USH1341H - High energy propellant formulation - Google Patents

High energy propellant formulation Download PDF

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USH1341H
USH1341H US07/627,169 US62716990A USH1341H US H1341 H USH1341 H US H1341H US 62716990 A US62716990 A US 62716990A US H1341 H USH1341 H US H1341H
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propellant
cellulose acetate
polyethylene glycol
butyrate
hexamethylene diisocyanate
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Charles W. Hughes
James H. Godsey
Robert F. Keller
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  • This invention relates to propellants for rockets and more particularly, this invention relates to a rocket propellant having about 22 to 27 weight percent binder and about 73 to 78 weight percent solids. Still more particularly, but without limitation thereto, this invention relates to a propellant having a binder using a specific range of ratios of cellulose acetate butyrate (CAB) to polyethylene glycol (PEG).
  • CAB cellulose acetate butyrate
  • PEG polyethylene glycol
  • This invention provides a very high performance nitrate ester plasticized polyether (NEPE) propellant based upon a unique cellulose acetate butyrate (CAB) polyethylene glycol (PEG) binder system.
  • NEPE nitrate ester plasticized polyether
  • CAB unique cellulose acetate butyrate
  • PEG polyethylene glycol
  • this invention provides a propellant with a long pot life, improved efficiency, low burn rate pressure sensitivity, excellent mechanical properties, high critical impact velocity, and a high delivered specific impulse.
  • An object of this invention is to develop an improved high energy propellant.
  • a further object of this invention is to develop an improved high energy propellant having optimal mechanical and ballistic properties.
  • the propellant binder has a cellulose acetate butyrate: polyethylene glycol ratio in the range of about 0.01 to 0.03 on a weight basis.
  • FIG. 1 shows graphs of the effect of PEG molecular weight on propellant mechanical properties.
  • the general composition of the high energy propellant is about 22 to 27 weight percent binder and about 73 to 78 weight percent solids.
  • the binder itself has several components: two polymers, a plasticizer, is a curative, and two stabilizers.
  • the binder also contains a trace amount of catalyst.
  • the solids component of the propellant is comprised of a metanized fuel, an energetic filler, and an oxidizer.
  • Table I illustrates four examples of preferred propellant compositions, by weight percent. Examples I and II exemplify the most preferred formulations. It is to be understood that the values specified in Table I are approximate, and some variations from those shown are still within the scope of this invention.
  • the preferred polymers are polyethylene glycol (PEG) and cellulose acetate butyrate (CAB).
  • PEG polyethylene glycol
  • CAB cellulose acetate butyrate
  • the polymer PEG functions to give physical strength to the binder when crosslinked with itself and/or CAB.
  • Polypropylene glycol can be used for some PEG but the plasticizers are less soluble in it so that in most cases it is preferred to use PEG as the polyol polymer.
  • PEG and CAB also serve as sources of fuel in the propellant.
  • CAB as a crosslinker provides physical strength by improving tensile strength and the modulus of elasticity.
  • such chemicals as cellulose acetate, cellulose butyrate, trimethylol propane, or glycerin can be substituted in part or in whole for the CAB component of the inventive fuel.
  • a mixture of cellulose acetate and cellulose butyrate are used in combination as substitutes for CAB rather than either alone.
  • the mechanical properties of the propellant can be modified by varying the molecular weight of the PEG employed in the propellant formulation.
  • Molecular weight of the polyether and the modulus of elasticity vary inversely but the elongation varies directly.
  • increasing the molecular weight of the polyether causes a steady drop in the modulus of elasticity and increases the elongation in the resultant fuel.
  • the molecular weight of the PEG has a direct bearing on the crosslink density and gelling efficiency of the present propellant, particularly at the higher Pl:P0 (i.e. plasticizer: polymer) levels due to the dilution of the polymer.
  • Pl:P0 i.e. plasticizer: polymer
  • FIG. 1 also demonstrates the effects of PEG molecular weight on the mechanical properties of the propellant.
  • various mechanical properties of the propellant can be modified by adjustment of the ingredients (i.e. ones selected and the amounts) to meet the particular requirements of a specific missile system, and thereby optimize its efficiency.
  • PEG with molecular weights of 1000-8000 can be used depending on the desired mechanical properties.
  • the preferred PEG has a nominal molecular weight of about 3500.
  • the mechanical properties of the propellant also vary with the ratio of CAB to PEG. It is desirable to have both high elongation and high tensile strength. However, while tensile strength is proportional to the CAB:PEG ratio, elongation is inversely proportional to said ratio. Taking this into consideration, it has been found that a CAB:PEG weight ratio in the range of about 0.001 to 0.05 is suitable. Where nitrocellulose is used for CAB, we have found the ratios of 0.001 to 1.0 to be suitable. We have found ratios of CAB in the range of about 0.01 to 0.03 to be preferred as producing on balance overall good results.
  • Another embodiment of the present invention allows a modification of the mechanical properties of the manufactured fuel by blending polyethers of various molecular weights. This effect is shown in Table IV.
  • PEG polypropylene glycol
  • the mechanical properties can be modified by blending the PEG component of the fuel with various amounts of polypropylene glycol (PPG) to form block copolymers.
  • PPG polypropylene glycol
  • Table V the use of PEG/PPG tends to yield a poor modulus.
  • the inclusion of polypropylene for PEG tends to reduce the solubility of plasticizers and thus in most cases PEG alone is preferred and used.
  • the preferred plasticizer is nitroglycerin (NG), a high energy compound.
  • NG nitroglycerin
  • the mixing of CAB and NG results in a material that is formable and plastic. Its use in the present invention results in improved mechanical properties and higher performance for the binder.
  • nitrate esters generally may serve as suitable plasticizers.
  • Butanethol trinitrate (BTTN), triethylene glycol dinitrate (TEGDN), diethylene glycol dinitrate (DEGDN), and trimethylolethane trinitrate (TMETN) are examples of plasticizers that can be utilized within the purview of the present invention.
  • the crosslinking curative of the subject invention is responsible for crosslinking the various components of the fuel.
  • a polyfunctional isocyanate containing the biuret trimer of hexamethylene diisocyanate is preferred. It has an NCO functionality of at least 3.
  • Desmodur N-100 commercially available from Mobay Chemical Co., which is a complex mixture of biurets, uretediones, isocyanurates and unreacted hexamethylene diisocyanate.
  • Optimal crosslinking and mechanical properties are obtained when the stabilizer for NG, N-methyl-p-nitroaniline (MNA), which is discussed later, acts to stabilize the complete propellant.
  • MNA N-methyl-p-nitroaniline
  • Pentaerythritol tetraisocyanate is a chemical which can be considered as an alternative curing agent.
  • Difunctional isocyanates tend to increase the elasticity of the resulting fuel to a great degree, and so are generally less preferred.
  • Triphenyl bismuth is the preferred cure catalyst in the present invention. It functions to speed up the crosslinking process and helps to provide a very long pot life or working life (i.e., until a viscosity of about 40 kilopoise is reached). Because TPB functions as a relatively slow reacting cure catalyst, it is particularly advantageous with large missiles where the set time for the fuel is longer. Competing and interfering reactions are minimized in this system.
  • organo metal cure catalysts can be employed in place of TPB.
  • TPB organo metal cure catalysts
  • examples are trialkyl bismuths, such as triethyl bismuth.
  • Other metals can be used but they can have adverse effects unrelated to cure. The choice depends on the final fuel qualities desired, and accommodations to be made to the exigencies of the particular production process employed. The considerations involved include the size of the missile for which the fuel is being manufactured.
  • the metal used to form the metallized fuel used in the preferred embodiment of the present invention is free metal aluminum (Al).
  • Al reacts with the oxidizers primarily to provide heat as a product of the combustion process. This fuel is particularly useful in larger missiles, and may be eliminated in smaller tactical missiles, or for minimum smoke missiles.
  • metallized fuels can be employed with that of the preferred embodiment or as substitutes for it, depending on the nature of the fuel desired.
  • Suitable other metals for use in metallized fuels are boron and beryllium (although the latter is quite toxic).
  • the energetic filler employed in the preferred embodiment of the present invention is cyclotetramethylene tetranitramine (HMX), which generates heat and gases. Also useful in this capacity is cyclotrimethylene trinitramine (RDX).
  • HMX size affects the mechanical properties of the propellant. The modulus of elasticity is not dramatically affected by HMX diameter. However, tensile strength and especially percent elongation increase dramatically as the particle size decreases. The particle size is varied to obtain a proper viscosity for processing, but the optimum mechanical properties are achieved with the finest possible HMX.
  • the preferred oxidizer in the present invention is ammonium perchlorate (AP), which functions to oxidize all of the hydrocarbons and the metal, aluminum, to generate heat and gases.
  • AP is also used to control the burning rate of the propellant.
  • Table I the particle size and ratio of the oxidizer can be varied to fit the needs of a particular fuel requirement.

Abstract

A high energy rocket propellant can be formed wherein the propellant binder has a cellulose acetate butyrate: polyethylene glycol ratio of about 0.01 to 0.03 on a weight basis.

Description

FIELD OF THE INVENTION
This invention relates to propellants for rockets and more particularly, this invention relates to a rocket propellant having about 22 to 27 weight percent binder and about 73 to 78 weight percent solids. Still more particularly, but without limitation thereto, this invention relates to a propellant having a binder using a specific range of ratios of cellulose acetate butyrate (CAB) to polyethylene glycol (PEG).
BACKGROUND OF THE INVENTION
There is a constant search for improved propellants that are easier to process, have improved mechanical properties, and are higher performance. This invention provides a very high performance nitrate ester plasticized polyether (NEPE) propellant based upon a unique cellulose acetate butyrate (CAB) polyethylene glycol (PEG) binder system.
Further, this invention provides a propellant with a long pot life, improved efficiency, low burn rate pressure sensitivity, excellent mechanical properties, high critical impact velocity, and a high delivered specific impulse.
OBJECTS OF THE INVENTION
An object of this invention is to develop an improved high energy propellant.
A further object of this invention is to develop an improved high energy propellant having optimal mechanical and ballistic properties.
SUMMARY OF THE INVENTION
These and other objects have been demonstrated by the present invention wherein the propellant binder has a cellulose acetate butyrate: polyethylene glycol ratio in the range of about 0.01 to 0.03 on a weight basis.
BRIEF DESCRIPTION OF THE DRAWING
FIG. 1 shows graphs of the effect of PEG molecular weight on propellant mechanical properties.
DESCRIPTION OF THE PREFERRED EMBODIMENT
The general composition of the high energy propellant is about 22 to 27 weight percent binder and about 73 to 78 weight percent solids. The binder itself has several components: two polymers, a plasticizer, is a curative, and two stabilizers. The binder also contains a trace amount of catalyst. The solids component of the propellant is comprised of a metanized fuel, an energetic filler, and an oxidizer.
Table I illustrates four examples of preferred propellant compositions, by weight percent. Examples I and II exemplify the most preferred formulations. It is to be understood that the values specified in Table I are approximate, and some variations from those shown are still within the scope of this invention.
                                  TABLE I                                 
__________________________________________________________________________
                 Percentage by Weight                                     
COMPONENTS       Example I                                                
                       Example II                                         
                             Example III                                  
                                    Example IV                            
__________________________________________________________________________
BINDER                                                                    
Polymers                                                                  
Polyethylene Glycol (PEG)                                                 
                 6.25  6.25  11.65  5.02                                  
Cellulose Acetate Butyrate (CAB)                                          
                 0.06  0.06   .00   0.20                                  
Plasticizer                                                               
Nitroglycerin (NG)                                                        
                 19.02 19.02 8.06   20.18                                 
Crosslinking Curative                                                     
Desmodur N-100   0.88  0.88  1.74   0.80                                  
Stabilizer                                                                
2 nitrodiphenylamine (2NDPA)                                              
                 0.19  0.19  0.08   0.20                                  
N-methyl-p-nitroaniline (MNA)                                             
                 0.60  0.60  0.47   0.60                                  
Cure Catalyst                                                             
Triphenyl bismuth (TPB)                                                   
                 0.02  0.02  0.02   0.02                                  
SOLIDS                                                                    
Fuel                                                                      
Aluminum         18.00 18.00 24.00  16.00                                 
Energetic Filler                                                          
Cyclotetramethylene                                                       
                 47.00 46.00 12.00  57.00                                 
Tetranitramine (HMX)                                                      
Particle Size     2μ-11μ                                            
                       2μ-11μ                                       
                              2μ 57μ/2μ                          
Ratio            1:1   1:1   --     34:23                                 
Oxidizer                                                                  
Ammonium Perchlorate (AP)                                                 
                 8.00  9.00  42.00                                        
Particle Size    20μ-50μ                                            
                       5μ-20μ                                       
                             200μ                                      
Ratio            1:1   1:1   --     --                                    
__________________________________________________________________________
Examples I and II in the Table, which represent the most preferred embodiments of the present invention, have the following mechanical properties:
______________________________________                                    
               Example I                                                  
                       Example II                                         
______________________________________                                    
Modulus (psi)    430       545                                            
Tensile strength (psi)                                                    
                  92        99                                            
Elongation (%)   270       273                                            
______________________________________
These values are determined at a 2 in/min pull rate at 80° F. The above values were obtained from a 600 gallon mixed batch.
The preferred polymers are polyethylene glycol (PEG) and cellulose acetate butyrate (CAB). The polymer PEG functions to give physical strength to the binder when crosslinked with itself and/or CAB. Polypropylene glycol can be used for some PEG but the plasticizers are less soluble in it so that in most cases it is preferred to use PEG as the polyol polymer. PEG and CAB also serve as sources of fuel in the propellant.
CAB as a crosslinker provides physical strength by improving tensile strength and the modulus of elasticity. In other embodiments, such chemicals as cellulose acetate, cellulose butyrate, trimethylol propane, or glycerin can be substituted in part or in whole for the CAB component of the inventive fuel. Preferably a mixture of cellulose acetate and cellulose butyrate are used in combination as substitutes for CAB rather than either alone.
In the present invention, the mechanical properties of the propellant can be modified by varying the molecular weight of the PEG employed in the propellant formulation. Molecular weight of the polyether and the modulus of elasticity vary inversely but the elongation varies directly. Thus, increasing the molecular weight of the polyether causes a steady drop in the modulus of elasticity and increases the elongation in the resultant fuel. The molecular weight of the PEG has a direct bearing on the crosslink density and gelling efficiency of the present propellant, particularly at the higher Pl:P0 (i.e. plasticizer: polymer) levels due to the dilution of the polymer. The various effects of PEG molecular weight modulation can be seen in Tables II and III.
              TABLE II                                                    
______________________________________                                    
EFFECT OF PEG MOLECULAR WEIGHT                                            
70% Solids, 2.8 Pl:Po                                                     
Approx.    σ      ε                                         
                               E                                          
MW         (psi)        (%)    (psi)                                      
______________________________________                                    
 430       64            37    680                                        
1020       70            56    728                                        
1376       77           100    510                                        
3240       65           292    296                                        
4100       67           411    204                                        
______________________________________                                    

              TABLE III                                                   
______________________________________                                    
EFFECT OF POLYETHER MOLECULAR WEIGHT                                      
ON MECHANICAL PROPERTIES                                                  
75% Solids, 1.2 NCO:OH                                                    
Approx.            .sup.σ m                                         
                          .sup.ε m                                
                                  .sup.ε f                        
                                       E                                  
MW       PL:Po     (psi)  (%)     (%)  (psi)                              
______________________________________                                    
1000     2.1       123    25      25   1040                               
1500     2.1       130    23      23   1100                               
3100     2.1       77     29      145  685                                
4000     2.1       72     260     260  425                                
7800     2.1       81     970     970  185                                
9400     2.1       82     1170    1170 215                                
1000     2.8       111    24      24   880                                
1500     2.8       114    25      25   810                                
3100     2.8       59     24      93   550                                
4000     2.8       54     295     295  455                                
7800     2.8       68     1000    1000 160                                
8100     2.8       69     1100    1100 130                                
9400     2.8       57     1130    1130 105                                
______________________________________
FIG. 1 also demonstrates the effects of PEG molecular weight on the mechanical properties of the propellant. Thus, various mechanical properties of the propellant can be modified by adjustment of the ingredients (i.e. ones selected and the amounts) to meet the particular requirements of a specific missile system, and thereby optimize its efficiency. PEG with molecular weights of 1000-8000 can be used depending on the desired mechanical properties. The preferred PEG has a nominal molecular weight of about 3500.
The mechanical properties of the propellant also vary with the ratio of CAB to PEG. It is desirable to have both high elongation and high tensile strength. However, while tensile strength is proportional to the CAB:PEG ratio, elongation is inversely proportional to said ratio. Taking this into consideration, it has been found that a CAB:PEG weight ratio in the range of about 0.001 to 0.05 is suitable. Where nitrocellulose is used for CAB, we have found the ratios of 0.001 to 1.0 to be suitable. We have found ratios of CAB in the range of about 0.01 to 0.03 to be preferred as producing on balance overall good results.
Another embodiment of the present invention allows a modification of the mechanical properties of the manufactured fuel by blending polyethers of various molecular weights. This effect is shown in Table IV.
              TABLE IV                                                    
______________________________________                                    
EFFECT OF POLYMER BLENDS                                                  
70% Solids, 2.1 Pl:Po, 1.2 NCO:OH                                         
             .sup.σ m                                               
                    .sup.ε m                                      
                               .sup.(ε f                          
                                    E                                     
Approx. MW   (psi)  (%)        (%)  (psi)                                 
______________________________________                                    
4000         72     260        260  425                                   
4000/7800    74     530        530  350                                   
7800         81     970        970  185                                   
3100         77      29        145  685                                   
3100/8100    76     745        745  295                                   
8100         85     960        960  315                                   
1500         130     23         23  1095                                  
1500/3100    88      26         58  795                                   
3100         77      29        145  685                                   
1500         130     23         23  1095                                  
1500/8100    56     485        485  325                                   
8100         85     960        960  315                                   
______________________________________                                    
 All blends were OH equivalent ratio of 1:1.
In alternate embodiments, other long chain polyols may be used in part or in whole in place of PEG. For instance, the mechanical properties can be modified by blending the PEG component of the fuel with various amounts of polypropylene glycol (PPG) to form block copolymers. This effect is demonstrated in Table V. However, the use of PEG/PPG tends to yield a poor modulus. The inclusion of polypropylene for PEG tends to reduce the solubility of plasticizers and thus in most cases PEG alone is preferred and used.
The preferred plasticizer is nitroglycerin (NG), a high energy compound. The mixing of CAB and NG results in a material that is formable and plastic. Its use in the present invention results in improved mechanical properties and higher performance for the binder.
In alternate embodiments, other nitrate esters generally may serve as suitable plasticizers. Butanethol trinitrate (BTTN), triethylene glycol dinitrate (TEGDN), diethylene glycol dinitrate (DEGDN), and trimethylolethane trinitrate (TMETN) are examples of plasticizers that can be utilized within the purview of the present invention.
The crosslinking curative of the subject invention is responsible for crosslinking the various components of the fuel. A polyfunctional isocyanate containing the biuret trimer of hexamethylene diisocyanate is preferred. It has an NCO functionality of at least 3.
An especially suitable curative is Desmodur N-100, commercially available from Mobay Chemical Co., which is a complex mixture of biurets, uretediones, isocyanurates and unreacted hexamethylene diisocyanate. Optimal crosslinking and mechanical properties are obtained when the stabilizer for NG, N-methyl-p-nitroaniline (MNA), which is discussed later, acts to stabilize the complete propellant.
              TABLE V                                                     
______________________________________                                    
COMPARISON OF PEG WITH                                                    
PEG/PPG COPOLYMERS                                                        
______________________________________                                    
Parameter                                                                 
% Solids 73      73      73    75    75    75                             
Wt % PEG/                                                                 
         100/0   10/90   40/60 50/50 50/50 70/30                          
Wt % PPG                                                                  
Pl:Po    2.1     1.8     1.72  2.1   2.8   2.8                            
NCO:OH   1.2     1.2     1.3   1.2   1.2   1.2                            
Mechanical Properties, 2 ipm                                              
σ (psi)                                                             
         95      62      69    52    53    62                             
ε (%)                                                             
         500     698     706   685   890   1000                           
E (psi)  350     135     202   165   105   140                            
______________________________________
In additional embodiments of the present invention, other polyfunctional isocyanates may be successfully employed as crosslinking curatives. Pentaerythritol tetraisocyanate is a chemical which can be considered as an alternative curing agent. Difunctional isocyanates tend to increase the elasticity of the resulting fuel to a great degree, and so are generally less preferred.
Organo bismuth compounds are used as cure catalysts. Triphenyl bismuth (TPB) is the preferred cure catalyst in the present invention. It functions to speed up the crosslinking process and helps to provide a very long pot life or working life (i.e., until a viscosity of about 40 kilopoise is reached). Because TPB functions as a relatively slow reacting cure catalyst, it is particularly advantageous with large missiles where the set time for the fuel is longer. Competing and interfering reactions are minimized in this system.
Other organo metal cure catalysts can be employed in place of TPB. Examples are trialkyl bismuths, such as triethyl bismuth. Other metals can be used but they can have adverse effects unrelated to cure. The choice depends on the final fuel qualities desired, and accommodations to be made to the exigencies of the particular production process employed. The considerations involved include the size of the missile for which the fuel is being manufactured.
The metal used to form the metallized fuel used in the preferred embodiment of the present invention is free metal aluminum (Al). Al reacts with the oxidizers primarily to provide heat as a product of the combustion process. This fuel is particularly useful in larger missiles, and may be eliminated in smaller tactical missiles, or for minimum smoke missiles.
In other embodiments, different metallized fuels can be employed with that of the preferred embodiment or as substitutes for it, depending on the nature of the fuel desired. Suitable other metals for use in metallized fuels are boron and beryllium (although the latter is quite toxic).
The energetic filler employed in the preferred embodiment of the present invention is cyclotetramethylene tetranitramine (HMX), which generates heat and gases. Also useful in this capacity is cyclotrimethylene trinitramine (RDX). As can be seen in Table 6, the particle size and ratio of the energetic filler can be varied to fit the needs of a particular fuel requirement. An increase in quantity enhances the energetic nature of the fuel. HMX size affects the mechanical properties of the propellant. The modulus of elasticity is not dramatically affected by HMX diameter. However, tensile strength and especially percent elongation increase dramatically as the particle size decreases. The particle size is varied to obtain a proper viscosity for processing, but the optimum mechanical properties are achieved with the finest possible HMX.
              TABLE VI                                                    
______________________________________                                    
Effect of HMX Size on Mechanical Properties                               
______________________________________                                    
HMX Size (μ)      4      2                                             
Tensile Strength (psi)                                                    
                     90     97                                            
Elongation (%)      290    450                                            
Modulus (psi)       430    370                                            
______________________________________
The preferred oxidizer in the present invention is ammonium perchlorate (AP), which functions to oxidize all of the hydrocarbons and the metal, aluminum, to generate heat and gases. AP is also used to control the burning rate of the propellant. As can be seen in Table I, the particle size and ratio of the oxidizer can be varied to fit the needs of a particular fuel requirement.
The propellants provided in Examples I and II specified in Table I have the following typical properties:
              TABLE VII                                                   
______________________________________                                    
                   Example I                                              
                           Example II                                     
______________________________________                                    
Density (lb/in.sup.3)                                                     
                     0.0665    0.0665                                     
Burning rate (1000 psi, 80° F., in/sec)                            
                     0.42      0.49                                       
Specific impulse, 1bf-sec/1bm                                             
                     271.5     271.4                                      
______________________________________
This invention has been described in detail with particular reference to certain preferred embodiments thereof, but it will be understood that variations and modifications can be effected within the spirit and scope of the invention.

Claims (18)

What is claimed is:
1. A propellant composition comprising:
polyethylene glycol;
a nitrate ester;
the biuret trimer of hexamethylene diisocyanate;
2-nitrodiphenylamine;
N-methyl-p-nitroaniline;
an organo-bismuth compound;
a metal selected from aluminum, boron and beryllium;
cyclotetramethylene tetranitramine;
ammonium perchlorate; and,
optionally at least one crosslinking agent selected from the group consisting of trimethylol propane, glycerin, cellulose acetate butyrate, cellulose acetate and cellulose butyrate alone, or said acetate and butyrate in combination.
2. The propellant according to claim 1 wherein said organo bismuth compound is triphenyl bismuth.
3. The propellant of claim 1 wherein the crosslinking agent is chosen from the group consisting of cellulose acetate butyrate, cellulose acetate, cellulose butyrate, or a combination of the acetate and the butyrate, the weight ratio of cellulose acetate butyrate, cellulose acetate, cellulose butyrate or a combination thereof to said polyethylene glycol being about 0.01 to 0.03.
4. The propellant according to claim 1 wherein said metal is aluminum.
5. The propellant of claim 1 wherein said bioret trimer of hexamethylene diisocyanate is a polyfunctional isocyanate having an NCO functionality of at least 3.
6. The propellant according to claim 1 wherein said nitrate ester is nitroglycerine.
7. The propellant of claim 1 wherein said polyethylene glycol has a hydroxyl functionality of about 2.
8. The propellant according to claim 1 wherein said polyethylene glycol is in the form of a polymer having a molecular weight of between about 1000 and 8000.
9. The propellant of claim 1 wherein said cellulose acetate butyrate has a hydroxyl equivalent weight of about 1100.
10. The propellant of claim 1 wherein the ratio of isocyanate functional groups of said biuret trimer of hexamethylene diisocyanate to the combined hydroxyl functionality of said polyethylene glycol and cellulose acetate butyrate is about 1.1 to 1.3.
11. The propellant of claim 1 wherein said cyclotetramethylene tetranitramine has an average particle size of about 6.5 μ.
12. A propellant composition comprises by weight percent:
about 6.25 polyethylene glycol,
about 0.06 cellulose acetate butyrate,
about 19.02 nitroglycerin,
about 0.88 biuret trimer of hexamethylene diisocyanate,
about 0.19 2-nitrodiphenylamine,
about 0.60 N-methyl-p-nitroaniline,
about 0.02 triphenyl bismuth,
about 18.0 aluminum,
about 46.0 cyclotetramethylene tetranitramine, and
about 9.0 ammonium perchlorate.
13. The propellant of claim 2 which further comprises a trace amount of triphenyl bismuth.
14. The propellant of claim 12 wherein said polyethylene glycol has nominal molecular weight of 3500.
15. The propellant of claim 12 wherein said bioret trimer of hexamethylene diisocyanate is a polyfunctional isocyanate having an NCO functionality of at least 3, and wherein said polyethylene glycol has a hydroxyl functionality of about 2 and said cellulose acetate butyrate has a hydroxyl equivalent weight of about 1100.
16. The propellant of claim 12 wherein the ratio of isocyanate functional groups in said biuret trimer of hexamethylene diisocyanate to the combined hydroxyl functionality of said polyethylene glycol and cellulose acetate butyrate is about 1.1 to 1.3.
17. The propellant of claim 12 wherein said cyclotetramethylene tetranitramine has an average particle size of about 6.5μ.
18. A propellant composition comprising by weight percent:
About 6.25 polyethylene glycol,
about 0.06 cellulose acetate butyrate,
about 19.02 nitroglycerin,
about 0.88 biuret trimer of hexamethylene diisocyanate,
about 0.19 2-nitrodiphenylamine,
about 0.60 N-methyl-p-nitroaniline,
about 0.02 triphenyl bismuth,
about 18.0 aluminum,
about 47.0 cyclotetramethylene tetranitramine, and
about 8.0 ammonium perchlorate.
US07/627,169 1990-12-14 High energy propellant formulation Abandoned USH1341H (en)

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Cited By (5)

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EP0790476A3 (en) * 1996-02-15 1997-12-29 Dynamit Nobel GmbH Explosivstoff- und Systemtechnik Selfpropelled missile
US6168677B1 (en) * 1999-09-02 2001-01-02 The United States Of America As Represented By The Secretary Of The Army Minimum signature isocyanate cured propellants containing bismuth compounds as ballistic modifiers
US6969434B1 (en) * 2002-12-23 2005-11-29 The United States Of America As Represented By The Secretary Of The Navy Castable thermobaric explosive formulations
US20140338803A1 (en) * 2013-05-14 2014-11-20 Agency For Defense Development Smokeless propellant composition containing bismuth-based compound and method of preparing the same
CN114591126A (en) * 2022-03-17 2022-06-07 西安近代化学研究所 Thermocuring intelligent gunpowder and preparation method thereof

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CN114591126A (en) * 2022-03-17 2022-06-07 西安近代化学研究所 Thermocuring intelligent gunpowder and preparation method thereof

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