US3865659A - Nitrocellulose propellant composition containing metal and triaminoguanidinium hydrazinium diazide - Google Patents
Nitrocellulose propellant composition containing metal and triaminoguanidinium hydrazinium diazide Download PDFInfo
- Publication number
- US3865659A US3865659A US465253A US46525365A US3865659A US 3865659 A US3865659 A US 3865659A US 465253 A US465253 A US 465253A US 46525365 A US46525365 A US 46525365A US 3865659 A US3865659 A US 3865659A
- Authority
- US
- United States
- Prior art keywords
- percent
- weight
- parts
- triaminoguanidinium
- diazide
- 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 48
- 239000003380 propellant Substances 0.000 title claims abstract description 34
- 239000000020 Nitrocellulose Substances 0.000 title claims abstract description 32
- 229920001220 nitrocellulos Polymers 0.000 title claims abstract description 32
- GKIUCMSRTHRSGJ-UHFFFAOYSA-P [N-]=[N+]=[N-].[N-]=[N+]=[N-].[NH3+]N.[NH3+]N Chemical compound [N-]=[N+]=[N-].[N-]=[N+]=[N-].[NH3+]N.[NH3+]N GKIUCMSRTHRSGJ-UHFFFAOYSA-P 0.000 title claims abstract description 19
- 229910052751 metal Inorganic materials 0.000 title abstract description 4
- 239000002184 metal Substances 0.000 title abstract description 4
- 239000011230 binding agent Substances 0.000 claims abstract description 26
- 239000007787 solid Substances 0.000 claims abstract description 21
- 239000007800 oxidant agent Substances 0.000 claims abstract description 9
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 claims description 16
- IPPYBNCEPZCLNI-UHFFFAOYSA-N trimethylolethane trinitrate Chemical compound [O-][N+](=O)OCC(C)(CO[N+]([O-])=O)CO[N+]([O-])=O IPPYBNCEPZCLNI-UHFFFAOYSA-N 0.000 claims description 16
- 229910052782 aluminium Inorganic materials 0.000 claims description 12
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 12
- 229920001944 Plastisol Polymers 0.000 claims description 11
- 239000004999 plastisol Substances 0.000 claims description 11
- AGCQZYRSTIRJFM-UHFFFAOYSA-N triethylene glycol dinitrate Chemical compound [O-][N+](=O)OCCOCCOCCO[N+]([O-])=O AGCQZYRSTIRJFM-UHFFFAOYSA-N 0.000 claims description 10
- 229910052790 beryllium Inorganic materials 0.000 claims description 9
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 claims description 9
- DVKJHBMWWAPEIU-UHFFFAOYSA-N toluene 2,4-diisocyanate Chemical compound CC1=CC=C(N=C=O)C=C1N=C=O DVKJHBMWWAPEIU-UHFFFAOYSA-N 0.000 claims description 8
- 239000004449 solid propellant Substances 0.000 claims description 7
- PAWQVTBBRAZDMG-UHFFFAOYSA-N 2-(3-bromo-2-fluorophenyl)acetic acid Chemical compound OC(=O)CC1=CC=CC(Br)=C1F PAWQVTBBRAZDMG-UHFFFAOYSA-N 0.000 claims description 4
- XYODKMYYACGWBN-UHFFFAOYSA-N aminoazanium;nitroformate Chemical compound [NH3+]N.[O-]C(=O)[N+]([O-])=O XYODKMYYACGWBN-UHFFFAOYSA-N 0.000 claims description 4
- LYAGTVMJGHTIDH-UHFFFAOYSA-N diethylene glycol dinitrate Chemical compound [O-][N+](=O)OCCOCCO[N+]([O-])=O LYAGTVMJGHTIDH-UHFFFAOYSA-N 0.000 claims description 4
- YGZIDGORJKNFDL-UHFFFAOYSA-M nitronium perchlorate Chemical compound O=[N+]=O.[O-]Cl(=O)(=O)=O YGZIDGORJKNFDL-UHFFFAOYSA-M 0.000 claims description 4
- 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 claims description 2
- LAZVTKQYCZFNSZ-UHFFFAOYSA-N nitro formate Chemical compound [O-][N+](=O)OC=O LAZVTKQYCZFNSZ-UHFFFAOYSA-N 0.000 claims 1
- 239000000446 fuel Substances 0.000 abstract description 6
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 4
- 229910052796 boron Inorganic materials 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000009472 formulation Methods 0.000 description 4
- 238000002156 mixing Methods 0.000 description 4
- FHIVAFMUCKRCQO-UHFFFAOYSA-N diazinon Chemical compound CCOP(=S)(OCC)OC1=CC(C)=NC(C(C)C)=N1 FHIVAFMUCKRCQO-UHFFFAOYSA-N 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 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 2
- 230000001747 exhibiting effect Effects 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 239000004014 plasticizer Substances 0.000 description 2
- LSLGCKBDVWXMSH-UHFFFAOYSA-N 1-[1-(2,2-dinitropropoxy)ethoxy]-2,2-dinitropropane;1-(2,2-dinitropropoxymethoxy)-2,2-dinitropropane Chemical compound [O-][N+](=O)C([N+]([O-])=O)(C)COCOCC(C)([N+]([O-])=O)[N+]([O-])=O.[O-][N+](=O)C(C)([N+]([O-])=O)COC(C)OCC(C)([N+]([O-])=O)[N+]([O-])=O LSLGCKBDVWXMSH-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 241000243251 Hydra Species 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- UZXHZRFWCCZBDW-UHFFFAOYSA-O aminoazanium;azide Chemical compound [NH3+]N.[N-]=[N+]=[N-] UZXHZRFWCCZBDW-UHFFFAOYSA-O 0.000 description 1
- -1 ammonium perchlorate triaminoguanidinium hydrazine diazide Chemical compound 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 125000005442 diisocyanate group Chemical group 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000000806 elastomer Substances 0.000 description 1
- DHIGSAXSUWQAEI-UHFFFAOYSA-N hydrazine azide Chemical compound NNN=[N+]=[N-] DHIGSAXSUWQAEI-UHFFFAOYSA-N 0.000 description 1
- OAKJQQAXSVQMHS-UHFFFAOYSA-O hydrazinium(1+) Chemical compound [NH3+]N OAKJQQAXSVQMHS-UHFFFAOYSA-O 0.000 description 1
- 239000012948 isocyanate Substances 0.000 description 1
- 150000002513 isocyanates Chemical class 0.000 description 1
- QRXWMOHMRWLFEY-UHFFFAOYSA-N isoniazide Chemical compound NNC(=O)C1=CC=NC=C1 QRXWMOHMRWLFEY-UHFFFAOYSA-N 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B25/00—Compositions containing a nitrated organic compound
- C06B25/18—Compositions containing a nitrated organic compound the compound being nitrocellulose present as 10% or more by weight of the total composition
- C06B25/22—Compositions containing a nitrated organic compound the compound being nitrocellulose present as 10% or more by weight of the total composition with a nitrated aromatic compound
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B25/00—Compositions containing a nitrated organic compound
- C06B25/18—Compositions containing a nitrated organic compound the compound being nitrocellulose present as 10% or more by weight of the total composition
-
- 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
- C06B33/12—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 the material being two or more oxygen-yielding compounds
- C06B33/14—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 the material being two or more oxygen-yielding compounds at least one being an inorganic nitrogen-oxygen salt
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B47/00—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
- C06B47/02—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
- C06B47/08—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant a component containing hydrazine or a hydrazine derivative
Definitions
- the present invention comprises a solid double-base propellant composition containing from about 2 to about 23 weight percent of a particulated solid fuel, from about l4 to about 35 weight percent of a particulated solid oxidizer, from about l2 to about 35 weight percent triaminoguanidinium hydrazinium diazide and from about 30 to about 50 weight percent of a binder.
- the composition comprises from about 8 to about 23 weight percent of a particulated solid fuel, from about 14 to about 35 weight percent of a particulated solid oxidizer, from about 12 to about 35 weight percent triaminoguanidinium hydrazinium diazide and from about 30 to about 40 weight percent of a plasticized nitrocellulose binder.
- the fuel is a member selected from the group consisting of aluminum, beryllium, boron and mixtures thereof.
- the oxidizer employed in the composition usually is selected from the group consisting of ammonium perchlorate, ammonium nitrate, hydrazine nitroformate, nitronium perchlorate, cyclotrimethylenetrinitramine, cyclotetramethylenetetranitramine and mixtures thereof.
- plasticized nitrocellulose is used as the binder.
- the binder is a blend containing, on a weight basis, from about 1 to about 5 parts ofa nitroplasticizer to 1 part of a plastisol grade nitrocellulose.
- triethyleneglycol dinitrate, trimethylolethane trinitrate and mixtures thereof are particularly effective plasticizers.
- One preferred embodiment of the present novel double base propellant composition consists essentially of from about 15 to about weight percent aluminum, from about l7 to about 26 weight percent ammonium perchlorate, from about 18 to about 23 weight percent triaminoguanidinium hydrazinium diazide and.
- a second preferred embodiment of the present invention consists essentially of on a weight basis from about 9 to about 13 percent beryllium, from about 23 to about 27 percent ammonium perchlorate, about 24 percent triaminoguanidinium hydrazinium diazide and about 40 percent of the plasticized nitrocellulose binder of composition as described hereinbefore.
- the present propellants usually are fabricated by mixing and blending the fuel, oxidizer and triaminoguanidinium hydrazine azide into the plasticized nitrocellulose binder, i.e., nitrosol binder. After mixing to provide a substantially homogeneous blend, the formulation is cast, extruded or otherwise formed and cured to produce a solid, elastomeric propellant grain of predetermined configuration.
- Satisfactory propellant grains are produced by curing the grains at room temperature, i.e. from about l8 to about 25 C., for about 12 to 24 hours, ordinarily about 16 hours with the less energetic nitroplasticizers. e.g., triethyleneglycol dinitrate or a mixture of trimethylolethane trinitrate and triethylene glycol dinitrate.
- the more energetic plasticizers e.g., trimethylolethane trinitrate alone
- higher curing temperatures of from about 50 to about 60 C.
- undesirable gases may be liberated during this curing period. This gassing at the higher curing temperatures can be avoided by incorporating from about l to 2 percent by weight of a diisocyanate or an isocyanate into the propellant composition.
- the present composition having triaminoguanidinium hydrazinium diazide as an essential component has a specific impulse markedly increased over the corresponding double base system not employing this component.
- the present novel composition finds utility as a propellant for rockets and rocket driven missiles.
- the present composition exhibits a somewhat reduced specific impulse but finds a particularly effective utility as a gas generator solid propellant or a smokeless solid propellant.
- EXAMPLE 1 A number of propellant grains were formed by blending finely divided aluminum or beryllium, ammonium perchlorate, triaminoguanidinium hydrazinium diazide and a nitrosol binder. The solid components ranged in particle size from about 40 to about mesh, US. Standard Sieve. Each of the blends was cast into a pro pellant' grain, cured, and fired in a closed bomb. The heat energy liberated and actual specific impulse were determined for each grain. The efficiency of each grain was determined by comparing the observed specific impulse with that theoretically calculated for the composition. Table I, which follows, summarizes the data and results of this study.
- plasticized grade nitrocellulose 55 parts by weight trimethylolethane trinitrate, parts by weight diethyleneglycol dinitrate. 5 parts by weight toluene diisocyanate.
- lulose, 26 parts by weight trimethylolethane trinitrate and 2 parts by weight toluene diisocyanate were blended together to form a plasticized nitrocellulose binder.
- About 19 parts by weight aluminum and 21 parts by weight triaminoguanidinium hydrazinium diazide were mixed into the binder followed by about parts by weight ammonium perchlorate. All solids ranged from about 40 to about 100 mesh U.S. Standard Sieve in particle size.
- the resulting blend was mixed until a substantially homogeneous mass resulted.
- the formulation was cast and cured for about 16 hours at a temperature ranging from about 50 to about 60 C.
- the resulting propellant grain was substantially voidfree and had a density of about 1.7 grams per cubic centimeter.
- EXAMPLE 3 A number 01 formulations of the present invention ⁇ vcrc fabricated into rocket grains. The combustion temperature and theoretical impulse of each of the resultant propellants were calculated. The propellant formulations data and performance results from this study are presented in Table 11 which follows.
- propellants having boron and mixtures of aluminum and/or beryllium with boron as a fuel and ammonium nitrate and nitronium perchlorate as an oxidizer plus triaminoguanidinium hydrazinium azide and mulated. Further, it is to be understood that the fuel and oxidizer components listed hereinbefore can be utilized in various combinations in the present propellants.
- a solid double base propellant composition comprising on a weight basis a. from about 2 to about 23 percent of a particulated solid fuel member selected from the group consisting of aluminum, beryllium, boron and mixtures thereof,
- a particulated solid oxidizer selected from the group consisting of ammonium perchlorate, ammonium nitrate, hydrazine nitroformate, nitronium perchlorate, cyclotrimethylenetrinitramine, cyclotetramethylenetetranitraminc and mixtures thereof,
- a solid double base propellant composition consisting essentially of on a weight basis a. from about 8 to about 23 percent of a member se- Propellant Composition Results NC TMETN Al Be THA AP HNF Combustion Temp. Specific impulse Run No. wt. percent ('14) lsp. (sec.)
- a plasticized nitrocellulose binder consisting of from about 16 to about 40 weight percent plastisol grade nitrocellulose and from about 84 to about 60 weight percent of a member selected from the group consisting of trimethylolethane trinitrate, diethyleneglycol dinitrate, triethyleneglycol dinitrate and mixtures thereof.
- a solid double base propellant composition consisting essentially of on a weight basis a. from about to about percent particulate aluminum,
- a plasticized nitrocellulose binder consisting of about 25 parts by weight plastisol grade nitrocellulose, about 55 to about 60 parts by weight trimethylolethane trinitrate, 15 parts by weight triethyleneglycol dinitrate and 0 to about 5 parts by weight toluene diisocyanate.
- a solid double base propellant composition consisting essentially of on a weight basis a. from about 9 to about 13 percent particulate beryllium,
- a plasticized nitrocellulose binder consisting of about 25 parts by weight plastisol grade nitrocellulose, about 55 to about parts by weight trimethylolethane trinitrate, l5 parts by weight triethyleneglycol dinitrate and 0 to about 5 parts by weight toluene diisocyanate.
- a solid double base propellant composition consisting essentially of on a weight basis a. about 19 percent particulate aluminum,
- a plasticized nitrocellulose binder said binder consisting; of about 30 weight percent plastisol grade nitrocellulose, about weight percent trimethylolethane trinitrate and about 5 weight percent toluene diisocyanate.
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Cosmetics (AREA)
Abstract
The present invention comprises a solid double-base propellant composition having on a weight basis from about 2 to about 23 percent of a light metal fuel, from about 14 to about 35 percent of a particulate solid oxidizer, from about 12 to about 35 percent triaminoguanidinium hydrazinium diazide and from about 30 to about 50 percent of a plasticized nitrocellulose binder.
Description
llnited States Patent 1 1 Flynn et a1.
[ NITROCELLULOSE PROPELLANT COMPOSITION CONTAINING METAL AND TRlAMlNOGUANlDlNlUM HYDRAZlNlUM DIAZIDE [75] lnventors: James P. Flynn; George A. Lane;
John J. Plomer, all of Midland,
Mich.
[73] Assignee: The Dow Chemical Company,
Midland, Mich.
[22] Filed: June 16, 1965 [21] Appl. No.: 465,253
[52] U.S. Cl l49/l9.4, 149/198, 149/20,
149/22, 149/36, 149/38 [51] Int. Cl C06d 5/06 [58] Field of Search 149/18, 19, 20, 38, 44,
[451 Feb. 11,1975
[56] References Cited UNITED STATES PATENTS 3,053,709 9/1962 Herty 149/198 3,138,499 6/1964 Camp et a1. 149/198 Primary ExaminerBenjamin R. Padgett Attorney, Agent, or FirmC. Kenneth Bjork [57] ABSTRACT 5 Claims, No Drawings N ITROCELLULOSE PROPELLANT COMPOSITION CONTAINING METAL AND TRIAMINOGUANIDINIUM I-IYDRAZINIUM DIAZIDE This invention relates to propellants and more particularly is concerned with a novel solid double base propellant composition exhibiting a high specific impulse.
It is a principal object of the present invention to provide a novel high energy propellant composition exhibiting a high specific impulse.
It is another object of the present invention to provide a novel double base solid propellant composition that cures at room temperature to a rubbery elastomer without undesirable gas formation.
- toluene diisocyanate.
These and other objects and advantages readily will become apparent from the detailed description presented hereinafter.
The present invention comprises a solid double-base propellant composition containing from about 2 to about 23 weight percent of a particulated solid fuel, from about l4 to about 35 weight percent of a particulated solid oxidizer, from about l2 to about 35 weight percent triaminoguanidinium hydrazinium diazide and from about 30 to about 50 weight percent of a binder.
Ordinarily, the composition comprises from about 8 to about 23 weight percent of a particulated solid fuel, from about 14 to about 35 weight percent ofa particulated solid oxidizer, from about 12 to about 35 weight percent triaminoguanidinium hydrazinium diazide and from about 30 to about 40 weight percent of a plasticized nitrocellulose binder.
Ordinarily the fuel is a member selected from the group consisting of aluminum, beryllium, boron and mixtures thereof.
The oxidizer employed in the composition usually is selected from the group consisting of ammonium perchlorate, ammonium nitrate, hydrazine nitroformate, nitronium perchlorate, cyclotrimethylenetrinitramine, cyclotetramethylenetetranitramine and mixtures thereof.
Preferably, as indicated hereinbefore, plasticized nitrocellulose is used as the binder. Ordinarily the binder is a blend containing, on a weight basis, from about 1 to about 5 parts ofa nitroplasticizer to 1 part ofa plastisol grade nitrocellulose. Diethyleneglycol dinitrate,
triethyleneglycol dinitrate, trimethylolethane trinitrate and mixtures thereof are particularly effective plasticizers.
One preferred embodiment of the present novel double base propellant composition consists essentially of from about 15 to about weight percent aluminum, from about l7 to about 26 weight percent ammonium perchlorate, from about 18 to about 23 weight percent triaminoguanidinium hydrazinium diazide and. from about to about weight percent of a plasticized nitrocellulose binder consisting of about 25 parts by weight plastisol grade nitrocellulose, 55 to 60parts by weight trimethylolethane trinitrate, 15 parts by weight A second preferred embodiment of the present invention consists essentially of on a weight basis from about 9 to about 13 percent beryllium, from about 23 to about 27 percent ammonium perchlorate, about 24 percent triaminoguanidinium hydrazinium diazide and about 40 percent of the plasticized nitrocellulose binder of composition as described hereinbefore.
The present propellants usually are fabricated by mixing and blending the fuel, oxidizer and triaminoguanidinium hydrazine azide into the plasticized nitrocellulose binder, i.e., nitrosol binder. After mixing to provide a substantially homogeneous blend, the formulation is cast, extruded or otherwise formed and cured to produce a solid, elastomeric propellant grain of predetermined configuration.
Satisfactory propellant grains are produced by curing the grains at room temperature, i.e. from about l8 to about 25 C., for about 12 to 24 hours, ordinarily about 16 hours with the less energetic nitroplasticizers. e.g., triethyleneglycol dinitrate or a mixture of trimethylolethane trinitrate and triethylene glycol dinitrate. With the more energetic plasticizers, e.g., trimethylolethane trinitrate alone, preferably higher curing temperatures of from about 50 to about 60 C. are used. At these temperatures undesirable gases may be liberated during this curing period. This gassing at the higher curing temperatures can be avoided by incorporating from about l to 2 percent by weight of a diisocyanate or an isocyanate into the propellant composition.
The present composition having triaminoguanidinium hydrazinium diazide as an essential component has a specific impulse markedly increased over the corresponding double base system not employing this component. The present novel composition finds utility as a propellant for rockets and rocket driven missiles.
If the metal fuel member is not included, the present composition exhibits a somewhat reduced specific impulse but finds a particularly effective utility as a gas generator solid propellant or a smokeless solid propellant.
The following Examples will serve to further illustrate the present invention but are not meant to limit it thereto.
EXAMPLE 1 A number of propellant grains were formed by blending finely divided aluminum or beryllium, ammonium perchlorate, triaminoguanidinium hydrazinium diazide and a nitrosol binder. The solid components ranged in particle size from about 40 to about mesh, US. Standard Sieve. Each of the blends was cast into a pro pellant' grain, cured, and fired in a closed bomb. The heat energy liberated and actual specific impulse were determined for each grain. The efficiency of each grain was determined by comparing the observed specific impulse with that theoretically calculated for the composition. Table I, which follows, summarizes the data and results of this study.
Table I Propellant Composition Combustion Results Nitrosol" Al Be AP THA AH Isp obs.) lsp (theo) Eff. Run No. by weight) (cal/g.) (sec.) (sec.) (71) l 40" I9 17 24 I387 247 274.8 89.8 2 40" 16 26 18 1543fl 247 272.6 90.6
Table I -Continued Propellant Composition Combustion Results Nitrosol" Al Be AP THA AH lsp (obs) lsp (theo) Eff.
Run No. by weight) (cal/g.) (sec.) (sec.) (7() 3 35" 16 26 23 ISOOfl 243 273.9 88.7
"' 25 parts by weight plasticized grade nitrocellulose, 55 parts by weight trimethylolethane trinitrate, parts by weight diethyleneglycol dinitrate. 5 parts by weight toluene diisocyanate.
25 parts by weight plastisol grade nitrocellulose, 60 parts by weight lrimethylolethane trinitrate and 15 parts by weight triethylene glycol dinitrate. ammonium perchlorate triaminoguanidinium hydrazine diazide EXAMPLE 2,
lulose, 26 parts by weight trimethylolethane trinitrate and 2 parts by weight toluene diisocyanate were blended together to form a plasticized nitrocellulose binder. About 19 parts by weight aluminum and 21 parts by weight triaminoguanidinium hydrazinium diazide were mixed into the binder followed by about parts by weight ammonium perchlorate. All solids ranged from about 40 to about 100 mesh U.S. Standard Sieve in particle size. The resulting blend was mixed until a substantially homogeneous mass resulted. The formulation was cast and cured for about 16 hours at a temperature ranging from about 50 to about 60 C. The resulting propellant grain was substantially voidfree and had a density of about 1.7 grams per cubic centimeter.
When fired in a rocket motor, this grain burned smoothly to completion.
EXAMPLE 3 A number 01 formulations of the present invention \vcrc fabricated into rocket grains. The combustion temperature and theoretical impulse of each of the resultant propellants were calculated. The propellant formulations data and performance results from this study are presented in Table 11 which follows.
In a manner similar to that described for the preceding Examples, propellants having boron and mixtures of aluminum and/or beryllium with boron as a fuel and ammonium nitrate and nitronium perchlorate as an oxidizer plus triaminoguanidinium hydrazinium azide and mulated. Further, it is to be understood that the fuel and oxidizer components listed hereinbefore can be utilized in various combinations in the present propellants.
Various modifications can be made in the present invention without departing from the spirit or scope thereof for it is understood that we limit ourselves only as defined in the appended claims.
We claim:
1. A solid double base propellant composition comprising on a weight basis a. from about 2 to about 23 percent of a particulated solid fuel member selected from the group consisting of aluminum, beryllium, boron and mixtures thereof,
b. from about 14 to about 35 percent of a particulated solid oxidizer selected from the group consisting of ammonium perchlorate, ammonium nitrate, hydrazine nitroformate, nitronium perchlorate, cyclotrimethylenetrinitramine, cyclotetramethylenetetranitraminc and mixtures thereof,
from about 12 to about 35 percent triaminoguanidinium hydrazinium diazide, and
d. from about 30 to about percent of a plasticized nitrocellulose binder. 2. A solid double base propellant composition consisting essentially of on a weight basis a. from about 8 to about 23 percent of a member se- Propellant Composition Results NC TMETN Al Be THA AP HNF Combustion Temp. Specific impulse Run No. wt. percent ('14) lsp. (sec.)
"' Nitrocellulose Trimethylolethane trinitrate 'l'riaminoguanidiniuni hydrazinium dia'lide Ammonium perchlorate Hydra/inc Nitrut'mniatc b. from about 14 to about 35 percent of a member selected from the group consisting of particulated ammonium perchlorate and hydrazine nitroformate,
c. from about 12 to about 35 percent triaminoguanidinium hydrazinium diazide, and
d. from about 30 to about 40 percent of a plasticized nitrocellulose binder, said binder consisting of from about 16 to about 40 weight percent plastisol grade nitrocellulose and from about 84 to about 60 weight percent of a member selected from the group consisting of trimethylolethane trinitrate, diethyleneglycol dinitrate, triethyleneglycol dinitrate and mixtures thereof.
3. A solid double base propellant composition consisting essentially of on a weight basis a. from about to about percent particulate aluminum,
b. from about 17 to about 26 percent particulate ammonium perchlorate,
c. from about 18 to about 23 percent triaminoguanidinium hydrazinium diazide, and
d. from about to about percent of a plasticized nitrocellulose binder consisting of about 25 parts by weight plastisol grade nitrocellulose, about 55 to about 60 parts by weight trimethylolethane trinitrate, 15 parts by weight triethyleneglycol dinitrate and 0 to about 5 parts by weight toluene diisocyanate.
4. A solid double base propellant composition consisting essentially of on a weight basis a. from about 9 to about 13 percent particulate beryllium,
b. from about 23 to about 27 percent particulate ammonium perchlorate,
c. about 24 percent triaminoguanidinium hydrazinium diazide, and
(1. about 40 percent of a plasticized nitrocellulose binder consisting of about 25 parts by weight plastisol grade nitrocellulose, about 55 to about parts by weight trimethylolethane trinitrate, l5 parts by weight triethyleneglycol dinitrate and 0 to about 5 parts by weight toluene diisocyanate.
5. A solid double base propellant composition consisting essentially of on a weight basis a. about 19 percent particulate aluminum,
b. about 20 percent particulate ammonium perchlorate,
c. about 21 percent triaminoguanidinium hydrazinium diazide, and
d. about 40 percent of a plasticized nitrocellulose binder, said binder consisting; of about 30 weight percent plastisol grade nitrocellulose, about weight percent trimethylolethane trinitrate and about 5 weight percent toluene diisocyanate.
l l l
Claims (5)
1. A SOLID DOUBLE BASE PROPELLANT COMPOSITION COMPRISING ON A WEIGHT BASIS A. FROM ABOUT 2 TO ABOUT 23 PERCENT OF A PARTICULATED SOLID FUEL MEMBER SELECTED FROM THE GROUP CONSISTING OF ALUMINUM, BERYLLIUM, BORON AND MIXTUES THEREOF, B. FROM ABOUT 14 TO ABOUT 35 PERCENT OF A PARTICULATED SOLID OXIDIZER SELECTED FROM THE GROUP CONSISTING OF AMMONIUM PERCHLORATE, AMMONIUM NITRATE, HYDRAXINE NITROFORMATE, NITRONIUM PERCHLORATE, CYCLOTRIMETHYLETRINITRAMINE, CYCLOTETRAMETHYLENETETRANITRAMINE AND MIXTURES THEREOF, C. FROM ABOUT 12 TO ABOUT 35 PERCENT TRIAMINOGUANIDINIUM HYDRAZINIUM DIAZIDE, AND D. FROM ABOUT 30 TO ABOUT 50 PERCENT OF A PLASTICIZED NITROCELLULOSE BINDER.
2. A solid double base propellant composition consisting essentially of on a weight basis a. from about 8 to about 23 percent of a member selected from the group consisting of particulated aluminum and beryllium, b. from about 14 to about 35 percent of a member selected from the group consisting of particulated ammonium perchlorate and hydrazine nitroformate, c. from about 12 to about 35 percent triaminoguanidinium hydrazinium diazide, and d. from about 30 to about 40 percent of a plasticized nitrocellulose binder, said binder consisting of from about 16 to about 40 weight percent plastisol grade nitrocellulose and from about 84 to about 60 weight percent of a member selected from the group consisting of trimethylolethane trinitrate, diethyleneglycol dinitrate, triethyleneglycol dinitrate and mixtures thereof.
3. A solid double base propellant composition consisting essentially of on a weight basis a. from about 15 to about 20 percent particulate aluminum, b. from about 17 to about 26 percent particulate ammonium perchlorate, c. from about 18 to about 23 percent triaminoguanidinium hydrazinium diazide, and d. from about 35 to about 40 percent of a plasticized nitrocellulose binder consisting of about 25 parts by weight plastisol grade nitrocellulose, about 55 to about 60 parts by weight trimethylolethane trinitrate, 15 parts by weight triethyleneglycol dinitrate and 0 to about 5 parts by weight toluene diisocyanate.
4. A solid double base propellant composition consisting essentially of on a weight basis a. from about 9 to about 13 percent particulate beryllium, b. from about 23 to about 27 percent particulate ammonium perchlorate, c. about 24 percent triaminoguanidinium hydrazinium diazide, and d. about 40 percent of a plasticized nitrocellulose binder consisting of about 25 parts by weight plastisol grade nitrocellulose, about 55 to about 60 parts by weight trimethylolethane trinitrate, 15 parts by weight triethyleneglycol dinitrate and 0 to about 5 parts by weight toluene diisocyanate.
5. A solid double base propellant composition consisting essentially of on a weight basis a. about 19 percent particulate aluminum, b. about 20 percent particulate ammonium perchlorate, c. about 21 percent triaminoguanidinium hydrazinium diazide, and d. about 40 percent of a plasticized nitrocellulose binder, said binder consisting of about 30 weight percent plastisol grade nitrocellulose, about 65 weight percent trimethylolethane trinitrate and about 5 weight percent toluene diisocyanate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US465253A US3865659A (en) | 1965-06-16 | 1965-06-16 | Nitrocellulose propellant composition containing metal and triaminoguanidinium hydrazinium diazide |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US465253A US3865659A (en) | 1965-06-16 | 1965-06-16 | Nitrocellulose propellant composition containing metal and triaminoguanidinium hydrazinium diazide |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3865659A true US3865659A (en) | 1975-02-11 |
Family
ID=23847042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US465253A Expired - Lifetime US3865659A (en) | 1965-06-16 | 1965-06-16 | Nitrocellulose propellant composition containing metal and triaminoguanidinium hydrazinium diazide |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3865659A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4002514A (en) * | 1965-09-30 | 1977-01-11 | The Dow Chemical Company | Nitrocellulose propellant composition |
| US4078954A (en) * | 1975-07-03 | 1978-03-14 | Societe Nationale Des Poudres Et Explosifs | Illuminating pyrotechnic composition which generates gases |
| NL7909134A (en) * | 1979-01-02 | 1980-07-04 | Nitrochemie Gmbh | MULTIPLE COMPONENT POWDER FOR PROPULSIVE CARGO. |
| FR2624113A1 (en) * | 1987-12-03 | 1989-06-09 | France Etat | Ejection charge for close defence ammunition |
| US6645325B1 (en) * | 1998-06-01 | 2003-11-11 | Russell R. Nickel | Fast-burning nitrocellulose compositions |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3053709A (en) * | 1959-09-08 | 1962-09-11 | Phillips Petroleum Co | Cooling solid propellant compositions during mixing |
| US3138499A (en) * | 1964-06-23 | Pressure |
-
1965
- 1965-06-16 US US465253A patent/US3865659A/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3138499A (en) * | 1964-06-23 | Pressure | ||
| US3053709A (en) * | 1959-09-08 | 1962-09-11 | Phillips Petroleum Co | Cooling solid propellant compositions during mixing |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4002514A (en) * | 1965-09-30 | 1977-01-11 | The Dow Chemical Company | Nitrocellulose propellant composition |
| US4078954A (en) * | 1975-07-03 | 1978-03-14 | Societe Nationale Des Poudres Et Explosifs | Illuminating pyrotechnic composition which generates gases |
| NL7909134A (en) * | 1979-01-02 | 1980-07-04 | Nitrochemie Gmbh | MULTIPLE COMPONENT POWDER FOR PROPULSIVE CARGO. |
| FR2445823A1 (en) * | 1979-01-02 | 1980-08-01 | Nitrochemie Gmbh | POWDERS FOR POLYBASIC PROPELLANT CHARGES |
| FR2624113A1 (en) * | 1987-12-03 | 1989-06-09 | France Etat | Ejection charge for close defence ammunition |
| US6645325B1 (en) * | 1998-06-01 | 2003-11-11 | Russell R. Nickel | Fast-burning nitrocellulose compositions |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7842144B1 (en) | Methods of making double base casting powder | |
| US3689331A (en) | Nitrocellulose base compositions and method for making same | |
| US3309249A (en) | Thermite-resin binder solid fuel composition | |
| US4216039A (en) | Smokeless propellant compositions having polyester or polybutadiene binder system crosslinked with nitrocellulose | |
| US20010003295A1 (en) | Propellent charge powder for barrel-type weapons | |
| US4002514A (en) | Nitrocellulose propellant composition | |
| US6024810A (en) | Castable double base solid rocket propellant containing ballistic modifier pasted in an inert polymer | |
| US3808061A (en) | Nitrocellulose solid propellant composition with load additive to reduce radar attenuation | |
| US3865659A (en) | Nitrocellulose propellant composition containing metal and triaminoguanidinium hydrazinium diazide | |
| US3844856A (en) | Nitrocellulose propellant composition containing aluminum hydride | |
| US4000025A (en) | Incorporating ballistic modifiers in slurry cast double base containing compositions | |
| 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 | |
| GB1277192A (en) | Improvements in and relating to nitrocellulose base propellant compositions | |
| US3732130A (en) | Gun propellant containing nonenergetic plasticizer,nitrocellulose and triaminoguanidine nitrate | |
| US3905846A (en) | Composite modified double base propellant with metal oxide stabilizer | |
| US3971681A (en) | Composite double base propellant with triaminoguanidinium azide | |
| US5085717A (en) | Autopyrolyzable composition for aerobic propulsion, the oxidizing agent of which is an explosive | |
| US3732131A (en) | Gun propellant containing nitroplasticized nitrocellulose and triaminoguanidine nitrate | |
| US3878003A (en) | Composite double base propellant with HMX oxidizer | |
| US3834956A (en) | Solid propellant composition containing lead and lead compounds | |
| US5798481A (en) | High energy TNAZ, nitrocellulose gun propellant | |
| US3755019A (en) | Solid propellant compositions containing plasticized nitrocellulose and aluminum hydride | |
| US3862864A (en) | Plasticized nitrocellulose propellant compositions containing hydrazinium nitroformate and aluminum hydride | |
| US3266959A (en) | Stabilized polyurethane propellants containing aluminum |