Explosive and thermic compositions or charges – Processes of making
Reexamination Certificate
1999-09-02
2001-02-06
Jordan, Charles T. (Department: 3641)
Explosive and thermic compositions or charges
Processes of making
C149S019200, C264S003100
Reexamination Certificate
active
06183574
ABSTRACT:
BACKGROUND OF THE INVENTION
Bismuth compounds have been used extensively as cure catalysts for isocyanate cured hydroxy terminated propellant binder systems. The most widely used of these bismuth compounds is triphenylbismuth (TPB). Triphenylbismuth is used in very small quantities, usually less than 0.03 percent by weight in the propellant formulation. There are no ballistics additive effects gained when this small amount is used.
Two bismuth compounds, bismuth salicylate(BS) and bismuth &bgr;-resorcylate(B&bgr;-R), have been identified to be effective as ballistic modifiers in minimum signature propellants(see Table I). These compounds are the salts of their corresponding organic acids, salicylic and &bgr;-resorcylic acids, respectively (see Table II). The ballistic modification properties of these bismuth compounds in minimum signature propellants were determined to be comparable to results obtained with similar lead compounds, lead salicylate and lead &bgr;-resorcylate. Lead salicylate and lead &bgr;-resorcylate are widely used as ballistic modifiers in some minimum signature Army tactical missile propellants.
Because of the toxic properties of lead compounds, Environmental Protection Agency requirements to eliminate lead from Army propulsion systems have fueled research activities to find alternatives. Bismuth compounds were evaluated as replacements for lead. Initial results were promising. The ballistic properties of the bismuth compounds in similar propellant formulations were comparable to lead compounds. However, researchers suspected and later confirmed that the bismuth compounds would cause a significant decrease in propellant potlife by prematurely catalyzing the propellant hydroxy/isocyanate cure reaction. Because of the significant reduction in propellant potlife caused by the bismuth compounds, research evaluating bismuth compounds as replacements was quickly curtailed.
Bismuth compounds tend to reduce the potlife of propellants to less than 1-hour, when used in quantities in excess of one tenth percent by weight in propellant formulations. A desirable potlife for castable solid propellants is 4-10 hours. Potlife can be defined as the time it takes for the viscosity of the propellant to increase to forty kilopoise(kp) after the addition of the curing agent. A viscosity of forty kp is generally considered the maximum where proper casting or loading of the propellant into motors can be achieved. Proper casting occurs when no voids or unfilled spaces are created in the propellant due to air being present during the cure reaction. These void formations are undesirable because they cause ballistic and/or mechanical anomalies.
Table I, Table II, and Table III, all set forth hereinbelow, show typical minimum signature propellant formulation, bismuth ballistic modifiers, and general propellant mixing procedure for minimum signature propellants, respectively. The typical mixing procedure (see Table III) used in formulating minimum signature propellants is to add all liquids, and then all the solids in increments. The mixture is then mixed at 150° F. under vacuum, for some set period of time to rid the mixture of any volatile components. The mixture is then cooled to 90-100° F., before the curing agent is added. When bismuth compounds are added at Step 2, the maximum potlife is less than 1-hour. Sometimes the mixture cures during the first 10-minutes after Step 6. With ballistic modifier addition at Step 2, cooling the mixture to less than 70° F. only slightly increased the potlife to approximately 1-hour. Eliminating the dibutyltin cure catalyst in step 6 only increased the potlife to nearly 2-hours. When the addition of the bismuth was delayed until Step 4, only an additional slight improvement in the potlife to less than 3-hours was achieved. By reviewing these tables one should more fully appreciate the novelty of the improved processing procedure set forth later in Table IV.
TABLE I
Typical Minimum Signature Propellant Formulation
Ingredients
% by weight
POLYMER
7.50
BTTN
16.41
TMETN
7.03
OXIDIZER
62.75
MNA
0.50
CARBON
0.50
Ballistic additive
4.00
N100
1.31
Total
100.00
NOTE: OXIDIZER(S) = RDX,HMX, AMMONIUM NITRATE
CATALYSTS = BISMUTH COMPOUNDS, ZrC
POLYMER(S) = ORP-2,PGA, CAPROLACTONES, etc.
TABLE II
Bismuth ballistic modifiers
Salicylic acid,
C
7
H
6
O
3
Bismuth salicylate,
C
7
H
5
O
3
Bi
&bgr;-Resorcylic acid,
C
7
H
6
O
4
Bismuth &bgr;-Resorcylate,
C
7
H
5
O
4
Bi
TABLE III
General Propellant mixing procedure for
minimum signature propellants
Step 1.
Weigh polymer, plasticizer(s), carbon,
add to mixer(preheated to 150° F.)
Step 2.
Add oxidizer(s), ballistic modifiers(bismuth, ZrC)
Step 3.
Mix under vacuum at 150° F. for 2-hours
Step 4.
Cool to 90-100° F.
Step 5.
Add MNA
Step 6.
Add curing agent, cure catalyst,
Mix additional 20 minutes
Step 7.
Cast in container(s)
Step 8.
Place in cure oven @ 140° F. for 7 days
Step 9.
Tests/evaluations
An object of this invention is to provide a procedure for processing isocyanate cured minimum signature propellants containing bismuth compounds as ballistic additives that will result in an adequate potlife for casting propellants into the desired missile configurations. When the proper processing procedure is used, adequate propellant potlife is achieved.
SUMMARY OF INVENTION
Bismuth compounds, such as bismuth salicylate and bismuth &bgr;-resorcylate, can be used as ballistic modifiers in isocyanate cured hydroxy-terminated propellant binder systems when the processing procedure is changed to delay the catalytic effects of the bismuth on the binder/cure agent reaction. Thus, the mixing procedure set forth in Table IV below depicts the preferred embodiment for obtaining a potlife of greater than 15 hours.
REFERENCES:
patent: 4379903 (1983-04-01), Reed, Jr. et al.
patent: 4389263 (1983-06-01), Allen
patent: 4517035 (1985-05-01), Duchesne et al.
patent: 4597811 (1986-07-01), Ducote
patent: 4775432 (1988-10-01), Kolonko et al.
patent: 4803019 (1989-02-01), Graham et al.
patent: 4915755 (1990-04-01), Kim
patent: 5031539 (1991-07-01), Hutchens
patent: 5398612 (1995-03-01), Graham et al.
patent: 5468313 (1995-11-01), Wallace, II et al.
patent: 5500061 (1996-03-01), Warren et al.
patent: 5639987 (1997-06-01), Berteleau et al.
Bush Freddie M.
Jordan Charles T.
Sanchez Glenda L.
The United States of America as represented by the Secretary of
Tischer Arthur H.
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