CA1327913C - Non-ricocheting projectile and method of making same - Google Patents
Non-ricocheting projectile and method of making sameInfo
- Publication number
- CA1327913C CA1327913C CA000592121A CA592121A CA1327913C CA 1327913 C CA1327913 C CA 1327913C CA 000592121 A CA000592121 A CA 000592121A CA 592121 A CA592121 A CA 592121A CA 1327913 C CA1327913 C CA 1327913C
- Authority
- CA
- Canada
- Prior art keywords
- projectile
- practice
- density
- sintered
- practice projectile
- 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.)
- Expired - Fee Related
Links
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
- F42B12/72—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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Powder Metallurgy (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE
A practice projectile for use with military aircraft and the like for training pilots in attacking ground targets comprises a unitary body formed of sintered sponge iron powder and having a sintered density equivalent to the apparent density of a projectile to be simulated.
A practice projectile for use with military aircraft and the like for training pilots in attacking ground targets comprises a unitary body formed of sintered sponge iron powder and having a sintered density equivalent to the apparent density of a projectile to be simulated.
Description
--"` 13~7~13 The present invention relates to a practice projectile or missile and, specifically, to a non-ricocheting practice projectile for aircraft.
BACKGROUND OF THE INVENTION
For several years, the Canadian Forces have been using the 2()-mm M55A2 TP projectile for training pilots in attacking ground targets. The practice projectile consists of a main steel body having a copper driving band and an aluminum nose cap. Air operations, flight safety and technical staff of Air Command are becoming increasingly concerned with the ricochet hazards to aircraft during training gunnery missions, particularly when tactical target areas are used and also during the winter months when air weapon ranges cannot be sanitized of spent projectiles. Many Canadian Forces aircrafts have been damaged by projectile ricochet strikes resulting in a significant financialloss, not to mention the loss of operational aircraft during the period of repair, and the potential of destroying the aircraft and killing its air crew.
There is a need, therefore, for target practice projectile for air to gro~lnd use which will appreciably reduce, if not completely eliminate, the ricochet hazards to the aircraft during air to ground training gunnery missions. There are at least two ways of eliminating ricochet hazards. The first method is to have the projectile penetrate the target (in the present case, the ~ro~lnd) in which all of the energy of the projectile is dissipated during penetration. The second method is to have the projectile break-up on impact into relatiYely smallfragments so that the non-aerodynamic shape of the fragments red~lce tlle ricochet envelope and thus minimize the hazard to the aircraft.
Penetration of the projectile into the target is not always possib]e to achieve because of the high degree of obliquity used during air to ground gunnery missions where the dive angle can be as low as 5. Also, the conditions of the ground impact area are not necessarily the same for different ranges an(lare greatly affected by the local meteorological conditions: the soil can be wetor dry, relatively hard or soft, frozen or it can be contaminated with pieces otrocks or spent projectiles. Because of all of these variables, it is virt~lally - .. .. : .
, . ,- .
1327~13 "~
BACKGROUND OF THE INVENTION
For several years, the Canadian Forces have been using the 2()-mm M55A2 TP projectile for training pilots in attacking ground targets. The practice projectile consists of a main steel body having a copper driving band and an aluminum nose cap. Air operations, flight safety and technical staff of Air Command are becoming increasingly concerned with the ricochet hazards to aircraft during training gunnery missions, particularly when tactical target areas are used and also during the winter months when air weapon ranges cannot be sanitized of spent projectiles. Many Canadian Forces aircrafts have been damaged by projectile ricochet strikes resulting in a significant financialloss, not to mention the loss of operational aircraft during the period of repair, and the potential of destroying the aircraft and killing its air crew.
There is a need, therefore, for target practice projectile for air to gro~lnd use which will appreciably reduce, if not completely eliminate, the ricochet hazards to the aircraft during air to ground training gunnery missions. There are at least two ways of eliminating ricochet hazards. The first method is to have the projectile penetrate the target (in the present case, the ~ro~lnd) in which all of the energy of the projectile is dissipated during penetration. The second method is to have the projectile break-up on impact into relatiYely smallfragments so that the non-aerodynamic shape of the fragments red~lce tlle ricochet envelope and thus minimize the hazard to the aircraft.
Penetration of the projectile into the target is not always possib]e to achieve because of the high degree of obliquity used during air to ground gunnery missions where the dive angle can be as low as 5. Also, the conditions of the ground impact area are not necessarily the same for different ranges an(lare greatly affected by the local meteorological conditions: the soil can be wetor dry, relatively hard or soft, frozen or it can be contaminated with pieces otrocks or spent projectiles. Because of all of these variables, it is virt~lally - .. .. : .
, . ,- .
1327~13 "~
impossible to design a practice projectile that will always penetrate the targetduring air to ground training gunnery missions.
SUMMARY OF THE INVENTION
The present invention provides a frangible practice projectile manufactured by powder metallurgy techniques in such a manner that the projectile will sustain the load and stresses induced by gun launch and free fl;ght but which will shatter at impact.
In accordance with one aspect of the present invention, there is provided a practice projectile for use with military aircraft and the like for training pilots in attacking ground targets, the projectile comprising a unitary body formed ot`sintered sponge iron powder and having a sintered density eqllivalent to the apparent density of a projectile to be simulated.
In accordance with another aspect of the present invention, there is provided a method of making a practice projectile for use with military aircrattand the like for training pilots in attacking ground targets. The method comprises the steps of compacting sponge iron powder in a mould hclving approximately the final shape of the projectile to form a cold compacted body, heating the cold compacted body in a furnace at a temperature which is less than the melting point of the powder for a predetermined time period of time in an atmosphere comprised of 95% Nitrogen and 5% Hydrogen to form .
heated solid body, and allowing the heated solid body to cool in the fl~rnace.
, . ~
1327~ 3 BR~EF DESCRIPTION OF THE DRAWINGS
These and other features of the invention will become more apparent from the following description in which reference is made to the appended drawing wherein:
S FIGURE 1 is a side elevational view, partially in section, of an M55A2 20-mm conventional practice projectile; and FIGURE 2 is a side elevational ~iew similar to FIGURE 1 of a practice projectile according one embodiment of the present invention.
DESCRIPTION OF PREFERRED EMBODIMENT
FIGURE 1 illustrates a standard MSSA2 20-mm pr~ctice projecti]e 10 having a hollow steel body 12 and an integral base 14, a copper driving band 16 circumferentially crimped onto body 12 near base 14 and an aluminum nose 18 pressed into the open end of the body remote from the base. The apparent density of this projectile is about 5.35 g/cc. This target practice proje~;tile is not designed to break-up upon impact; indeed, this type of structure is very resistant to compressive and tensile stresses. Theoretical analysis has shown that the compressive stresses imposed on the body are close to the yield strength of the material when the pressure behind the projectile reaches its maxim~lm d~lring launch but fall to almost zero in free flight. On the other hand, the tensile stresses increase with the spin rate and reach a maximum level at the muzzle of the gun; however, this is well below the yield strength of the material. Thisprojectile has high ricochet characteristics and, therefore, is a potential hazard for aircraft firing them.
With reference to FIGURE 2, the practice projectile 20 of the present invention comprises a unitary body 22, having an integral base 24, an integral circumferential driving band 26 near base 24 and an integral nose 28 ~t the end of the body remote from the base. Body 22 is a solid body having a ~lniformly distributed porosity throughout and is formed of sponge iron powc~er by an incomplete sintering process to the same size, shape and apparent density clS the standard practice projectile described above.
, ~ ~ , . , ;
. . . . . .
~327~13 The term "incomplete sintering" means that the sintering process is conducted at a temperature which is considerably lower than the melting point of iron powder, and, more generally, than the temperature at which iron powder is normally sintered. As a result, the iron p~rticles are only partially 5 consolidated. This characteristic coupled with the uniformly distributed porosity promotes fracture propagation on impact. The sintering temperature is selected so that the resulting body will have sufficient strength to withstand gun launchand free flight but promote fracture propagation on impact with even soft targets such as sand, a common medium employed to test ricochet occurrence.
Normally, iron powder components are sintered at about 1120C to reach a density of 7.0 to 7.5 glcc which corresponds to 90-95% of the theoretical density of iron. In accordance with the present invention, for the specific practice projectile described above, the iron powder is heated at a temperature of 750C. To make a projectile according to the present invention, a pre-15 weighted quantity of sponge iron powder is poured into a rubber or steel mo~lld whose interior cavity has the desired shape of the projectile to be manufactured.
The powder is compacted at 15,000 psi in an isostatic press if a rubber mould is used or in a uniaxial press if a steel mould is used. After de-mo~llding fromeither of the above moulds, the resulting "cold compact" is transferred into a 20 conventional furnace and heated to a temperature of 750C for one hour in an atmosphere comprised of 95% Nitrogen and 5% Hydrogen. After allowing the "so]id compact" to cool in the furnace, it is either sized in a press or finish machined to the final dimensions.
It will be understood that the present invention is not limited to the 2S specific projectile illustrated in the drawings and described hereinabove.
, ' ' . , ~ .- : ' :, , , , . :: .
.
SUMMARY OF THE INVENTION
The present invention provides a frangible practice projectile manufactured by powder metallurgy techniques in such a manner that the projectile will sustain the load and stresses induced by gun launch and free fl;ght but which will shatter at impact.
In accordance with one aspect of the present invention, there is provided a practice projectile for use with military aircraft and the like for training pilots in attacking ground targets, the projectile comprising a unitary body formed ot`sintered sponge iron powder and having a sintered density eqllivalent to the apparent density of a projectile to be simulated.
In accordance with another aspect of the present invention, there is provided a method of making a practice projectile for use with military aircrattand the like for training pilots in attacking ground targets. The method comprises the steps of compacting sponge iron powder in a mould hclving approximately the final shape of the projectile to form a cold compacted body, heating the cold compacted body in a furnace at a temperature which is less than the melting point of the powder for a predetermined time period of time in an atmosphere comprised of 95% Nitrogen and 5% Hydrogen to form .
heated solid body, and allowing the heated solid body to cool in the fl~rnace.
, . ~
1327~ 3 BR~EF DESCRIPTION OF THE DRAWINGS
These and other features of the invention will become more apparent from the following description in which reference is made to the appended drawing wherein:
S FIGURE 1 is a side elevational view, partially in section, of an M55A2 20-mm conventional practice projectile; and FIGURE 2 is a side elevational ~iew similar to FIGURE 1 of a practice projectile according one embodiment of the present invention.
DESCRIPTION OF PREFERRED EMBODIMENT
FIGURE 1 illustrates a standard MSSA2 20-mm pr~ctice projecti]e 10 having a hollow steel body 12 and an integral base 14, a copper driving band 16 circumferentially crimped onto body 12 near base 14 and an aluminum nose 18 pressed into the open end of the body remote from the base. The apparent density of this projectile is about 5.35 g/cc. This target practice proje~;tile is not designed to break-up upon impact; indeed, this type of structure is very resistant to compressive and tensile stresses. Theoretical analysis has shown that the compressive stresses imposed on the body are close to the yield strength of the material when the pressure behind the projectile reaches its maxim~lm d~lring launch but fall to almost zero in free flight. On the other hand, the tensile stresses increase with the spin rate and reach a maximum level at the muzzle of the gun; however, this is well below the yield strength of the material. Thisprojectile has high ricochet characteristics and, therefore, is a potential hazard for aircraft firing them.
With reference to FIGURE 2, the practice projectile 20 of the present invention comprises a unitary body 22, having an integral base 24, an integral circumferential driving band 26 near base 24 and an integral nose 28 ~t the end of the body remote from the base. Body 22 is a solid body having a ~lniformly distributed porosity throughout and is formed of sponge iron powc~er by an incomplete sintering process to the same size, shape and apparent density clS the standard practice projectile described above.
, ~ ~ , . , ;
. . . . . .
~327~13 The term "incomplete sintering" means that the sintering process is conducted at a temperature which is considerably lower than the melting point of iron powder, and, more generally, than the temperature at which iron powder is normally sintered. As a result, the iron p~rticles are only partially 5 consolidated. This characteristic coupled with the uniformly distributed porosity promotes fracture propagation on impact. The sintering temperature is selected so that the resulting body will have sufficient strength to withstand gun launchand free flight but promote fracture propagation on impact with even soft targets such as sand, a common medium employed to test ricochet occurrence.
Normally, iron powder components are sintered at about 1120C to reach a density of 7.0 to 7.5 glcc which corresponds to 90-95% of the theoretical density of iron. In accordance with the present invention, for the specific practice projectile described above, the iron powder is heated at a temperature of 750C. To make a projectile according to the present invention, a pre-15 weighted quantity of sponge iron powder is poured into a rubber or steel mo~lld whose interior cavity has the desired shape of the projectile to be manufactured.
The powder is compacted at 15,000 psi in an isostatic press if a rubber mould is used or in a uniaxial press if a steel mould is used. After de-mo~llding fromeither of the above moulds, the resulting "cold compact" is transferred into a 20 conventional furnace and heated to a temperature of 750C for one hour in an atmosphere comprised of 95% Nitrogen and 5% Hydrogen. After allowing the "so]id compact" to cool in the furnace, it is either sized in a press or finish machined to the final dimensions.
It will be understood that the present invention is not limited to the 2S specific projectile illustrated in the drawings and described hereinabove.
, ' ' . , ~ .- : ' :, , , , . :: .
.
Claims (17)
1. A practice projectile for use with military aircraft and the like for training pilots in attacking ground targets, said projectile comprising:
a unitary and solid body formed from sintered sponge iron powder having a uniformly distributed porosity throughout and having a sintered density equivalent to the apparent density of a projectile to be simulated.
a unitary and solid body formed from sintered sponge iron powder having a uniformly distributed porosity throughout and having a sintered density equivalent to the apparent density of a projectile to be simulated.
2. A practice projectile as defined in Claim 1, wherein said density equivalent to the apparent density is substantially less than the theorectical density of iron.
3. A practice projectile as defined in Claim 1, said body having an integralnose.
4. A practice projectile as defined in Claim 1, said body having an integraldriving band.
5. A practice projectile as defined in Claim 1, said body having an integralnose and driving band.
6. A practice projectile as defined in Claim 1, said body having a uniformlydistributed porosity for promoting fracture on impact.
7. A practice projectile for use with military aircraft and the like for training pilots in attacking ground targets, said projectile comprising:
a unitary and solid body having an integral nose and driving band and equivalent formed from sintered sponge iron powder having a sintered density equivalent to the apparent density of a projectile to be simulated and a uniformly distributed porosity for promoting fracture on impact.
a unitary and solid body having an integral nose and driving band and equivalent formed from sintered sponge iron powder having a sintered density equivalent to the apparent density of a projectile to be simulated and a uniformly distributed porosity for promoting fracture on impact.
8. A practice projectile as defined in Claim 7, wherein said density equivalent to the apparent density is substantially less than the theorectical density of iron.
9. A practice projectile as defined in Claim 1, said body being sintered at atemperature which only partially consolidates powder particles and provides sufficient strength to enable said body to sustain loads and stresses induced by gun launch and free flight while shattering on impact.
10. A practice projectile as defined in Claim 9, wherein said temperature is 750°C.
11. A method of making a practice projectile for use with military aircraft and the like for training pilots in attacking ground targets, said method comprising the steps of:
compacting sponge iron powder in a mould having approximately the final shape of said projectile to form a cold compacted body, heating said cold compacted body in a furnace at a temperature which is less than the melting point of said powder for a predetermined time period of time in an atmosphere comprised of 95% Nitrogen and 5% Hydrogen to form a heated solid body, and allowing said heated solid body to cool in the furnace.
compacting sponge iron powder in a mould having approximately the final shape of said projectile to form a cold compacted body, heating said cold compacted body in a furnace at a temperature which is less than the melting point of said powder for a predetermined time period of time in an atmosphere comprised of 95% Nitrogen and 5% Hydrogen to form a heated solid body, and allowing said heated solid body to cool in the furnace.
12. A method as defined in claim 11, said compaction step including cold isostatic compacting said powder in a rubber mould.
13. A method as defined in claim 11, said compaction step including uniaxial compaction of said powder in a steel mould.
14. A method as defined in claim 11, said manufacturing step including manufacturing said projectile having a sintered density equivalent to the apparent density of a projectile to be simulated.
15. A method as defined in claim 11, said temperature being approximately 750°C.
16. A method as defined in claim 11, said pressure being approximately 15,000psi.
17. A method as defined in claim 15, said pressure being approximately 15,000psi.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000592121A CA1327913C (en) | 1989-02-24 | 1989-02-24 | Non-ricocheting projectile and method of making same |
| US07/406,304 US4958572A (en) | 1989-02-24 | 1989-09-12 | Non-ricocheting projectile and method of making same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000592121A CA1327913C (en) | 1989-02-24 | 1989-02-24 | Non-ricocheting projectile and method of making same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1327913C true CA1327913C (en) | 1994-03-22 |
Family
ID=4139694
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000592121A Expired - Fee Related CA1327913C (en) | 1989-02-24 | 1989-02-24 | Non-ricocheting projectile and method of making same |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US4958572A (en) |
| CA (1) | CA1327913C (en) |
Families Citing this family (34)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5198616A (en) * | 1990-09-28 | 1993-03-30 | Bei Electronics, Inc. | Frangible armor piercing incendiary projectile |
| GB9310915D0 (en) * | 1993-05-27 | 1993-07-14 | Royal Ordance Plc | Improvements in or relating to projectiles |
| US6158351A (en) * | 1993-09-23 | 2000-12-12 | Olin Corporation | Ferromagnetic bullet |
| US5399187A (en) * | 1993-09-23 | 1995-03-21 | Olin Corporation | Lead-free bullett |
| AUPN554295A0 (en) * | 1995-09-20 | 1996-02-01 | Australian Defence Industries Limited | Frangible ammunition |
| US5847313A (en) * | 1997-01-30 | 1998-12-08 | Cove Corporation | Projectile for ammunition cartridge |
| US5789698A (en) * | 1997-01-30 | 1998-08-04 | Cove Corporation | Projectile for ammunition cartridge |
| US6607692B2 (en) | 1997-01-30 | 2003-08-19 | Doris Nebel Beal Intervivos Patent Trust | Method of manufacture of a powder-based firearm ammunition projectile employing electrostatic charge |
| US6551376B1 (en) | 1997-03-14 | 2003-04-22 | Doris Nebel Beal Inter Vivos Patent Trust | Method for developing and sustaining uniform distribution of a plurality of metal powders of different densities in a mixture of such metal powders |
| US6892647B1 (en) | 1997-08-08 | 2005-05-17 | Ra Brands, L.L.C. | Lead free powdered metal projectiles |
| US5917143A (en) * | 1997-08-08 | 1999-06-29 | Remington Arms Company, Inc. | Frangible powdered iron projectiles |
| US6090178A (en) | 1998-04-22 | 2000-07-18 | Sinterfire, Inc. | Frangible metal bullets, ammunition and method of making such articles |
| US6270549B1 (en) | 1998-09-04 | 2001-08-07 | Darryl Dean Amick | Ductile, high-density, non-toxic shot and other articles and method for producing same |
| US6527880B2 (en) * | 1998-09-04 | 2003-03-04 | Darryl D. Amick | Ductile medium-and high-density, non-toxic shot and other articles and method for producing the same |
| US7267794B2 (en) * | 1998-09-04 | 2007-09-11 | Amick Darryl D | Ductile medium-and high-density, non-toxic shot and other articles and method for producing the same |
| US6248150B1 (en) | 1999-07-20 | 2001-06-19 | Darryl Dean Amick | Method for manufacturing tungsten-based materials and articles by mechanical alloying |
| US6640724B1 (en) | 1999-08-04 | 2003-11-04 | Olin Corporation | Slug for industrial ballistic tool |
| SE517797C2 (en) * | 1999-09-03 | 2002-07-16 | Norma Prec Ab | Projectile of sintered metal powder |
| US6670300B2 (en) * | 2001-06-18 | 2003-12-30 | Battelle Memorial Institute | Textured catalysts, methods of making textured catalysts, and methods of catalyzing reactions conducted in hydrothermal conditions |
| US20030047032A1 (en) * | 2001-06-22 | 2003-03-13 | Newman Keith E. | Method of producing powder metal parts from metallurgical powders including sponge iron |
| CA2462976A1 (en) * | 2001-10-16 | 2003-04-24 | International Non-Toxic Composites Corporation | High density non-toxic composites comprising tungsten, another metal and polymer powder |
| NZ532693A (en) * | 2001-10-16 | 2005-03-24 | Internat Non Toxic Composites | Sintered composite material containing tungsten and bronze |
| US7422720B1 (en) | 2004-05-10 | 2008-09-09 | Spherical Precision, Inc. | High density nontoxic projectiles and other articles, and methods for making the same |
| US7690312B2 (en) * | 2004-06-02 | 2010-04-06 | Smith Timothy G | Tungsten-iron projectile |
| US8122832B1 (en) | 2006-05-11 | 2012-02-28 | Spherical Precision, Inc. | Projectiles for shotgun shells and the like, and methods of manufacturing the same |
| US8393273B2 (en) | 2009-01-14 | 2013-03-12 | Nosler, Inc. | Bullets, including lead-free bullets, and associated methods |
| US9709368B2 (en) | 2014-04-30 | 2017-07-18 | G9 Holdings, Llc | Projectile with enhanced ballistics |
| US20160091290A1 (en) * | 2014-09-29 | 2016-03-31 | Pm Ballistics Llc | Lead free frangible iron bullets |
| US11313657B1 (en) | 2016-11-14 | 2022-04-26 | Erik Agazim | Multi-piece projectile with an insert formed via a powder metallurgy process |
| US20180135950A1 (en) * | 2016-11-14 | 2018-05-17 | Erik Agazim | Frangible Bullet Tip |
| CA3136297A1 (en) * | 2019-04-05 | 2020-10-22 | Vista Outdoor Operations Llc | Rimfire cartridge |
| US11428517B2 (en) | 2019-09-20 | 2022-08-30 | Npee L.C. | Projectile with insert |
| US11150063B1 (en) * | 2020-05-11 | 2021-10-19 | Rocky Mountain Scientific Laboratory, Llc | Enhanced castable frangible breaching round |
| US11105597B1 (en) | 2020-05-11 | 2021-08-31 | Rocky Mountain Scientific Laboratory, Llc | Castable frangible projectile |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2442155A (en) * | 1944-07-25 | 1948-05-25 | Wilfred W Weese | Bore cleaning bullet |
| US2995090A (en) * | 1954-07-02 | 1961-08-08 | Remington Arms Co Inc | Gallery bullet |
| US3123003A (en) * | 1962-01-03 | 1964-03-03 | lange | |
| GB1176879A (en) * | 1966-05-17 | 1970-01-07 | Karlsruhe Augsburg Iweka | Disintegrating Bullet |
| NL145953B (en) * | 1973-09-18 | 1975-05-15 | Nederl Wapen & Munitie | DISCONTINUATION PROJECTILE. |
| US3902683A (en) * | 1973-11-07 | 1975-09-02 | Us Air Force | Plastic frangible training projectile |
| US4165692A (en) * | 1977-10-25 | 1979-08-28 | Calspan Corporation | Frangible projectile for gunnery practice |
-
1989
- 1989-02-24 CA CA000592121A patent/CA1327913C/en not_active Expired - Fee Related
- 1989-09-12 US US07/406,304 patent/US4958572A/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| US4958572A (en) | 1990-09-25 |
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| MKLA | Lapsed |