U.S. patent number 3,876,477 [Application Number 04/491,496] was granted by the patent office on 1975-04-08 for fluorocarbon solid propellant with burning rate modifier.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to Robert L. Dow, Judson B. Eldridge, Elmo C. Julian, George B. Rice.
United States Patent |
3,876,477 |
Eldridge , et al. |
April 8, 1975 |
Fluorocarbon solid propellant with burning rate modifier
Abstract
Solid fluorocarbon propellant compositions containing burning
rate modifi which have high structural integrity and a long storage
life under varying environmental conditions.
Inventors: |
Eldridge; Judson B. (China
Lake, CA), Julian; Elmo C. (Cincinnati, OH), Dow; Robert
L. (China Lake, CA), Rice; George B. (Ibapah, UT) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (Washington,
DC)
|
Family
ID: |
23952476 |
Appl.
No.: |
04/491,496 |
Filed: |
September 15, 1965 |
Current U.S.
Class: |
149/19.3; 149/20;
149/40; 149/44; 228/178; 228/248.1 |
Current CPC
Class: |
C06B
23/007 (20130101); C06B 45/10 (20130101) |
Current International
Class: |
C06B
45/00 (20060101); C06B 23/00 (20060101); C06B
45/10 (20060101); C06d 005/06 () |
Field of
Search: |
;149/19,19.3,20,44,40 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Padgett; Benjamin R.
Assistant Examiner: Miller; E. A.
Attorney, Agent or Firm: Sciascia; R. S. Miller; Roy
Claims
1. A solid propellant composition consisting essentially of the
following:
2. A solid propellant composition consisting essentially of the
following:
3. A solid propellant composition consisting essentially of the
following:
4. A solid propellant composition consisting essentially of the
following:
5. A solid propellant composition consisting essentially of the
following:
6. A solid propellant composition consisting essentially of the
following:
Description
The invention described herein may be manufactured and used by or
for the Government of the U.S.A. for governmental purposes without
the payment of any royalties thereon or therefor.
The present invention relates to improved solid propellants. A
specific aspect relates to solid fluorocarbon propellants
containing burning rate modifiers.
The fluorocarbon family of polymers has developed as excellent
binders for composite solid propellants. 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 possess many
desirable properties for propellant compositions. The propellants
prepared with these binders have high structural integrity, long
storage life, and good physical properties. The present invention
provides a composition with increased burning rates, low pressure
exponent or low temperature coefficient.
It is therefore an object of the present invention to provide a
propellant with an improved burning rate for use in rocket motors
and similar vehicles.
Another object is to provide a propellant with exceptionally high
structural integrity and a long storage life under varying
environmental conditions.
Yet another object is to provide an improved propellant composition
which can be produced in large volumes at low cost.
Other objects and many attendant advantages of this invention will
be readily appreciated as the same become better understood from
the following description:
According to the present invention there is provided a propellant
comprising up to 60 percent by weight of an oxidizer from 5 to 65
percent by weight of a binder consisting of a mixture of
fluorocarbon polymers; up to 30 percent by weight metal fuel; and
from 1 to 3 percent by weight chemical modifiers.
The oxidants which are applicable to the solid propellant of this
invention are those oxygen-containing solids which readily give up
oxygen and include ammonium, alkali metal and alkaline earth metal
salts of nitric, perchloric, and chloric acids, and mixtures
thereof. Ammonium perchlorate, potassium perchlorate, ammonium
nitrate and hydrazine diperchlorate are preferred oxidizers for
this invention.
The fluorocarbon polymers used in the composition consist of
polytetrafluoroethylene (hereinafter referred to as Teflon) and a
copolymer of vinylidene fluoride and hexafluoropropylene
(hereinafter referred to as Viton-A) and mixtures thereof.
The high energy fuels preferred are aluminum, magnesium, zirconium,
uranium, thorium, beryllium and mixtures thereof. These metals will
usually have a particle size within the ranges of 1 to 100
microns.
The chemical modifiers preferred for the present composition
consist of copper, lead, tin, sodium, ammonium and potassium
fluoborates; sodium, potassium, lithium, lead, copper, and calcium
fluorides; potassium and ammonium dichromate; lead and zinc
stearate; cesium carbonate; potassium and ammonium sulfate; copper
chromite; oxides of magnesium, copper and manganese; boron; zinc
dust; and carbon black.
One convenient method, and the presently preferred method, of
preparing this composition comprises, first, dissolving the Viton-A
in a solvent selected from a low-boiling ketone; acetone was used.
The Teflon and other ingredients (fuel, oxidizer and modifier) were
then thoroughly mixed into the Viton-A solution to form a uniform
slurry or suspension. The slurry was washed for from 5 to 10
minutes with hexane, the volume of hexane being from 1 to 4 times
the volume of slurry. By this step the Viton precipitates onto the
other solids in the slurry. After the suspension had settled, the
supernatant hexane was decanted and the resulting residue was dried
under ambient conditions for from 8 to 24 hours. The slurry may be
washed with normal hexane 2 or 3 times, as necessary.
A general formulation for a propellant composition prepared in
accordance with the invention is as follows:
Ingredients Percent by weight
______________________________________ Binder 5 to 65 Viton-A 10 to
15 Teflon 5 to 50 Oxidizer up to 65 Metal Fuel up to 35 Chemical
modifier 1 to 3 ______________________________________
The following examples will serve to further illustrate the
invention.
EXAMPLE I ______________________________________ Ingredients % by
weight Function ______________________________________ Teflon 25
Binder Viton-A 15 Binder Aluminum 20 Fuel Potassium perchlorate 35
Oxidizer Sodium fluoride 2.5 Chemical modifier Potassium dichromate
2.5 Chemical modifier ______________________________________
The above ingredients were processed by the shock-gel technique
described hereinbefore. The Viton is available in acetone solution
for which an assay should be available. The solution should contain
a minimum of 8 and a maximum of 22 weight percent Viton. All of the
ingredients are added to a slurry pot. A volume of hexane equal to
4 times the volume of the Viton solution is placed in a container.
While stirring the slurry, hexane is added slowly and mixing
continues for about 15 minutes. The Viton is precipitated or
shock-gelled onto the solids in the slurry. The supernatant hexane
is siphoned off and an additional volume of fresh hexane, equal to
the first volume, is added. Again, the supernatant hexane is
siphoned off and the resulting composition is collected in a cloth
bag and dried in a drying oven for from 8 to 24 hours at
approximately 140.degree. F. Some of the material was extruded into
strands for burning tests. This composition showed a burning rate
at 1000 psi of 0.298-inch per second and a pressure exponent of
0.61.
EXAMPLE II ______________________________________ Ingredients
percent by weight Function ______________________________________
Teflon 15 Binder Viton-A 15 Binder Aluminum 25 Fuel Potassium
perchlorate 43 Oxidizer Sodium fluoride 2 Modifier
______________________________________
The Viton-A is dissolved in acetone. To this solution the Teflon,
aluminum, potassium perchlorate and sodium fluoride were added and
mixed for about 10 minutes forming a slurry. The slurry was washed
with hexane (4 volumes of hexane to 1 volume of Viton solution) for
10 minutes. The resulting mixture was let settle and hexane was
siphoned off. The residue was washed with an additional volume of
hexane for about 5 minutes. The supernatant hexane was again
siphoned off, the composition collected in a cloth bag and dried.
This material extrudes well. It showed a burning rate at 2000 psia
of 0.63 inch per second and a pressure exponent of 0.53.
EXAMPLE III
The following three samples (a, b and c) using 300 grams each of
the product prepared in Example II were modified with boron and
copper chromite:
(a) Ingredients Weight in grams
______________________________________ Composition of Example II
300 Boron 6 ______________________________________
About 300 grams of the cured composition prepared in Example II
were placed in a small sigma-blade mixer. The boron was suspended
in about 100 ml of hexane, then poured into the mixer and
thoroughly stirred for about 10 minutes. The product was
transferred to a stainless steel container and dried overnight.
Strands were extruded for burn rate determination.
______________________________________ (b) Ingredients Weight in
grams ______________________________________ Composition of Example
II 300 Copper chromite 6 ______________________________________
The above ingredients were processed in the same manner as
described in (a) above.
______________________________________ (c) Ingredients Weight in
grams ______________________________________ Composition of Example
II 300 Boron 3 Copper chromite 3
______________________________________
The boron and copper chromite were stirred into hexane, and the
process proceeded as described hereinabove. Burn strands were
extruded for burning rate determination.
Burning rate results for these three compositions are as
follows:
(a) .98 in/sec; pressure exponent .68 (b) .68 in/sec; pressure
exponent .60 (c) .81 in/sec; pressure exponent .62
EXAMPLE IV ______________________________________ Ingredients
Percent by weight Function ______________________________________
Teflon 16.3 Binder Viton-A 16.3 Binder Potassium perchlorate 65.2
Oxidizer Sodium fluoride 2.2 Chemical modifier
______________________________________
The Viton was dissolved in acetone and all the ingredients were
stirred therein for about 10 minutes forming a slurry or
suspension. The suspension was dropped into rapidly agitated hexane
and stirred for 10 minutes. (About 4 volumes of hexane to one of
Viton solution). After letting the composition settle out, the
hexane was siphoned off. The composition was washed again with
hexane which was decanted and the material was collected and dried.
Some of this composition was extruded for burn rate
determination.
EXAMPLE V ______________________________________ Ingredients
Percent by weight Function ______________________________________
Viton-A 15 Binder Teflon 15 Binder Potassium perchlorate 49
Oxidizer Aluminum 18 Fuel Zinc(dust) 2 Modifier Sodium fluoride 1
Modifier ______________________________________
These ingredients were processed as those in the previous examples.
Burn strands formed from this composition showed a burning rate at
2000 psi of 0.74 inch per second and a pressure exponent of
0.77.
EXAMPLE VI ______________________________________ Ingredients
Percent by weight Function ______________________________________
Viton-A 15 Binder Teflon 15 Binder Potassium perchlorate 49
Oxidizer Aluminum 18 Fuel Cupric oxide 2 Modifier Sodium fluoride 1
Modifier ______________________________________
Strands of this composition gave a burning rate at 2000 psi of 0.68
inch per second and a pressure exponent of 0.82.
EXAMPLE VII ______________________________________ Ingredients
Percent by weight Function ______________________________________
Viton-A 15 Binder Teflon 15 Binder Ammonium perchlorate 49 Oxidizer
Aluminum 18 Fuel Lead 2 Modifier Sodium fluoride 1 Modifier
______________________________________
Strands were extruded of this composition which gave a burning rate
at 2000 psi of 0.76 inch per second and a pressure exponent of
0.78.
EXAMPLE VIII ______________________________________ Ingredients
Percent by weight Function ______________________________________
Teflon 51 Binder Viton-A 15 Binder Magnesium 31 Fuel Cupric
fluoride 3 Modifier ______________________________________
The ingredients were processed in accordance with the prior samples
and strands were extruded for burning rate determination.
EXAMPLE IX ______________________________________ Ingredients
Percent by weight Function ______________________________________
Viton-A 14.7 Binder Teflon 4.9 Binder Zirconium 36.9 Fuel Ammonium
perchlorate 41.5 Oxidizer Magnesium oxide 2.0 Modifier
______________________________________
The same basic ingredients consisting of Viton, Teflon, Zirconium,
and ammonium perchlorate used in this sample were modified with 2`%
by weight each of the member selected from manganese dioxide,
cellulose acetate, dibutyl tin maleate, potassium sulfate,
potassium dichromate, lithium fluoride, lead fluoride, and
potassium acid tartrate. These modified fluorocarbon compositions
were all extruded into strands and the burning rate determination
were made.
EXAMPLE X ______________________________________ Ingredients Weight
in grams ______________________________________ Composition of
Example II 300 Copper fluoroborate 8
______________________________________
Since the fluoroborate used herein is hygroscopic, it is mixed into
the basic formulation immediately prior to extrusion. Strands were
extruded and burned with double dipped Viton inhibitor.
The above examples clearly demonstrate the effectiveness of the
chemical modifiers on the fluorocarbon propellants which have great
potential in the missile field today.
As will be evident to those skilled in the art various other
modifications of the invention can be made, or followed, in view of
the above disclosure, without departing from the spirit or scope of
the invention.
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