .
- the tracer 110 is secured in the projectile 100 by the capture ring 136 external threads mating up with the projectile tracer cavity 114 internal threads.
- the projectile 100 comprises a medium (i.e., 20-75 mm) or large caliber (75 mm and larger) direct fire ammunition.
- the tracer 110 activation sequence is as follows: upon firing, the cartridge primer ignites the main propelling charge which generates the propelling gasses. As the cartridge internal pressure rapidly increases, the cartridge internal pressure bears against all exposed surfaces (the cartridge case internal surfaces and the projectile 100 base) including the smaller diameter section of the stepped tracer closure 126 with the tracer transparent window 128 . The propelling gas pressure force generated on the stepped tracer closure column 126 loads the tracer outer ampoule 112 , which in turn passes the column load against the closed end protrusion 120 that in turn bears against the blind end 124 of the projectile tracer cavity 114 . At a predetermined pressure value, the protrusion 120 is loaded to the point where it collapses, crushing the frangible inner ampoule 130 .
- This action frees the two liquid chemiluminescent chemicals to come into contact and react in a luminescent reaction, while maintaining a liquid-tight integrity.
- the radiation released from this reaction escapes from the outer ampoule 112 through the transparent window 128 facing aft towards the gunner.
- the forward sliding motion of the outer ampoule 112 is arrested when the outer ampoule 112 is crushed to the point where the two liquid chemicals are hydraulically compressed, halting the forward motion of the outer ampoule 112 .
- a physical/mechanical motion limiting/stop feature (not illustrated) can also be utilized.
- the tracer 110 is accordingly activated independent of the motion of the projectile 100 , (including projectile acceleration/setback, spin-up, and deceleration/set-forward/impact).
- FIG. 2 is a cross-sectional side view of a projectile 200 having a tracer 210 with a piston-activator 240 configured in accordance with embodiments of the disclosure.
- the projectile 200 includes several features generally similar to those described with reference to FIG. 1 , including an inner ampoule 230 positioned within an outer ampoule 212 within a projectile tracer cavity 214 .
- the inner ampoule 230 is positioned against an outer ampoule protrusion 220 as described above with reference to FIG. 1 .
- the tracer 210 is shielded from the propellant gasses by a stepped piston 240 , the smaller diameter of which bears against an aft surface 242 of the outer ampoule 212 , leaving the larger diameter's aft end 244 to be acted upon by the propellant gasses.
- the whole piston 240 is supported by the projectile's aft end or drag cone/fin 252 .
- a plurality of small equalizing ports/holes 246 is positioned in a tapered forward-facing end 248 of a projectile drag cone/fin 252 that communicates with the stepped diameter of the piston 240 .
- the piston 240 is held in position by a plurality of shear pins 250 arranged radially around the periphery of the piston's larger diameter and anchored in the projectile aft end or drag cone/fin 252 .
- the sheer pins 250 are configured to securely maintain the piston's position and prevent activation of the tracer 210 prior to firing of the projectile, such as during rough handling and/or transport.
- the shear pins 250 are configured so they will shear and release the piston upon application of very high loads applied on the piston by the pressurized gas generated upon firing of the projectile.
- the piston 240 is positioned in the projectile's aft end or drag cone/fin 252 such that the force of the propellant gasses can push the piston 240 forward a calculated distance after first shearing the shear pins 250 .
- the propellant gasses provide approximately 82,000 pounds psi of force at launch.
- the moving piston 240 transmits this force to the tracer ampoule 212 causing it to move forward as well. This forward motion crushes the outer ampoule protrusion 220 and initiates the tracer action in a manner similar to the embodiment described above with reference to FIG. 1 .
- the forward motion of the projectile 200 causes a near vacuum/low-pressure area to be established at the projectile's aft end or drag cone/fin 252 as well as air to be forced into the forward facing equalizing ports 246 .
- This near vacuum/low pressure acting upon the aft face of the large diameter section of the piston 240 coupled with air pressure on the forward surface of the stepped section of the piston 240 from the air entering the forward facing equalizing ports 246 , results in a force to effect the separation of the piston 240 from the projectile 200 .
- This separation unmasks the functioning tracer 210 .
- FIG. 3 is a cross-sectional side view of a small-caliber projectile 300 having a tracer 310 configured in accordance with embodiments of the disclosure.
- the projectile 300 includes several features generally similar to those described above with reference to FIGS. 1 and 2 .
- the projectile 300 has a tubular aft end 344 in which is positioned a metallic cylindrical liner 360 .
- the liner 360 can be steel or an alloy of steel.
- the liner 360 serves as a re-enforcing element to maintain projectile integrity upon the spin-stabilized projectile's 300 exit from the barrel as centrifugal forces act upon the chemiluminescent payload to burst the projectile 300 .
- a frangible inner ampoule 330 containing one of the chemiluminescent components is positioned within the liner 360 .
- the frangible ampoule 330 has a smaller diameter than the inside diameter of the metallic liner 360 and its forward end 362 is nested into a centrally-located depression 364 .
- the inner ampoule 330 is long enough so that when seated into the projectile 300 , an aft end 366 projects slightly from an aft end 368 of the metallic liner 360 ; i.e., the inner ampoule 330 is slightly longer than the metallic liner 360 .
- a transparent lens 328 manufactured from a tough heat and shock resistant transparent material (such as, for example, artificial sapphire as commonly used with scratch-proof watch crystals), is treated with a sealant on its periphery then positioned in the base of the projectile 300 , in effect sealing the aft open end 344 of the projectile 300 .
- the lens 328 is held in this position by the sealant as well as a cannelure/crimp groove 372 impressed on the projectile's outer surface 374 .
- the cannelure 372 is configured to maintain the lens' 328 position and prevent activation of the tracer 310 during handling and transport.
- the lens 328 is secured by rolling the aft open end 344 of the projectile copper jacket 374 over the aft outer edge of the lens 328 .
- the projectile 300 is a small-caliber ammunition, such as 5.56 mm ⁇ 45 (.22-caliber), 7.62 mm ⁇ 51 (.30-caliber), 12.7 mm ⁇ 99 (.50 caliber Browning Machine Gun), and up to 20 mm caliber.
- the tracer 310 functions at firing by the lens 328 being moved forward by the propelling gas pressure acting upon it. During this slight forward motion, independent of the projectile 300 , the lens 328 first overcomes the cannelure 372 then fractures the internal frangible ampoule 330 , allowing the chemiluminescent components to mix and fluoresce. In some embodiments, the lens 328 can make contact with the aft end 368 of the metallic liner 360 shortly before the lens 328 comes into light contact with the aft end 366 of the frangible ampoule 330 . The small air space in the annular chemiluminescent component 370 enables the slight forward motion of the lens 328 without the hydraulic resistance should the chemiluminescent components become solidly compressed.
- the lens' 328 forward motion is halted by the lens 328 outer periphery encountering the annular aft end 368 of the metallic liner 360 .
- the radiation liberated by the chemiluminescent payload escapes rearward from the projectile 300 through the transparent lens 328 to be seen by the weapon's gunner/spotter.
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Abstract
The present disclosure is directed to propellant gas initiation of a non-pyrotechnic projectile tracer. In some embodiments, cartridge-propellant gasses act upon a piston to break a frangible chemiluminescent liquid chemical ampoule to initiate a luminous reaction independently of and prior to any projectile motion. The piston may be a distinct piston, a separate component functioning as a piston, or the overall tracer container acting in the manner of a piston. Embodiments of the disclosure are applicable to direct-fire ammunition ranging from small arms through large caliber main battle tank ammunition.
Description
- This application claims priority to and the benefit of U.S. Provisional Patent Application No. 61/474,582, filed Apr. 12, 2011 and titled PROPELLANT GAS OPERATION/INITIATION OF A NON-PYROTECHNIC PROJECTILE TRACER, which is incorporated in its entirety herein by reference thereto.
- The present invention is related to projectile tracer assemblies, and more particularly to non-pyrotechnic projectile tracer assemblies and related methods.
- Base-mounted tracers for gun-launched projectiles have traditionally been characterized by the use of pyrotechnic compounds that are ignited/initiated by the act of firing the projectile. The hot propellant gases come into contact with and ignite the tracer's pyrotechnic compounds. Upon the projectile's exit from the launching gun and for a portion of or all of the projectile's flight, the tracer marks the projectile's trajectory by virtue of the combusting pyrotechnic tracer compound.
- Because tracers are pyrotechnic in nature, they present a potential fire hazard during employment, particularly on firing ranges during training operations. This issue is addressed by the use of non-pyrotechnic tracer elements such as liquid bi-chemical chemiluminescent elements (U.S. Pat. No. 6,990,905). Typically, chemiluminescent systems consist of two liquid chemicals that when brought together in intimate contact experience a reaction, the products of which are visible light and infrared energy. Initially, the two chemicals are kept separate by the use of special/frangible containers (transparent or equipped with a transparent section) positioned coaxially one inside the other. Upon activation, one or both of these special/frangible containers is ruptured, thus allowing the two liquid chemicals to come into contact with each other and start the reaction. The rupturing of the container(s) is accomplished by subjecting the projectile to stimulation at the desired time of tracer activation, typically launch and/or target impact. Launch stimuli may be predicated upon acceleration (setback) of the projectile, spin-up of spin-stabilized projectiles in guns that are rifled, and deceleration (set forward) of the projectile as it emerges from the gun's barrel (ending acceleration) and encounters open air. These stimuli act upon designed mechanisms, such as inertia masses (US Patent Application Publication No. 2010/0175577), to rupture the container(s).
- The present invention overcomes drawbacks experienced in the prior art and provides other benefits. Embodiments of the invention provide a non-pyrotechnic projectile tracer, such as an ammunition round with chemiluminescent tracer portion configured for propellant gas operation or initiation of the non-pyrotechnic tracer material upon firing.
-
FIG. 1 is a cross-sectional side view of a projectile having a tracer configured in accordance with embodiments of the disclosure. -
FIG. 2 is a cross-sectional side view of a projectile having a tracer with a piston-activator configured in accordance with embodiments of the disclosure. -
FIG. 3 is a cross-sectional side view of a small-caliber projectile having a tracer configured in accordance with embodiments of the disclosure. -
FIG. 1 is a cross-sectional side view of aprojectile 100 having atracer 110 configured in accordance with embodiments of the disclosure. Thetracer 110 includes an outercylindrical ampoule 112 positioned within atracer cavity 114. In one embodiment, theouter ampoule 112 is non-frangible when the projectile is fired from a gun or other launching mechanism. The illustratedouter ampoule 112 has an open internally-threadedend 116 and an opposite closedend 118 with apronounced protrusion 120. Theouter ampoule 112 is positioned on anaft end 122 of theprojectile 100 such that theprotrusion 120 on theouter ampoule 112 is bearing against ablind end 124 of theprojectile tracer cavity 114. Thetracer 110 includes an externally threadedstepped closure 126 equipped with acentral window 128 constructed of a rugged, high temperature resistant material, such as sapphire. Thewindow 128 can be substantially transparent to visible and/or infrared radiation. Thestepped closure 126 can have threads to match theouter ampoule 112. Thetracer 110 further includes an inner frangiblecylindrical ampoule 130 positioned longitudinally within theouter ampoule 112, theinner ampoule 130 having afirst end 132 bearing against theouter ampoule protrusion 120 and asecond end 134 opposite thefirst end 132 and proximate to thecentral window 128. Theouter ampoule 112 can contain a first chemiluminescent component and theinner ampoule 130 can contain a second chemiluminescent component. - The
tracer 110 can further include an externally threaded capture ring 136 (threaded to match the designated projectile interface) whose central hole can permit a smooth sliding fit with thestepped closure 126. Thecapture ring 136 can include an internal sliding seal that bears upon the smaller diameter section of thestepped closure 126. The entireouter ampoule 112 is sized to be a sliding fit in the projectile'stracer cavity 114. Thetracer 110 is secured in theprojectile 100 by thecapture ring 136 external threads mating up with theprojectile tracer cavity 114 internal threads. When assembled, theouter ampoule 112 is captured in theprojectile tracer cavity 114 by thecapture ring 136 with theouter ampoule protrusion 120 bearing against the blind closedend 124 of theprojectile tracer cavity 114 and thetransparent window 128 exposed and flush with the aft end of thecapture ring 136. In some embodiments, theprojectile 100 comprises a medium (i.e., 20-75 mm) or large caliber (75 mm and larger) direct fire ammunition. - The
tracer 110 activation sequence is as follows: upon firing, the cartridge primer ignites the main propelling charge which generates the propelling gasses. As the cartridge internal pressure rapidly increases, the cartridge internal pressure bears against all exposed surfaces (the cartridge case internal surfaces and theprojectile 100 base) including the smaller diameter section of thestepped tracer closure 126 with the tracertransparent window 128. The propelling gas pressure force generated on the steppedtracer closure column 126 loads the tracerouter ampoule 112, which in turn passes the column load against the closedend protrusion 120 that in turn bears against theblind end 124 of theprojectile tracer cavity 114. At a predetermined pressure value, theprotrusion 120 is loaded to the point where it collapses, crushing the frangibleinner ampoule 130. This action frees the two liquid chemiluminescent chemicals to come into contact and react in a luminescent reaction, while maintaining a liquid-tight integrity. The radiation released from this reaction (visible and/or infrared) escapes from theouter ampoule 112 through thetransparent window 128 facing aft towards the gunner. The forward sliding motion of theouter ampoule 112 is arrested when theouter ampoule 112 is crushed to the point where the two liquid chemicals are hydraulically compressed, halting the forward motion of theouter ampoule 112. In some embodiments, a physical/mechanical motion limiting/stop feature (not illustrated) can also be utilized. Thetracer 110 is accordingly activated independent of the motion of theprojectile 100, (including projectile acceleration/setback, spin-up, and deceleration/set-forward/impact). -
FIG. 2 is a cross-sectional side view of aprojectile 200 having atracer 210 with a piston-activator 240 configured in accordance with embodiments of the disclosure. Theprojectile 200 includes several features generally similar to those described with reference toFIG. 1 , including aninner ampoule 230 positioned within anouter ampoule 212 within aprojectile tracer cavity 214. Theinner ampoule 230 is positioned against anouter ampoule protrusion 220 as described above with reference toFIG. 1 . In this embodiment, thetracer 210 is shielded from the propellant gasses by astepped piston 240, the smaller diameter of which bears against anaft surface 242 of theouter ampoule 212, leaving the larger diameter'saft end 244 to be acted upon by the propellant gasses. Thewhole piston 240 is supported by the projectile's aft end or drag cone/fin 252. A plurality of small equalizing ports/holes 246 is positioned in a tapered forward-facingend 248 of a projectile drag cone/fin 252 that communicates with the stepped diameter of thepiston 240. Thepiston 240 is held in position by a plurality ofshear pins 250 arranged radially around the periphery of the piston's larger diameter and anchored in the projectile aft end or drag cone/fin 252. Thesheer pins 250 are configured to securely maintain the piston's position and prevent activation of thetracer 210 prior to firing of the projectile, such as during rough handling and/or transport. Theshear pins 250, however, are configured so they will shear and release the piston upon application of very high loads applied on the piston by the pressurized gas generated upon firing of the projectile. - The
piston 240 is positioned in the projectile's aft end or drag cone/fin 252 such that the force of the propellant gasses can push thepiston 240 forward a calculated distance after first shearing theshear pins 250. In some operational settings, the propellant gasses provide approximately 82,000 pounds psi of force at launch. The movingpiston 240 transmits this force to thetracer ampoule 212 causing it to move forward as well. This forward motion crushes theouter ampoule protrusion 220 and initiates the tracer action in a manner similar to the embodiment described above with reference toFIG. 1 . Upon shot exit from the gun barrel and after theprojectile 200 transitions the muzzle shock bottle phenomenon, the forward motion of theprojectile 200 causes a near vacuum/low-pressure area to be established at the projectile's aft end or drag cone/fin 252 as well as air to be forced into the forward facing equalizingports 246. This near vacuum/low pressure acting upon the aft face of the large diameter section of thepiston 240, coupled with air pressure on the forward surface of the stepped section of thepiston 240 from the air entering the forward facing equalizingports 246, results in a force to effect the separation of thepiston 240 from the projectile 200. This separation unmasks the functioningtracer 210. -
FIG. 3 is a cross-sectional side view of a small-caliber projectile 300 having atracer 310 configured in accordance with embodiments of the disclosure. The projectile 300 includes several features generally similar to those described above with reference toFIGS. 1 and 2 . In this embodiment, the projectile 300 has a tubularaft end 344 in which is positioned a metalliccylindrical liner 360. In some embodiments, theliner 360 can be steel or an alloy of steel. Theliner 360 serves as a re-enforcing element to maintain projectile integrity upon the spin-stabilized projectile's 300 exit from the barrel as centrifugal forces act upon the chemiluminescent payload to burst the projectile 300. A frangibleinner ampoule 330 containing one of the chemiluminescent components is positioned within theliner 360. Thefrangible ampoule 330 has a smaller diameter than the inside diameter of themetallic liner 360 and itsforward end 362 is nested into a centrally-locateddepression 364. In some embodiments, theinner ampoule 330 is long enough so that when seated into the projectile 300, anaft end 366 projects slightly from anaft end 368 of themetallic liner 360; i.e., theinner ampoule 330 is slightly longer than themetallic liner 360. Anannular space 370 between thefrangible ampoule 330 and the inside diameter of themetallic liner 360 is nearly filled with the second chemiluminescent component leaving a small air space. Atransparent lens 328 manufactured from a tough heat and shock resistant transparent material (such as, for example, artificial sapphire as commonly used with scratch-proof watch crystals), is treated with a sealant on its periphery then positioned in the base of the projectile 300, in effect sealing the aftopen end 344 of the projectile 300. Thelens 328 is held in this position by the sealant as well as a cannelure/crimp groove 372 impressed on the projectile'souter surface 374. Thecannelure 372 is configured to maintain the lens' 328 position and prevent activation of thetracer 310 during handling and transport. Lastly, thelens 328 is secured by rolling the aftopen end 344 of theprojectile copper jacket 374 over the aft outer edge of thelens 328. In some embodiments, the projectile 300 is a small-caliber ammunition, such as 5.56 mm×45 (.22-caliber), 7.62 mm×51 (.30-caliber), 12.7 mm×99 (.50 caliber Browning Machine Gun), and up to 20 mm caliber. - The
tracer 310 functions at firing by thelens 328 being moved forward by the propelling gas pressure acting upon it. During this slight forward motion, independent of the projectile 300, thelens 328 first overcomes thecannelure 372 then fractures the internalfrangible ampoule 330, allowing the chemiluminescent components to mix and fluoresce. In some embodiments, thelens 328 can make contact with theaft end 368 of themetallic liner 360 shortly before thelens 328 comes into light contact with theaft end 366 of thefrangible ampoule 330. The small air space in theannular chemiluminescent component 370 enables the slight forward motion of thelens 328 without the hydraulic resistance should the chemiluminescent components become solidly compressed. The lens' 328 forward motion is halted by thelens 328 outer periphery encountering the annularaft end 368 of themetallic liner 360. The radiation liberated by the chemiluminescent payload escapes rearward from the projectile 300 through thetransparent lens 328 to be seen by the weapon's gunner/spotter. - From the foregoing, it will be appreciated that specific embodiments of the invention have been described herein for purposes of illustration, but that various modifications may be made without deviating from the scope of the invention. Accordingly, the invention is not limited except as by the appended claims.
Claims (2)
1. A projectile having a chemiluminescent tracer and being fireable from a launching mechanism, comprising:
a tracer having a tracer cavity and a threaded stepped closure with a central window substantially transparent to visible and/or infrared radiation, the stepped closure having first threads;
an outer ampoule positioned within the tracer cavity, the ampoule containing a first chemiluminescent component and being non-frangible when the projectile is fired from a launching mechanism, the outer ampoule has an open end and a closed end opposite the open end, the closed end having a pronounced protrusion, the outer ampoule is positioned on an aft end of the projectile such that the protrusion is bearing against a blind end of the projectile tracer cavity;
a frangible cylindrical inner ampoule positioned longitudinally within the outer ampoule, the inner ampoule containing a second chemiluminescent component and having a first end bearing against the outer ampoule protrusion and a second end opposite the first end and proximate to the central window;
an externally threaded capture ring having a central hole that permits a smooth sliding fit with the stepped closure, the capture ring having a internal sliding seal that bears upon a smaller diameter section of the stepped closure, and wherein the entire outer ampoule is sized to be a sliding fit in the projectile's tracer cavity, the tracer having external second threads that mate with the first threads of the stepped closure;
wherein the outer ampoule protrusion bears against the blind closed end of the projectile tracer cavity and the transparent window is exposed and flush with the aft end of the capture ring such that chemiluminescent light generated upon mixing of the first and second chemiluminescent components after the inner ampoule breaks can be seen through the transparent window.
2. A projectile having a chemiluminescent tracer, comprising:
a tracer having a tracer cavity and a closure with a central window;
a first ampoule in the tracer cavity and containing a first chemiluminescent component, the first ampoule being configured to remain in tact when the projectile is fired from a launching mechanism, the first ampoule having a closed end opposite with a protrusion bearing against the tracer cavity;
a frangible second ampoule positioned longitudinally within the first ampoule, the second ampoule containing a second chemiluminescent component that will generate light when mixed with the first chemiluminescent component, the second ampoule having a first end bearing against the protrusion and a second end opposite the first end and proximate to the central window;
a capture ring having an internal sliding seal that bears upon a smaller diameter section of the stepped closure, and wherein the entire outer ampoule is sized to be a sliding fit in the tracer cavity;
wherein the transparent window is exposed and flush with the aft end of the capture ring such that the chemiluminescent light generated upon mixing of the first and second chemiluminescent components after the second ampoule breaks can be seen through the transparent window.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/444,743 US20130014667A1 (en) | 2011-04-12 | 2012-04-11 | Propellant gas operation/initiation of a non-pyrotechnic projectile tracer |
US14/205,244 US20140196626A1 (en) | 2011-04-12 | 2014-03-11 | Propellant gas operation/initiation of a non-pyrotechnic projectile tracer |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201161474582P | 2011-04-12 | 2011-04-12 | |
US13/444,743 US20130014667A1 (en) | 2011-04-12 | 2012-04-11 | Propellant gas operation/initiation of a non-pyrotechnic projectile tracer |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/205,244 Continuation US20140196626A1 (en) | 2011-04-12 | 2014-03-11 | Propellant gas operation/initiation of a non-pyrotechnic projectile tracer |
Publications (1)
Publication Number | Publication Date |
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US20130014667A1 true US20130014667A1 (en) | 2013-01-17 |
Family
ID=47518167
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/444,743 Abandoned US20130014667A1 (en) | 2011-04-12 | 2012-04-11 | Propellant gas operation/initiation of a non-pyrotechnic projectile tracer |
US14/205,244 Abandoned US20140196626A1 (en) | 2011-04-12 | 2014-03-11 | Propellant gas operation/initiation of a non-pyrotechnic projectile tracer |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
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US14/205,244 Abandoned US20140196626A1 (en) | 2011-04-12 | 2014-03-11 | Propellant gas operation/initiation of a non-pyrotechnic projectile tracer |
Country Status (2)
Country | Link |
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US (2) | US20130014667A1 (en) |
WO (1) | WO2013133854A1 (en) |
Cited By (4)
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US20150083012A1 (en) * | 2011-07-20 | 2015-03-26 | Enrico R. Mutascio | Rear ejection impact marking ammunition assembly |
US10921104B1 (en) * | 2019-10-28 | 2021-02-16 | Kyle Pittman | Rotation inhibited projectile tip |
CN115060121A (en) * | 2022-07-01 | 2022-09-16 | 西北工业大学 | Air suction type gas-solid mixed collimator |
CN115289914A (en) * | 2022-07-28 | 2022-11-04 | 西安现代控制技术研究所 | Speed reducer with windward nest for high-speed flight |
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Publication number | Priority date | Publication date | Assignee | Title |
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EP3940331A1 (en) * | 2020-07-16 | 2022-01-19 | BAE SYSTEMS plc | Non-incendiary tracers |
EP4182627A1 (en) | 2020-07-16 | 2023-05-24 | BAE SYSTEMS plc | Non-incendiary tracers |
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CN115289914A (en) * | 2022-07-28 | 2022-11-04 | 西安现代控制技术研究所 | Speed reducer with windward nest for high-speed flight |
Also Published As
Publication number | Publication date |
---|---|
US20140196626A1 (en) | 2014-07-17 |
WO2013133854A1 (en) | 2013-09-12 |
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