US3156594A - Polymeric base propellant compositions containing lithium fluoride catalyst - Google Patents

Polymeric base propellant compositions containing lithium fluoride catalyst Download PDF

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Publication number
US3156594A
US3156594A US374214A US37421464A US3156594A US 3156594 A US3156594 A US 3156594A US 374214 A US374214 A US 374214A US 37421464 A US37421464 A US 37421464A US 3156594 A US3156594 A US 3156594A
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lithium fluoride
burning
compositions containing
containing lithium
polymeric base
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US374214A
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Horton Marvin Duane
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    • 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
    • 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

Definitions

  • This invention relates to a new solid propellant composition, and more particularly to a solid propellant composition with a plateau type burning characteristic.
  • the velocity at which a solid propellant is consumed during operation is called the burning rate. It is measured in a direction normal to the propellant surface and is usually expressed in inches per second.
  • Most of the new propellant compositions which have been developed Within recent years do not possess burning-rate characteristics comparable to those of the old-fashioned compositions; that is, the logarithmic plot of burning-rate versus pressure no longer assumes a straight line called linear burning; but instead mesa and plateau burning have appeared.
  • a plateau-burning propellant is one for which the logarithmic plot of burning-rate versus pressure deviates from that of linear in the following manner. At low pressures, the burning-rate-pressure relationship is generally linear with a moderately high pressure exponent. This is followed by a pressure range where the burning rate becomes nearly constant.
  • the general purpose of the present invention is to blend lithium fluoride with an inorganic oxidizer, a polymeric fuel binder and a low molecular resin such as one of the condensation polymers of epichlorohydrin and bisphenol-A (sold under the tradename Epon 828) to form a rocket propellant composition exhibiting the plateau burning phenomenon.
  • Another object of this invention is to provide a propellant composition having improved physical properties.
  • Yet another object is to provide a propellant which will find use in rocket motors of simplified design.
  • a propellant composition consisting essentially of the following ingredients:
  • Ammonium perchlorate Lithium fluoride Polybutyl acrylic acid terpolymer A resin consisting of a condensation product of epichlorohydrin and bisphenol A.
  • composition of claim 1 wherein the ammonium perchlorate comprises a mixture of particle sizes of about 10 weight percent of 65 50 weight percent of 93 ,u. and about 90 weight percent of 130;.
  • a propellant composition consisting essentially of the following:
  • composition of claim 3 wherein the ammonium perchlorate consists of particle sizes ranging from 63 1. to 1301i.

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  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Dispersion Chemistry (AREA)
  • Molecular Biology (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Fire-Extinguishing Compositions (AREA)

Description

United States Patent 3,156,594 PULYMERKZ BASE PROPELLANT COB/WOSITIUNS CONTING LIT FLUURIDE CATALYST Marvin Duane Horton, Provo, Utah, assignor to the United States of America as represented by the Secretary of the Navy No Drawing. Filed June 10, 1964, Ser. N 374,214 4 Claims. (Cl. 149-19) (Granted under Title 35, US. Code (1952), sec. 266) The invention herein described 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.
This invention relates to a new solid propellant composition, and more particularly to a solid propellant composition with a plateau type burning characteristic.
The velocity at which a solid propellant is consumed during operation is called the burning rate. It is measured in a direction normal to the propellant surface and is usually expressed in inches per second. Most of the new propellant compositions which have been developed Within recent years do not possess burning-rate characteristics comparable to those of the old-fashioned compositions; that is, the logarithmic plot of burning-rate versus pressure no longer assumes a straight line called linear burning; but instead mesa and plateau burning have appeared. A plateau-burning propellant is one for which the logarithmic plot of burning-rate versus pressure deviates from that of linear in the following manner. At low pressures, the burning-rate-pressure relationship is generally linear with a moderately high pressure exponent. This is followed by a pressure range where the burning rate becomes nearly constant. Finally, the burning rate becomes about as sensitive to changes in pressure as it was at the low pressure. Significant advances have been made in improving solid propellant burning-rate characteristics by modification of the composition. The general purpose of the present invention is to blend lithium fluoride with an inorganic oxidizer, a polymeric fuel binder and a low molecular resin such as one of the condensation polymers of epichlorohydrin and bisphenol-A (sold under the tradename Epon 828) to form a rocket propellant composition exhibiting the plateau burning phenomenon.
It is therefore an object of this invention to provide a new propellant composition having a controlled burning rate.
Another object of this invention is to provide a propellant composition having improved physical properties.
Yet another object is to provide a propellant which will find use in rocket motors of simplified design.
Other objects, features and many of the attendant advantages of this invention will become easily appre- 3,156,594 Patented Nov. 10, 1964 ciated as the same become better understood by reference to the following description.
The example given herein is a typical formulation Whereinlithium fluoride apparently influences the burning rate.
Ingredients: Percent by weight Ammonium perchlorate Polybutyl acrylic acid terpolymer 20.4 Epichlorohydrin and bisphenol resin 3.6 Lithium fluoride (powder) 1 The oxidizer used above was made up of ammonium perchlorate of the following three particle sizes:
10 weight percent about 65;]. 50 weight percent about 93 weight percent about g The above ingredients were blended in a mixer until homogeniety resulted. The mixture was then cast into the desired configurations and cured for several days at about 130 F.
It is possible that the coarse ammonium perchlorate and a little lithium fluoride will change many composite propellant compositions to plateau-burning types.
Obviously many modifications and variations 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:
l. A propellant composition consisting essentially of the following ingredients:
Ammonium perchlorate Lithium fluoride Polybutyl acrylic acid terpolymer A resin consisting of a condensation product of epichlorohydrin and bisphenol A.
2. The composition of claim 1 wherein the ammonium perchlorate comprises a mixture of particle sizes of about 10 weight percent of 65 50 weight percent of 93 ,u. and about 90 weight percent of 130;.
3. A propellant composition consisting essentially of the following:
Ingredients: Percent by weight Ammonium perchlorate 75 Lithium fluoride 1 Polybutyl acrylic acid terpolymer 20.4 Resin consisting of epichlorohydrin and hisphenol 3.6
4. The composition of claim 3 wherein the ammonium perchlorate consists of particle sizes ranging from 63 1. to 1301i.
No references cited.

Claims (1)

1. A PROPELLANT COMPOSITION CONSISTING ESSENTIALLY OF THE FOLLOWING INGREDIENTS: AMMONIUM PERCHLORATE LITHIUM FLUORIDE POLYBUTYL ACRYLIC ACID TERPOLYMER A RESIN CONSISTING OF A CONDENSATION PRODUCT OF EPICHLOROHYDRIN AND BISPHENOL A.
US374214A 1964-06-10 1964-06-10 Polymeric base propellant compositions containing lithium fluoride catalyst Expired - Lifetime US3156594A (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3873385A (en) * 1968-03-11 1975-03-25 Kenneth Henrich Sodium fluoride ignition aid in solid propellant compositions
US3876477A (en) * 1965-09-15 1975-04-08 Us Navy Fluorocarbon solid propellant with burning rate modifier
DE4307731A1 (en) * 1992-03-11 1993-09-30 Poudres Et Explosifs Paris Soc Highly flammable gunpowder with low susceptibility to heat and impact

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (4)

* 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
US3873385A (en) * 1968-03-11 1975-03-25 Kenneth Henrich Sodium fluoride ignition aid in solid propellant compositions
DE4307731A1 (en) * 1992-03-11 1993-09-30 Poudres Et Explosifs Paris Soc Highly flammable gunpowder with low susceptibility to heat and impact
US5468312A (en) * 1992-03-11 1995-11-21 Societe Nationale Des Poudres Et Explosifs Ignition-sensitive low-vulnerability propellent powder

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