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Burning rate catalysts for ammonium nitrate propellants

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US2963356A
US2963356A US60977956A US2963356A US 2963356 A US2963356 A US 2963356A US 60977956 A US60977956 A US 60977956A US 2963356 A US2963356 A US 2963356A
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Guth Eugene Daniel
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ConocoPhillips Co
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    • CCHEMISTRY; METALLURGY
    • C06EXPLOSIVES; MATCHES
    • C06BEXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B45/00Compositions or products which are defined by structure or arrangement of component of product
    • C06B45/04Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive
    • C06B45/06Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component
    • C06B45/10Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component the organic component containing a resin
    • CCHEMISTRY; METALLURGY
    • C06EXPLOSIVES; MATCHES
    • C06BEXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B23/00Compositions characterised by non-explosive or non-thermic constituents
    • C06B23/007Ballistic modifiers, burning rate catalysts, burning rate depressing agents, e.g. for gas generating
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S149/00Explosive and thermic compositions or charges
    • Y10S149/11Particle size of a component
    • Y10S149/112Inorganic nitrogen-oxygen salt
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S149/00Explosive and thermic compositions or charges
    • Y10S149/11Particle size of a component
    • Y10S149/113Inorganic oxygen-halogen salt

Description

EURNING RATE CATALYSTS FOR AIMMONIUM NETRATE PROPELLANTS Eugene Daniel Guth, Bartlesville, kla., assignor to Phillips Petroleum Company, a corporation of Delawere No Drawing. Filed Sept. 13, 1956, Ser. No. 609,779

7 Claims. (Cl. 52-.5)

This invention relates to solid propellants. More particularly, this invention relates to a new class of burning rate catalysts for solid propellants.

Recently it has been discovered that superior solid propellant materials are obtained comprising a solid oxidant such as ammonium nitrate or ammonium perchlorate, and a rubbery copolymer of butadiene and a vinylpyridine or other vinyl substituted heterocyclic nitrogen base compound, which after incorporation of the oxidant is cured by a quaternization reaction or a vulcanization reaction. Solid propellant mixtures of this nature and a process for their production are disclosed and claimed in copending application Serial No. 284,447, filed April 2,063,356 Patented D es. 6, teen An object of this invention is to provide a new class of burning rate catalysts for solid propellants prepared from ammonium nitrate and a rubbery binder. A further object of this invention is to provide such propellants having increased burning rates.

Other objects and advantages of this invention will be apparent to one skilled in the art upon reading this disclosure.

It is believed that this invention can be best understood from a specific example including a series of runs employing this new group of burning rate catalysts.

In the following table a series of catalyst systems are set forth and the burning rate is given at two different pressures. In each case, the amount used is given as parts by weight per 100 parts of the propellant. The column headed temperature of reaction with N 0 refers to the temperature at which the catalyst compound begins to react with N 0. The tests with nitrous oxide were made with the catalyst, finely divided, in a tube which was inside a furnace. The nitrous oxide was passed through the tube at a flow rate sufiicient to maintain a fairly pure atmosphere over the material. The temperature was gradually increased during each run and visual observations were made to determine when the reaction occurred. The burning rate of the propellant is about 0.100 inch per second when no burning rate catalyst is used.

TABLE I Reaction of catalyst systems with nitrous oxide [Strand data. 1' vs. P curve] Tempera- 1- at 600 r at 1,000 ture of Propellant Catalyst System, Parts p.s.i. p.s.i. 12 Reaction Remarks (in/sec.) (um/sec.) w 1172] 5. 0,

Ila/@1101"; glue 0.144 0.199 0. 58 300 1 Oil l1B 2 4.0 Sodium borohydrlde 0-153 211 61 fig i ggfig g 0. 147 0. 204 0. 64 220 g g fi fi gf 0.15s 0. 225 0. 55 400 Vigorous glow.

. 011 11G 4,0 Zincon'dum carbide 0.168 0. 223 0. 52 400 D0. :8 j 0.191 0. 246 0. 51 220 D0. 4.0 Milori blue. 0.165 0. 201 300 25, 1952, and now abandoned, by W. B. Reynolds and J. E. Pritchard.

Various materials have been added to these compositions in order to increase the burning rate thereof. I have discovered that a group of metals, metal hydrides, or metal carbides will increase the burning rate of these propellants in which the ammonium nitrate is used as the oxidant. Metals, metal hydrides, or metal carbides which are applicable are those which react with nitrous oxide at initial temperatures below 406 C. and which do not react with ammonium nitrate at temperatures below 60 C. These materials react with the nitrous oxide to give a glowing hot solid and act as an ignition source behind the flame, thereby increasing the burning rate of the propellants. They should not react with ammonium nitrate below 60 C., in order to eliminate the possibility of reaction in storage. Examples of these compounds include sodium borohydride, zirconium, zirconium hydride, zirconium carbide, titanium and cerium. These compounds are added to the solid propellant during the formulation thereof and are preferably added as finely divided materials. Broadly, the amount of these materials added is in the range of 0.5 to 10 parts per 100 parts of total propellant, 1 to 4 parts being most commonly used.

Therefore, the following are objects of this invention:

It is readily obvious from the data in this table that there is a correlation between the reaction temperature of each material with nitrous oxide at atmosphere pressure and the burning rate increase. Those materials which have a low temperature of reaction with nitrous oxide increase the burning rate more than those with a high reaction temperature.

The rubbery polymers employed as binders in the solid propellant compositions of this invention are copolymers of conjugated dienes with polymerizable heterocyclic nitrogen bases of the pyridine series. These copolymers can vary in consistency from very soft rubbers, i.e., materials which are soft at room temperature but will show retraction when relaxed, to those having a Mooney value (ML4) up to 100. Copolymers of higher Mooney value can be used if large softener loadings are used. The rubbery copolymers most frequently preferred have Mooney values in the range between 10 and 40. They may be prepared by any polymerization methods known to the art, e.g., mass or emulsion polymerization. One convenient method for preparing these c0- polymers is by emulsion polymerization at temperatures in the range between 0 and F. Recipes such as the iron pyrophosphate-hydroperoxide, either sugar-free or containing sugar, the sulfoxylate and the persulfate recipes are among those which are applicable. It is advantageous to polymerize to high conversion as the unreacted vinylpyridine monomer is diflicult to remove by stripping.

The conjugated dienes employed are those containing from 4 to 6 carbon atoms per molecule and'include- 1,3- butadiene, isoprene, 2-mcthyl-l,3-butadiene, 2,3dimethyl 1,3-butadiene, and the like. Various alkoxy, such as methoxy and ethoxy and cyano derivatives of these conjugated dienes, are also applicable. Thus, other dienes, suchas phenylbutadiene, 2,3-dimethyl-1,3-hexadien'e, 2- meth'oXy-3-ethylbutadiene, 2-ethoxy-3-ethyl l,3-ihexadiene, 2-cyano-1,3-butadiene, are also applicable in the preparation of the polymeric binders of this invention.

Instead of using a single conjugated diene, a mixture of conjugated dienes can be employed. Thus, a mixture of 1,3-butadiene and isoprene can be employed as the conjugated 'diene'porti0n of the monomer system.

The polymerizable heterocyclic nitrogen bases which are applicable for the production of the polymeric materials are those of the pyridine, quinoline, and isoquinoline series which are copolymerizable with a conjugated diene and contain one, and only one,

/R'. CH2=C substituent wherein R is either hydrogen or a methyl group. That is, the substituent is either a vinyl or an .alpha-methylvinyl (isopropenyl) group. Of these, the compounds of the pyridine series are of the greatest interest commercially at present. Various substituted derivatives are also applicable but the total number of carbon atoms in the groups attached to the carbon atoms of the heterocyclic nucleus should not be greater. than 12 because the polymerization rate decreases somewhat with increasing size of the alkyl group. Compounds where the alkyl substituents are methyl and/or ethyl are available commercially.

These heterocyclic nitrogen bases have the formula where R is selected from the group consisting of hydrogen, alkyl, vinyl, alpha-methylvinyl, alkoxy, halo, hydroxy, cyano, aryloxy, aryl, and combinations of these groups such as haloalkyl, alkylaryl, hydroxyaryl, and the like; one and only one of said groups being selected from the group consisting of vinyl and alpha-methylvinyl; and the total number of carbon atoms in the nuclear substituted groups, in addition to the vinyl or alpha-methylvinyl group, being not greater than 12. Examples of such compounds are 2-vinylpyridine; 2-vinyl-5-ethylpyridine; 2-methyl-5-vinylpyridine; 4-vinylpyridine; 2,3,4-trimethy1- S-vinylpyridine; 3,4,5,6-tetra-methyl-2-vinylpyridine; 3- ethyl-S-vinylpyridine; 2,6-diethyl-4-vinylpyridine; 2-isopropyl-4-nonyl-5-vinylpyridine; 2-methyl-5-undecyl-3-vinylpyridine; 2,4-dimethyl-5,6-dipentyl-3-vinylpyridine; 2- decy1-5-(alpha-methylvinyl)pyridine; 2-vinyl-3-methyl-5- ethylpyridine; 2-methoxy-4-chloro-6-vinylpyridine; 3-vinyl-S-ethoxypyridine; 2-vinyl-4,5-dichloropyridine; 2-(alpha-methylvinyl)-4-hydroxy-6-cyanopyridine; 2-vinyl-4- phenoxy-S-methylpyridine; 2-cyano-5-(alpha methylvinyl)pyridine; 3-vinyl-5-phenylpyridine; Z-(para-methylphenyl)-3-vinyl-4-methylpyridine; 3-vinyl 5 (hydroxyphenyl)-pyridine; 2-vinylquinoline; 2-vinyl-4-ethylquinoline; 3-vinyl6,7-di-n-propylquinoline; 2-methyl-4-nonyl-6- vinylquinoline; 4-(alpha-methylvinyl)-8-dodecylquinoline; 3-viny1isoquinoline; 1,6-dimethyl-3-vinylisoquinoline; 2- vinyl-4-benzylquinoline; 3-vinyl-5-chloroethylquinoline; 3- vinyl-S,6-dichloroisoquinoline; 2-vinyl-6-ethoxy-7-methylquinoline; 3-vinyl-6-hydroxymethylisoquinoline; and the like. Mixtures of these heterocyclic nitrogen bases can be used, if desired.

The polymer used'as the binder in the propellant 111118 previously described was a portion of the product produced in a series of 55 runs. The following recipe was "'used:

Parts by weight Butadiene 1 90 Z-methyl-S-vinylpyridine 10 Water 200 Potassium fatty acid soap 6.0 KCI 0.1 Sodium alkyl aryl sulfonate 0.3 Tetra sodium salt of ethylenediamine tetracetic acid 0.005 Tertiary dodecyl mercaptan Variable Ferrous sulfate heptahydrate 0.2 Potassium pyrophosphate 0.253 Paramenthane hydroperoxide 0.1 or 0.135

'dithiocarbamate an amount of 0.15 part. The polymer was stabilized by adding 1.75 percent by weight based on the polymer of phenyl-beta-napthylamine.

The latex was masterbatched with 19.5 parts of Philblack A carbon black per parts of rubber and acid coagulated. The crumb was caustic (potassium hydroxide) washed at a high pH to convert the organic acid to soap which was washed out to obtain a product with low organic acid and soap and subsequently dried. The binder for propellants 1 through 6 was as follows:

Parts by weight Copolymer 100 Carbon black 20 ZP-2l1 1 20 Flexamine 3 3 1 5,8.11,13.16.19-hex cxa-n-tricosane.

5 A physical mixture .ontaining 65 percent of a complex dtarylamine-ketone react on product and 35 percent of N,N- diphenyl-p-phenylenedlamine.

The binder for propellant 7 was as follows:

Parts by weight Copolymer 100 Carbon black 20 Benzophenone 20 Flexamine 1 3.0

N,N-dimethyl-S-tert-butylsulfenyl dithiocarbamate 1.0 Sulfur 0.75 Zinc oxide 3.0

I 5,8,11,13,16,19-hexoxa-n-tr1cosane.

Lia K...)

The complete composition of each propellant is shown in the following table:

For each run, the polymer was placed on a roll mill and additional black was added to bring the loading to the desired level. The Flexamine was also added on the mill.

The resulting mixture was placed in a Baker-Perkins mixer and the plasticizer and magnesium oxide and curatives, if used, were added and the composition mixed until a homogeneous mixture was obtained. The catalyst and ammonium nitrate were blended together and added to the binder in four portions, each time the mixing being continued until the mixer started drawing power. A final mixing of 5 to 10 minutes after addition of all the oxidizer was provided to insure uniformity.

The propellant was made into strands by extruding it under a pressure of 8000 p.s.i.

Regular propellant grade ammonium nitrate or ammonium perchlorate is used as the oxidant in the propellants of my invention. It should be finely divided, preferably in a range of 300 to 10 microns average particle size. The amount of oxidant is generally in the range of 50 to 90 percent by weight of the total of the oxidant and binder. If desired, however, less than 50 percent by weight can be used.

The combustion rate catalysts of my invention can be used alone or in combination with combustion rate catalysts known in the art, such as ammonium dichromate and metal ferrocyanides and ferricyanides. Ferric ferrocyanides, such as Prussian, Berlin, Hamburg, Chinese, Paris and Milori blue, soluble ferric ferrocyanide, such as soluble Berlin or Prussian blue which contains potassium ferric ferrocyanide, and ferric ferrocyanide which has been treated with ammonia, are among the materials which can be used. Ferrous ferricyanide, T urnbulls blue is also applicable. Milori blue is a pigment similar to Prussian blue but having a red tint and is prepared by the oxidation of a paste of potassium ferrocyanide and ferrous sulfate. Other metal compounds such as nickel and copper ferrocyanides can also be employed.

The amount of burning rate catalyst used, in the propellant compositions of this invention, are usually in the range of l to 60 parts per 100 parts of rubbery polymer with from 5 to 50 parts being most frequently preferred. The amount of combustion catalyst will usually be 0.5 to 10 parts by weight per hundred parts of oxidant and binder, with a range of l to 4 parts being preferred. When the combination catalysts are used from 0.5 to 10 parts of the catalyst according to the present invention (metal, metal carbide, or metal hydride) is used per 100 parts by weight of propellant and from 0.25 to 5 parts of the prior art catalyst such as Milori blue are used.

The binder contains a rubbery copolymer of the type hereinbefore described and, in addition, there can be present one or more reinforcing agents, plasticizers, wetting agents, and antioxidants. Other ingredients which are employed for sulfur vulcanization include a vulcanization accelerator, a vulcanizing agent such as sulfur, and an accelerator activator, such as zinc oxide.

The copolymer comprising a conjugated diene and a polymerizable heterocyclic nitrogen base can also be cured by a quaternization reaction by incorporating therein a quaternizing agent and subjecting the resulting mixture to quaternizing conditions of temperature. Suitable quaternizing agents include alkyl halides such as methyl iodide, methyl bromide; alkylene halides such as methylene iodide, ethylene bromide; substituted alkanes such as chloroform, bromoform; alkyl sulfates such as methyl sulfate; and various substituted aromatic compounds such as benzoyl chloride, methyl benzene sulfonate, and the like.

The quaternizing temperature is usually in the range zero to 175 0, although temperatures outside this range can be used.

A general formulation for a binder composition prepared by sulfur vulcanization is given below:

Parts by weight Rubbery copolymer (as hereinbefore described) Reinforcing agent 0-50 Plasticizer 0-100 Wetting agent 0-10 Antioxidant 0-3 Vulcanization accelerator 0-5 Sulfur 0-2 Zinc oxide 0-5 Reinforcing agents include carbon black, silica gel, lignin, and various reinforcing resins such as styrene-divinylbenzene, methyl acrylate-divinyl-benzene, acrylic acid-styrene-divinylbenzene, and methyl acrylate-acrylic acid-divinyl-benzene resins.

In general, any rubber plasticizers can be employed in these binder compositions. Materials such as Pentaryl A (amylbiphenyl), Parafiux (saturated polymerized hydrocarbon), Circosol-ZXH (petroleum hydrocarbon softener having a specific gravity of 0.940 and a Saybolt Universal viscosity at 100 F. of about 2000 seconds), di (1,4,7-trioxaundecyl)methane, and dioctyl phthalate are suitable plasticizers. Materials which provide rubber having good low temperature properties are preferred. It is also frequently preferred that the plasticizers be oxygen-containing materials.

Wetting agents aid in deflocculating or dispersing the oxidizer, Aerosol OT (dioctyl ester of sodium sulfosuccinic acid), lechithin, and Duomeen C diacetate (the diacetate of trimethylene diamine substituted by a coconut oil product) are among the materials which are applicable.

Antioxidants include Flexamine (physical mixture containing 65 percent of a complex diarylamine-ketone reaction product and 35 percent of N,N-diphenyl-p-phenylenediamine), phenyl-beta-naphthylamine, 2,2-methylenebis(4-methy1-6-tert-butylphenol), and the like. Rubber antioxidants, in general, may be employed or if desired may be omitted.

Examples of vulcanization accelerators are those of the carbamate type, such as N,N-dimethyl-S-tert-butylsulfenyl dithiocarbamate and Butyl-Eight. Butyl Eight is a rubber accelerator of the dithiocarbamate type described in Handbook of Material Trade Names by Zimmerman and Lavine, 1953 edition, as a brown liquid; specific gravity 1.01; partially soluble in water and gasoline; and soluble in acetone, alcohol, benzol, carbon disulfide and chloroform.

It is to be understood that each of the various types of compounding ingredients may be used singly or mixtures of various ingredients performing a certain function may be employed. It is sometimes preferred, for example, to use mixtures of plasticizers rather than a single material.

The various ingredients in the propellant composition may be mixed on a roll mill or an internal mixer such as a Banbury or a Baker-Perkins dispersion blade mixer may be employed. The binder forms a continous phase in the propellant with the oxidant as the discontinuous phase.

Rocket grains are formed by compression molding, injection molding, or extrusion.

The curing temperature will be limited by the oxidizer employed in some cases but will generally be in the range between 70 and 250 F., preferably between and 200 F.

The curing time must be long enough to give required creep resistance and other mechanical properties in the propellant. The time will generally range from around three hours when the higher curing temperatures are employed to seven days when curing is eflect'ed at lower temperatures- A 1 v p As many. possible embodiments may be made of this invention without departing from the scopethereof, it is to be'understood that all matter herein set forth is to be interpreted as illustrative and not in a limiting sense.

I claim:

, 1. A-propellant composition comprisingfrom 50 to 90 parts by weight of ammonium nitrate; from- 10 to 50parts by weight of a copolymer of'b'utadiene a'nd'Z-methyl-S- inylpyfidine to make a total of 100 parts by weight; from 0.25 to 5 parts by Weight of Milori blue; and from 0.5' to IO-parts by weightof sodiumb'orohydride.

2. A-propellant composition comprising from 50 to 90 parts by-weightof ammonium nitrate; from to 50 parts by weight-o? a-copolymer of butadiene and Z-methyl-S- yinylpyridineto make a--total "of 100 parts by weight; from 0.25 to '5 parts by weight of Milori-blue; and from 0.5 to 10partsby weight of-zirconium.

3. A propellant composition comprising from 50 to 90' parts by weight ofammonium nitrate; from 10 to 50 parts by'weight of a copolymer of butadiene and Z-methyl- 5-vinylpyridine to make a total of 100 parts by weight; from 0.25 to 5 parts by weight of Milori blue; and from 0.5 to 10 parts by weight of zirconium hydride.

4. A propellant composition comprising from 50 to 90 parts by weight of ammonium nitrate; from- 10 to 50 parts by weight of a copolymer of butadiene and 2-methyls vinylpyridine to make a total of 100 parts by weight; from 0.25-to 5 parts by weight of Milori blue; and from 0.5 to 10 parts by weight of zirconium carbide. -5'. A propellant composition comprising from 5010 90 parts -by weight of ammonium nitrate; from 10 to 50 parts by Weight of a copolymer of butadiene andZ-methyl- 5-vinylpynidine to make a total of 100 parts by weight; from 0.25 to 5 parts of 100 parts by weight; from 0.25

'ing'upte 8 carbon" atoms 'permolecule with at'lea'st one 1 substituted heterocylic nitrogen' base selected from the group consisting of pyridine, quinoline, alkyl substituted pyridine,- and alkyl substituted quinoline, wherein the total number of carbon atoms in the nuclear alkyl substituents is not more than 12 and wherein R is selected from thegroup consisting of hydrogen and a methyl radical, to'make a total of parts by weight; from 0.25 to 5 parts by'weight'of a compound selected from the group consisting of ammonium dichromate, .ferric ferrocyanide, ferrousferricyanide, copper ferrocyanide and nickel ferrocyanideyand-from 0.5 to 10 parts by weightof a material selectedfrom the group consisting of sodium borohydride, zirconium, zirconium hydride, zirconium carbide, titanium and cerium. t r

7. The propellant ofclaim 6 wherein'said-copolymer is a copolymer of butadiene'and Z-methyl-S-vinylpyridine.

References Cited in the file of this patent UNITED STATES PATENTS

Claims (1)

1. A PROPELLANT COMPOSITION COMPRISING FROM 50 TO 90 PARTS BY WEIGHT OF AMMONIUM NITRATE, FROM 10 TO 50 PARTS BY WEIGHT OF A COPOLYMER OF BUTADIENE AND2-METHYL-5VINYLPYRIDINE TO MAKE A TOTAL OF 100 PARTS BY WEIGHT, FROM 0.25 TO 5 PARTS BY WEIGHT OF MILORI BLUE, AND FROM 0.5 TO 10 PARTS BY WEIGHT OF SODIUM BOROHYDRIDE.
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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3159104A (en) * 1959-11-02 1964-12-01 Solid Fuels Corp Laminated tape propellants
US4302259A (en) * 1979-10-31 1981-11-24 The United States Of America As Represented By The Secretary Of The Army MgH2 and Sr(NO3)2 pyrotechnic composition
US6306232B1 (en) 1996-07-29 2001-10-23 Automotive Systems Laboratory, Inc. Thermally stable nonazide automotive airbag propellants
US20050257866A1 (en) * 2004-03-29 2005-11-24 Williams Graylon K Gas generant and manufacturing method thereof
US20090057609A1 (en) * 2007-07-13 2009-03-05 Snpe Materiaux Energetiques Solid hydrogen source compounds and method for generating hydrogen

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1708186A (en) * 1924-05-21 1929-04-09 Sterner St P Meek Tracer composition
US2309978A (en) * 1940-06-21 1943-02-02 Atlas Powder Co Propellent fuel assembly
US2433943A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Operation of jet propulsion motors with nitroparaffin
US2555333A (en) * 1948-05-27 1951-06-05 Joseph A Grand Solid fuel
GB655585A (en) * 1947-09-29 1951-07-25 Frans Tore Baltzar Bonell Improvements in or relating to methods for producing propellent charges for rockets and the like
US2570632A (en) * 1948-04-01 1951-10-09 Us Rubber Co Improving the cut growth resistance of butadiene-vinyl pyridine rubbery copolymers

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1708186A (en) * 1924-05-21 1929-04-09 Sterner St P Meek Tracer composition
US2309978A (en) * 1940-06-21 1943-02-02 Atlas Powder Co Propellent fuel assembly
US2433943A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Operation of jet propulsion motors with nitroparaffin
GB655585A (en) * 1947-09-29 1951-07-25 Frans Tore Baltzar Bonell Improvements in or relating to methods for producing propellent charges for rockets and the like
US2570632A (en) * 1948-04-01 1951-10-09 Us Rubber Co Improving the cut growth resistance of butadiene-vinyl pyridine rubbery copolymers
US2555333A (en) * 1948-05-27 1951-06-05 Joseph A Grand Solid fuel

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3159104A (en) * 1959-11-02 1964-12-01 Solid Fuels Corp Laminated tape propellants
US4302259A (en) * 1979-10-31 1981-11-24 The United States Of America As Represented By The Secretary Of The Army MgH2 and Sr(NO3)2 pyrotechnic composition
US6306232B1 (en) 1996-07-29 2001-10-23 Automotive Systems Laboratory, Inc. Thermally stable nonazide automotive airbag propellants
US20050257866A1 (en) * 2004-03-29 2005-11-24 Williams Graylon K Gas generant and manufacturing method thereof
US20100269965A1 (en) * 2004-03-29 2010-10-28 Williams Graylon K Gas generant and manufacturing method thereof
US20090057609A1 (en) * 2007-07-13 2009-03-05 Snpe Materiaux Energetiques Solid hydrogen source compounds and method for generating hydrogen
US7964111B2 (en) * 2007-07-13 2011-06-21 Snpe Materiaux Energetiques Solid hydrogen source compounds and method for generating hydrogen

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