|Publication number||US3811966 A|
|Publication date||May 21, 1974|
|Filing date||Jun 24, 1969|
|Priority date||Jun 24, 1969|
|Publication number||US 3811966 A, US 3811966A, US-A-3811966, US3811966 A, US3811966A|
|Inventors||Beason L, Hill W|
|Original Assignee||Us Army|
|Export Citation||BiBTeX, EndNote, RefMan|
|Referenced by (3), Classifications (13)|
|External Links: USPTO, USPTO Assignment, Espacenet|
3,811,966 COMPOSITE MODIFIED DOUBLE-BASE PROPEL- LANTS WITH VERY HIGH BURNING RATES William E. Hill and Lew R. Beason, Huntsville, Ala., assignors to the United States of America as represented by the Secretary of the Army No Drawing. Filed June 24, 1969, Ser. No. 836,177 Int. Cl. C06d /06 US. Cl. 14919.2 5 Claims ABSTRACT OF THE DISCLOSURE Composite modified double-base propellants with very high burning rates result when ll-isopropenyl, 12-prop-(2- one)-yl-carborane (IPCA), a liquid ketone derivative of isopropenylcarborane, is employed as the burning rate catalyst for the propellant composition.
BACKGROUND OF THE INVENTION This invention relates to solid double-base propellant compositions which generally include the ingredients: nitrocellulose, an inorganic oxidizing salts, plasticizers, stabilizer, burning rate modifier or catalyst, curing agent, processing aid, and generally, metal as a fuel.
Dicarbaclovododecaborane (carborane) and derivatives of carborane belong to a class of compounds which are known to be effective ballistic modifiers for obtaining high burning rates; however, most derivatives of carborane are not compatible with the nitrocellulose used as binders in composite modified double-base propellants.
The problem resulting from using most derivatives of carborane with nitrocellulose is failure of the nitrocellulose to swell to form a homogeneous rubbery matrix which is essential for a solid propellant grain. As known in the art, nitrocellulose must be swollen by nitrate ester plasticizers such as Triethyleneglycoldinitrate (TEGDN) in order to form a homogeneous, rubbery matrix in which the solid components of the propellant (e.g., ammonium perchlorate and aluminum) are evenly dispersed.
A need exists for non-fiber composite modified doublebase propellants with high burning rates. In order to use carborane derivatives as ballistic modifiers to produce a high burning rate propellant without sacrificing the mechanical properties of the propellant, the carborane derivative must not interfere with the swelling process of nitrocellulose caused by the reaction of the plasticizer and the nitrocellulose.
A need exists for carborane derivative which will not interfere with the swelling reaction of nitrocellulose. Thus, a carborane derivative which provides ballistic modifier action by causing a very high burning rate when used with double-base formulations containing nitrocellulose is greatly desired.
United States Patent O Therefore, the present invention has, as its principal Another object is to provide a derivative of carborane which can be used in propellants which are relatively easy to produce by standard techniques known to those familiar with the art.
A further object is to provide propellant formulations which represent an improvement over prior art propellant formulations which require the use of metal fibers and special mixing and casting techniques to obtain fast burning rates for composite modified double-base propellants.
SUMMARY OF THE INVENTION The objects of this invention are achieved by means of a derivative of carborane employed in composite modified double-base propellant compositions. ll-isopropenyl, 12- prop-(2-one)-yl-carboraue, a derivative of carborane and referred to as IPCA, serves to increase the burning rate of double-base propellants wherein used. The double-base propellants of this invention are comprised of IPCA of about 5 to about 25 weight percent, nitrocellulose of about 5 to about 20 weight percent, plasticizer of about 10 to about 30 weight percent, inorganic oxidizer of about 35 to about 52 weight percent, metal fuel of about 5 to about 20 weight percent, stabilizer of about 0.5 to about 2. weight percent, cross-linking agent selected from suitable plasticizer type compounds of about 3 to about 10 Weight percent, and processing aid (e.g. lecithin).
Suitable plasticizers of this invention include nitroglycerin, triacetin, adiponitrile, di-n-propyl adipate, and TEGDN (triethyleneglycoldinitrate). Useful inorganic oxidizing salts of this invention include the ammonium, alkali metal and alkaline earth metal salts of nitric, perchloric, and chloric acids, and mixtures thereof. Metal fuels such as the powdered metals, of aluminum, magneslum, titanium, zirconium and borons are useful in this invention (aluminum is the preferred metal). Stabilizers such as resorcinol and 2-nitro-diphenylamine are used in the compositions of this invention. Plasticizer compounds of the type which perform functions of curing propellant by assisting in cross-linking, chain extending, and chain branching reactions which directly result in imparting desirable physical properties to the propellant are used. Suitable plasticizer type compounds for the described function are adiponitrile, di-n-propyl adipate, triacetin, and the like.
Various other ingredients in trace amounts can also be added for specific purposes without departing from the scope of the invention. For example, lecithin can be added to improve the castability of the uncured propellant. Certain polymerization modifiers such as t-butyl catecol or cobalt 2-ethyl hexanoate may be employed to obtain certain curing conditions and finished product. Modifiers of this type do not interfere with the catalytic values imparted by IPCA to the combustion processes when the propellant is used.
DESCRIPTION OF THE PREFERRED EMBODIMENT A fast burning double-base propellant with qualitatively attractive mechanical properties is produced by incorporating IPCA, a liquid ketone derivative of isopropenylcarborane, into the propellant mixture as a ballistic modifier. The burning rates and composition of the propellant mixture are compared to a control propellant with no ballistic modifier as indicated in Table I.
The propellants are made by weighing the ingredients into a jacketed vertical mixer kept at 60 F. by cooling water. Mixing is accomplished with an air motor driven paddle stirrer for two hours. The propellant mixture is kept under vacuum during mixing at 60 F. When the propellants are well mixed they are cast into small motors at atmospheric pressure. After casting, vacuum is applied to the motors, and they are vibrated for about 45 minutes. This procedure results in motors with void free propellant which are cured over night by placing the motors in an oven held at 60 C. The burning rates of the propellant are then determined by firing the motors fitted with appropriate nozzles to produce various pressures during firing. The burning rates obtained for the propellant with IPCA as the ballistic modifier are about double the rates for the control without modifier at all three pressures listed in Table I.
The burning rate at 2000 p.s.i. for the composite modified double-base propellant containing IPCA shown in Table I is increased to 6.5 in./sec. by substituting ultrafine ammonium perchlorate (2.5 microns Particle size) for the ammonium perchlorate blend shown in Table I. The calculated burning rate (maximum possible) for propellant without IPCA as a ballistic modifier but with ultrafine ammonium perchlorate as oxidizer is 3.0 in/sec. at 2000 p.s.i. Preparative procedures for IPCA which provides the ballistic modifier action for the propellant formulations of this invention are as follows: after flushing the reaction flask and accessory equipment, with dry ni trogen, 50 grams of isopropenylcarborane and 300 milliliters of anhydrous ethyl ether are combined in a three necked flask equipped with two addition funnels, cooling and heating accessory equipment, and accessory equipment for reflux procedure. Butyl lithium (171 milliliters of 1.60 molar) is placed into one addition funnel, and 40 milliliters of propylene oxide is placed in the other one. The flask is cooled to C., and the butyl lithium is added dropwise. After the butyl lithium is added, the flask is heated to reflux and the propylene oxide is added dropwise. After the addition is complete the flask is refluxed for an additional 1 /2 hours. Contents of the flask are then poured into a separatory funnel and washed with an equal portion of water. The water layer is drained 01f and discarded and the ether layer is washed with two ZOO-ml. portions of HQ in water. The acid layers are discarded and the ether layer dried over magnesium sulfate. The ether is removed on a rotary evaporator. The remaining oil is washed into another 3-neck flask with 100-ml. of ether and treated dropwise with a chromic acid solution of 95.6 grams K Cr O 42.6 ml. cone. H 80 and 120 ml. water after the flask is cooled to 0 C. Throughout the addition the ice bath should remain around the flask as heat is generated in this reaction. After the addition of the chromic acid, the ice bath is removed and the reaction stirred at room temperature over night.
The reaction mixture is poured into a separatory funnel and washed with water. The water layer is discarded. The ether layer is then washed twice with saturated sodium bicarbonate-water solutions. The water layer is discarded and the ether layer dried over magnesium sulfate. The ether is removed on an evaporator and the remaining roHio C-CH: lCCH:
The NMR spectrum consists of four absorptions centered at 1.95, 2.18, 3.07 and 5.57 ppm. The 5.57 p.p.m. absorption, due to the vinylic protons, has the gross appearance of a quartet (J=-1 c.p.s.) and a singlet superimposed on one another. The 3.07 and 2.18 p.p.rn. absorptions, due to the CH and CH of the acetone group, are singlets while the ppm peak assigned to isopropenyl CH group has the appearance of a doublet (J'=-1 c.p.s.).
The examples set forth hereinabove demonstrate that non-fiber double-base propellants with fast burning rates can be produced when certain compatible derivatives of carborane are used as ballistic modifiers The propellants are relatively easy to produce by standard techniques known to those familiar with the art and represent an improvement over prior art which requires the use of metal fibers and special mixing and casting techniques to obtain fast burning rates for composite modified double-base propellants.
1. In a double-base solid propellant composition having a rubbery matrix binder formed by swollen nitrocellulose, the improvement in burning rate of said composition achieved by including in said composition a derivative of carborane that is compatible with the swelling process whereby nitrocellulose is swollen by a reaction between the nitrocellulose and plasticizers contained in said composition, said derivative of carborane being 11- isopropenyl, 12-prop-(2-one)-yl-carborane; said doublebase solid propellant composition comprising an inorganic oxidizing salt, plasticizers, metal fuel, nitrocellulose, and said ll-isopropenyl, 12-prop-(2-one)-yl-carborane.
2. The propellant composition of claim 1 and wherein said inorganic oxidizing salt is selected from ammonium, alkali metal, and alkaline earth metal salts of nitric, perchloric, and chloric acids, and mixtures thereof in an amount from about 35 to about 52 weight percent; said plasticizers are selected from nitroglycerin, triacetin, adiponitrile, and triethyleneglycoldinitrate in an amount from about 10 to about 30 weight percent; said metal fuel is selected from aluminum, magnesium, titanium, zirconium, and boron in amount from about 5 to about 20 weight percent; said nitrocellulose is present in amount from about 5 to about 20 weight percent; and wherein said ll-isopropenyl, 12-prop-(2-one)-yl-carborane is present in amount from about 5 to about 25 weight percent.
3. The propellant composition of claim 2 and also comprising a stabilizer selected from resorcinol and 2-nitrodiphenylamine in amounts from about 0.5 to about 2 weight percent.
4. The propellant composition of claim 3 and wherein said inorganic oxidizing salt is ammonium perchlorate, blended of about 5 parts ammonium perchlorate having particle size of about 8 microns and 1 part of ammonium perchlorate having particle size of about 16 microns; said blended perchlorate present in an amount of about 48.0 Weight percent; said nitrocellulose is present in an amount of about 12.0 weight percent; said plasticizer comprised of triethyleneglycoldinitrate of about 20.0 weight percent of the propellant composition and adiponitrile of about 3.0 weight percent of the propellant composition; said ll-isopropenyl, 12-prop-(2-one)-ylcarborane is present in an amount of about 12.0 weight percent; and said stabilizer is resorcinol present in an amount of about 1.0 weight percent.
5. The propellant composition of claim 3 and wherein said inorganic oxidizing salt is ammonium perchlorate 5 having particle size of about 2.5 microns, said perchlorate being present in an amount of about 48.0 weight percent; said nitrocellulose being present in an amount of about 12.0 weight percent; said plasticizer comprised of triethyleneglycoldinitrate of about 20.0 weight percent of the propellant composition and adiponitrile of about 3.0 weight percent of the propellant composition; said 11- isopropenyl, 12-prop-(2-one)-y1-carborane being present in an amount of about 12.0 weight percent; and said stabilizer is resorcinol present in an amount of about 1.0 weight percent.
References Cited UNITED STATES PATENTS 3,107,187 10/1963 Rumbel et al. 14922 3,130,097 4/ 1964 Drummond 14922 3,306,790 2/1967 Crescenzo et al. l4993 6 3,307,985 5/1967 Iago 149--18 3,375,148 3/1968 Finnegan et al. 149--18 3,378,416 4/ 1968 Perry et a1. 149-22 3,406,203 10/1968 Morrow et al. 260-583 3,419,445 12/1968 Markels 149-19 3,489,623 1/ 1970 Griflith et al. 149-20 10 USSR, 37, p. 1301 (June 1967).
CARL D. QUARFORTH, Primary Examiner E. A. MILLER, Assistant Examiner U.S. Cl. X.R.
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US3873386 *||Jun 28, 1971||Mar 25, 1975||Us Navy||Double-base propellant containing poly (carboranyl lower alkyl acrylate)|
|US3954531 *||Jun 14, 1973||May 4, 1976||The United States Of America As Represented By The Secretary Of The Navy||Composite double base propellant composition containing ferric fluoride|
|US4944816 *||Mar 26, 1976||Jul 31, 1990||The United States Of America As Represented By The Secretary Of The Army||Ultra-ultrahigh burning rate composite modified double-base propellants containing porous ammonium perchlorate|
|U.S. Classification||149/19.2, 149/98, 149/38, 149/22, 149/76, 149/97|
|International Classification||C06B23/00, C06B47/10, C06B47/00|
|Cooperative Classification||C06B47/10, C06B23/007|
|European Classification||C06B47/10, C06B23/00F|