US3914142A - Solid propellants with biradical burning rate catalysts - Google Patents

Solid propellants with biradical burning rate catalysts Download PDF

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US3914142A
US3914142A US078331A US7833170A US3914142A US 3914142 A US3914142 A US 3914142A US 078331 A US078331 A US 078331A US 7833170 A US7833170 A US 7833170A US 3914142 A US3914142 A US 3914142A
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David C Sayles
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    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
    • C06B23/007—Ballistic modifiers, burning rate catalysts, burning rate depressing agents, e.g. for gas generating
    • 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
    • C06B45/04—Compositions 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
    • C06B45/06—Compositions 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
    • C06B45/10—Compositions 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

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  • the disclosed means for achieving high burning rates are compounds which exist in the biradical form and contain two trivalent carbon atoms in each molecule which contains a quinoid structure based on paramagnetic susceptibility measurements.
  • the disclosed biradical compounds may be used to enhance the burning rate of crosslinkable double-base propellants.
  • Representative crosslinkable double-base propellants using the biradical compounds are disclosed.
  • HTPB hydroxylterminated polybutadiene
  • CPB carboxyl'terminated polybutadiene
  • Processing aids e.g., lecithin
  • stabilizers e.g., lecithin
  • curatives may be used in minor amounts in the basic formulation or as additives to the propellant composition.
  • Catalyst materials of the prior art include iron oxide,
  • the present invention deals with earlier studied compounds which exist entirely in the biradical form. More particularly the present invention deals with specific biradical compounds which have been found to be useful as burning rate catalysts for solid propellant compositions.
  • an object of this invention is to provide biradical compounds which are useful as burning rate catalysts for solid propellants.
  • Another object is to provide solid propellant formulations of the crosslinkable double-base type which utiliZe a biradical compound which functions as a burning rate catalyst and a ballistic modifier to inhibit resonance burning and combustion instability.
  • Another object of this invention is to provide hydrox- SUMMARY OF THE INVENTION
  • the catalyst of this invention is selected from the biradical compounds, p, p-biphenylene-bis(diphenyl- 5 methyl) and p, p'-phenylene-bis(diphenylmethyl).
  • Table I illustrates how the biradical burning rate catalyst of this invention is used in a crosslinkable double- Ph C CPhg
  • Still another object of this invention is to provide carboxl-terminated polybutadiene-based propellants which employ a biradical compound as theburning rate catalyst.
  • compositions A and C of Table l are near smokeless double-base propellants, an improvement in the smokeless properties is gained in composition B where a complete replacement of lead peroxide is made by p, p'-biphenylene-bis(diphenylmethyl).
  • Table 11 illustrates how the biradical burning rate cat- 30 alyst (compound A or B) of this invention is used in a hydroxyl-terminated polybutadiene-based propellant.
  • Table 11 The propellants of Table 111 employ a'carboxyl-terminated polybutadiene binder, ammonium perchlorate oxidizer, aluminum metal fuel, n-butylferrocene catalyst (in standard composition A) and p, p'-biphenylene-bis(diphenylmethyl) (in composition B), and crosslinking agent tris[l-(2-methyl)aziridinyl]-phosphine oxide.
  • Tris(oxiranyl)-para-aminophenol and iron linoleate are curatives each of which are added in trace
  • a Comparison of Hydroxyl-Terminated Polybutadiene-Based Propellants With and Without Biradical Burning Rate Catalyst PROPELLANT COMPOSITION INGREDIENTS/BURNING RATE PERCENT BY WEIGHT AND BURNING RATES INGREDIENT Hydroxyl-terminated Polybutadiene Prepolymer 9.84 9.84 Dimeryl Diisocyanate 1.92 1.92 Bonding Agent* 0.24 0.24 Ammonium Perchlorate 73.
  • Bonding agent is formulated of cquimnlar quantities of trisl 1-( Z-methyl)aziridinyllphosphine oxide. tartaric acid. and adipic acid. Bonding agent is used in an amount from about 0.1-0.3 percent by weight of propellant composition.
  • the propellants of Table I] employ a hydroxyl-terminated polybutadiene binder, ammonium perchlorate oxidizer, aluminum metal fuel, the burning rate catalyst p, p'-biphenylene-bis(diphenylmethyl), and materials for additives which include the crosslinking compound dimeryl diisocyanate and a bonding agent to provide desirable physical properties through crosslinking and curing reactions.
  • a marked increase in burning rate is achieved with Propellant B of Table I1 which contains the burning rate catalyst, p, p-biphenylene-bis(diphenylmethyl).
  • Propellant A of Table II is the standard propellant.
  • the use of the biradical catalyst to control burning rates of HTPB-based propellants is attractive because of the compatibility of this type compound with HTPB-based propellants.
  • Table III illustrates how the biradical burning rate catalyst (compoundA or B) of this invention is used in amounts from about 0.1 to about 0.5 percent by weight of the total weight of all the other combined propellant ingredients.
  • propellant ingredients of the doublebase type propellants disclosed herein are (in percent by weight of the propellant composition) as follows: binder from casting powder (formulated of nitrocellulose of about 10.1 parts, of about 0.95 parts nitroglycerine, and of about 0.20 parts Z-nitrodiphenylamine) from about 6.to about 23; TEGDN from about 20 to about 35; BTTN from about 10 to about 20; HMX from about 30 to about 50; biradical catalyst (selected from p, p-biphenylene-bis(diphenylmethyl) and p, p'-phenylene-bis(diphenylmethyl)) from about 2.0 to'about 8.0; lead peroxide from about 2.0 to about 6.0; stabilizers from about 0.5 to about 1.0; and curative additives from about 0.5 to about 2.0.
  • binder from casting powder formulated of nitrocellulose of about 10.1 parts, of about 0.95 parts nitroglycerine, and of about 0.20 parts Z-nitrodiphenylamine
  • the ranges of the composite propellant ingredients, using carboxylterminated polybiitadiene binder in the compositions disclosed herein, are )(in percent by weight" of the p'ropellant composition) as follows: biradical catalyst selected from pj'pFbiphenylene-bisb cliphenylm'e'thylji'and p'-phenylene-bis(diphenylmethyl) from about 2.0 to about 8.0;ariinibnjiiim perchlorate from about 60 to about'70; aluminum metal fuel from about 5 to "about20; carboxyl-terminated polybutadi'ene prepo'lyrner' from about?
  • crosslinking agent tris[ 1-( 2-methyl)aziridiny1]phosphine oxide
  • curatives tris(oxiranyl)-para-aminophenol) and iron linoleate, each in an amount from about 0.1 to about 0.5 percent by weight of the total weight of all the other propellant ingredients.
  • a solid propellant composition comprising a binder, an oxidizer, a burning rate catalyst selected from the biradical compounds consisting of p, p-biphenylene-bis(diphenylmethyl) and p, p-phenylene-bis(- diphenylmethyl), and a crosslinking agent.
  • the propellant composition of claim 1 wherein said binder is present in an amount from about 6 to about 23 percent by weight of said propellant composition, said binder being constituted of about 10.1 parts nitrocellulose, about 0.95 parts nitroglycerin, and about 020 parts of 2-nitrodiphenylamine; said oxidizer is cyclotetramethylenetetranitramine which is present in an amount from about 30 to about 50 percent by weight of said propellant composition; said catalyst selected is p, p-biphenylene-bis(diphenylmethyl) which clotetramethylenetetranitramine --is present .6 V ispresent in an amount from about 2 to about 8'percent by weight of said.propellantcomposition; said composition includes the plasticizer, triethylene glycol dinitrate in an amount from about 20 to about 35 percent by weight of said propellant composition and the plasticizer, butanetriol'trinitrate in an amount from about 10 to about 20percent by weight of said propellant composition; said propellant composition additionally incl
  • the propellant compositionof claim 2 wherein said binder is present in an amount of about 1 1.25 percent b-y'weight of said propellant composition; said eyin an amount of about 36 to about '40 percent by weight of said propellant composition; said triethylene glycol dinitrate is present-in an amount of about 28.75 percent by weight of said propellant composition; said butanetriol trinitrate is present in an amount of about 15.5 percent by weight of said propellant composition; said p, p'-biphenylene-bis(diphenylmethyl) is present in an amount of about 4.0 percent by weight of said propellant composition; and said resorcinol is present in an amount of about 0.5 percent by weight of said propellant composition.
  • the propellant composition of claim 1 wherein said binder is hydroxyl-terminated polybutadiene which is present in an amount from about 7 to about 15 percent by weight of said propellant composition; said oxidizer is ammonium perchlorate which is present in an amount from about to about percent by weight of said propellant composition; said catalyst selected is p, p'-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said crosslinking agent is dimeryl diisocyanate which is present in an amount from about 0.5 to about 2.0 percent by weight of said propellant composition; said composition contains a bonding agent formulated of equimolar quantities of tris[1-(2-methyl)-aziridinyl]phosphine oxide, tartaric acid, and adipic acid, said bonding agent is present in an amount from about 0.1 to about 0.3 percent by weight of said propellant composition; and wherein said propellant composition additionally contains aluminium metal fuel in an amount from
  • the propellant composition of claim 5 wherein said binder is present in an amount of about 9.84 percent by weight of said propellant composition; said ammonium perchlorate is present in an amount of about 71 percent by weight of said propellant composition; said p, p'-biphenylene-bis(diphenylmethyl) is present in an amount of about 2 percent by weight of said propellant composition; said dimeryl diisocyanate is present in an amount of about 1.92 percent by weight of said propellant composition; said bonding agent is present in an amount of about 0.24 percent by weight of said propellant composition; and said aluminium metal fuel is present in an amount of about 15 percent by weight of said propellant composition.
  • the propellant composition of claim 1 wherein said binder is carboxyl-terminated polybutadiene which is present in an amount from about 7 to about l percent by weight of said propellant composition; said oxidizer is ammonium perchlorate which is present in an amount from about 60 to about 70 percent by weight of said propellant composition; said catalyst selected is p, p'-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said crosslinking agent is tris[ l-(2-methyl)aziridinyl]-phosphine oxide which is present in an amount from about 05 to about 2.0 percent by weight of said propellant composition; said propellant composition includes aluminum metal fuel in an amount from about 5 to about percent by weight of said propellant composition; and wherein said propellant composition additionally in- 8 cludes the curatives consisting of tris(oxiranyl)-paraaminophenol and iron linoleate which are each added to said propellant composition in an
  • phosphine oxide is present in an amount of about 0.5 percent by weight of said propellant composition; said aluminium metal fuel is present in an amount of about 14 percent by weight of said propellant composition; and said tris(oxiranyl)-para-aminophenol and iron linoleate are each present in an amount of about 0.1 percent by weight of all the other propellant ingredients.

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Abstract

Disclosed are p, p''-biphenylene-bis(diphenylmethyl) and p, p''phenylene-bis(diphenylmethyl) as the means for achieving high burning rates of solid propellant compositions. The disclosed means for achieving high burning rates are compounds which exist in the biradical form and contain two trivalent carbon atoms in each molecule which contains a quinoid structure based on paramagnetic susceptibility measurements. The disclosed biradical compounds may be used to enhance the burning rate of crosslinkable double-base propellants. Representative crosslinkable double-base propellants using the biradical compounds are disclosed. Also, disclosed are representative hydroxyl-terminated polybutadiene (HTPB)-based propellants and carboxyl-terminated polybutadiene (CTPB)-based propellants which employ the biradical compound as catalyst. Processing aids (e.g., lecithin), stabilizers, and curatives may be used in minor amounts in the basic formulation or as additives to the propellant composition.

Description

[ Oct. 21, 1975 SOLID PROPELLANTS WITH B IRADICAL BURNING RATE CATALYSTS Appl. No.: 78,331
[44] Published under the Trial Voluntary Protest Program on January 28, 1975 as document no. B 78,331.
[52] US. Cl. l49/19.8; 149/19.9; 149/44; 149/76; 149/92 [51] Int. Cl. C06D 5/06 [58] Field of Search 149/19, 44, 76, 60, 61, 149/83, 92, 97, 100, 19.8, 19.9
[56] References Cited UNITED STATES PATENTS 3,203,842 8/1965 Godfrey 149/76 X 3,364,086 1/1968 Oversohl et al... 149/76 X 3,400,025 9/1968 Hopper et al 149/92 X 3,455,883 7/1969 Kamal et al 260/775 3,476,622 11/1969 Harada et al. 149/19 3,498,856 3/1970 Harris 149/19 3,585,090 6/1971 7 Sayles 149/19 Primary Examiner-Benjamin R. Padgett Assistant Examiner-E. A. Miller Attorney, Agent, or FirmNathan Edelberg; Robert P. Gibson; Jack W. Voigt ABSTRACT Disclosed are p, p-biphenylene-bis(diphenylmethyl) and p, p'-phenylene-bis(diphenylmethyl) as the means for achieving high burning rates of solid propellant compositions. The disclosed means for achieving high burning rates are compounds which exist in the biradical form and contain two trivalent carbon atoms in each molecule which contains a quinoid structure based on paramagnetic susceptibility measurements. The disclosed biradical compounds may be used to enhance the burning rate of crosslinkable double-base propellants. Representative crosslinkable double-base propellants using the biradical compounds are disclosed. Also, disclosed are representative hydroxylterminated polybutadiene (HTPB)-based propellants and carboxyl'terminated polybutadiene (CTPB)-based propellants which employ the biradical compound as catalyst. Processing aids (e.g., lecithin), stabilizers, and curatives may be used in minor amounts in the basic formulation or as additives to the propellant composition.
8 Claims, N0 Drawings SOLID PROPELLANTS WITH BIRADICAL BURNING RATE CATALYSTS BACKGROUND OF THE INVENTION Catalysis or means for promoting the burning rates of propellants permits the expulsion of a larger amount of energy over a shorter period of time to thereby result in a higher specific impulse or force to perform a desired function by propulsion means. In many instances the use of a relatively smallamount of a catalyst material (e.g., 1-2% by weight) enables one to change a slower burning propellant into a faster burning propellant.
Catalyst materials of the prior art include iron oxide,
copper oxide, copper chromite, the organoiron compound (ferrocene and its derivatives), and other organometallic compounds. More recently carborane and carborane derivatives have been investigated as catalyst materials for propellants.
Biradical compounds have been studied by Schonberg, Trans. Faraday Soc. 32, 515 (1936).
The present invention deals with earlier studied compounds which exist entirely in the biradical form. More particularly the present invention deals with specific biradical compounds which have been found to be useful as burning rate catalysts for solid propellant compositions.
Therefore, an object of this invention is to provide biradical compounds which are useful as burning rate catalysts for solid propellants.
Another object is to provide solid propellant formulations of the crosslinkable double-base type which utiliZe a biradical compound which functions as a burning rate catalyst and a ballistic modifier to inhibit resonance burning and combustion instability.
Another object of this invention is to provide hydrox- SUMMARY OF THE INVENTION The catalyst of this invention is selected from the biradical compounds, p, p-biphenylene-bis(diphenyl- 5 methyl) and p, p'-phenylene-bis(diphenylmethyl). The
' composition.
DESCRIPTION OF THE PREFERRED EMBODIMENTS The biradical compound p, p'-biphenylene-bis(diphenylmethyl) (referred to for simplicity as compound A) 'is illustrated by the following structural formula:
wherein Ph is the abbreviation for phenyl, C l-I The biradical compound p, p'-phenylene-bis(diphenylmethyl) (referred to for simplicity as compound B) is illustrated by the following structural formula:
wherein Ph is the abbreviation for phenyl, C6H
Table I illustrates how the biradical burning rate catalyst of this invention is used in a crosslinkable double- Ph C CPhg
PhzC
CPh
base propellant formulation.
Table I A Comparison of Crosslinkable Double-Base Propellants With and Without Burning Rate INGREDIENTS/BURNING RATE Catalyst PROPELLANT COMPOSITIONS PERCENT BY WEIGHT AND BURNING RATES A B C Casting Powder (binder) ll.25 11.25 .25 Triethylene Glycol Dinitrate (TEGDN) 28.75 28.75 28.75 Butanetriol Trinitrate (B'ITN) l5.5 15.5 15.5 Cyclotetramethylenetetranitramine (HMX) 40.0 40.0 36,0 Lead Peroxide 4.0 4.0 p,p'-Biphenylene-bis(diphenylmethyl) 4.0 4.0 Resorcinol 0.5 0.5 0.5 Toluene Diisocyanate (added) 1.0 1.0 1.0 Burning Rate (ips at 1000 psi) 1 0.35 0.72 0.85
*Casting powder formulation: l0.l parts nitrocellulose .95 parts nitroglycerine .20 parts 2-nitrodiphenylamine TOTAL I 1.25 parts Casting powder The biradical catalysts are effective both as burning rate promoters as well as inhibitors for resonance burnyl-terminated polybutadiene-based propellants which employ a biradical compound as the burning rate catalyst. 1
. Still another object of this invention is to provide carboxl-terminated polybutadiene-based propellants which employ a biradical compound as theburning rate catalyst.
3 (ballistic modifier and catalyst), resorcinol (stabilizer), and toluene diisocyanate (crosslinking agent). Al
a carboxyl-terminated polybutadiene-based propellant.
Table 111 A Comparison of a Carboxyl-Terminated Polybutadiene-Based Propellant (CTPB) Using N-Butylferrocene as Burning Rate Catalyst With a CTPB-Based Propellant Using Biradical Burning Rate Catalyst though, compositions A and C of Table l are near smokeless double-base propellants, an improvement in the smokeless properties is gained in composition B where a complete replacement of lead peroxide is made by p, p'-biphenylene-bis(diphenylmethyl).
Table 11 illustrates how the biradical burning rate cat- 30 alyst (compound A or B) of this invention is used in a hydroxyl-terminated polybutadiene-based propellant.
Table 11 The propellants of Table 111 employ a'carboxyl-terminated polybutadiene binder, ammonium perchlorate oxidizer, aluminum metal fuel, n-butylferrocene catalyst (in standard composition A) and p, p'-biphenylene-bis(diphenylmethyl) (in composition B), and crosslinking agent tris[l-(2-methyl)aziridinyl]-phosphine oxide. Tris(oxiranyl)-para-aminophenol and iron linoleate are curatives each of which are added in trace A Comparison of Hydroxyl-Terminated Polybutadiene-Based Propellants With and Without Biradical Burning Rate Catalyst PROPELLANT COMPOSITION INGREDIENTS/BURNING RATE PERCENT BY WEIGHT AND BURNING RATES INGREDIENT Hydroxyl-terminated Polybutadiene Prepolymer 9.84 9.84 Dimeryl Diisocyanate 1.92 1.92 Bonding Agent* 0.24 0.24 Ammonium Perchlorate 73. 71. Aluminum 15. 15. p,p'-Biphenylene-bis(diphenylmethyl) 2. Burning Rate (ips at 1000 psi) 0.35 0.78
Bonding agent is formulated of cquimnlar quantities of trisl 1-( Z-methyl)aziridinyllphosphine oxide. tartaric acid. and adipic acid. Bonding agent is used in an amount from about 0.1-0.3 percent by weight of propellant composition.
The propellants of Table I] employ a hydroxyl-terminated polybutadiene binder, ammonium perchlorate oxidizer, aluminum metal fuel, the burning rate catalyst p, p'-biphenylene-bis(diphenylmethyl), and materials for additives which include the crosslinking compound dimeryl diisocyanate and a bonding agent to provide desirable physical properties through crosslinking and curing reactions. A marked increase in burning rate is achieved with Propellant B of Table I1 which contains the burning rate catalyst, p, p-biphenylene-bis(diphenylmethyl). Propellant A of Table II is the standard propellant. The use of the biradical catalyst to control burning rates of HTPB-based propellants is attractive because of the compatibility of this type compound with HTPB-based propellants.
Table III illustrates how the biradical burning rate catalyst (compoundA or B) of this invention is used in amounts from about 0.1 to about 0.5 percent by weight of the total weight of all the other combined propellant ingredients.
The ranges of propellant ingredients of the doublebase type propellants disclosed herein are (in percent by weight of the propellant composition) as follows: binder from casting powder (formulated of nitrocellulose of about 10.1 parts, of about 0.95 parts nitroglycerine, and of about 0.20 parts Z-nitrodiphenylamine) from about 6.to about 23; TEGDN from about 20 to about 35; BTTN from about 10 to about 20; HMX from about 30 to about 50; biradical catalyst (selected from p, p-biphenylene-bis(diphenylmethyl) and p, p'-phenylene-bis(diphenylmethyl)) from about 2.0 to'about 8.0; lead peroxide from about 2.0 to about 6.0; stabilizers from about 0.5 to about 1.0; and curative additives from about 0.5 to about 2.0.
foregcrosslinking functions, bonding agent. functions,
curing functions, etc. from about 0,5,to-about 2.0.
The ranges of the composite propellant ingredients, using carboxylterminated polybiitadiene binder in the compositions disclosed herein, are )(in percent by weight" of the p'ropellant composition) as follows: biradical catalyst selected from pj'pFbiphenylene-bisb cliphenylm'e'thylji'and p'-phenylene-bis(diphenylmethyl) from about 2.0 to about 8.0;ariinibnjiiim perchlorate from about 60 to about'70; aluminum metal fuel from about 5 to "about20; carboxyl-terminated polybutadi'ene prepo'lyrner' from about? to about crosslinking agent (tris[ 1-( 2-methyl)aziridiny1]phosphine oxide) from about 0.5 to about 2.0; and curatives (tris(oxiranyl)-para-aminophenol) and iron linoleate, each in an amount from about 0.1 to about 0.5 percent by weight of the total weight of all the other propellant ingredients.
Because of the compatibility of the biradical compounds of this invention with both double base-propel- I lant ingredients and composite propellants using hy-' any unavailability of facilities for the manufacture of the boron-containing catalysts.
No special procedures are required for the mixing of propellants employing the disclosed biradical compounds. The standard methods or procedures employed in the art for propellant mixing of double-base and composite propellants have been proven to be very satisfactory for the propellants of this invention.
I claim:
1. A solid propellant composition comprising a binder, an oxidizer, a burning rate catalyst selected from the biradical compounds consisting of p, p-biphenylene-bis(diphenylmethyl) and p, p-phenylene-bis(- diphenylmethyl), and a crosslinking agent.
2. The propellant composition of claim 1 wherein said binder is present in an amount from about 6 to about 23 percent by weight of said propellant composition, said binder being constituted of about 10.1 parts nitrocellulose, about 0.95 parts nitroglycerin, and about 020 parts of 2-nitrodiphenylamine; said oxidizer is cyclotetramethylenetetranitramine which is present in an amount from about 30 to about 50 percent by weight of said propellant composition; said catalyst selected is p, p-biphenylene-bis(diphenylmethyl) which clotetramethylenetetranitramine --is present .6 V ispresent in an amount from about 2 to about 8'percent by weight of said.propellantcomposition; said composition includes the plasticizer, triethylene glycol dinitrate in an amount from about 20 to about 35 percent by weight of said propellant composition and the plasticizer, butanetriol'trinitrate in an amount from about 10 to about 20percent by weight of said propellant composition; said propellant composition additionally incl'udesan agent for stabilizingwhich is resorcinol which is presentin an amount from about 0.5 to about 1.0 percent by weight of said propellantcomposition; and wherein said crosslinking agent is toluene diisocyanate which is addedin an'amount of about 1.0 percent by weight of the total weight of all the other propellant ingredients.
3: The propellant compositionof claim 2 wherein said binder is present in an amount of about 1 1.25 percent b-y'weight of said propellant composition; said eyin an amount of about 36 to about '40 percent by weight of said propellant composition; said triethylene glycol dinitrate is present-in an amount of about 28.75 percent by weight of said propellant composition; said butanetriol trinitrate is present in an amount of about 15.5 percent by weight of said propellant composition; said p, p'-biphenylene-bis(diphenylmethyl) is present in an amount of about 4.0 percent by weight of said propellant composition; and said resorcinol is present in an amount of about 0.5 percent by weight of said propellant composition.
4. The propellant composition of claim 3 wherein said cyclotetramethylenetetranitramine is present in an amount of about 36 percent by weight of said propellant composition; and wherein said composition additionally contains the ballistic modifier, lead peroxide, in an amount of about 4.0 percent by weight of said propellant composition.
5. The propellant composition of claim 1 wherein said binder is hydroxyl-terminated polybutadiene which is present in an amount from about 7 to about 15 percent by weight of said propellant composition; said oxidizer is ammonium perchlorate which is present in an amount from about to about percent by weight of said propellant composition; said catalyst selected is p, p'-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said crosslinking agent is dimeryl diisocyanate which is present in an amount from about 0.5 to about 2.0 percent by weight of said propellant composition; said composition contains a bonding agent formulated of equimolar quantities of tris[1-(2-methyl)-aziridinyl]phosphine oxide, tartaric acid, and adipic acid, said bonding agent is present in an amount from about 0.1 to about 0.3 percent by weight of said propellant composition; and wherein said propellant composition additionally contains aluminium metal fuel in an amount from about 5 to about 20 percent by weight of said propellant composition.
6. The propellant composition of claim 5 wherein said binder is present in an amount of about 9.84 percent by weight of said propellant composition; said ammonium perchlorate is present in an amount of about 71 percent by weight of said propellant composition; said p, p'-biphenylene-bis(diphenylmethyl) is present in an amount of about 2 percent by weight of said propellant composition; said dimeryl diisocyanate is present in an amount of about 1.92 percent by weight of said propellant composition; said bonding agent is present in an amount of about 0.24 percent by weight of said propellant composition; and said aluminium metal fuel is present in an amount of about 15 percent by weight of said propellant composition.
7. The propellant composition of claim 1 wherein said binder is carboxyl-terminated polybutadiene which is present in an amount from about 7 to about l percent by weight of said propellant composition; said oxidizer is ammonium perchlorate which is present in an amount from about 60 to about 70 percent by weight of said propellant composition; said catalyst selected is p, p'-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said crosslinking agent is tris[ l-(2-methyl)aziridinyl]-phosphine oxide which is present in an amount from about 05 to about 2.0 percent by weight of said propellant composition; said propellant composition includes aluminum metal fuel in an amount from about 5 to about percent by weight of said propellant composition; and wherein said propellant composition additionally in- 8 cludes the curatives consisting of tris(oxiranyl)-paraaminophenol and iron linoleate which are each added to said propellant composition in an amount from about 0.1 to about 0.5 percent by weight of the total weight of all the other propellant ingredients.
8. The propellant composition of claim 7 wherein said binder is present in an amount of about 12.5 percent by weight of said propellant composition; said ammonium perchlorate is present in an amount of about 66 percent by weight of said perchlorate composition; said p,.p'-biphenylene-bis(diphenylmethyl) is present in an amount of about 7 percent by weight of said propellant composition; said tris[l-(2-methyl)aziridinyl]-.
phosphine oxide is present in an amount of about 0.5 percent by weight of said propellant composition; said aluminium metal fuel is present in an amount of about 14 percent by weight of said propellant composition; and said tris(oxiranyl)-para-aminophenol and iron linoleate are each present in an amount of about 0.1 percent by weight of all the other propellant ingredients.

Claims (8)

1. A SOLID PROPELLANT COMPOSITION COMPRISING A BINDER, AN OXIDIZER, A BURNING RATE CATALYST SELECTED FROM THE BIRADICAL COMPOUNDS CONSISTING OF P, P''-BIPHENYLENE-BIS(DIPHENYLMETHYL) AND P, P''-PHENYLENE-BIS(DIPHENYLMETHYL), AND A CROSSLINKING AGENT.
2. The propellant composition of claim 1 wherein said binder is present in an amount from about 6 to about 23 percent by weight of said propellant composition, said binder being constituted of about 10.1 parts nitrocellulose, about 0.95 parts nitroglycerin, and about 0.20 parts of 2-nitrodiphenylamine; said oxidizer is cyclotetramethylenetetranitramine which is present in an amount from about 30 to about 50 percent by weight of said propellant composition; said catalyst selected is p, p''-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said composition includes the plasticizer, triethylene glycol dinitrate in an amount from about 20 to about 35 percent by weight of said propellant composition and the plasticizer, butanetriol trinitrate in an amount from about 10 to about 20 percent by weight of said propellant composition; said propellant composition additionally includes an agent for stabilizing which is resorcinol which is present in an amount from about 0.5 to about 1.0 percent by weight of said propellant composition; and wherein said crosslinking agent is toluene diisocyanate which is added in an amount of about 1.0 percent by weight of the total weight of all the other propellant ingredients.
3. The proPellant composition of claim 2 wherein said binder is present in an amount of about 11.25 percent by weight of said propellant composition; said cyclotetramethylenetetranitramine is present in an amount of about 36 to about 40 percent by weight of said propellant composition; said triethylene glycol dinitrate is present in an amount of about 28.75 percent by weight of said propellant composition; said butanetriol trinitrate is present in an amount of about 15.5 percent by weight of said propellant composition; said p, p''-biphenylene-bis(diphenylmethyl) is present in an amount of about 4.0 percent by weight of said propellant composition; and said resorcinol is present in an amount of about 0.5 percent by weight of said propellant composition.
4. The propellant composition of claim 3 wherein said cyclotetramethylenetetranitramine is present in an amount of about 36 percent by weight of said propellant composition; and wherein said composition additionally contains the ballistic modifier, lead peroxide, in an amount of about 4.0 percent by weight of said propellant composition.
5. The propellant composition of claim 1 wherein said binder is hydroxyl-terminated polybutadiene which is present in an amount from about 7 to about 15 percent by weight of said propellant composition; said oxidizer is ammonium perchlorate which is present in an amount from about 65 to about 75 percent by weight of said propellant composition; said catalyst selected is p, p''-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said crosslinking agent is dimeryl diisocyanate which is present in an amount from about 0.5 to about 2.0 percent by weight of said propellant composition; said composition contains a bonding agent formulated of equimolar quantities of tris(1-(2-methyl)-aziridinyl)phosphine oxide, tartaric acid, and adipic acid, said bonding agent is present in an amount from about 0.1 to about 0.3 percent by weight of said propellant composition; and wherein said propellant composition additionally contains aluminium metal fuel in an amount from about 5 to about 20 percent by weight of said propellant composition.
6. The propellant composition of claim 5 wherein said binder is present in an amount of about 9.84 percent by weight of said propellant composition; said ammonium perchlorate is present in an amount of about 71 percent by weight of said propellant composition; said p, p''-biphenylene-bis(diphenylmethyl) is present in an amount of about 2 percent by weight of said propellant composition; said dimeryl diisocyanate is present in an amount of about 1.92 percent by weight of said propellant composition; said bonding agent is present in an amount of about 0.24 percent by weight of said propellant composition; and said aluminium metal fuel is present in an amount of about 15 percent by weight of said propellant composition.
7. The propellant composition of claim 1 wherein said binder is carboxyl-terminated polybutadiene which is present in an amount from about 7 to about 15 percent by weight of said propellant composition; said oxidizer is ammonium perchlorate which is present in an amount from about 60 to about 70 percent by weight of said propellant composition; said catalyst selected is p, p''-biphenylene-bis(diphenylmethyl) which is present in an amount from about 2 to about 8 percent by weight of said propellant composition; said crosslinking agent is tris(1-(2-methyl)aziridinyl)-phosphine oxide which is present in an amount from about 0.5 to about 2.0 percent by weight of said propellant composition; said propellant composition includes aluminum metal fuel in an amount from about 5 to about 15 percent by weight of said propellant composition; and wherein said propellant composition additionally includes the curatives consisting of tris(oxiranyl)-para-aminophenol and iron linoleate which are each added to said propellant composition in an amount from about 0.1 to about 0.5 percent by weight of the total weight of all the other propellant ingredients.
8. The propellant composition of claim 7 wherein said binder is present in an amount of about 12.5 percent by weight of said propellant composition; said ammonium perchlorate is present in an amount of about 66 percent by weight of said perchlorate composition; said p, p''-biphenylene-bis(diphenylmethyl) is present in an amount of about 7 percent by weight of said propellant composition; said tris(1-(2-methyl)aziridinyl)phosphine oxide is present in an amount of about 0.5 percent by weight of said propellant composition; said aluminium metal fuel is present in an amount of about 14 percent by weight of said propellant composition; and said tris(oxiranyl)-para-aminophenol and iron linoleate are each present in an amount of about 0.1 percent by weight of all the other propellant ingredients.
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US3969166A (en) * 1975-05-21 1976-07-13 The United States Of America As Represented By The Secretary Of The Army Anti-erosive, solid rocket propellant compositions
US4299636A (en) * 1974-04-05 1981-11-10 Hercules Incorporated Alkoxy substituted aromatic stabilizers for crosslinked CMDB propellant
US4304614A (en) * 1975-09-04 1981-12-08 Walker Franklin E Zirconium hydride containing explosive composition
US5154782A (en) * 1991-08-15 1992-10-13 Thiokol Corporation Obscuring and nontoxic smoke compositions
CN103708985A (en) * 2013-12-19 2014-04-09 中北大学 Progressive combustion solid propellant coated with microporous structure

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US3364086A (en) * 1964-12-09 1968-01-16 Nitrochemie G M B H Muhldorf Propellants containing nitrocellulose
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US3455883A (en) * 1963-01-09 1969-07-15 Gen Mills Inc Polyisocyanates and derivatives
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US3498856A (en) * 1967-07-24 1970-03-03 Standard Oil Co Combustion catalyst for solid ammonium nitrate propellant grain
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US3455883A (en) * 1963-01-09 1969-07-15 Gen Mills Inc Polyisocyanates and derivatives
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US3364086A (en) * 1964-12-09 1968-01-16 Nitrochemie G M B H Muhldorf Propellants containing nitrocellulose
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4299636A (en) * 1974-04-05 1981-11-10 Hercules Incorporated Alkoxy substituted aromatic stabilizers for crosslinked CMDB propellant
US3969166A (en) * 1975-05-21 1976-07-13 The United States Of America As Represented By The Secretary Of The Army Anti-erosive, solid rocket propellant compositions
US4304614A (en) * 1975-09-04 1981-12-08 Walker Franklin E Zirconium hydride containing explosive composition
US5154782A (en) * 1991-08-15 1992-10-13 Thiokol Corporation Obscuring and nontoxic smoke compositions
CN103708985A (en) * 2013-12-19 2014-04-09 中北大学 Progressive combustion solid propellant coated with microporous structure
CN103708985B (en) * 2013-12-19 2016-04-13 中北大学 A kind of solid gun propellant of coated multi-cellular structure progressive burning

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