U.S. patent number 3,609,115 [Application Number 04/312,782] was granted by the patent office on 1971-09-28 for propellant binder.
This patent grant is currently assigned to North American Rockwell Corporation. Invention is credited to Liles G. Herring, George D. Sammons.
United States Patent |
3,609,115 |
Sammons , et al. |
September 28, 1971 |
PROPELLANT BINDER
Abstract
This invention relates to solid propellant formulations. More
particularly, it relates to a novel binder for utilization in such
solid propellants.
Inventors: |
Sammons; George D. (Waco,
TX), Herring; Liles G. (Waco, TX) |
Assignee: |
North American Rockwell
Corporation (N/A)
|
Family
ID: |
23212984 |
Appl.
No.: |
04/312,782 |
Filed: |
September 30, 1963 |
Current U.S.
Class: |
523/180;
149/19.1; 149/20; 149/88; 149/92; 524/260; 564/109; 149/19.6;
149/38; 149/89; 149/102; 524/259; 524/602; 564/111 |
Current CPC
Class: |
C08G
73/02 (20130101); C06B 45/10 (20130101) |
Current International
Class: |
C08G
73/00 (20060101); C08G 73/02 (20060101); C06B
45/10 (20060101); C06B 45/00 (20060101); C08f
045/44 (); C08g 051/44 () |
Field of
Search: |
;149/19,75
;260/75,85.7,83.5,2EP,29.1,30.6,31.4,31.6,31.8,32.4,33.2,78,78.4,80,583,584,836 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Sebastian; Leland A.
Claims
We claim:
1. Polymers having the backbone
, said polymer formed from the addition polymerization of monomers
having the formula:
wherein x is a whole integer from two to six and R is selected from
the class consisting of: ##SPC4##
wherein R' is selected from the class consisting of H and CH.sub.3
and R" is an alkylene radical of from one to five carbon atoms.
2. The polymers of claim 1 further polymerized with a compound
capable of entering into addition polymerization to cross-link said
polymers.
3. The polymer formed from the reaction of
1,2,14,15-diepoxy-4,12-dioxa-6,8,10-trinitrazapentadecane with
3,11-dioxa-5,7,9-trinitrazatridecane-1,13-diol.
4. The polymer formed from the reaction of
1,2,14,15-diepoxy-4,12-dioxa-6,8,10-trinitrazapentadecane with
3,11-dioxa-5,7,9-trinitrazatridecane-1,13-dicarboxyl.
5. The polymer formed from the reaction of
1,2,14,15-diepoxy-4,12-dioxa-6,8,10-trinitrazapentadecane with
3,11-dioxa-5,7,9-trinitrazatridecane-1,13-diol and maleic
anhydride.
6. The polymer formed from the reaction of
1,2,14,15-diepoxy-4,12-dioxa-6,8,10-trinitrazapentadecane with
3,11-dioxa-5,7,9-trinitrazatridecane-1,13-dioic acid and citric
acid.
7. The polymer of claim 5 wherein the ratio of
diol:anhydride:diepoxide is within the range 1:0.75-2:1-3.
8. The polymer of claim 6 wherein the ratio of dioic acid:citric
acid:diepoxide is 1:0.25-2:1-3.
9. The polymer formed from the reaction of
1,2,14,15-diepoxy-4,12-dioxa-6,8,10-trinitrazapentadecane with
citric acid.
10. A solid propellant binder composition comprising:
a polymer having the backbone
, said polymer formed from the addition polymerization of monomers
having the formula:
wherein x is a whole integer from two to six and R is selected from
the class consisting of: ##SPC5##
wherein R' is selected from the class consisting of H and CH.sub.3
and R" is an alkylene radical of from one to five carbon atoms,
a cross-linking agent for said polymer.
11. The binder of claim 10 additionally comprising:
a plasticizer in an amount up to 75 weight percent of the binder
composition.
12. The binder of claim 11 wherein said plasticizer is a
nitroplasticizer selected from the class consisting of:
bis-dinitropropylformal, bis-dinitropropylacetal, and
2,2-nitropropane.
Description
Solid propellants found in application today are divided into two
distinct categories; double-base propellants and composite
propellants. The distinction is based on the physical
characteristics of the propellants and their composition. Most
propellants contain a sufficient amount of oxygen such that upon
ignition they can be readily burned and converted to gaseous
product. Thus, without any additional source of oxygen a solid
propellant can sustain continuous burning producing a great amount
of pressure to be utilized in producing thrust.
In general, a double-base propellant contains as its principle
ingredient, nitrocellulose, and an explosive plasticizer normally
nitroglycerin. Double-base propellants can contain inert
plasticizers, stabilizers, ballistic modifiers and other high
energy materials which may, in fact, be highly explosive themself.
The composite propellants embrace a solid particulate oxidizer
material dispersed throughout a matrix of plastic or resinous-type
material. The matrix may provide the fuel for the combustion,
however, normally today a solid particulate fuel is dispersed
within the matrix. This fuel is normally a finely ground metal or
metal wire. The composite propellants are also known as hydrocarbon
systems because of the normally hydrocarbon binder material used.
The three types of binders previously used in these hydrocarbon
systems include polyurethane, polybutadiene-acrylic acid or PBAA
and more recent, carboxy-terminated linear polybutadiene. Use of
these binders, as well as the double-base system binders, often
introduces several problems.
Particularly concerned with the processing of the propellant, data
has indicated that double-base systems based on nitrocellulose and
high energy plasticizers such as trimethylolethanetrinitrate or
triethyleneglycoldinitrate with oxidizers such as ammonium
perchlorate, hydrazine nitroform or nitronium perchlorate and fuels
such as aluminum hydride can produce very high specific impulses.
However, in processing it is difficult to obtain the necessary
level of solids loading in the double-base system. That is, it is
often impossible to incorporate successfully the high percentages
of the solid particulate oxidizer and fuel necessary to produce the
theoretical impulse that could be derived from such a system.
Additionally, double-base systems are characterized by the extreme
sensitivity to impact. This results in a serious drawback in the
processing of such propellants due to the extreme danger in
handling.
With regard to the composite propellants, the presence of
polyurethane, polybutadiene acrylic acid or carboxy-terminated
linear polybutadiene binders require very high total solids loading
to achieve desired high impulse goals. However, the impact
sensitivity of the final propellant is much lower than that of the
double-base systems and thus processing from the sensitivity
standpoint is improved. Generally, though, the impulse to be
derived from the composite systems is lower than that obtained from
the double-base ones.
On the basis of performance, it is apparent that the highest
impulse is obtainable only with a double-base binder. There is
generally little difference among the hydrocarbon systems except
that higher solids loading is possible with the carboxy-terminated
linear polybutadiene binder. However, it is much more difficult to
achieve desired high impulse with the hydrocarbon binders. From a
safety point, the hydrocarbon binders appear to be considerably
superior to the double-base ones. Processing problems are normal
with the double-base binder but are more difficult with the
hydrocarbon ones due to the fact that the high total solids loading
is required to obtain high impulse.
Thus, it is an object of this invention to provide a novel
propellant binder system having high performance with regard to
specific impulse.
Another object of this invention is to provide a solid propellant
binder that has good safety for handling and processing.
A further object of the invention is to provide a new solid
propellant binder having ease of processing.
The above and other objects are accomplished by a binder system
based upon a linear polymethylenenitramine. The nitramine backbone
has the following formula which will be represented as Z:
it may appear from two to six times in the monomers utilized to
prepare the final polymeric product. It is preferred that it appear
three times in the monomer. The monomers that will form the
polymeric binder of this invention have the following general
formula:
Wherein x may vary from two to six and R is a functional group
capable of entering into cross-linking or polymerization. Thus, R
can be selected from the class consisting of: ##SPC1##
wherein R' is selected from the class consisting of H and CH.sub.3
and R" is an alkylene radical of from one to five carbon atoms.
Because of the preferred method of synthesis of the monomers, R is
normally a substituted alkoxy group. Thus, an ether linkage is
normally present connecting the terminal group to the backbone.
Additionally, an ester linkage can be formed instead of the ether
using a carboxy acid instead of an alcohol in the synthesis of the
monomers, however, this type of ester linkage is less desirable
than the ether one from the standpoint of hydrolytic stability. The
preferred terminal functional groups capable of chain extension and
polymerization which are present on the R's are the epoxy, carboxy
and hydroxy groups because of their case of cross-linking to form
good propellant binders. The number of carbon atoms in the R chain
should be kept generally to a minimum, preferably not more than
four though up to six may be usable. A resin having the minimum
number of carbon atoms is desired to produce a polymer having the
highest percentage of the nitramine backbone to give high energy.
The presence of the carbon atoms will tend to detract from this
desired property.
It is important in the formation of solid propellant binders that
in the polymerization reaction there be no condensation material
which must be removed from the propellant. As a result, the
particular terminal functional groups present must be ones which
are capable of entering into an addition-type polymerization so
that no byproducts such as water or the like are formed which would
deleteriously effect the propellant.
It is found that particularly good results are obtained when one of
the monomers that is reacted to form the polymeric binder of the
invention is a compound having epoxy terminal groups. The most
preferred monomer having the epoxide end groupings is
1,2,14,15-diepoxy-4,12-dioxa-6,8,10-trinitrazapentadecane having
the following formula:
This monomer may in turn be reacted with another monomer having the
nitramine backbone and having one of the functional groupings above
described such as carboxy or hydroxy and the like. It is preferred
to react the particular preferred diepoxide monomer with either an
acid anhydride such as maleic anhydride and
3,11-dioxa-5,7,9-trinitrazatridecane-1,13-diol or
3,11dioxa-5,7,9-trinitrazatridecane-1,13-dioc acid and a suitable
cross-linker such as citric acid.
The nitramine binders of this invention are particularly adapted to
propellant processing in that they are liquid at processing
temperatures before curing or polymerization. This provides for
their ease of casting. When combined with a nitroplasticizer,
particularly, the binders yield propellant that is castable, stable
(Class II) and has a high delivered impulse. For example, an
unmetallized propellant would have a delivered impulse of above 240
sec., with aluminum--above 245 sec., with beryllium--above 255
sec., with aluminum hydride--above 255 sec., and with beryllium
hydride--above 265 sec.
The starting material for the synthesis of the monomers is
hexamethylenetetramine or hexamine as it is commonly called. The
compound is commercially available in quantity. The first step in
the synthesis is to prepare the compound
1,7-diacetoxy-2,4,6-trinitrazaheptane called BSX. This is carried
out by nitrolysis according to the following reaction. ##SPC2##
The resultant compound, BSX, and the above method of preparation
are well known in the literature. BSX is then reacted with HCl to
form GSX.
like BSX, GSX and its method of preparation are well known in the
literature.
The chloro groups of GSX are very reactive because of activation by
the nitramine group. GSX reacts readily with hydroxy compounds,
splitting out hydrogen chloride and forming an ether. The
hydroxy-terminated monomer used in the invertion is synthesized by
reacting GSX with ethyleneglycol according to the following
reaction.
This above reaction and the compound called TNDO are known. The
carboxy-terminated monomers can be prepared by reacting GSX
ethylacetate as known in the literature.
The preparation of the desired epoxy-terminated monomers called
TNDE are formed by reacting GSX with glycidol according to the
following reaction. ##SPC3##
The detail synthesis of the diepoxide is as follows in Example
I.
EXAMPLE I
The starting material GSX must be free from organic contaminants
which it may pick up during its synthesis and metal autoclaves. One
recrystallization from ethylene dichloride is adequate if the hot
solution of GSX in ethylene dichloride is filtered through
diatomaceous earth before allowing the GSX to crystallize. An 18
-liter glass reactor was equipped with electric mantle, magnetic
stirrer, thermometer and gas outlet. The reactor was then charged
with the following.
2,387 grams GSX (recrystallized)
9,320 ml. glycidol
2,400 grams CaCO.sub.3 (low alkali)
1,200 grams MgSO.sub.4 (anhydrous)
4,000 ml. dioxane
The mixture was stirred and heated until the temperature reaches
60.degree. C. The temperature was then maintained between
60.degree. and 65.degree. C. by the use of heat or water bath as
necessary. An initial exotherm was experienced somewhere in the
vicinity of 60.degree. C. After 5 hours above 60.degree. C., the
reaction mixture was cooled to room temperature with an ice bath
and filtered immediately through diatomaceous earth. The clear
filtrate was then placed in a rotary evaporator, and the dioxane
removed at 65.degree. C. with a water aspirator. The majority of
the glycidol was then removed using the same apparatus but
evacuating to below 2 mm. with a vacuum pump. A total of 4,223
grams of glycidol was removed leaving a 7,067-gram residue. The
residue was diluted with 8 liters of ethylene dichloride, cooled in
a refrigerator overnight and then filtered. The filtrate was
washed, 2 liters at a time, with three 500 ml. portions of cold
water. The wet solution was placed in a rotary evaporator and the
ethylene dichloride removed with a water aspirator and a bath
temperature of 65.degree. C. The residue was then brought to a
weight loss of only 1.4 grams in two hours at 65.degree. C. and
less than 2 mm. vacuum. The product was completely colorless and
slightly milky at ambient temperature. The yield was 1,906 grams
with an epoxy equivalent of 304. The diepoxide is a mixture of
monomer and various polymers formed during the diepoxide synthesis.
The epoxy equivalent may vary from 141 to 400 by variation in
processing techniques.
The reaction of two nitramine monomers of this invention capable of
polymerizing produces a linear polymer. The same result can occur
by using a single nitramine monomer and reacting it with an agent
that is capable of chain extension. The agent would react with the
terminal groups of the nitramine monomer forming a linear polymer.
For utilization as solid propellant binders, it is generally
necessary that the linear polymers are cross-linked. Cross-linking
can be accomplished by utilization of additional compounds
containing three or more functional groups capable of entering into
the polymerization. The cross-linking produces a solid propellant
matrix having a higher tensile strength and better modulus of
elasticity and other improved physical properties. For example, the
diepoxide monomer can be reacted with citric acid. The diepoxide
monomer can be both extended linearly and cross-linked by the
addition of trifunctional compound citric acid. The percent of the
carboxy equivalents from the citric acid can be from 0 to 100
percent. Any of the monomers of the invention can be extended and
cross-linked by the addition of various known cross-linking
additives which are capable of reacting with the terminal groups
present on the nitramine monomers. Additionally, linear polymers
can be formed by the reaction of two of the nitramine monomers
having terminal groups capable of polymerization with each other.
The resultant linear polymers will generally only have one reactive
site on each end and cannot cross-link. As a result, to accomplish
such cross-linking, it is generally necessary to add an agent
capable of causing such a transpire.
When the preferred diepoxide monomer is reacted with a
dicarboxy-terminated monomer, citric acid may be used as a
cross-linking agent. Other cross-linking agents include:
1,2,3,4-butane tetracarboxylic acid, trimesic acid, trimellitic
acid and 1,2,3-propane tricarboxylic acid. It should be apparent
that not all of the above cross-linking agents are compatible with
all the nitramine monomers of the invention. The method of
selecting the proper cross-linker is well within the skill of the
art. As the selection of appropriate nitramine monomers, the choice
of a cross-linking agent is based on ones that can react with the
terminal functional group of the nitramine monomers forming an
addition-type polymer.
The proportion of the three ingredients is dependent on the end
functional groups of each. It is desirable that substantially all
of the end functional groups are reacted. For example, the ratio of
epoxy to carboxy equivalents would for most practical formulations
be from 1:1 to 4:1. The amount of cross-linker present can be from
0 to 100 percent of total carboxy equivalents present depending on
properties desired.
When the preferred diepoxide is used with a nitramine diol and an
anhydride, maleic anhydride being preferred, a cross-linked polymer
is formed. The anhydride reacts with the diol to form a dicarboxy
acid which then reacts with the diepoxide. This polymerization
would give only a linear polymer except that when the ester linkage
is made, a hydroxy group is produced which can react with excess
anhydride to form a carboxy group along the chain for a
cross-linking site. Other usable anhydrides include: phthalic
anhydride, hexahydrophthalic anhydride, succinic anhydride and
glutaric anhydride.
It should be apparent that not all of the above anhydrides are
compatible with all the nitramine monomers of the invention. The
method of selecting the proper anhydride is well within the skill
of the art. This anhydride must primarily be an anhydride of a
dicarboxy acid. The proportion of the three ingredients is
dependent on the end functional groups of each. It is desirable
that substantially all of the end functional groups are reacted.
For example, the ratio of equivalents of diol: maleic anhydride:
diepoxide are 1:0.75-2:1-3 for the most practical formulations.
The metal fuel may constitute 0.2 to 32 weight percent propellant
grain of this invention, preferably is one or more of the metals of
Groups I-A, II-A, III-A and Groups I-B through VII-B, and Group
VIII of the Periodic Table. Thus, the metal may be Group I-A
elements such as lithium, and Group II-A metals such as beryllium
or magnesium. Illustrative of the Group III-A metals is aluminum.
The metals of Group I-B through VII-B include copper, silver, zinc,
cadmium, titanium, zirconium, vanadium, niobium, chromium,
molybdenum, tungsten, manganese, iron, cobalt, nickel, ruthenium,
rhodium, osmium, palladium, and platinum. Additionally, hydrides of
the metals such as beryllium hydride and aluminum hydride are
contemplated.
To aid in the processing of the propellant, it is often advisable
to employ plasticizers in the preparation and utilization of the
polymeric and plastimeric materials employed in the invention. The
plasticizers can be up to 75 percent by weight of the binder
composition. It is preferred that energetic plasticizers be used
with the polymers of this invention to give higher impulse. Such
preferred ones include the nitroplasticizers such as
bis-dinitropropylformal, bis-dinitroproplyacetal, and 2,2-nitro
propane. Other plasticizers may be of the general type of inert and
explosive plasticizers. Examples of inert plasticizers include
triacetin, the various phthalates such as diethyl phthalate,
dibutyl phthalate, dioctyl phthalate, di-(methoxyethyl) phthalate,
methyl phthalyl ethyl glycolate, ethyl phthalyl ethyl glycolate and
butyl phthalyl butyl glycolate, sebacates such as dibutyl and
dioctyl sebacates, adipates such as dioctyl adipate and
di(3,5,5-trimethylhexyl)adipate, glycol esters of higher fatty
acids, organic phosphate esters such as tributoxyethyl phosphate,
and the like. The explosive plasticizers include nitroglycerin,
butane triol trinitrate, diglycol dinitrate, ethylene glycol
dinitrate, and the like.
The solids oxidizing agents utilized can be compounds such as metal
perchlorates and metal nitrates. The metal perchlorates employed as
oxidizing agents or oxygen carriers in the compositions are
anhydrous and have the general formula M(ClO.sub.4) , wherein M is
NH.sub.4 or a metal and x is the valence of M. Since the propellant
composition is required to withstand high-temperature storage, it
is preferable that the melting point and the decomposition
temperatures of the oxidizer be as high as possible. The
perchlorates of the Group I-A, Group I-B, and Group II-A metals are
found to have the required high-temperature stability and are
employed in the preparation of propellant compositions by the
process of this invention. Hence, the metal perchlorates used in
the preparation of the propellant compositions include lithium
perchlorate, sodium perchlorate, potassium perchlorate, rubidium
perchlorate, and cesium perchlorate which are the perchlorates of
the metals of Group I-A of the Periodic Table of Elements; silver
perchlorate which is a perchlorate of the Group I-B metal; and
magnesium perchlorate, calcium perchlorate, strontium perchlorate,
and barium perchlorate which are the perchlorates of the Group II-A
metals. In addition to the metal perchlorates, the compounds
ammonium perchlorate and nitronium perchlorate find extensive use
in propellant compositions. Examples of the nitrates of the Group
I-A, and I-B and II-B which are employed in preparing propellant
compositions by the process of this invention are compounds such as
lithium nitrate, sodium nitrate, potassium nitrate, magnesium
nitrate, calcium nitrate, barium nitrate, strontium nitrate, etc.
Ammonium nitrate is also used. The amount of oxidizer present falls
within the range of 25 to 80 weight percent of the propellant
composition.
The ratio of total solids-to-polymeric binder material in a
propellant falls in the range of from about 1:1 to about 9:1 with
an optimum ratio of about 7:3.
Other substances which are employed in the preparation of
propellants by the process of this invention include minor amounts
of burning catalysts, well known in propellant compositions. These
are composed of one or a mixture of two or more metal oxide powders
in amounts sufficient to improve the burning rate of the
composition. The amounts usually range from about 0.01 to about 3
weight percent, based on the weight of the oxidizer employed. The
particle size of the powders can range from about 10 to about 250
microns in diameter. Nonlimiting examples of metals that serve as
burning catalysts are copper, vanadium, chromium, silver,
molybdenum, zirconium, antimony, manganese, iron, cobalt, and
nickel. Examples of metal oxide burning catalysts are ferric oxide,
aluminum, copper oxide, chromic oxide, as well as the oxides of
other metals mentioned above.
Burning rate depressants and modifiers are also sometimes
advantageously added to the solid propellant grain of this
invention. These are generally compounds added in the amounts of
0.05 to 5 weight percent of the propellant composition. These
compounds tend to inhibit burning reaction rates or absorb heat and
include specifically carbonyl chloride, oximide, nitroguanidine,
guanidine nitrate, and oxalic acid.
Curing catalysts are often added in minor amounts to cure the
polymer in the performance of the process of this invention.
Nonlimiting examples of catalysts used for this purpose are
aluminum chloride, tristrimethylsilyl borate, benzoyl peroxide, and
other catalysts well known in the curing of plastics, resin,
polymers, and rubbers. Examples of various catalysts may be found
in text books such as "Synthetic Rubber," by G. S. Whitley, pp.
892-933, 1954 Ed., published by John Wiley and Sons, Inc., New
York. The curing catalysts are added in amounts of from 0.1 to
about 10 weight percent based on the weight of the polymer, resin
or elastomer. The particular catalyst and amount employed depend on
the state of cure desired and the nature of the polymeric material
employed in the composition.
The following example indicates the preparation of a propellant
formulation utilizing the polymeric binder of this invention.
EXAMPLE II
The following constituents were utilized to form the propellant
grain.
---------------------------------------------------------------------------
Binder Grams
__________________________________________________________________________
TNDE 38.90 Maleic anhydride 4.78 TNDO 13.48 BDNPF-BDNPA 40.30
__________________________________________________________________________
(mixture 50 percent: 50 percent of bis-dinitropropylformal:
bis-dinitropropyl acetal)
Oxidizer Grams Ammonium perchlorate 149.3 Aluminum 78.0
__________________________________________________________________________
All of the binder ingredients are placed in a vertical or
horizontal mixer such as the Baker-Perkins mixer which has been
previously heated to 150.degree.-175.degree. F. The binder
ingredients were then mixed for a period of time sufficient to wet
all the ingredients. Vacuum is then placed on the mixer and mixing
is continued for 20 minutes. At this point, the mix was very fluid
and transparent. The aluminum powder is then added and mixed until
wet. Vacuum was then placed on the mixer and mixing was continued
for about 2 minutes until the aluminum was thoroughly dispersed.
The mixer was then stopped and the oxidizer was added in three
equal increments. After each of the first two increments, the
ingredients were mixed for 10 minutes under vacuum. After the last
increment of oxidizer was added, the final ingredients were mixed
for 30 minutes under vacuum. The mixer is then finally stopped and
the ingredients are ready for pouring into a mold to be cast. The
propellant mixed is poured into a mold and cured at atmospheric
pressure at 24 to 120 hours at 120.degree. F.
EXAMPLE III
The process of manufacturing propellant as set forth in above
example II was repeated, utilizing the following formulation. The
only difference from the process of example II was between 20 and
50 p.s.i.g. pressure was used when curing the material.
---------------------------------------------------------------------------
Propellant LCH-35 Percent Grams TNDE 11.27 225.6 TNDA 4.10 82.0
Citric acid 0.33 6.4 Diethylene glycol dinitrate 14.17 283.4
Resorcinol 0.13 2.6 Ammonium perchlorate 68.00 1359.00 Aluminum
2.00 40.00
__________________________________________________________________________
In this example it is noted that nitrate ester plasticizer was
used. The plasticizer was stabilized with the presence of a small
amount of resorcinol.
EXAMPLE IV
A more preferred propellent formulation due to physical properties
of cured propellant is shown below. It was prepared in accord with
the procedure of example II.
---------------------------------------------------------------------------
propellant CLH-43-1 Percent Grams TNDE 13.42 402.6 Citric acid 2.28
68.4 Petrin (plasticizer pentaerythritol) 14.00 420.0 Ethyl
centralite (stabilizer for plasticizer) 0.30 9.0 Ammonium
perchlorate 46.0 1380.0 Aluminum 24.0 720.0
__________________________________________________________________________
Several 2-inch and 6-inch rocket motors were made utilizing the
formulations set forth in the previous examples as well as varying
the relative proportion of the constituents so as to obtain range
of properties for the grains. Typical properties obtained from the
formulation tested follow:
---------------------------------------------------------------------------
Mechanical Properties Elongation, e.sub.m, percent 11-37 Tensile
Strength, s.sub.m, p.s.i. 95-260 Modulus E, p.s.i. 520-3400
Density, lb.-cu.-in. 0.063-0.068 Impact Sensitivity, in.-lb. 13-32
Burning Rate, in.-sec.
500 p.s.i.a. 0.178-0.266 1000 p.s.i.a. 0.229-0.351 Pressure
Exponent, n 0.34-0.40
__________________________________________________________________________
Although the invention has been described and illustrated in
detail, it is to be clearly understood that the same is by way of
illustration and example only and is not to be taken by way of
limitation, the spirit and scope of this invention being limited
only by the terms of the appended claims.
* * * * *