US3389025A - Propellant composition containing high energy metal in the form of multi-di-mensional crosses - Google Patents
Propellant composition containing high energy metal in the form of multi-di-mensional crosses Download PDFInfo
- Publication number
- US3389025A US3389025A US625922A US62592267A US3389025A US 3389025 A US3389025 A US 3389025A US 625922 A US625922 A US 625922A US 62592267 A US62592267 A US 62592267A US 3389025 A US3389025 A US 3389025A
- Authority
- US
- United States
- Prior art keywords
- propellant
- composition
- staples
- burning
- staple
- 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 - Lifetime
Links
- 239000000203 mixture Substances 0.000 title description 28
- 239000003380 propellant Substances 0.000 title description 24
- 229910052751 metal Inorganic materials 0.000 title description 13
- 239000002184 metal Substances 0.000 title description 13
- 230000000694 effects Effects 0.000 description 5
- 239000004449 solid propellant Substances 0.000 description 5
- 239000011230 binding agent Substances 0.000 description 3
- 238000005266 casting Methods 0.000 description 3
- 238000001723 curing Methods 0.000 description 3
- 239000007800 oxidant agent Substances 0.000 description 3
- 229910002651 NO3 Inorganic materials 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000003607 modifier Substances 0.000 description 2
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 description 1
- 229920002126 Acrylic acid copolymer Polymers 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- NHNBFGGVMKEFGY-UHFFFAOYSA-N Nitrate Chemical compound [O-][N+]([O-])=O NHNBFGGVMKEFGY-UHFFFAOYSA-N 0.000 description 1
- 239000000020 Nitrocellulose Substances 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- XTEGARKTQYYJKE-UHFFFAOYSA-N chloric acid Chemical class OCl(=O)=O XTEGARKTQYYJKE-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- GUJOJGAPFQRJSV-UHFFFAOYSA-N dialuminum;dioxosilane;oxygen(2-);hydrate Chemical compound O.[O-2].[O-2].[O-2].[Al+3].[Al+3].O=[Si]=O.O=[Si]=O.O=[Si]=O.O=[Si]=O GUJOJGAPFQRJSV-UHFFFAOYSA-N 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- -1 nitrate ester Chemical class 0.000 description 1
- 229920001220 nitrocellulos Polymers 0.000 description 1
- 235000011837 pasties Nutrition 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 239000004014 plasticizer Substances 0.000 description 1
- 239000005077 polysulfide Substances 0.000 description 1
- 229920001021 polysulfide Polymers 0.000 description 1
- 150000008117 polysulfides Polymers 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 239000002002 slurry Substances 0.000 description 1
- 238000007582 slurry-cast process Methods 0.000 description 1
- 239000007790 solid phase Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910052726 zirconium Inorganic materials 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/26—Burning control
Definitions
- This invention relates to an improved staple design and particularly to one used as a burning rate modifier for solid propellant grains.
- Metal staples that is, thin fragments of metal wire, strip or filament are employed in solid propellant grains to obtain improved burning characteristics. Incorporation of metal staples throughout the grain provides substantially accelerated burning rates by increasing conduction of heat from the burning surface to the interior of the grain.
- the staples also serve as a source of high energy fuel in the propellant composition, the metal employed being aluminum, magnesium, zirconium or other metal or alloy which releases a large amount of energy upon combustion.
- Staple-containing propellant compositions are particularly useful in rapid-accelerating rocket motors that require minimum time from launch to target.
- One of the problems presented in the use of metal staples in propellant grains is orientation of the staples in the desired manner.
- the staples should be oriented with their longest axis perpendicular to the direction of burning. Orientation parallel to the direction of burning is undesirable in that a minimum of reproducibility is realized.
- the staples are oriented parallel to the burning surface at the internal perforation and outer edge of the grain. Perpendicular, rather than parallel, orientation with respect to the burning surface is particularly desired at these locations. Perpendicular orientation at the internal perforation would provide a high initial burning rate and rapid attainment of maximum thrust. Similarly, perpendicular orientation along the outer wall of the grain would produce rapid burning when the last portions of the propellant grain are being consumed so as to retain a high thrust for the longest possible period.
- This invention provides an improved staple design such that orientation of the staples parallel to the burning surface is impossible. A random distribution effect is achieved.
- the preferred embodiment of this invention employs a multi-dimensioned cross.
- the staple construction consists of a two-dimensional cross in a horizontal plane with another length of the material being used in a plane perpendicular to the aforementioned cross, and passing through the intersection of the cross arms. All arms of the resulting multi-dimensional cross are preferably equal in length.
- FIGURE 1 is a cross-sectional view of a motor casing employing a propellant grain containing a prior art staple design
- FIGURE 2 is a cross-sectional view of a motor casing employing a propellant grain containing a staple design of this invention.
- FIGURE 3 is a perspective view of a staple of this invention.
- FIGURES l and 2 there is shown generally cylindrical motor cases 1 which serve as casting molds.
- a cylindrical mandrel 2 is disposed axially in each of motor cases 1 to form an internal perforation extending the full length of the grain.
- FIGURES 1 and 2 a comparison between conventional staples 3 and the improved staple design 4 of this invention in the motor cases is depicted in FIGURES 1 and 2. It can be seen in the case of conventional staples 3 that a wall effect exists at the walls of motor case 1 and mandrel 2. Conversely, with the improved staple design 4 of this invention (FIGURE 3), this effect cannot occur because some portion of the staple will always be aligned perpendicular to the direction of burning. The random orientation which occurs is enough to minimize the wall effect.
- propellant staples consist of circular fragments of wire about ,5 to inch long and 5 to 20 microns in diameter or metal strips of the same length, 0.0045 to 0.04 inch wide and 0.0008 to 0.008 inch thick.
- the staple design of this invention (FIGURE 3) preferably has arms about to inch long and 5 to 20 microns in diameter (or width and thickness).
- This invention is applicable to staple-containing propellant compositions which exhibit physical properties in the uncured state for fabrication by casting (preferably low viscosity), and the chemical composition of the propellant composition is not critical.
- this invention is useful for composite-type propellant compositions comprising a liquid polymeric binder such as polysulfides, polyurethanes, polydienes, polydiene-acrylic acid copolymers and the like, an inorganic oxidizing agent such as ammonium perchlorate or other nitrate or chlorate salt and other additives such as curing agents and burning rate catalysts along with the metal staples.
- Propellant compositions of this type normally contain a relatively large amount such as 20 to 50 weight percent of the solid-phase oxidizer so that the uncured composition is a relatively low viscosity slurry formulation.
- Metal staples typically comprise about 3 to 7 weight percent of the composition.
- Other types of staple-containing propellants such as double-base propellants employing nitrocellulose assapzs as the propellant binder and a nitrate ester plasticizer may also be fabricated according to this invention.
- the propellant composition is poured to the desired level in the motor case mold and the resulting propellant grain is cured to impart strength and rigidity therein.
- Previously known curing methods which normally involve the application of mild heat for an extended period, may be employed.
- a composition for solid propellants having incorhaving arms in a first plane, and two other arms located in a plane perpendicular to said first plane and passing through the intersection of the arms of said twodimensional cross.
- composition of claim 1 wherein said two-dimensional cross is equilateral.
- composition of claim 1 wherein all of said arms of said multi-dimensional cross are of the same length.
- composition of claim 3 wherein said composition is of low viscosity.
- composition of claim 4 wherein said composition comprises an oxidizing agent, a liquid polymeric binder and a curing agent.
- composition of claim 5 wherein said arms are generally circular in cross section and about ten microns in diameter.
- composition of claim 6 wherein said arms are generally circular in cross section and about ten microns lll diameter.
Description
June 18, 1968 J, NIX L 3,389,025
PROPELLANT COMPOSITION CONTAINING HIGH ENERGY METAL IN THE FORM OF MULTI-DIMENsIoNAL CROSSES Filed March 22, 1967 (PRIOR ART) Joseph E. Nix
Winford 6. Brock,
INVENTORS.
United States Patent Office 3,389,025 Patented June 18, 1968 ABSTRACT OF THE DISCLOSURE A novel shape for metal staples used as a, burning rate modifier for solid propellant grains. The shape is that of a multi-dimensional cross.
Background of the invention This invention relates to an improved staple design and particularly to one used as a burning rate modifier for solid propellant grains.
Metal staples, that is, thin fragments of metal wire, strip or filament are employed in solid propellant grains to obtain improved burning characteristics. Incorporation of metal staples throughout the grain provides substantially accelerated burning rates by increasing conduction of heat from the burning surface to the interior of the grain. The staples also serve as a source of high energy fuel in the propellant composition, the metal employed being aluminum, magnesium, zirconium or other metal or alloy which releases a large amount of energy upon combustion. Staple-containing propellant compositions are particularly useful in rapid-accelerating rocket motors that require minimum time from launch to target.
One of the problems presented in the use of metal staples in propellant grains is orientation of the staples in the desired manner. For maximum effectiveness, the staples should be oriented with their longest axis perpendicular to the direction of burning. Orientation parallel to the direction of burning is undesirable in that a minimum of reproducibility is realized.
Control of staple orientation has proven to be a particularly diflicult task for propellant grains prepared by slurry casting. In applicants composition, the uncured propellant composition, while in a pasty gel state, is poured into a mold of the desired con-figuration, normally an elongated cylindrical container having an axially disposed mandrel in its center to produce an internal perforation. The internal perforation provides a burning surface extending throughout the body of the grain, and the amount of burning surface is controlled by varying the design of the perforation. In casting grains of this type, the staples tend to become aligned parallel to the direction of flow of the propellant composition, which is at least partially parallel to the mold and mandrel walls. As a result, the staples are oriented parallel to the burning surface at the internal perforation and outer edge of the grain. Perpendicular, rather than parallel, orientation with respect to the burning surface is particularly desired at these locations. Perpendicular orientation at the internal perforation would provide a high initial burning rate and rapid attainment of maximum thrust. Similarly, perpendicular orientation along the outer wall of the grain would produce rapid burning when the last portions of the propellant grain are being consumed so as to retain a high thrust for the longest possible period.
It is, therefore, the principal object of this invention to provide a metal staple whereby malalignment of the staple is impossible when incorporated in a propellant composition.
Summary of the invention This invention provides an improved staple design such that orientation of the staples parallel to the burning surface is impossible. A random distribution effect is achieved.
Although several designs are possible, the preferred embodiment of this invention employs a multi-dimensioned cross. Specifically, the staple construction consists of a two-dimensional cross in a horizontal plane with another length of the material being used in a plane perpendicular to the aforementioned cross, and passing through the intersection of the cross arms. All arms of the resulting multi-dimensional cross are preferably equal in length.
Brief description of the drawing Other objects and advantages of this invention will be apparent from the description that follows, from the appended claims and from the drawing, in which:
FIGURE 1 is a cross-sectional view of a motor casing employing a propellant grain containing a prior art staple design;-
FIGURE 2 is a cross-sectional view of a motor casing employing a propellant grain containing a staple design of this invention; and
FIGURE 3 is a perspective view of a staple of this invention.
Description of the preferred embodiment Referring now to FIGURES l and 2, there is shown generally cylindrical motor cases 1 which serve as casting molds. A cylindrical mandrel 2 is disposed axially in each of motor cases 1 to form an internal perforation extending the full length of the grain. To illustrate the principleinvolved, a comparison between conventional staples 3 and the improved staple design 4 of this invention in the motor cases is depicted in FIGURES 1 and 2. It can be seen in the case of conventional staples 3 that a wall effect exists at the walls of motor case 1 and mandrel 2. Conversely, with the improved staple design 4 of this invention (FIGURE 3), this effect cannot occur because some portion of the staple will always be aligned perpendicular to the direction of burning. The random orientation which occurs is enough to minimize the wall effect.
Normally, propellant staples consist of circular fragments of wire about ,5 to inch long and 5 to 20 microns in diameter or metal strips of the same length, 0.0045 to 0.04 inch wide and 0.0008 to 0.008 inch thick. The staple design of this invention (FIGURE 3) preferably has arms about to inch long and 5 to 20 microns in diameter (or width and thickness).
This invention is applicable to staple-containing propellant compositions which exhibit physical properties in the uncured state for fabrication by casting (preferably low viscosity), and the chemical composition of the propellant composition is not critical. In general, this invention is useful for composite-type propellant compositions comprising a liquid polymeric binder such as polysulfides, polyurethanes, polydienes, polydiene-acrylic acid copolymers and the like, an inorganic oxidizing agent such as ammonium perchlorate or other nitrate or chlorate salt and other additives such as curing agents and burning rate catalysts along with the metal staples. Propellant compositions of this type normally contain a relatively large amount such as 20 to 50 weight percent of the solid-phase oxidizer so that the uncured composition is a relatively low viscosity slurry formulation. Metal staples typically comprise about 3 to 7 weight percent of the composition. Other types of staple-containing propellants such as double-base propellants employing nitrocellulose assapzs as the propellant binder and a nitrate ester plasticizer may also be fabricated according to this invention.
The propellant composition is poured to the desired level in the motor case mold and the resulting propellant grain is cured to impart strength and rigidity therein. Previously known curing methods, which normally involve the application of mild heat for an extended period, may be employed.
It is thus seen that improved solid propellant compositions can be made according to this invention. The use of the herein described cross design keeps staples from being aligned with respect to the burning plane of the propellant; that is, it gives a random distribution effect. This provides for a maximum and more reproducible burning of propellant grains It is to be understood that various changes and modifications may be employed Without departing from the spirit and scope of this invention.
We claim:
1. A composition for solid propellants having incorhaving arms in a first plane, and two other arms located in a plane perpendicular to said first plane and passing through the intersection of the arms of said twodimensional cross.
2. The composition of claim 1 wherein said two-dimensional cross is equilateral.
.3. The composition of claim 1 wherein all of said arms of said multi-dimensional cross are of the same length.
4. The composition of claim 3 wherein said composition is of low viscosity.
5. The composition of claim 4 wherein said composition comprises an oxidizing agent, a liquid polymeric binder and a curing agent.
6. The composition of claim 5 wherein said arms are about one eighth of an inch long.
7. The composition of claim 5 wherein said arms are generally circular in cross section and about ten microns in diameter.
8. The composition of claim 6 wherein said arms are generally circular in cross section and about ten microns lll diameter.
References Cited lTJNlTED STATES PATENTS BENJAMIN R. PADGETT, Primary Examiner.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US625922A US3389025A (en) | 1967-03-22 | 1967-03-22 | Propellant composition containing high energy metal in the form of multi-di-mensional crosses |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US625922A US3389025A (en) | 1967-03-22 | 1967-03-22 | Propellant composition containing high energy metal in the form of multi-di-mensional crosses |
Publications (1)
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US3389025A true US3389025A (en) | 1968-06-18 |
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Application Number | Title | Priority Date | Filing Date |
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US625922A Expired - Lifetime US3389025A (en) | 1967-03-22 | 1967-03-22 | Propellant composition containing high energy metal in the form of multi-di-mensional crosses |
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Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3827715A (en) * | 1972-04-28 | 1974-08-06 | Specialty Prod Dev Corp | Pyrotechnic gas generator with homogenous separator phase |
US3919013A (en) * | 1972-07-12 | 1975-11-11 | Hercules Inc | Use of graphite fibers to augment propellant burning rate |
US4072546A (en) * | 1971-12-22 | 1978-02-07 | Hercules Incorporated | Use of graphite fibers to augment propellant burning rate |
US4097315A (en) * | 1968-03-21 | 1978-06-27 | Hercules Incorporated | Magnetic orientation of casting powder granules |
US4410470A (en) * | 1981-01-07 | 1983-10-18 | The United States Of America As Represented By The Secretary Of The Army | Increasing burning rate of solid propellants by electric field effects |
US4756251A (en) * | 1986-09-18 | 1988-07-12 | Morton Thiokol, Inc. | Solid rocket motor propellants with reticulated structures embedded therein to provide variable burn rate characteristics |
US4764319A (en) * | 1986-09-18 | 1988-08-16 | Morton Thiokol, Inc. | High solids ratio solid rocket motor propellant grains and method of construction thereof |
US4798142A (en) * | 1986-08-18 | 1989-01-17 | Morton Thiokol, Inc. | Rapid buring propellant charge for automobile air bag inflators, rocket motors, and igniters therefor |
US4812179A (en) * | 1984-09-10 | 1989-03-14 | The United States Of America As Represented By The Secretary Of The Army | Method of increasing the burning rate enhancement by mechanical accelerators |
US5024160A (en) * | 1986-08-18 | 1991-06-18 | Thiokol Corporation | Rapid burning propellant charge for automobile air bag inflators, rocket motors, and igniters therefor |
US5062365A (en) * | 1986-08-18 | 1991-11-05 | Thiokol Corporation | Rapid burning propellent charge for automobile air bag inflators, rocket motors, and igniters therefor |
US5127223A (en) * | 1986-09-18 | 1992-07-07 | Thiokol Corporation | Solid rocket motor propellants with reticulated structures embedded therein and method of manufacture thereof |
US6508177B1 (en) * | 1999-09-13 | 2003-01-21 | The Ensign-Bickford Company | Explosives with embedded bodies |
US6748868B2 (en) | 2002-05-15 | 2004-06-15 | Atlantic Research Corp. | Destroying airborne biological and/or chemical agents with solid propellants |
US6846372B1 (en) * | 2003-03-31 | 2005-01-25 | The United States Of America As Represented By The Secretary Of The Navy | Reactively induced fragmentating explosives |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3116692A (en) * | 1959-11-27 | 1964-01-07 | Atlantic Res Corp | Propellant grains |
US3140663A (en) * | 1955-06-09 | 1964-07-14 | Atlantic Res Corp | Propellent grains |
-
1967
- 1967-03-22 US US625922A patent/US3389025A/en not_active Expired - Lifetime
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3140663A (en) * | 1955-06-09 | 1964-07-14 | Atlantic Res Corp | Propellent grains |
US3116692A (en) * | 1959-11-27 | 1964-01-07 | Atlantic Res Corp | Propellant grains |
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4097315A (en) * | 1968-03-21 | 1978-06-27 | Hercules Incorporated | Magnetic orientation of casting powder granules |
US4072546A (en) * | 1971-12-22 | 1978-02-07 | Hercules Incorporated | Use of graphite fibers to augment propellant burning rate |
US3827715A (en) * | 1972-04-28 | 1974-08-06 | Specialty Prod Dev Corp | Pyrotechnic gas generator with homogenous separator phase |
US3919013A (en) * | 1972-07-12 | 1975-11-11 | Hercules Inc | Use of graphite fibers to augment propellant burning rate |
US4410470A (en) * | 1981-01-07 | 1983-10-18 | The United States Of America As Represented By The Secretary Of The Army | Increasing burning rate of solid propellants by electric field effects |
US4812179A (en) * | 1984-09-10 | 1989-03-14 | The United States Of America As Represented By The Secretary Of The Army | Method of increasing the burning rate enhancement by mechanical accelerators |
US4798142A (en) * | 1986-08-18 | 1989-01-17 | Morton Thiokol, Inc. | Rapid buring propellant charge for automobile air bag inflators, rocket motors, and igniters therefor |
US5024160A (en) * | 1986-08-18 | 1991-06-18 | Thiokol Corporation | Rapid burning propellant charge for automobile air bag inflators, rocket motors, and igniters therefor |
US5062365A (en) * | 1986-08-18 | 1991-11-05 | Thiokol Corporation | Rapid burning propellent charge for automobile air bag inflators, rocket motors, and igniters therefor |
US4764319A (en) * | 1986-09-18 | 1988-08-16 | Morton Thiokol, Inc. | High solids ratio solid rocket motor propellant grains and method of construction thereof |
US4756251A (en) * | 1986-09-18 | 1988-07-12 | Morton Thiokol, Inc. | Solid rocket motor propellants with reticulated structures embedded therein to provide variable burn rate characteristics |
US5127223A (en) * | 1986-09-18 | 1992-07-07 | Thiokol Corporation | Solid rocket motor propellants with reticulated structures embedded therein and method of manufacture thereof |
US6508177B1 (en) * | 1999-09-13 | 2003-01-21 | The Ensign-Bickford Company | Explosives with embedded bodies |
US6748868B2 (en) | 2002-05-15 | 2004-06-15 | Atlantic Research Corp. | Destroying airborne biological and/or chemical agents with solid propellants |
US6782827B2 (en) | 2002-05-15 | 2004-08-31 | Aerojet-General Corporation | Solid propellant formulations and methods and devices employing the same for the destruction of airborne biological and/or chemical agents |
US6808572B2 (en) | 2002-05-15 | 2004-10-26 | Aerojet-General Corporation | Solid propellant formulations and methods and devices employing the same for the destruction of airborne biological and/or chemical agents |
US6846372B1 (en) * | 2003-03-31 | 2005-01-25 | The United States Of America As Represented By The Secretary Of The Navy | Reactively induced fragmentating explosives |
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