US3784419A - Propellant composition containing a nickle-silver composite - Google Patents
Propellant composition containing a nickle-silver composite Download PDFInfo
- Publication number
- US3784419A US3784419A US00267737A US3784419DA US3784419A US 3784419 A US3784419 A US 3784419A US 00267737 A US00267737 A US 00267737A US 3784419D A US3784419D A US 3784419DA US 3784419 A US3784419 A US 3784419A
- Authority
- US
- United States
- Prior art keywords
- staple
- percent
- staples
- composition
- propellant composition
- 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 claims abstract description 40
- 229910052709 silver Inorganic materials 0.000 title claims description 8
- 239000004332 silver Substances 0.000 title claims description 8
- 239000003380 propellant Substances 0.000 title abstract description 17
- 239000002131 composite material Substances 0.000 title description 5
- 239000004449 solid propellant Substances 0.000 claims abstract description 15
- 229910052751 metal Inorganic materials 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 12
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 8
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims description 5
- 238000000034 method Methods 0.000 abstract description 9
- 238000005266 casting Methods 0.000 abstract description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 7
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 6
- 229910052782 aluminium Inorganic materials 0.000 description 6
- 239000000020 Nitrocellulose Substances 0.000 description 5
- 229920001220 nitrocellulos Polymers 0.000 description 5
- 239000000843 powder Substances 0.000 description 5
- RUKISNQKOIKZGT-UHFFFAOYSA-N 2-nitrodiphenylamine Chemical compound [O-][N+](=O)C1=CC=CC=C1NC1=CC=CC=C1 RUKISNQKOIKZGT-UHFFFAOYSA-N 0.000 description 4
- SNIOPGDIGTZGOP-UHFFFAOYSA-N Nitroglycerin Chemical compound [O-][N+](=O)OCC(O[N+]([O-])=O)CO[N+]([O-])=O SNIOPGDIGTZGOP-UHFFFAOYSA-N 0.000 description 4
- 239000000006 Nitroglycerin Substances 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 4
- 239000000654 additive Substances 0.000 description 4
- 229960003711 glyceryl trinitrate Drugs 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- QUAMCNNWODGSJA-UHFFFAOYSA-N 1,1-dinitrooxybutyl nitrate Chemical compound CCCC(O[N+]([O-])=O)(O[N+]([O-])=O)O[N+]([O-])=O QUAMCNNWODGSJA-UHFFFAOYSA-N 0.000 description 3
- 239000011230 binding agent Substances 0.000 description 3
- 229920002301 cellulose acetate Polymers 0.000 description 3
- 239000011888 foil Substances 0.000 description 3
- 239000004615 ingredient Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229910052759 nickel Inorganic materials 0.000 description 3
- 229910052757 nitrogen Inorganic materials 0.000 description 3
- GHMLBKRAJCXXBS-UHFFFAOYSA-N resorcinol Chemical compound OC1=CC=CC(O)=C1 GHMLBKRAJCXXBS-UHFFFAOYSA-N 0.000 description 3
- AGCQZYRSTIRJFM-UHFFFAOYSA-N triethylene glycol dinitrate Chemical compound [O-][N+](=O)OCCOCCOCCO[N+]([O-])=O AGCQZYRSTIRJFM-UHFFFAOYSA-N 0.000 description 3
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 description 2
- QTBSBXVTEAMEQO-UHFFFAOYSA-N Acetic acid Chemical group CC(O)=O QTBSBXVTEAMEQO-UHFFFAOYSA-N 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- FLKPEMZONWLCSK-UHFFFAOYSA-N diethyl phthalate Chemical compound CCOC(=O)C1=CC=CC=C1C(=O)OCC FLKPEMZONWLCSK-UHFFFAOYSA-N 0.000 description 2
- DMBHHRLKUKUOEG-UHFFFAOYSA-N diphenylamine Chemical compound C=1C=CC=CC=1NC1=CC=CC=C1 DMBHHRLKUKUOEG-UHFFFAOYSA-N 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- MOUPNEIJQCETIW-UHFFFAOYSA-N lead chromate Chemical compound [Pb+2].[O-][Cr]([O-])(=O)=O MOUPNEIJQCETIW-UHFFFAOYSA-N 0.000 description 2
- 230000005415 magnetization Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- UZGLIIJVICEWHF-UHFFFAOYSA-N octogen Chemical compound [O-][N+](=O)N1CN([N+]([O-])=O)CN([N+]([O-])=O)CN([N+]([O-])=O)C1 UZGLIIJVICEWHF-UHFFFAOYSA-N 0.000 description 2
- 239000004014 plasticizer Substances 0.000 description 2
- -1 polyethylene Polymers 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000002904 solvent Substances 0.000 description 2
- URAYPUMNDPQOKB-UHFFFAOYSA-N triacetin Chemical compound CC(=O)OCC(OC(C)=O)COC(C)=O URAYPUMNDPQOKB-UHFFFAOYSA-N 0.000 description 2
- XTFIVUDBNACUBN-UHFFFAOYSA-N 1,3,5-trinitro-1,3,5-triazinane Chemical compound [O-][N+](=O)N1CN([N+]([O-])=O)CN([N+]([O-])=O)C1 XTFIVUDBNACUBN-UHFFFAOYSA-N 0.000 description 1
- PAWQVTBBRAZDMG-UHFFFAOYSA-N 2-(3-bromo-2-fluorophenyl)acetic acid Chemical compound OC(=O)CC1=CC=CC(Br)=C1F PAWQVTBBRAZDMG-UHFFFAOYSA-N 0.000 description 1
- CDVAIHNNWWJFJW-UHFFFAOYSA-N 3,5-diethoxycarbonyl-1,4-dihydrocollidine Chemical compound CCOC(=O)C1=C(C)NC(C)=C(C(=O)OCC)C1C CDVAIHNNWWJFJW-UHFFFAOYSA-N 0.000 description 1
- NIXOWILDQLNWCW-UHFFFAOYSA-M Acrylate Chemical compound [O-]C(=O)C=C NIXOWILDQLNWCW-UHFFFAOYSA-M 0.000 description 1
- 229920002126 Acrylic acid copolymer Polymers 0.000 description 1
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000952 Be alloy Inorganic materials 0.000 description 1
- 229910000975 Carbon steel Inorganic materials 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 229910000861 Mg alloy Inorganic materials 0.000 description 1
- 239000004677 Nylon Substances 0.000 description 1
- JPYHHZQJCSQRJY-UHFFFAOYSA-N Phloroglucinol Natural products CCC=CCC=CCC=CCC=CCCCCC(=O)C1=C(O)C=C(O)C=C1O JPYHHZQJCSQRJY-UHFFFAOYSA-N 0.000 description 1
- 239000005062 Polybutadiene Substances 0.000 description 1
- 239000004698 Polyethylene Substances 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- KHRZATIAIMJVCG-UHFFFAOYSA-N [Be].[B].[B].[B].[B].[B].[B] Chemical compound [Be].[B].[B].[B].[B].[B].[B] KHRZATIAIMJVCG-UHFFFAOYSA-N 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000013019 agitation Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- SNAAJJQQZSMGQD-UHFFFAOYSA-N aluminum magnesium Chemical compound [Mg].[Al] SNAAJJQQZSMGQD-UHFFFAOYSA-N 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 229910052790 beryllium Inorganic materials 0.000 description 1
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 description 1
- CNVULGHYDPMIHD-UHFFFAOYSA-L bis[(2-hydroxybenzoyl)oxy]lead Chemical compound [Pb+2].OC1=CC=CC=C1C([O-])=O.OC1=CC=CC=C1C([O-])=O CNVULGHYDPMIHD-UHFFFAOYSA-L 0.000 description 1
- UORVGPXVDQYIDP-UHFFFAOYSA-N borane Chemical class B UORVGPXVDQYIDP-UHFFFAOYSA-N 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 239000010962 carbon steel Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- JGDFBJMWFLXCLJ-UHFFFAOYSA-N copper chromite Chemical compound [Cu]=O.[Cu]=O.O=[Cr]O[Cr]=O JGDFBJMWFLXCLJ-UHFFFAOYSA-N 0.000 description 1
- PWGQHOJABIQOOS-UHFFFAOYSA-N copper;dioxido(dioxo)chromium Chemical compound [Cu+2].[O-][Cr]([O-])(=O)=O PWGQHOJABIQOOS-UHFFFAOYSA-N 0.000 description 1
- LYAGTVMJGHTIDH-UHFFFAOYSA-N diethylene glycol dinitrate Chemical compound [O-][N+](=O)OCCOCCO[N+]([O-])=O LYAGTVMJGHTIDH-UHFFFAOYSA-N 0.000 description 1
- AXZAYXJCENRGIM-UHFFFAOYSA-J dipotassium;tetrabromoplatinum(2-) Chemical compound [K+].[K+].[Br-].[Br-].[Br-].[Br-].[Pt+2] AXZAYXJCENRGIM-UHFFFAOYSA-J 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 235000013773 glyceryl triacetate Nutrition 0.000 description 1
- 239000001087 glyceryl triacetate Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 150000004678 hydrides Chemical class 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- DCYOBGZUOMKFPA-UHFFFAOYSA-N iron(2+);iron(3+);octadecacyanide Chemical compound [Fe+2].[Fe+2].[Fe+2].[Fe+3].[Fe+3].[Fe+3].[Fe+3].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-].N#[C-] DCYOBGZUOMKFPA-UHFFFAOYSA-N 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 229910000464 lead oxide Inorganic materials 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 239000000395 magnesium oxide Substances 0.000 description 1
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 description 1
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 description 1
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 description 1
- 229910052753 mercury Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- XIFJZJPMHNUGRA-UHFFFAOYSA-N n-methyl-4-nitroaniline Chemical compound CNC1=CC=C([N+]([O-])=O)C=C1 XIFJZJPMHNUGRA-UHFFFAOYSA-N 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 229920000620 organic polymer Polymers 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- YEXPOXQUZXUXJW-UHFFFAOYSA-N oxolead Chemical compound [Pb]=O YEXPOXQUZXUXJW-UHFFFAOYSA-N 0.000 description 1
- BRBAEHHXGZRCBK-UHFFFAOYSA-N pentrinitrol Chemical compound [O-][N+](=O)OCC(CO)(CO[N+]([O-])=O)CO[N+]([O-])=O BRBAEHHXGZRCBK-UHFFFAOYSA-N 0.000 description 1
- 229950006286 pentrinitrol Drugs 0.000 description 1
- VLTRZXGMWDSKGL-UHFFFAOYSA-M perchlorate Inorganic materials [O-]Cl(=O)(=O)=O VLTRZXGMWDSKGL-UHFFFAOYSA-M 0.000 description 1
- VLTRZXGMWDSKGL-UHFFFAOYSA-N perchloric acid Chemical compound OCl(=O)(=O)=O VLTRZXGMWDSKGL-UHFFFAOYSA-N 0.000 description 1
- QCDYQQDYXPDABM-UHFFFAOYSA-N phloroglucinol Chemical compound OC1=CC(O)=CC(O)=C1 QCDYQQDYXPDABM-UHFFFAOYSA-N 0.000 description 1
- 229960001553 phloroglucinol Drugs 0.000 description 1
- 229920002857 polybutadiene Polymers 0.000 description 1
- 229920000573 polyethylene Polymers 0.000 description 1
- 229920000642 polymer Polymers 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
- 229910001487 potassium perchlorate Inorganic materials 0.000 description 1
- 229960003351 prussian blue Drugs 0.000 description 1
- 239000013225 prussian blue Substances 0.000 description 1
- 239000005060 rubber Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 229960002622 triacetin Drugs 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 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
- C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
- C06B21/0033—Shaping the mixture
- C06B21/0058—Shaping the mixture by casting a curable composition, e.g. of the plastisol type
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S149/00—Explosive and thermic compositions or charges
- Y10S149/11—Particle size of a component
- Y10S149/114—Inorganic fuel
Definitions
- This invention relates to a solid propellant composition having improved performance characteristics.
- the present method comprises the steps of mixing conventional propellants ingredients to form a batch, adding a staple to the batch, agitating the mixture to obtain substantially even distribution of the staple throughout said mixture, casting the mixture, subjecting the casting to a magnetic force in order to magnetically orientate the staples within the castings, and solidifying the casting.
- An exemplary propellant of the present invention may be composed of, a combination of; a binder, oxidizer, fuel and additives.
- the binder may be an inert or explosive polymer.
- Suitable binders include the following, singly or in combination: nitrocellulose; crosslinked nitrocellulose and plasticizer; polysulfide rubber; polyurethane; nitropolyurethane; petrin acrylate; polybutadiene acrylic acid copolymers; etc.
- Oxidizers include the following, singly or in combination: ammonium perchlorate; nitrionium perchlorate; potassium perchlorate; ammonium nitrate; cyclotetramethylenetetranitramine (HMX); cyclotrimethylenetrinitramine (RDX); pentaerythritol-tetrianitrate (PETN); etc.
- Fuels include the following, singly or in combination: aluminum; magnesium; aluminum and magnesium alloys; beryllium and beryllium alloys; hydrides of aluminum, magnesium or beryllium; boron and boron hydrides; etc. Additives may be utilized for the purpose of improving performance, stabilization and processability.
- Suitable additives include the following, singly or in combination: diphenylamine; 2-nitrodiphenylamine; N-methylparanitroaniline; magnesium oxide; resorcinol; phloroglucinol; lead oxide; lead salicylate; lead chromate; copper chromate; copper chromite; ferricacetylacetonate; prussian blue; etc.
- Plasticizers include the following, singly or in combination: nitroglycerin; butane-trioltrinitrate; triethyleneglycol dinitrate; diethyleneglycoldinitrate; trimetrioltrinitrate; triacetin; diethylphthalate; etc.
- the aforementioned materials are considered typical classes which can be utilized and the present invention is not considered to be limited thereto.
- the staple utilized is a small piece of metal of very small dimensions which is added to the propellant batch specifically to improve performance.
- the staple may be of any configuration, e.g., rectangular or cylindrical.
- the substance of the staple may be a magnetizable material, notably a highly magnetizable metal such as iron, cobalt or nickel, or combination thereof with a non magnetizable metal, e. g. copper, silver, gold, aluminum, zirconium, tungsten, etc., including alloys thereof.
- the staple may be composite in construction which may be achieved through rolling, stamping, gluing, welding, brazing, twisting, knotting, etc. The more effective arrangements are small rectangular shapes of metals or combinations of metals.
- the metallic staple may also be combined with a coating, casing, etc. of a non-metallic material, e.g. an organic polymer such as polyethylene, nylon, etc. The invention is not considered to be limited by the above choices, as others would be suggested to a person skilled in the art.
- FIG. I is a process flow sheet of the present method.
- FIG. 2 is a schematic of a system for the radial orientation of staples in a solid propellant prior to magnetical orientation.
- FIG. 3 is a view through line 33 of FIG. 2.
- FIG. 4 is a schematic of a system for the radial orientation of staples in a solid propellant after magnetical orientation.
- FIG. 5 is a view through line 55 of FIG. 4.
- FIG. 6 is a schematic of an alternative system for the parallel orientation of staples in a solid propellant prior to magnetical orientation.
- FIG. 7 is a schematic of an alternative system for the parallel orientation of staples in a solid propellant subsequent to magnetical orientation.
- FIG. 8 is a graph comparing the burning rate performance of a propellant composition with a radial oriented aluminum clad steel staple incorporated therein with a base composition.
- EXAMPLE 1 A 3,000 gram batch was prepared of a composition consisting of the following components in the percent by weight indicated:
- the ingredients were positioned in a vertically agitated jacketed vessel of approximately 2 gallon capacity.
- the jacket of the vessel was connected to a circulating hot water source.
- the batch was agitated at a temperature of to F at approximately 30 rpm under a vacuum of approximately 10mm of mercury. Agitation was continued until all ingredients were wetted and a batch viscosity of approximately 30,000 centipoises was achieved. This mixing covered a period of approximately 1 to 2 hours.
- 30 grams (1 percent by weight) of a staple was added to the batch.
- the staple utilized was composed of an inner layer of steel foil of approximately 0.0042 inch thickness to which was bonded by rolling two outer layers of aluminum foil each of approximately 0.0004 inch thickness.
- the layered foil was then cut to give staple pieces each approximately 0.005 inch in overall thickness, 0.015 inch wide and 0.170 inch long.
- the staple containing composition was agitated under mm l-lg at 30 rpm at a temperature of 90 to 100F for a period of approximately minutes.
- the casting cylinder utilized had an inside diameter of 3.29 inches and a height of 4.0 inches. While a cellulose acetate form was utilized, other materials, e.g., steel are operable.
- Cylindrical rod 15 constructed of carbon steel was inserted in a depression in plug 13, not shown, in a position coaxially with cylindrical form 11. The rod was approximately 1.29 inches in diameter. Rod 15 extends approximately 8 inches beyond the open end of form 11.
- Coil l7 composed of 1,908 turns of a 15 gauge copper magnet was affixed to the upper end of rod 15. The coil in turn was connected to a 12 volt battery source, designated 19. The current was adjusted and controlled by potentiometer 21 and switch 23.
- form 11 is filled with a composition containing staples 25.
- Switch 23 is closed as shown in FIG. 4 to complete the electrical circuit between battery l9 and coil 17 positioned on rod 15 thereby radially orienting staples 25 in the propellant composition, as illustrated in FIG. 5.
- Current through the coil was adjusted to 1.0 ampere.
- Cellulose acetate form 11 and the magnetic apparatus, excluding the battery, were then placed in an oven maintained at a temperature of l40F in order to solidify the mixture. The mixture was left in the oven for a period of 3 days. The current to the coil was discontinued after a period of one day and the coil removed when it was considered that the mixture was sufficiently solid so as not to affect the staple orientation due to settling.
- Propellant grains prepared by the above process were statically fired in rocket motors for measurement of pressure-time characteristics.
- a base composition identical to the present composition but containing no metal staples was prepared and also statically fired in rocket motors for measurement of pressure-time characteristics.
- the data obtained was used to calculate burning rate-pressure performance, as illustrated in FIG. 8.
- the data obtained indicates that improved performance, i.e., a burning rate increase of about 40 percent, was obtained through the employment of the present magnetically oriented staple containing composition.
- the pressure-time characteristics obtained with the magnetically oriented staple containing composition were very uniform, smooth and reproducible.
- the pressure-time characteristics obtained with the identical staple containing composition, wherein the staples were not magnetically oriented tended to be non-uniform, irregular and nonreproducible.
- Example 2 The method of Example l was modified to include 1.5 percent lead chromate by weight as a performance additive in the base composition of Example 1, and 1.0 percent by weight of a silver clad nickel foil 0.001 inch thickness cut to approximately 0.005 by 0.125 inch was added as the staple in place of the aluminum clad steel staple.
- An identical composition but containing no staples was also prepared.
- the propellants prepared with and without the radially oriented staples were test fired at ambient temperatures in static rocket motors. A to 200 percent increase in burning rate at 1,000 psi pressure was obtained by the utilization of the present propellant. In addition to the improved burning rate performance, pressure-time histories of combustion were extremely uniform and smooth.
- EXAMPLE 3 A 3,000 gram batch was prepared of a composition consisting of the following components in the percent by weight indicated:
- EXAMPLE 4 A propellant composition was prepared in accordance with the procedure set forth in Example 1. Alternative means of magnetically orienting the staples were utilized as shown schematically in FlGS. 6 and 7. The drawings illustrate that the apparatus for magnetization may be designed to any desired type of predetermined form to achieve orientation of the staple within the mixture to specific directions.
- a solid propellant composition having a dispersed staple, magnetically oriented therein said staple being a composite of a magnetizable metal, said magnetizable metal being nickel, and of another metal joined thereto, said other metal being silver.
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Crystallography & Structural Chemistry (AREA)
- Medicinal Preparation (AREA)
Abstract
Solid propellants compositions and method for the preparation thereof, comprising the addition of a staple to a wetted propellant composition, casting, subjecting the casting to a magnetic force in order to radially orient the staples therein, solidifying and recovering the product.
Description
United States Patent 1191 Baumann et al.
1 PROPELLANT COMPOSITION CONTAINING A NICKLE-SILVER COMPOSITE Inventors: Robert P. Baumann, Dover; Eugene F. Bozza, Rockaway, both of N.J.; Gardner S. Hunt, Freeport, Maine The United States of America as represented by the Secretary of the Army, Washington, DC.
Filed: June 30, 1972 Appl. N0.: 267,737
Related U.S. Application Data Division of Ser. No. 120,683, March 3, 1971,
abandoned.
[7 3] Assignee:
521 U.S. c1 149/2, 149/20, 149/38,
149/44, 149/114 1111. c1 C06b 19/00 Field of Search 149/2, 3120, 114,
ing the product.
Jan. 8, 1974 ""iieferii'cifd UNITED STATES PATENTS 11/1965 Papell 149/87 X 8/1971 Sayles 264/3 R X 11/1971 Lenoir 264/3 C Primary Examiner-Stephen J. Lechert, Jr. 4 ttomey- Edward T. Kelley and Herbert Berl [5 7] ABSTRACT 4 Claims, 8 Drawing Figures INVENTORS lllll HH Hiul OMOTOR FlRlNGS "BASE COMPOSITON o MOTOR FIRINGS COMPOSITION |.O
GOO
BURNING RATE PERFORMANCE FF'ENTEUJAW 8 i974 N N AMM iv m A BB \U P R E U RNN in 0. mm: 0 G Y B ATTORNEYS PROPELLANT COMPOSITION CONTAINING A NICKLE-SILVER COMPOSITE This is a division, of application Ser. No. 120,683, filed Mar. 3, 1971 now abandoned.
The invention described herein may be manufactured, used, and licensed by or for the Government for governmental purposes without the payment to us of any royalty thereon.
This invention relates to a solid propellant composition having improved performance characteristics.
The present method comprises the steps of mixing conventional propellants ingredients to form a batch, adding a staple to the batch, agitating the mixture to obtain substantially even distribution of the staple throughout said mixture, casting the mixture, subjecting the casting to a magnetic force in order to magnetically orientate the staples within the castings, and solidifying the casting.
An exemplary propellant of the present invention may be composed of, a combination of; a binder, oxidizer, fuel and additives. The binder may be an inert or explosive polymer. Suitable binders include the following, singly or in combination: nitrocellulose; crosslinked nitrocellulose and plasticizer; polysulfide rubber; polyurethane; nitropolyurethane; petrin acrylate; polybutadiene acrylic acid copolymers; etc. Oxidizers include the following, singly or in combination: ammonium perchlorate; nitrionium perchlorate; potassium perchlorate; ammonium nitrate; cyclotetramethylenetetranitramine (HMX); cyclotrimethylenetrinitramine (RDX); pentaerythritol-tetrianitrate (PETN); etc. Fuels include the following, singly or in combination: aluminum; magnesium; aluminum and magnesium alloys; beryllium and beryllium alloys; hydrides of aluminum, magnesium or beryllium; boron and boron hydrides; etc. Additives may be utilized for the purpose of improving performance, stabilization and processability. Suitable additives include the following, singly or in combination: diphenylamine; 2-nitrodiphenylamine; N-methylparanitroaniline; magnesium oxide; resorcinol; phloroglucinol; lead oxide; lead salicylate; lead chromate; copper chromate; copper chromite; ferricacetylacetonate; prussian blue; etc. Plasticizers include the following, singly or in combination: nitroglycerin; butane-trioltrinitrate; triethyleneglycol dinitrate; diethyleneglycoldinitrate; trimetrioltrinitrate; triacetin; diethylphthalate; etc. The aforementioned materials are considered typical classes which can be utilized and the present invention is not considered to be limited thereto.
The staple utilized is a small piece of metal of very small dimensions which is added to the propellant batch specifically to improve performance. The staple may be of any configuration, e.g., rectangular or cylindrical. The substance of the staple may be a magnetizable material, notably a highly magnetizable metal such as iron, cobalt or nickel, or combination thereof with a non magnetizable metal, e. g. copper, silver, gold, aluminum, zirconium, tungsten, etc., including alloys thereof. The staple may be composite in construction which may be achieved through rolling, stamping, gluing, welding, brazing, twisting, knotting, etc. The more effective arrangements are small rectangular shapes of metals or combinations of metals. The metallic staple may also be combined with a coating, casing, etc. of a non-metallic material, e.g. an organic polymer such as polyethylene, nylon, etc. The invention is not considered to be limited by the above choices, as others would be suggested to a person skilled in the art.
It is an object of this invention to provide and disclose a solid propellant composition having improved performance characteristics.
It is a further object of the invention to provide and disclose a solid propellant composition having magnetically oriented staples incorporated therein.
It is a further object of this invention to provide and disclose a method for magnetically orienting staples in a solid rocket propellant.
Other objects and a fuller understanding of the invention may be had by referring to the following description and claims taken in conjunction with the accompanying drawing in which:
FIG. I is a process flow sheet of the present method.
FIG. 2 is a schematic of a system for the radial orientation of staples in a solid propellant prior to magnetical orientation.
FIG. 3 is a view through line 33 of FIG. 2.
FIG. 4 is a schematic of a system for the radial orientation of staples in a solid propellant after magnetical orientation.
FIG. 5 is a view through line 55 of FIG. 4.
FIG. 6 is a schematic of an alternative system for the parallel orientation of staples in a solid propellant prior to magnetical orientation.
FIG. 7 is a schematic of an alternative system for the parallel orientation of staples in a solid propellant subsequent to magnetical orientation.
FIG. 8 is a graph comparing the burning rate performance of a propellant composition with a radial oriented aluminum clad steel staple incorporated therein with a base composition.
Set forth below are examples of the method utilized to carry out the present invention.
EXAMPLE 1 A 3,000 gram batch was prepared of a composition consisting of the following components in the percent by weight indicated:
a. 21 percent of a powder consisting of 90.0 percent nitrocellulose (12.6 nitrogen); 8.0 nitroglycerin and 2.0 percent nitrodiphenylamine, having a diameter of approximately l0 microns,
b. 0.5 percent of a powder consisting of 75.0 percent nitrocellulose (12.6 percent nitrogen); 24.0 percent nitroglycerin, and 1.0 percent 2- nitrodiphenylarnine, having a diameter of approximately 20-30 microns,
c. 44.5 percent of a solvent consisting of 34.0 percent butanetrioltrinitrate; 65.0 percent triethyleneglycol-dinitrate, and 1.0 percent 2- nitrodiphenylamine,
d. 13.0 percent aluminum comprising an atomized powder of approximately 15 microns in diameter,
e. 21.0 percent ammonium perchlorate atomized powder approximately 10 microns in diameter, and
f. 2.0 percent resorcinol, reagent grade.
The ingredients were positioned in a vertically agitated jacketed vessel of approximately 2 gallon capacity. The jacket of the vessel was connected to a circulating hot water source. The batch was agitated at a temperature of to F at approximately 30 rpm under a vacuum of approximately 10mm of mercury. Agitation was continued until all ingredients were wetted and a batch viscosity of approximately 30,000 centipoises was achieved. This mixing covered a period of approximately 1 to 2 hours. After the desired viscosity was achieved 30 grams (1 percent by weight) of a staple was added to the batch. The staple utilized was composed of an inner layer of steel foil of approximately 0.0042 inch thickness to which was bonded by rolling two outer layers of aluminum foil each of approximately 0.0004 inch thickness. The layered foil was then cut to give staple pieces each approximately 0.005 inch in overall thickness, 0.015 inch wide and 0.170 inch long. The staple containing composition was agitated under mm l-lg at 30 rpm at a temperature of 90 to 100F for a period of approximately minutes.
Thin walled cellulose acetate cylinder 11, which was closed at the bottom by removable plug 13, was utilized to cast the propellant. Illustrative, but without limitations, the casting cylinder utilized had an inside diameter of 3.29 inches and a height of 4.0 inches. While a cellulose acetate form was utilized, other materials, e.g., steel are operable. Cylindrical rod 15 constructed of carbon steel was inserted in a depression in plug 13, not shown, in a position coaxially with cylindrical form 11. The rod was approximately 1.29 inches in diameter. Rod 15 extends approximately 8 inches beyond the open end of form 11. Coil l7 composed of 1,908 turns of a 15 gauge copper magnet was affixed to the upper end of rod 15. The coil in turn was connected to a 12 volt battery source, designated 19. The current was adjusted and controlled by potentiometer 21 and switch 23.
In operation, form 11 is filled with a composition containing staples 25. Switch 23 is closed as shown in FIG. 4 to complete the electrical circuit between battery l9 and coil 17 positioned on rod 15 thereby radially orienting staples 25 in the propellant composition, as illustrated in FIG. 5. Current through the coil was adjusted to 1.0 ampere. Cellulose acetate form 11 and the magnetic apparatus, excluding the battery, were then placed in an oven maintained at a temperature of l40F in order to solidify the mixture. The mixture was left in the oven for a period of 3 days. The current to the coil was discontinued after a period of one day and the coil removed when it was considered that the mixture was sufficiently solid so as not to affect the staple orientation due to settling. Propellant grains prepared by the above process were statically fired in rocket motors for measurement of pressure-time characteristics. A base composition identical to the present composition but containing no metal staples was prepared and also statically fired in rocket motors for measurement of pressure-time characteristics. The data obtained was used to calculate burning rate-pressure performance, as illustrated in FIG. 8. The data obtained indicates that improved performance, i.e., a burning rate increase of about 40 percent, was obtained through the employment of the present magnetically oriented staple containing composition. The pressure-time characteristics obtained with the magnetically oriented staple containing composition were very uniform, smooth and reproducible. In contrast thereto the pressure-time characteristics obtained with the identical staple containing composition, wherein the staples were not magnetically oriented, tended to be non-uniform, irregular and nonreproducible. By alignment of staples according to this invention it was possible to approach maximum buming rates achieved with continuous wire filaments.
EXAMPLE 2 The method of Example l was modified to include 1.5 percent lead chromate by weight as a performance additive in the base composition of Example 1, and 1.0 percent by weight of a silver clad nickel foil 0.001 inch thickness cut to approximately 0.005 by 0.125 inch was added as the staple in place of the aluminum clad steel staple. An identical composition but containing no staples was also prepared. The propellants prepared with and without the radially oriented staples were test fired at ambient temperatures in static rocket motors. A to 200 percent increase in burning rate at 1,000 psi pressure was obtained by the utilization of the present propellant. In addition to the improved burning rate performance, pressure-time histories of combustion were extremely uniform and smooth.
EXAMPLE 3 A 3,000 gram batch was prepared of a composition consisting of the following components in the percent by weight indicated:
a. 55 percent of a powder consisting of 90.0 percent nitrocellulose (12.6 nitrogen), 8.0 percent nitroglycerin, 2.0 percent Z-nitrodiphenylamine, approximately 10 microns in diameter, and
b. 45 percent of a casting solvent consisting of 34.0
percent butanetrioltrinitrate, 65.0 percent triethyleneglycoldinitrate and 1.0 percent 2- nitrodiphenylamine. All other aspects of the invention practiced in this example were identical to those utilized in Example 1. An identical composition was prepared except that no staples were incorporated. The propellant grains prepared with and without the radially oriented staples were tested in rocket motors. Grains prepared in accordance with the present invention exhibited increased buming rate performance concurrent with smooth and uniform pressure-time combustion histories.
EXAMPLE 4 A propellant composition was prepared in accordance with the procedure set forth in Example 1. Alternative means of magnetically orienting the staples were utilized as shown schematically in FlGS. 6 and 7. The drawings illustrate that the apparatus for magnetization may be designed to any desired type of predetermined form to achieve orientation of the staple within the mixture to specific directions.
Although we have described our invention with a certain degree of particularity, we wish it to be understood that we do not desire to be limited to the exact details of formulations of propellants and means of magnetization shown and described, for obvious modifications will occur to a person skilled in the art.
Having described our invention, we claim.
1. A solid propellant composition having a dispersed staple, magnetically oriented therein said staple being a composite of a magnetizable metal, said magnetizable metal being nickel, and of another metal joined thereto, said other metal being silver.
2. A solid propellant composition in accordance with claim 1 wherein the staple is radially oriented.
3. A solid propellant composition in accordance with claim 1 wherein the staple is parallel oriented.
4. A solid propellant composition in accordance with plaim 1 wherein the metal staple is a silver clad nickel oil.
Claims (3)
- 2. A solid propellant composition in accordance with claim 1 wherein the staple is radially oriented.
- 3. A solid propellant composition in accordance with claim 1 wherein the staple is parallel oriented.
- 4. A solid propellant composition in accordance with claim 1 wherein the metal staple is a silver clad nickel foil.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US26773772A | 1972-06-30 | 1972-06-30 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3784419A true US3784419A (en) | 1974-01-08 |
Family
ID=23019951
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US00267737A Expired - Lifetime US3784419A (en) | 1972-06-30 | 1972-06-30 | Propellant composition containing a nickle-silver composite |
Country Status (1)
Country | Link |
---|---|
US (1) | US3784419A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US5325783A (en) * | 1988-11-10 | 1994-07-05 | Composite Materials Technology, Inc. | Propellant formulation and process |
US5348597A (en) * | 1988-11-10 | 1994-09-20 | Composite Materials Technology, Inc. | Propellant formulation and process containing bi-metallic metal mixture |
US5388518A (en) * | 1988-11-10 | 1995-02-14 | Composite Materials Technology, Inc. | Propellant formulation and process |
US5472533A (en) * | 1994-09-22 | 1995-12-05 | Alliant Techsystems Inc. | Spectrally balanced infrared flare pyrotechnic composition |
US20070251615A1 (en) * | 2003-03-10 | 2007-11-01 | Amtower Paul K Ii | Propellant formulation and projectiles and munitions employing same |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3215572A (en) * | 1963-10-09 | 1965-11-02 | Papell Solomon Stephen | Low viscosity magnetic fluid obtained by the colloidal suspension of magnetic particles |
US3598668A (en) * | 1965-11-30 | 1971-08-10 | Us Army | Staple-containing solid propellant grain and method of preparation |
US3617586A (en) * | 1963-12-30 | 1971-11-02 | John M Lenoir | Burning rate accelerating method |
-
1972
- 1972-06-30 US US00267737A patent/US3784419A/en not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3215572A (en) * | 1963-10-09 | 1965-11-02 | Papell Solomon Stephen | Low viscosity magnetic fluid obtained by the colloidal suspension of magnetic particles |
US3617586A (en) * | 1963-12-30 | 1971-11-02 | John M Lenoir | Burning rate accelerating method |
US3598668A (en) * | 1965-11-30 | 1971-08-10 | Us Army | Staple-containing solid propellant grain and method of preparation |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US5325783A (en) * | 1988-11-10 | 1994-07-05 | Composite Materials Technology, Inc. | Propellant formulation and process |
US5348597A (en) * | 1988-11-10 | 1994-09-20 | Composite Materials Technology, Inc. | Propellant formulation and process containing bi-metallic metal mixture |
US5388518A (en) * | 1988-11-10 | 1995-02-14 | Composite Materials Technology, Inc. | Propellant formulation and process |
US5404813A (en) * | 1988-11-10 | 1995-04-11 | Composite Materials Technology, Inc. | Propellant formulation and process |
US5472533A (en) * | 1994-09-22 | 1995-12-05 | Alliant Techsystems Inc. | Spectrally balanced infrared flare pyrotechnic composition |
US20070251615A1 (en) * | 2003-03-10 | 2007-11-01 | Amtower Paul K Ii | Propellant formulation and projectiles and munitions employing same |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US5411615A (en) | Aluminized eutectic bonded insensitive high explosive | |
US8361258B2 (en) | Reactive compositions including metal | |
US3689331A (en) | Nitrocellulose base compositions and method for making same | |
US6969434B1 (en) | Castable thermobaric explosive formulations | |
US5034073A (en) | Insensitive high explosive | |
US3784419A (en) | Propellant composition containing a nickle-silver composite | |
US3695952A (en) | Solid propellant compositions containing hydroxymethyl-terminated polydienes | |
US3986910A (en) | Composite propellants containing critical pressure increasing additives | |
US3379588A (en) | Manufacture of plastic high-power blasting explosive compositions and charges | |
US3726729A (en) | Solid propellant compositions having a nitrocellulose-hydroxyl-terminated polybutadiene binder and method of preparing the same | |
US3923564A (en) | Double base propellant with thorium containing ballistic modifier | |
US4000025A (en) | Incorporating ballistic modifiers in slurry cast double base containing compositions | |
CA1168052A (en) | Poly-base propellant | |
GB1277192A (en) | Improvements in and relating to nitrocellulose base propellant compositions | |
US3755019A (en) | Solid propellant compositions containing plasticized nitrocellulose and aluminum hydride | |
US3180770A (en) | Propellant fuel containing magnesium aluminum alloy | |
US3598668A (en) | Staple-containing solid propellant grain and method of preparation | |
US3834956A (en) | Solid propellant composition containing lead and lead compounds | |
US3742859A (en) | Explosive charge | |
US6641683B1 (en) | Plasticized, wax-based binder system for melt castable explosives | |
US3767489A (en) | Nitrasol propellant | |
US3317361A (en) | Flexible plasticized explosive of cyclonitramine and nitrocellose and process therefor | |
US4039361A (en) | Dry blasting agents | |
US4154633A (en) | Method for making solid propellant compositions having a soluble oxidizer | |
US3140207A (en) | Pyrotechnic composition |