USH717H - High burn rate ammonium perchlorate propellant - Google Patents

High burn rate ammonium perchlorate propellant Download PDF

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Publication number
USH717H
USH717H US07/243,539 US24353988A USH717H US H717 H USH717 H US H717H US 24353988 A US24353988 A US 24353988A US H717 H USH717 H US H717H
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United States
Prior art keywords
weight percent
tbd
amount
solid propellant
catocene
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Abandoned
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US07/243,539
Inventor
William D. Stephens
Larry C. Warren
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US Department of Army
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US Department of Army
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Priority to US07/243,539 priority Critical patent/USH717H/en
Assigned to UNITED STATES OF AMERICA, THE, AS REPRESENTED BY THE SECRETARY OF THE ARMY reassignment UNITED STATES OF AMERICA, THE, AS REPRESENTED BY THE SECRETARY OF THE ARMY ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: STEPHENS, WILLIAM D., WARREN, LARRY C.
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Publication of USH717H publication Critical patent/USH717H/en
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    • 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
    • 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

Definitions

  • Hycat 6D bis(ethyldicyclopentadienyliron)methane, registered under Trademark Hycat 6D.
  • Hycat 6D migrated readily within the solid propellant producing unsatisfactory propellant properties.
  • Hycat 6D has a total of six alpha hydrogens (hydrogen adjacent to aromatic ring). It is known that hydrogens adjacent to aromatic ring systems are susceptible to oxidation to form acids and/or hydroperoxides. Hydroperoxides are known to be highly unstable compounds.
  • Catocene Since the alpha hydrogens were believed to be the reason for long term oxidation problems, Catocene was developed by coupling two ethylferrocenes with acetone, thus replacing the two bridged hydrogens with two methyl groups. Catocene then became the choice as a burn rate accelerator for ammonium perchlorate-based propellants. By replacing the two bridged hydrogens with methyl groups, long term oxidation and migration problems were reduced. However, accidental ignitions of solid propellants containing Catocene have occurred in both freshly prepared and aged propellants.
  • an object of this invention is to provide a solid propellant composition which employs a dicyclopentadienyliron compound as a burn rate enhancer while retaining improved safety characteristics for the propellant formulation as compared with Catocene employed in a similar propellant formulation.
  • the solid propellant formulation of this invention employing 2,2-bis(t-butyldicylopentadienyliron)propane (TBD) as the burn rate enhancer yields higher threshold values for ignition by impact and improved friction and spark testing values to thereby render the solid propellant formulation less hazardous to personnel during handling.
  • TBD solid propellant formulations also give improved results of the desired pressure exponent, potlife, and maximum stress characteristics when compared to similar solid propellant formulation containing Catocene.
  • the improved solid propellant composition having the properties described above is comprised of TBD as a burn rate enhancer in amounts from about 2 to about 6 weight percent, of about 68 weight percent of ammonium perchlorate of a trimodel blend of 200, 1.7, and 0.7 micron particle size, of aluminum powder of about 18 weight percent of a burner of hydroxyterminated polybutadience of about 9 weight percent, of an isocyanate curing agent as an additive of about 1 weight percent, and solid propellant processing aids in trace amounts.
  • the solid propellant composition set forth below under Example illustrates the use of TBD as a burning rate enhancer with the formulation ingredients in weight percent.
  • This formulation in above Example is mixed, cast, and cured by techniques and methods that are commonly used in the industry and that are known by personnel skilled in the art of propellant formulations.
  • this solid propellant formulation is applicable to any program where there is a need for high burn rates and improved safety characteristics.
  • Hycat 6D was a good burn rate enhancer, but was susceptible to long term oxidation. Hycat 6D also yielded poor results with respect to migration properties. Hycat 6D has a total of six alpha hydrogens (hydrogen adjacent to aromatic ring). It is believed that hydrogens adjacent to aromatic ring systems are suscepticle to oxidation to form acids and/or hydroperoxides. Hydroperoxides are known to be highly unstable compounds.
  • Catocene was the next compound developed which showed early promise of meeting the burn rate enhancer requirement; however, it too had problems related to stability in spite of replacing two bridged hydrogens with two methyl groups as discussed below.
  • Catocene Since the alpha hydrogens were believed to be the reason for long term oxidation problems, Catocene was developed by coupling two ethyferrocenes with acetone, thus replacing the two bridged hydrogens with two methyl groups. Catocene became a choice as a burn rate accelerator for ammonium perchlorate-based propellants. By replacing the two bridged hydrogens with methyl groups, long term oxidation and migration problems were reduced. However, accidental ignitions of propellants containing Catocene have occurred in both freshly prepared and aged propellants. Hence, the need for TBD was established.
  • TBD The purpose of the work relating to TBD is to synthesize a compound that has no alpha hydrogens. TBD does not have hydrogens on carbon adjacent to the aromatic ring structure; therefore, long term oxidation and reduced problem of migration are among the benefits derived. TBD was synthesized and a propellant mix was evaluated and compared to a similar mix containing Catocene. ##STR1##

Abstract

A solid propellant composition employing 2,2-bis(t-butyldicyclopentadienyon)propane (TBD) as the burn rate enhancer in a weight percent from about 2 to about 6 weight percent yields higher threshold values for ignition by impact and improved friction and spark testing values to thereby render the solid propellant composition less hazardous to personnel during handling as compared to similar solid propellant compositions containing Catocene, (2,2-bis(ethyldicylopentadienyliron)propane). The TBD solid propellant composition also comprises from about 9 to about 10 weight percent of hydroxyterminated polybutadiene binder system including an isocyanate curative added in amount of up to 1.0 weight percent and optional modifiers in small amounts with adjustment of the weight percent of other ingredients. Other propellant ingredients comprise a trimodal mix of 200, 1.7, and 0.7 micron particle sizes of ammonium perchlorate oxidizer in amounts from about 66 to about 70 weight percent, and aluminum metal powder in amounts from about 18 to about 20 weight percent. TBD is synthesized to contain no alpha hydrogens, i.e., does not have hydrogens on carbon adjacent to the aromatic ring structure which contributes to long term oxidation and migration problems of Hycat 6D and Catocene.

Description

DEDICATORY CLAUSE
The invention described herein may be manufactured, used, and licensed by or for the Government for governmental purposes without the payment to us of any royalties thereon.
BACKGROUND OF THE INVENTION
In line with the Army's continuing efforts to minimize hazards associated with propellant formulations used in its missile systems, a replacement propellant formulation has been sought that reduces some of the hazards associated with ammonium perchlorate propellants that use certain modifiers or additives such as 2,2-bis(ethyldicyclopentadienyliron)propane (also known as the trademark material Catocene) to enhance or increase propellant burn rate. Iron-containing compounds are now the current choice as burn rate enhancers for ammonium perchlorate propellants. Of these iron-containing compounds, ferrocene and its derivatives are the most efficient.
Earlier work with propellants containing solid iron compounds gave inconsistent burn rate enhancement because of the difficulty of getting a homogeneous mixture. Thereafter, liquid iron compounds were sought since it was believed that liquids would be better for mixing purposes. This plan of action lead to the development of bis(ethyldicyclopentadienyliron)methane, registered under Trademark Hycat 6D. Hycat 6D migrated readily within the solid propellant producing unsatisfactory propellant properties. Hycat 6D has a total of six alpha hydrogens (hydrogen adjacent to aromatic ring). It is known that hydrogens adjacent to aromatic ring systems are susceptible to oxidation to form acids and/or hydroperoxides. Hydroperoxides are known to be highly unstable compounds.
Since the alpha hydrogens were believed to be the reason for long term oxidation problems, Catocene was developed by coupling two ethylferrocenes with acetone, thus replacing the two bridged hydrogens with two methyl groups. Catocene then became the choice as a burn rate accelerator for ammonium perchlorate-based propellants. By replacing the two bridged hydrogens with methyl groups, long term oxidation and migration problems were reduced. However, accidental ignitions of solid propellants containing Catocene have occurred in both freshly prepared and aged propellants.
Therefore, the current status of Catocene in light of the concern for safety, where accidental ignition has been a problem for both freshly prepared and aged propellants, has motivated the development of a dicyclopentadienyliron compound that performs at the level of Catocene while having improved safety characteristics.
Therefore, an object of this invention is to provide a solid propellant composition which employs a dicyclopentadienyliron compound as a burn rate enhancer while retaining improved safety characteristics for the propellant formulation as compared with Catocene employed in a similar propellant formulation.
SUMMARY OF THE INVENTION
The solid propellant formulation of this invention employing 2,2-bis(t-butyldicylopentadienyliron)propane (TBD) as the burn rate enhancer yields higher threshold values for ignition by impact and improved friction and spark testing values to thereby render the solid propellant formulation less hazardous to personnel during handling. TBD solid propellant formulations also give improved results of the desired pressure exponent, potlife, and maximum stress characteristics when compared to similar solid propellant formulation containing Catocene.
The improved solid propellant composition having the properties described above is comprised of TBD as a burn rate enhancer in amounts from about 2 to about 6 weight percent, of about 68 weight percent of ammonium perchlorate of a trimodel blend of 200, 1.7, and 0.7 micron particle size, of aluminum powder of about 18 weight percent of a burner of hydroxyterminated polybutadience of about 9 weight percent, of an isocyanate curing agent as an additive of about 1 weight percent, and solid propellant processing aids in trace amounts.
DESCRIPTION OF THE PREFERRED EMBODIMENT
The solid propellant composition set forth below under Example illustrates the use of TBD as a burning rate enhancer with the formulation ingredients in weight percent.
EXAMPLE 
______________________________________                                    
               WEIGHT    WEIGHT PERCENT                                   
INGREDIENT     PERCENT   RANGE                                            
______________________________________                                    
Binder.sup.1,4  9.0       9-10                                            
TBD.sup.2       5.0      2-6                                              
Aluminum powder                                                           
               18.0      18-20                                            
Ammonium Perchlorate.sup.3                                                
               68.0      66-70                                            
______________________________________                                    
 Notes:                                                                   
 .sup.1 Hydroxyterminated Polybutadiene (HTPB) binder system including an 
 isocyanate curative as an additive up to about 1 weight percent.         
 .sup.2 TBD concentration can be varied from 2-6% to give the desired burn
 rate.                                                                    
 .sup.3 The ammonium perchlorate is a trimodal mix of particle sizes 200, 
 1.7, and 0.7 microns.                                                    
 .sup.4 Other additives, isocyanate curatives and modifiers can be added i
 small quantities with adjustment of the percent of content of other      
 ingredients as required for desired performance.
This formulation in above Example is mixed, cast, and cured by techniques and methods that are commonly used in the industry and that are known by personnel skilled in the art of propellant formulations.
The use of this solid propellant formulation is applicable to any program where there is a need for high burn rates and improved safety characteristics.
The structural formulae (A and B) of Hycat 6D, and Catocene, respectively, are presented below for comparison with TBD; the structural formula (C) for TBD is also presented below. Hycat 6D was a good burn rate enhancer, but was susceptible to long term oxidation. Hycat 6D also yielded poor results with respect to migration properties. Hycat 6D has a total of six alpha hydrogens (hydrogen adjacent to aromatic ring). It is believed that hydrogens adjacent to aromatic ring systems are suscepticle to oxidation to form acids and/or hydroperoxides. Hydroperoxides are known to be highly unstable compounds.
Catocene was the next compound developed which showed early promise of meeting the burn rate enhancer requirement; however, it too had problems related to stability in spite of replacing two bridged hydrogens with two methyl groups as discussed below.
Since the alpha hydrogens were believed to be the reason for long term oxidation problems, Catocene was developed by coupling two ethyferrocenes with acetone, thus replacing the two bridged hydrogens with two methyl groups. Catocene became a choice as a burn rate accelerator for ammonium perchlorate-based propellants. By replacing the two bridged hydrogens with methyl groups, long term oxidation and migration problems were reduced. However, accidental ignitions of propellants containing Catocene have occurred in both freshly prepared and aged propellants. Hence, the need for TBD was established.
The purpose of the work relating to TBD is to synthesize a compound that has no alpha hydrogens. TBD does not have hydrogens on carbon adjacent to the aromatic ring structure; therefore, long term oxidation and reduced problem of migration are among the benefits derived. TBD was synthesized and a propellant mix was evaluated and compared to a similar mix containing Catocene. ##STR1##
EVALUATION OF TBD IN PROPELLANT FORMULATIONS
During the development program for TBD in solid propellants, several areas of interest were evaluated to determine the properties of a solid propellant composition containing TBD as compared to one containing Catocene.
The areas of interest evaluated are summarized in Table I. Sensitivity Results; Table II. One-Gallon Mix Data; and Table III. Pint Mix Preliminary Ballistic Data as follows:
              TABLE I                                                     
______________________________________                                    
SENSITIVITY RESULTS                                                       
                 Cured Sensitivity                                        
                       Impact  Spark  Friction                            
Mix No.   Percent Catalyst                                                
                       (lb-cm) (joules)                                   
                                      (lb)                                
______________________________________                                    
27 (TBD)  6            78      0.125  60                                  
29 (TBD)  5            66      2.25   60                                  
30 (TBD)  5            60      1.00   50                                  
31 (TBD)  5            72      4.00   90                                  
32 (TBD)  0            74      25     90                                  
49 (TBD)  6            78      1.00   ND                                  
1-gallon (TBD)                                                            
          5            74      6.25   80                                  
Catocene Mix                                                              
          5            48      1.00   50                                  
______________________________________                                    

              TABLE II                                                    
______________________________________                                    
ONE-GALLON MIX DATA                                                       
Catalyst (%)      TBD 5%   Catocene 5%                                    
______________________________________                                    
EOM Viscosity, KP 3        4                                              
Potlife to 40 Kp, Hr                                                      
                  16.4     14                                             
NCO/OH            0.89     0.89                                           
Maximum Stress, psi                                                       
                  423      251                                            
Strain at Max. Stress,                                                    
                  28       35                                             
percent                                                                   
Tangent Modulus   1893     812                                            
Burn Rate @ 1000 psi  3.12     3.19                                       
          @ 2000 psi  4.20     4.33                                       
Pressure Exponent 0.43     0.46                                           
______________________________________                                    

              TABLE III                                                   
______________________________________                                    
PINT MIX PRELIMINARY BALLISTIC DATA                                       
            Burn Rate @                                                   
                  1000     2000 Pressure                                  
Mix No.   % TBD   (psi)    (psi)                                          
                                Exponent                                  
______________________________________                                    
27        6       2.95     3.98 0.44                                      
29        5       3.22     4.33 0.43                                      
30        5       3.20     4.25 0.42                                      
31        5       3.20     4.25 0.42                                      
32        0       0.46     0.98 0.72                                      
                                (1.00 @ 2000 psi)                         
49        6       3.50     4.78 0.45                                      
______________________________________

Claims (2)

We claim:
1. A solid propellant composition comprising:
(i) a trimodal mix of particle sizes 200, 1.7, and 0.7 microns of ammonium perchlorate oxidizer in an amount from about 66 to about 70 weight percent, said trimodal mix having a major portion of said 1.7 and 0.7 micron particle sizes with the remainder of said weight percent being 200 micron particle size;
(ii) hydroxyterminated polybutadiene binder system in an amount from about 9 to about 10 weight percent, said hydroyx-terminated polybutadiene binder system including an isocyanate curative added in an amount of up to about 1.0 weight percent and optional modifiers in small amounts with adjustment of the weight of other ingredients;
(iii) aluminum metal powder from about 18 to 20 weight percent; and,
(iv) a burning rate enhancer of 2,2-bis(t-butyldicylopentadienyliron)propane in amount from about 2 to about 6 weight percent.
2. The solid propellant composition of claim 1 wherein said trimodial mix of said ammonium perchlorate is present in an amount of about 68 weight percent; said hydroxyterminated polybutadiene binder system is present in amount of about 9 weight percent; said aluminum metal powder is present in an amount of about 18 weight percent; and wherein said burn rate enhancer of 2,2-bis(t-butyldicyclopentadienyliron)propane is present in an amount of about 5 weight percent.
US07/243,539 1988-09-12 1988-09-12 High burn rate ammonium perchlorate propellant Abandoned USH717H (en)

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5112417A (en) * 1991-05-20 1992-05-12 United States Of America Method of controlling the increase in potlife of propellants during processing
US5281286A (en) * 1992-04-09 1994-01-25 The United States Of America As Represented By The Secretary Of The Army Microcoacervation of propellant ingredients
US5872328A (en) * 1996-03-06 1999-02-16 Chemische Betriebe Pluto Gmbh Ferrocene derivatives
US6217682B1 (en) 1997-10-27 2001-04-17 Cordant Technologies Inc. Energetic oxetane propellants
US6740180B1 (en) * 1997-07-15 2004-05-25 Anthony Joseph Cesaroni Thermoplastic polymer propellant compositions
US6815522B1 (en) 1998-11-12 2004-11-09 Alliant Techsystems Inc. Synthesis of energetic thermoplastic elastomers containing oligomeric urethane linkages
US6997997B1 (en) 1998-11-12 2006-02-14 Alliant Techsystems Inc. Method for the synthesis of energetic thermoplastic elastomers in non-halogenated solvents
US7011722B2 (en) 2003-03-10 2006-03-14 Alliant Techsystems Inc. Propellant formulation
US20060157173A1 (en) * 1998-11-12 2006-07-20 Sanderson Andrew J Synthesis of energetic thermoplastic elastomers containing both polyoxirane and polyoxetane blocks
US7101955B1 (en) 1998-11-12 2006-09-05 Alliant Techsystems Inc. Synthesis of energetic thermoplastic elastomers containing both polyoxirane and polyoxetane blocks

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5112417A (en) * 1991-05-20 1992-05-12 United States Of America Method of controlling the increase in potlife of propellants during processing
US5281286A (en) * 1992-04-09 1994-01-25 The United States Of America As Represented By The Secretary Of The Army Microcoacervation of propellant ingredients
US5872328A (en) * 1996-03-06 1999-02-16 Chemische Betriebe Pluto Gmbh Ferrocene derivatives
US6740180B1 (en) * 1997-07-15 2004-05-25 Anthony Joseph Cesaroni Thermoplastic polymer propellant compositions
US6217682B1 (en) 1997-10-27 2001-04-17 Cordant Technologies Inc. Energetic oxetane propellants
US6815522B1 (en) 1998-11-12 2004-11-09 Alliant Techsystems Inc. Synthesis of energetic thermoplastic elastomers containing oligomeric urethane linkages
US6997997B1 (en) 1998-11-12 2006-02-14 Alliant Techsystems Inc. Method for the synthesis of energetic thermoplastic elastomers in non-halogenated solvents
US20060074215A1 (en) * 1998-11-12 2006-04-06 Sanderson Andrew J Synthesis of energetic thermoplastic elastomers containing oligomeric urethane linkages
US20060157173A1 (en) * 1998-11-12 2006-07-20 Sanderson Andrew J Synthesis of energetic thermoplastic elastomers containing both polyoxirane and polyoxetane blocks
US7101955B1 (en) 1998-11-12 2006-09-05 Alliant Techsystems Inc. Synthesis of energetic thermoplastic elastomers containing both polyoxirane and polyoxetane blocks
US20090088506A1 (en) * 1998-11-12 2009-04-02 Alliant Techsystems Inc. Synthesis of energetic thermoplastic elastomers containing both polyoxirane and polyoxetane blocks
US7011722B2 (en) 2003-03-10 2006-03-14 Alliant Techsystems Inc. Propellant formulation

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