US3732132A - Extrudable fluorocarbon propellants - Google Patents

Extrudable fluorocarbon propellants Download PDF

Info

Publication number
US3732132A
US3732132A US00413680A US3732132DA US3732132A US 3732132 A US3732132 A US 3732132A US 00413680 A US00413680 A US 00413680A US 3732132D A US3732132D A US 3732132DA US 3732132 A US3732132 A US 3732132A
Authority
US
United States
Prior art keywords
propellant
teflon
ingredients
viton
percent
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
Application number
US00413680A
Inventor
R Merrow
E Julian
J Eldridge
G Rice
R Dow
C Rodgers
B Stull
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
US Department of Navy
Original Assignee
US Department of Navy
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by US Department of Navy filed Critical US Department of Navy
Application granted granted Critical
Publication of US3732132A publication Critical patent/US3732132A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/16—Halogen-containing compounds
    • 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
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
    • C08L27/00—Compositions of homopolymers or copolymers of compounds having one or more unsaturated aliphatic radicals, each having only one carbon-to-carbon double bond, and at least one being terminated by a halogen; Compositions of derivatives of such polymers
    • C08L27/02—Compositions of homopolymers or copolymers of compounds having one or more unsaturated aliphatic radicals, each having only one carbon-to-carbon double bond, and at least one being terminated by a halogen; Compositions of derivatives of such polymers not modified by chemical after-treatment
    • C08L27/12—Compositions of homopolymers or copolymers of compounds having one or more unsaturated aliphatic radicals, each having only one carbon-to-carbon double bond, and at least one being terminated by a halogen; Compositions of derivatives of such polymers not modified by chemical after-treatment containing fluorine atoms
    • C08L27/18—Homopolymers or copolymers or tetrafluoroethene
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
    • C08L27/00—Compositions of homopolymers or copolymers of compounds having one or more unsaturated aliphatic radicals, each having only one carbon-to-carbon double bond, and at least one being terminated by a halogen; Compositions of derivatives of such polymers
    • C08L27/02—Compositions of homopolymers or copolymers of compounds having one or more unsaturated aliphatic radicals, each having only one carbon-to-carbon double bond, and at least one being terminated by a halogen; Compositions of derivatives of such polymers not modified by chemical after-treatment
    • C08L27/12—Compositions of homopolymers or copolymers of compounds having one or more unsaturated aliphatic radicals, each having only one carbon-to-carbon double bond, and at least one being terminated by a halogen; Compositions of derivatives of such polymers not modified by chemical after-treatment containing fluorine atoms
    • C08L27/16—Homopolymers or copolymers or vinylidene fluoride
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S149/00—Explosive and thermic compositions or charges
    • Y10S149/11—Particle size of a component
    • Y10S149/114—Inorganic fuel

Definitions

  • the present invention relates to improved fluorocarbon propellant compositions.
  • Binders for composite solid propellants have, historically, consisted of natural or synthetic plastics, resins, or elastomeric materials composed of the elements carbon, hydrogen, oxygen, and nitrogen. Because of their high density, thermal stability, water impermeability compatibility with a Wide range of propellant ingredients, and high heat of reaction with metals, the fluorinated binders exhibit many desirable properties in the propellant field. They can be divided into two classes, those which are castable and those which must be processed by extrusion or compression molding New high density solid propellants and their preparation utilizing a single fluorocarbon as a binder are described in copending patent application Ser. No.
  • propellants which contain a metal-hydride as the fuel and ammonium perchlorate as the oxidizer, are processed by isostatic pressing.
  • the present invention is for improved fluorocarbon composite propellants which have better chemical and physical properties than other known solid propellants.
  • Still another object is to provide a propellant with exceptionally high structural integrity.
  • a further object of this invention is to provide a propellant which has long storage life under varying temperature and humidity conditions.
  • Yet another object is to provide a propellant which can be produced in large volumes at low cost.
  • Another object is to provide a propellant with a wide range of burning rates and physical properties without changing over-all composition or energy level.
  • Another object of this invention is to provide a propellant for use in seatejection and cockpit-capsule-ejec tion devices or other devices having high inert mass to propellant volume ratio.
  • the present propellant composition comprises from 5 to 60 percent binder which is composed of polytetrafluoroethylene (hereinafter referred to by its trade name Teflon) and a copolymer of vinvlidene fluoride and perfluoropropylene (hereinafter referred to by its trade name Viton), in weight ratios of from 3:1 to 1:10; from 10 to percent by weight oxidizer selected from the group consisting of ammonium perchlorate, lithium perchlorate, potassium perchlorate, cyclotetramethylene tetranitramine, nitronium perchlorate, hydrazine, diperchlorate, hydrazine nitroform and hydroxylamine perchlorate; from 0 to 90 percent by weight metallic fuel selected from the group consisting of aluminum, magnesium, zirconium, hafnium, tungsten, thorium, beryllium, uranium, boron, titanium, aluminum hydride, beryllium hydride, zirconium
  • the Viton is first dissolved in a solvent selected from a low-boiling ketone such as acetone and methylethylketone or a low boiling ester such as ethyl acetate, methyl acetate and butylacetate, and nitroalkanes such as nitraethane.
  • a solvent selected from a low-boiling ketone such as acetone and methylethylketone or a low boiling ester such as ethyl acetate, methyl acetate and butylacetate, and nitroalkanes such as nitraethane.
  • the Teflon and other ingredients are then thoroughly mixed into the Viton solution to form a uniform slurry.
  • the slurry or suspension is washed for from 5 to 10 minutes with hexane, the volume of hexane being from one to four times the volume of slurry.
  • the supernatant hexane is decanted or si
  • the slurry may be washed with normal hexane or other low boiling liquid hydrocarbon two or three times, as necessary.
  • Other wash materials depending on solubility of propellant ingredients are Freons and chlorocarbons.
  • EXAMPLE III Ingredients: Percent by weight Teflon 10 Viton A l5 Ammonium perchlorate 55 Aluminum powder 20
  • This propellant was static-fired in both 2-inch and 5- inch diameter evaluation motors at 65, 70, and F.
  • the specific impulse at 70 F. was 235 lbf.-sec./lbm., corrected to 1000/ 14.7.
  • the performance of this propellant was also demonstrated in two flight tests of 5-inch motors, at a ratio of inert mass to propellant volume of 550 lb./cu. ft.
  • These motors flew 10,515 and 10,575 yards respectively, while control rounds using a state of-the-art polyurethane propellant flew an average of 8,350 yards.
  • the above propellant composition was successfully static-fired in 5-inch diameter motors at 65, 70, and 165 F., and was evaluated in two flight tests in 5-inch hardware at a mass-to-volume ratio of 550 lb./cu. ft. These motors flew 11,350 and 11,020 yards respectively. This represents an average increase in range of 34% over that of control rounds containing the same volume of a state of-the-art polyurethane propellant and an increase over the range attained by the higher impulse aluminum-fluorocarbon propellant described in Example III above.
  • EXAMPLE VI Ingredients: Percent by weight Viton A 20 Teflon 20 Ammonium perchlorate 30 Zirconium (22 30).
  • the above composition has high density with less than solids in the exhaust products. This is an example of the use of fluorine in the binder as an oxidizer to form gaseous metal products in place of liquid or solid oxides. This formulation is suitable for spin application where some solids inthe exhaust products deposit in the combustion chamber.
  • EXAMPLE VII Ingredients: Percent by weight Viton A l5 Teflon Ammonium perchlorate 30 Zirconium (22 40 The above propellant composition is approximately optimum (at that binder level and binder composition) on the basis of burnt velocity at a mass-to-volume ratio of 1000.
  • This composition was successfully fired in 5" 38 RA-P projectiles (Rocket Assisted Projectile) and withstood 21,000 centrifugal Gs. It is an example of a propellant that can endure severe environmental conditions and remain structurally intact. This has been demonstrated in grains ranging from 1" to 3 /2" in diameter.
  • EXAMPLE IX Ingredients: Percent by weight Viton A 12 Teflon 8 Nitronium perchlorate 45 Triaminoguanidine 15 Aluminum The above composition is an example of fluorocarbon binder compatability with highly energetic propellant ingredients.
  • the above composition was extruded into 5-inch propellant grains. It had a measured density of 5.76 g./cm. a measured specific impulse of 72 lb.-sec./ lb. and a specific impulse efficiency of 69% in a 5-inch motor because of a large percentage of nongases in the exhaust jet. Although this composition was formulated for use in Tailored Exhaust Velocity Rockets (TEVR), it out-distanced stateofthe-art polyurethane propellants.
  • TEVR Tailored Exhaust Velocity Rockets
  • EXAMPLE XI Ingredients: Percent by weight Viton A l2 Teflon 8 Nitrogen perchlorate 50 Aluminum 5 Aluminum hydride 25 This is a typical example of a high specific impulse propellant using fluorocarbon binders in accordance with this invention.
  • EXAMPLE XII Ingredients: Percent by weight VitonA 15 Teflon 15 Potassium perchlorate 50 Aluminum 19 Boron 1 This is an example of a thermally stable propellant.
  • the specific impulse of the above composition at 70 F. was 230 lbf.-sec./lbs., corrected to 1000/l4.7.
  • the specific impulse of the above composition at 70 F. was 214 lbf.-sec./lbm., corrected to 1000/ 14.7.
  • EXAMPLE XV Ingredients: Percent by weight Teflon 5 VitonA 15 Aluminum 25 Hydrazine diperchlorate 55
  • a preform or article such as a solid rod or internal star-perforated grain may be formed by pressing, by rolling, or by extrusion.
  • the Viton- Teflon binder markedly reduces the temperature and/or pressure necessary to process and extrude the propellant in a finished well consolidated form.
  • Both aluminum and zirconium fuels with ammonium perchlorate as oxidizer in the Teflon-Viton binder system have produced high performance propellants.
  • the aluminum composition yields higher specific impulses than those containing zirconium, but the latter have significantly greater densities.
  • the choice of fuel depends on the characteristics of the system in which the propellant is to be used.
  • the use of small amounts of tungsten in the formulation increases the density impulse without greatly sacrificing specific impulse.
  • Incorporating beryllium in the fluorocarbon binder yields the highest specific impulse of any of the metallic fuels.
  • Zirconium metal powder is known to be sensitive to static electricity but it was found that the 22-micron powder which was generally used in this invention could be handled safely with normal precautions. However, a finer grade (a particle size) presented a serious hazard, since its electrostatic sensitivity was 1000 ergs or less. Use of the finer metal results in a rapid increase in burning rate. In order to use this material, it was necessary to desensitize it.
  • fluorocarbon polymers may be used as alternatives for Viton A in the Teflon-Viton binder.
  • a similar oopolymer selling under the trade name Fluorel (hexafluoropropylene-vinylidene fluoride) or the homopolymer of chlorotrifluoroethylene, generally known as Kel-F elastomers, and nitrosorubber provide properties about as good as the Viton.
  • the copolymer of tetrafluoroethylene and hexafluoropropylene known to the trade as Teflon 100 was used as an alternative for polytetrafluoroethylene (Teflon) in preparing the binder.
  • a propellant composition comprising the following:
  • a propellant composition comprising the following:
  • a propellant composition comprising the following:

Abstract

PROPELLANT COMPOSITIONS ARE PREPARED CONTAINING METALS, OXIDIZING AGENTS AND A COPOLYMER OF VINYLIDENE FLUORIDE AND PERFLUOROPROPYLENE WITH POLYTETRAFLUOROETHYLENE.

Description

United States Patent 6 Int. Cl. C06d /06 U.S. Cl. 149-19 7 Claims ABSTRACT OF THE DISCLOSURE Propellant compositions are prepared containing metals, oxidizing agents and a copolymer of vinylidene fluoride and perfiuoropropylene with polytetrafluoroethylene.
The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
The present invention relates to improved fluorocarbon propellant compositions.
In the last few years considerable interest has developed in the fluorocarbon family of polymers as potential binder materials for composite solid propellants. Binders for composite solid propellants have, historically, consisted of natural or synthetic plastics, resins, or elastomeric materials composed of the elements carbon, hydrogen, oxygen, and nitrogen. Because of their high density, thermal stability, water impermeability compatibility with a Wide range of propellant ingredients, and high heat of reaction with metals, the fluorinated binders exhibit many desirable properties in the propellant field. They can be divided into two classes, those which are castable and those which must be processed by extrusion or compression molding New high density solid propellants and their preparation utilizing a single fluorocarbon as a binder are described in copending patent application Ser. No. 99,967 filed Mar. 31, 1961. These propellants which contain a metal-hydride as the fuel and ammonium perchlorate as the oxidizer, are processed by isostatic pressing. The present invention is for improved fluorocarbon composite propellants which have better chemical and physical properties than other known solid propellants.
It is an object of the present invention to provide a solid propellant with a high density impulse along with a relatively high specific impulse.
Still another object is to provide a propellant with exceptionally high structural integrity.
A further object of this invention is to provide a propellant which has long storage life under varying temperature and humidity conditions.
Yet another object is to provide a propellant which can be produced in large volumes at low cost.
Another object is to provide a propellant with a wide range of burning rates and physical properties without changing over-all composition or energy level.
Another object of this invention is to provide a propellant for use in seatejection and cockpit-capsule-ejec tion devices or other devices having high inert mass to propellant volume ratio.
Other objects and many attendant advantages of this invention will be readily appreciated as the same become better understood from the following disclosure.
The present propellant composition comprises from 5 to 60 percent binder which is composed of polytetrafluoroethylene (hereinafter referred to by its trade name Teflon) and a copolymer of vinvlidene fluoride and perfluoropropylene (hereinafter referred to by its trade name Viton), in weight ratios of from 3:1 to 1:10; from 10 to percent by weight oxidizer selected from the group consisting of ammonium perchlorate, lithium perchlorate, potassium perchlorate, cyclotetramethylene tetranitramine, nitronium perchlorate, hydrazine, diperchlorate, hydrazine nitroform and hydroxylamine perchlorate; from 0 to 90 percent by weight metallic fuel selected from the group consisting of aluminum, magnesium, zirconium, hafnium, tungsten, thorium, beryllium, uranium, boron, titanium, aluminum hydride, beryllium hydride, zirconium hydride alloys and mixtures thereof; from 0 to 30 percent by weight of a member selected from the group consisting of triaminoguanidine, triaminoguanidine azide, double salt triaminoguanidine azide-hydrazine azide, and mixtures thereof.
In preparing these formulations the Viton is first dissolved in a solvent selected from a low-boiling ketone such as acetone and methylethylketone or a low boiling ester such as ethyl acetate, methyl acetate and butylacetate, and nitroalkanes such as nitraethane. The Teflon and other ingredients (oxidizer, fuel, and additives) are then thoroughly mixed into the Viton solution to form a uniform slurry. The slurry or suspension is washed for from 5 to 10 minutes with hexane, the volume of hexane being from one to four times the volume of slurry. After the suspension has settled the supernatant hexane is decanted or siphoned off and the resulting residue is dried under ambient conditions for 8 to 24 hours. The material is now ready for extrusion in a standard propellant extrusion press.
The slurry may be washed with normal hexane or other low boiling liquid hydrocarbon two or three times, as necessary. Other wash materials depending on solubility of propellant ingredients are Freons and chlorocarbons.
The following examples are given for a better understanding of this invention and no unnecessary limitations are to be understood therefrom.
The burning rate of the above composition at 1000 p.s.i. 70 F., was 0.35 in./sec.
EXAMPLE III Ingredients: Percent by weight Teflon 10 Viton A l5 Ammonium perchlorate 55 Aluminum powder 20 This propellant was static-fired in both 2-inch and 5- inch diameter evaluation motors at 65, 70, and F. The specific impulse at 70 F. was 235 lbf.-sec./lbm., corrected to 1000/ 14.7. The performance of this propellant was also demonstrated in two flight tests of 5-inch motors, at a ratio of inert mass to propellant volume of 550 lb./cu. ft. These motors flew 10,515 and 10,575 yards respectively, while control rounds using a state of-the-art polyurethane propellant flew an average of 8,350 yards.
3 EXAMPLE 1v Ingredients: Percent by weight Viton A 15 Teflon 5 Ammonium perchlorate 65 Beryllium 15 EXAMPLE V Ingredients: Percent by weight Viton A 15 Teflon 5 Ammonium perchlorate 42.4 Zirconium (22 37.6
The above propellant composition was successfully static-fired in 5-inch diameter motors at 65, 70, and 165 F., and was evaluated in two flight tests in 5-inch hardware at a mass-to-volume ratio of 550 lb./cu. ft. These motors flew 11,350 and 11,020 yards respectively. This represents an average increase in range of 34% over that of control rounds containing the same volume of a state of-the-art polyurethane propellant and an increase over the range attained by the higher impulse aluminum-fluorocarbon propellant described in Example III above.
This same composition using zirconium particles of 5;; increased the burning rate by a factor of 3. By varying the weight ratios of the 22 and 5 particles of zirconium, a burning rate of .34 in/sec. to 1 in/sec. was achieved.
EXAMPLE VI Ingredients: Percent by weight Viton A 20 Teflon 20 Ammonium perchlorate 30 Zirconium (22 30 The above composition has high density with less than solids in the exhaust products. This is an example of the use of fluorine in the binder as an oxidizer to form gaseous metal products in place of liquid or solid oxides. This formulation is suitable for spin application where some solids inthe exhaust products deposit in the combustion chamber.
EXAMPLE VII Ingredients: Percent by weight Viton A l5 Teflon Ammonium perchlorate 30 Zirconium (22 40 The above propellant composition is approximately optimum (at that binder level and binder composition) on the basis of burnt velocity at a mass-to-volume ratio of 1000.
EXAMPLE VIII Ingredients: Percent by weight Viton A 15 Teflon 10 Ammonium perchlorate 44.4 Zirconium (22 30.6
This composition was successfully fired in 5" 38 RA-P projectiles (Rocket Assisted Projectile) and withstood 21,000 centrifugal Gs. It is an example of a propellant that can endure severe environmental conditions and remain structurally intact. This has been demonstrated in grains ranging from 1" to 3 /2" in diameter.
EXAMPLE IX Ingredients: Percent by weight Viton A 12 Teflon 8 Nitronium perchlorate 45 Triaminoguanidine 15 Aluminum The above composition is an example of fluorocarbon binder compatability with highly energetic propellant ingredients.
4 EXAMPLE X Ingredients: Percent by weight Viton A 7 Teflon 4 Magnesium 4 Ammonium perchlorate 10 Tungsten (6.5
The above composition was extruded into 5-inch propellant grains. It had a measured density of 5.76 g./cm. a measured specific impulse of 72 lb.-sec./ lb. and a specific impulse efficiency of 69% in a 5-inch motor because of a large percentage of nongases in the exhaust jet. Although this composition was formulated for use in Tailored Exhaust Velocity Rockets (TEVR), it out-distanced stateofthe-art polyurethane propellants.
EXAMPLE XI Ingredients: Percent by weight Viton A l2 Teflon 8 Nitrogen perchlorate 50 Aluminum 5 Aluminum hydride 25 This is a typical example of a high specific impulse propellant using fluorocarbon binders in accordance with this invention.
EXAMPLE XII Ingredients: Percent by weight VitonA 15 Teflon 15 Potassium perchlorate 50 Aluminum 19 Boron 1 This is an example of a thermally stable propellant.
EXAMPLE XIII Ingredients: Percent by weight Teflon 12.8
Viton A 19.2 Ammonium perchlorate 63.0 Aluminum 5.0
The specific impulse of the above composition at 70 F. was 230 lbf.-sec./lbs., corrected to 1000/l4.7.
EXAMPLE XIV Ingredients: Percent by weight Teflon 15 Viton A 22.5 Ammonium perchlorate 62.5
The specific impulse of the above composition at 70 F. was 214 lbf.-sec./lbm., corrected to 1000/ 14.7.
EXAMPLE XV Ingredients: Percent by weight Teflon 5 VitonA 15 Aluminum 25 Hydrazine diperchlorate 55 In carrying out the invention a preform or article such as a solid rod or internal star-perforated grain may be formed by pressing, by rolling, or by extrusion. The Viton- Teflon binder markedly reduces the temperature and/or pressure necessary to process and extrude the propellant in a finished well consolidated form.
Both aluminum and zirconium fuels with ammonium perchlorate as oxidizer in the Teflon-Viton binder system have produced high performance propellants. The aluminum composition yields higher specific impulses than those containing zirconium, but the latter have significantly greater densities. The choice of fuel depends on the characteristics of the system in which the propellant is to be used. The use of small amounts of tungsten in the formulation increases the density impulse without greatly sacrificing specific impulse. Incorporating beryllium in the fluorocarbon binder yields the highest specific impulse of any of the metallic fuels.
Optimization of the fuel system requires consideration not only of theoretical performance calculations by also of such practical factors as processability, mechanical properties and efficiency of combustion.
A large number of performance calculations were made, covering not only a wide range of fuel/oxidizer/binder ratios but also a variety of binder compositions in terms of the ratio of Teflon to Viton. The effects of compositional changes on both specific impulse and burnt velocity were determined. Because the effects of density on performance are greatest at high mass-to-volume ratios, the value of 1000 lb./cu. ft. was chosen as being typical of the volume limited systems in which this family of propellants would be most useful. By varying the amount of binder (consisting of 50% Teflon and 50% Viton) it was found that the 1520% binder level is near optimum for obtaining the highest specific impulse, but that 10%; or less binder is desirable for obtaining the maximum burnt velocity. However, for a practical system, 20% binder is about the minimum amount which can be used, based on consideration of extrudability and mechanical properties. In the zirconium system, something over 30% binder is required to achieve maximum theoretical specific impulse. Reduction in the average particle size of the metal fuel or oxidizer results in a significant increase in both strength and modulus and in a slight decrease in elongation. The effects of Teflon particle size appears to be in the opposite direction. The use of larger sized Teflon increases the modulus significantly, and the strength to a lesser extent, while decreasing the elongation slightly. The Teflon thus acts as a binder, as well as a filler, since it can undergo appreciable elongation.
Zirconium metal powder is known to be sensitive to static electricity but it was found that the 22-micron powder which was generally used in this invention could be handled safely with normal precautions. However, a finer grade (a particle size) presented a serious hazard, since its electrostatic sensitivity was 1000 ergs or less. Use of the finer metal results in a rapid increase in burning rate. In order to use this material, it was necessary to desensitize it.
Other fluorocarbon polymers may be used as alternatives for Viton A in the Teflon-Viton binder. A similar oopolymer selling under the trade name Fluorel (hexafluoropropylene-vinylidene fluoride) or the homopolymer of chlorotrifluoroethylene, generally known as Kel-F elastomers, and nitrosorubber provide properties about as good as the Viton. Also the copolymer of tetrafluoroethylene and hexafluoropropylene known to the trade as Teflon 100 was used as an alternative for polytetrafluoroethylene (Teflon) in preparing the binder.
Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.
What is claimed is:
1. A propellant composition comprising the following:
Ingredients: Percent by weight Copolymer of vinylidene fluoride and perfluoropropylene 15-20 Polytetrafluoroethylene 5-20 Ammonium perchlorate 30-45 Zirconium 30-40 Ingredients: Percent by weight Copolymer of vinylidene fluoride and pcrfluoropropylene l2 Polytetrafluoroethylene 8 Nitronium perchlorate 50 Aluminum 5 Aluminum hydride 25 6. A propellant composition comprising the following:
Ingredients: Percent by weight Copolymer of vinylidene fluoride and perfluoropropylene l2 Polytetrafluoroethylene 8 Nitronium perchlorate 45 Triaminoguanidine 15 Aluminum 20 7. A propellant composition comprising the following:
Ingredients: Percent by weight Copolymer of vinylidene fluoride and perfluoropropylene 7 Polytetrafluoroethylene 4 Magnesium 4 Ammonium perchlorate l0 Tungsten References Cited UNITED STATES PATENTS 3,027,283 3/1962 Bice 149-19 3,067,074 12/1962 Gey l49'l19 3,122,462 2/1964 Kaufman 149l9 3,235,421 2/1966 Berenbaum et al. l49l9 3,257,248 6/1966 Short et al l4919 3,513,043 5/1970 Burnside 14919 BENJAMIN R. PADGETT, Primary Examiner US. Cl. X.R. 149-20, 21, 36, 114
US00413680A 1964-11-23 1964-11-23 Extrudable fluorocarbon propellants Expired - Lifetime US3732132A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US41368064A 1964-11-23 1964-11-23

Publications (1)

Publication Number Publication Date
US3732132A true US3732132A (en) 1973-05-08

Family

ID=23638188

Family Applications (1)

Application Number Title Priority Date Filing Date
US00413680A Expired - Lifetime US3732132A (en) 1964-11-23 1964-11-23 Extrudable fluorocarbon propellants

Country Status (1)

Country Link
US (1) US3732132A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3876477A (en) * 1965-09-15 1975-04-08 Us Navy Fluorocarbon solid propellant with burning rate modifier
US3963542A (en) * 1973-10-18 1976-06-15 Rockwell International Corporation Oxidizer compatible solid propellant fluorine atom gas generator
US3980509A (en) * 1975-08-07 1976-09-14 Trw Inc. Solid fluoro-oxidizer systems for chemical lasers
US3981756A (en) * 1975-09-09 1976-09-21 The United States Of America As Represented By The Secretary Of The Navy Process for preparing high density solid propellants
US3991680A (en) * 1975-05-15 1976-11-16 The United States Of America As Represented By The United States Energy Research And Development Administration Tagging explosives with sulfur hexafluoride
US4003771A (en) * 1975-08-07 1977-01-18 Trw Inc. Solid grain fuels containing polyphosphonitrilics difluoride for chemical lasers
US4276100A (en) * 1976-02-13 1981-06-30 The United States Of America As Represented By The Secretary Of The Navy Process for disposing of decoy flare material
US4445947A (en) * 1983-03-18 1984-05-01 Thiokol Corporation Low cost fluorocarbon flare compositions
US5042386A (en) * 1974-09-27 1991-08-27 The United States Of America As Represented By The Secretary Of The Navy Destructive device for metal oxide-semiconductors
WO1994017014A1 (en) * 1991-12-06 1994-08-04 E.I. Du Pont De Nemours And Company Fibrillatable ptfe in plastic-bonded explosives
US5339624A (en) * 1990-11-23 1994-08-23 Nobelkrut Ab Ramjet propellants

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3876477A (en) * 1965-09-15 1975-04-08 Us Navy Fluorocarbon solid propellant with burning rate modifier
US3963542A (en) * 1973-10-18 1976-06-15 Rockwell International Corporation Oxidizer compatible solid propellant fluorine atom gas generator
US5042386A (en) * 1974-09-27 1991-08-27 The United States Of America As Represented By The Secretary Of The Navy Destructive device for metal oxide-semiconductors
US3991680A (en) * 1975-05-15 1976-11-16 The United States Of America As Represented By The United States Energy Research And Development Administration Tagging explosives with sulfur hexafluoride
US3980509A (en) * 1975-08-07 1976-09-14 Trw Inc. Solid fluoro-oxidizer systems for chemical lasers
US4003771A (en) * 1975-08-07 1977-01-18 Trw Inc. Solid grain fuels containing polyphosphonitrilics difluoride for chemical lasers
US3981756A (en) * 1975-09-09 1976-09-21 The United States Of America As Represented By The Secretary Of The Navy Process for preparing high density solid propellants
US4276100A (en) * 1976-02-13 1981-06-30 The United States Of America As Represented By The Secretary Of The Navy Process for disposing of decoy flare material
US4445947A (en) * 1983-03-18 1984-05-01 Thiokol Corporation Low cost fluorocarbon flare compositions
US5339624A (en) * 1990-11-23 1994-08-23 Nobelkrut Ab Ramjet propellants
WO1994017014A1 (en) * 1991-12-06 1994-08-04 E.I. Du Pont De Nemours And Company Fibrillatable ptfe in plastic-bonded explosives

Similar Documents

Publication Publication Date Title
US3732132A (en) Extrudable fluorocarbon propellants
US5567912A (en) Insensitive energetic compositions, and related articles and systems and processes
US3309249A (en) Thermite-resin binder solid fuel composition
US5716557A (en) Method of making high energy explosives and propellants
US4098625A (en) Explosive compositions bonded with fluorocarbon polymers
US6576072B2 (en) Insensitive high energy booster propellant
US3725516A (en) Mixing process and extrusion of solid propellants
US4002514A (en) Nitrocellulose propellant composition
US3841929A (en) Solid propellant containing strontium carbonate-calcium citrate burning rate depressant
US4570540A (en) LOVA Type black powder propellant surrogate
US2425854A (en) Propellent powder
US3734788A (en) High density solid propellants and method of preparation using fluoro-polymers
US3923564A (en) Double base propellant with thorium containing ballistic modifier
US3732130A (en) Gun propellant containing nonenergetic plasticizer,nitrocellulose and triaminoguanidine nitrate
US3640070A (en) Hybrid propellant system
US3834956A (en) Solid propellant composition containing lead and lead compounds
US3102834A (en) Composition comprising nitrocellulose, nitroglycerin and oxides of lead or copper
US3726729A (en) Solid propellant compositions having a nitrocellulose-hydroxyl-terminated polybutadiene binder and method of preparing the same
US5798481A (en) High energy TNAZ, nitrocellulose gun propellant
US3732131A (en) Gun propellant containing nitroplasticized nitrocellulose and triaminoguanidine nitrate
US3386868A (en) Heat resistant propellants containing organic oxidizers
US3473982A (en) Nitrocellulose explosive containing a charcoal binder-oxidizer mixture
US4012244A (en) High density impulse solid propellant
US3086896A (en) Nitroguanidine propellant composition and process of preparation
US3755019A (en) Solid propellant compositions containing plasticized nitrocellulose and aluminum hydride