Abstract:
Environmentally friendly high performance minimum signature propellants have been demonstrated for use in next generation tactical missile applications. Bismuth salicylate and bismuth citrate have each been used in propellant formulations and evaluated for processing, ballistic, mechanical, aging and signature properties. These high performance formulations have potential to replace current formulations used in some fielded tactical systems. The propellant binder network is achieved using energetic nitramine polymers where inert polymers have been the polymer of choice for minimum signature propellants. The significance of this has to do with achieving propellant specific impulses greater than 245 seconds without nitroglycerin being used in the formulation. This improves propellant safety properties during the propellant processing and the manufacturing of the final missile configurations. The Army has mandated that the next generation propellant formulations show improvements in safety to the end users. These formulations are environmentally friendly (no-lead) and do not use nitroglycerin to achieve high performance.

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
     This application is related to concurrently filed application by Inventor: Larry C. Warren; Invention Docket No.: AMPC 4974, and Titled: “A Processing Procedure For Isocyanate Cured Propellants Containing Some Bismuth Compounds.” 
    
    
     DEDICATORY CLAUSE 
     The invention described herein may be manufactured, used and licensed by or for the Government for governmental purposes without the payment to me of any royalties thereon. 
     BACKGROUND OF INVENTION 
     The U.S. Army Aviation and Missile Command at Redstone Arsenal has long been interested in the removal of environmental hazards in its tactical missile propellants. Of particular interest is the removal of lead from the exhaust products of all tactical missiles. Lead compounds are currently the major ballistic modifiers used in the traditional minimum signature propellants for tactical missile applications. Lead is currently found in nearly all tactical missiles where minimum signature is required. The toxicity of lead has been well documented and is the incentive behind the Army&#39;s desire to remove it from missile systems. However, this task has proven to be difficult, especially when minimum signature and ballistic integrity of the propellant must be maintained. Typically, when an ingredient is found to control ballistic properties, a loss in minimum signature properties has resulted also. This information was disclosed in an earlier presentation by L. C Warren, “Burning Rate Catalysis of Ammonium Nitrate Propellants”, presented at the Tri-service propellant Formulators Conference, Edward AFB, August 1990. A later presentation by L. C. Warren et al., “High Performance Ammonium Nitrate Propellants for Next Generation Survivable Propulsion Systems”, was presented at 1995 JANNAF PDCS, JPL, Pasadena, Calif. More detailed information is presented in the Information Disclosure Citation filed with this application. 
     Two bismuth compounds, bismuth salicylate and bismuth citrate, have been evaluated as lead alternatives in a propellant formulation similar in theoretical performance properties of currently fielded propulsion systems. Industrially, bismuth is considered the less toxic of the heavy metals. The MSDS for bismuth compounds, bismuth salicylate and bismuth citrate has been furnished by Shepherd Chemical Company. Some forms of bismuth are less toxic than others. One such compound is bismuth salicylate. Bismuth salicylate is used in some medicines and is the active ingredient in the non-prescription medicine Pepto Bismol®, an oral over the counter medication used for relieving upset stomach problems. Both bismuth salicylate and bismuth citrate are readily available and are inexpensive. 
     An object of this invention is to provide a propellant formulation with minimum signature and ballistic integrity of high performance. 
     Another object of this invention is to provide a lead free propellant formulation and a nitroglycerin free propellant formulation, which is environmentally more attractive based on current EPA requirements. 
     SUMMARY OF INVENTION 
     A general description of the bismuth compounds used in the evaluations of this invention is set forth in Table A below. 
     
       
         
               
             
               
               
               
               
             
           
               
                 TABLE A 
               
             
             
               
                   
               
               
                 BISMUTH COMPOUNDS EVALUATED 
               
             
          
           
               
                   
                   
                 Formula 
                   
               
               
                 Supplier 
                 Bismuth Compound 
                 wt. (g) 
                 Density (g/cc) 
               
               
                   
               
               
                 The Shepherd Chemical 
                 Bismuth Salicylate 
                 362 
                 2.36 
               
               
                 Company 
                 C 7 H 5 BiO 4   
               
               
                 SIGMA Chemical 
                 Bismuth Citrate 
                 398 
                 3.46 
               
               
                 Company 
                 C 6 H 5 O 7 Bi 
               
               
                   
               
             
          
         
       
     
     The baseline propellant formulation of this invention is outlined in Table B below. 
     
       
         
               
             
               
               
               
             
           
               
                 TABLE B 
               
             
             
               
                   
               
               
                 BASELINE PROPELLANT FORMULATION 
               
             
          
           
               
                   
                 Ingredient 
                 % 
               
               
                   
                   
               
               
                   
                 ORP-2 
                 7.00 
               
               
                   
                 BTTN 
                 20.17 
               
               
                   
                 TMETN 
                 8.64 
               
               
                   
                 CARBON 
                 0.50 
               
               
                   
                 RDX, 17μ 
                 34.36 
               
               
                   
                 RDX, 4μ 
                 6.24 
               
               
                   
                 HMX, 2.75μ 
                 17.40 
               
               
                   
                 ZrC, 7μ 
                 1.50 
               
               
                   
                 MNA 
                 0.50 
               
               
                   
                 Bi COMPOUND 
                 2.00 
               
               
                   
                 N100 
                 1.69 
               
               
                   
                   
               
             
          
         
       
     
     The propellant binder system consists of the energetic nitramine prepolymer(s) ORP-2 or 9DT-NIDA, plasticized with the nitrate esters BTTN and TMETN, and cured with N 100. Without nitroglycerin, an energetic polymer such as ORP-2 or 9DT-NIDA, is needed to enhance propellant performance impulse to greater than 245 seconds. The elimination of NG is proven to be more beneficial for immediate safety considerations than the elimination of lead. ORP-2 and 9DT-NIDA also enhance propellant burning rates and mechanical properties, two great improvement needs for minimum signature propellants. 
     Initial evaluations centered on determining the effectiveness of various bismuth additives as the sole ballistic modifier (without zirconium carbide stabilizer) in propellant formulations. By themselves neither lead salicylate nor bismuth salicylate will affect significantly minimum signature propellant burning rate properties. However, it was discovered that the addition of zirconium carbide with either ingredient present, resulted in significant enhancement in propellant ballistic properties, in particular lowering propellant burning rate pressure exponent. Bismuth salicylate was equally as effective as lead salicylate or lead citrate in the presence of zirconium carbide for increasing propellant burning rates and reducing burning rate pressure exponent values. Bismuth citrate appeared to be only slightly less efficient than the bismuth salicylate. This could be because the concentration of bismuth in the citrate derivative is less than in the salicylate. 
     During these evaluations an unexpected influence by carbon on the propellant ballistic properties was observed. In this work two different carbons were used, Thermax and Sterling R. The particle size of the carbon black played a significant role in enhancing propellant burning rates and reducing burning rate exponents. Superior ballistic properties were achieved with Sterling R carbon as opposed to Thermax carbon. The average particle sizes of the Thermax and Sterling R carbons are 270 and 60 nanometers, respectively. A similar phenomenon concerning average particle size of the bismuth compounds was observed. When the average particle size of the bismuth compounds was less than 5 microns, the ballistic properties adequate for tactical missile applications were achieved. 
    
    
     BRIEF DESCRIPTION OF THE DRAWING 
     FIG. 1 is a plot of 2% bismuth salicylate and Thermax propellant strand data. 
     FIG. 2 is a plot of 2% bismuth salicylate and Thermax 2×4 motor data. 
     FIG. 3 is a plot of 2% bismuth salicylate and Sterling R propellant strand data. 
     FIG. 4 is a plot of bismuth salicylate and Sterling R propellant 2×4 motor data. 
     FIG. 5 is a mna depletion graph of a 2% bismuth salicylate propellant. 
     FIG. 6 is a mna depletion graph of a 2% bismuth citrate propellant. 
     FIG. 7 is a plot of 9dt-nida propellant strand data. 
     FIG. 8 is a plot of 9dt-nida propellant 2×4 motor burn rate data with burn rate pressure exponent of 0.4. 
    
    
     DESCRIPTION OF PREFERRED EMBODIMENT 
     
       
         
               
               
               
               
             
           
               
                   
                   
               
               
                   
                 Ingredient 
                 % 
                 Notes 
               
               
                   
                   
               
             
             
               
                   
                 polymer 
                 6.00-7.00 
                 1 
               
               
                   
                 plasticizers 
                 28.00-29.00 
                 2 
               
               
                   
                 carbon black 
                 0.50-0.60 
                 3 
               
               
                   
                 nitrocellulose 
                 0.15-0.25 
                 4 
               
               
                   
                 oxidizers 
                 58.00-63.00 
                 5 
               
               
                   
                 ZrC 
                 1.00-1.50 
                 6 
               
               
                   
                 MNA 
                 0.50-0.75 
                 7 
               
               
                   
                 Ballistic additive 
                 2.00-4.00 
                 8 
               
               
                   
                 N100 
                 1.50-1.80 
                 9 
               
               
                   
                   
               
             
          
         
       
     
     Notes: 
     1.0 POLYMERS-ORP-2 or 9DT-NIDA are the preferred polymers. The polymer percentage can be as low as six percent for 9DT-NIDA and seven percent for ORP-2. These are the lower limits for good mechanical properties; higher polymer concentrations may reduce propellant performance, but ballistic properties will not vary greatly. 
     2.0 PLASTICIZERS-A combination of BTTN and TMETN is preferred for performance Isp 245 to 250 seconds. A 70 to 30 percent blend of BTTN and TMETN is preferred with an approximate Pl/Po ratio from 3.3 to 3.7. Desirable properties can be achieved with all nitrate ester plasticizers. 
     3.0 CARBON BLACK—Sterling R carbon used with ZrC and the bismuth compound gave the best ballistic properties in these evaluations. The significant feature of the Sterling R carbon versus Thermax carbon is a smaller average particle size. Other carbons of the same particle size or smaller may give similar results. The average particle size of Sterling R carbon is 70 nanometers versus 270 nanometers for Thermax. The increased surface area over Thermax carbon stabilizes the combustion of the propellant to achieve the desired burn rate pressure exponent between 1000 and 2000 psi. Typically carbon is added at the half percent (0.5%) level. 
     4.0 NITROCELLULOSE-Nitrocellulose is used as a crosslinking agent to shore up propellant mechanical properties. An added benefit is a slight improvement in propellant burning rate. Nitrocellulose percent can vary from 0.15-0.25% for improving propellant mechanical properties. 
     5.0 OXIDIZERS-A combination of RDX and HMX is preferred from 58-63 percent. The particle size distribution of 60%(RDX, 17μ), 30%(HMX, 2.75μ) and 10%(RDX, 4μ) was used for these evaluations. Slight variations in distributions should not change propellant overall results. CL-20 (2,4,6,8,10,12-Hexanitrohexaazaisowurtzitane) (HNIW) can be used for either RDX or HMX and not change overall ballistic properties, significantly. CL-20 would however cause an increase in propellant performance Isp, burning rates and density. 
     6.0 ZIRCONIUM CARBIDE(ZrC)-ZrC in combination with bismuth and carbon is necessary to achieve desired propellant ballistic properties. The average particle size for these evaluations was 7μ. 
     7.0 MNA-Typical percent of MNA added is 0.5-0.75%. When propellant is cured at 70 degrees F less MNA is used up during the usual week long curing process at 140 degrees F. Therefore, service life of propellant containing bismuth catalysts should increase significantly. 
     8.0 BALLISTIC CATALYSTS-Bismuth salicylate or bismuth citrate in combination with ZrC and carbon can be used instead of the lead compounds to achieve desired ballistic properties. The percent can vary from 2-4% of the propellant formulation. The propellant can be cured at ambient without additional cure catalyst for bismuth salicylate. When bismuth citrate is used a cure catalyst such as dibutyltin dilaurate is necessary for ambient cures. 
     9.0 CURATIVE-The preferred curing agent is triisocyanate (Desmodur N100). Polymer cure ratio can vary from 1.1 to 1.3. 
     INGREDIENTS DEFINED 
     Bismuth citrate Salt of citrate acid 
     Bismuth citrate salt of salicylic acid, also called bismuth subsalicylate 
     9DT-NIDA energetic nitramine polymer developed by Thiokol under a MICOM contract 
     ORP-2 energetic nitramine polymer, developed by Olin Corporation 
     BTTN butanetriol trinitrate-plasticizer 
     CARBON Thermax (270 nanometers) and Sterling R (75 nanometers) carbon blacks 
     Ballistic-modifiers bismuth compounds-bismuth salicylate and citrate(less than 5 microns) 
     HMX tetramethylene tetranitramine 
     Ips inches per second 
     MNA N-methyl para nitroaniline-chemical aging stabilizer 
     N100 triisocyanate, curing agent, Desmodur N100 
     RDX trimethylene trinitramine 
     Sterling R carbon black rubber grade (particle size 75 nanometers) supplied by Cabot 
     TMETN trimethylolethane trinitrate-plasticizer 
     ZrC zirconium carbide-ballistic stabilizer 
     PROPELLANT PROCESSING PROPERTIES 
     Some bismuth compounds are excellent catalysts for the isocyanate cure reaction. When used as a cure catalyst only a very small amount(&lt;0.03%) of the total weight of the formulation is required. However, to be effective as a ballistic additive, concentrations greater than two percent by weight in the propellant formulation appear to be necessary. For maximum dispersion the catalyst is usually added after the addition of the oxidizers at the initial mix temperature of 140° F. When the bismuth salicylate was added at 140° F., the potlife of the propellant was significantly less than one hour. Propellant potlife less than twenty minutes was the norm. Reducing the temperature from 140° F. to 70° F. before adding the bismuth salicylate resulted in an increase in potlife to one to two hours. Propellant Potlife is generally defined as the time it takes for the propellant to reach forty kilopoise after the addition of the curing agent. 
     However, when the propellant mixture temperature was lowered to 60° F. before the addition of the bismuth salicylate, a potlife greater than ten hours was achieved. This is the process patent application disclosed and claimed in the concurrently filed application referenced hereinabove. It is postulated that when bismuth salicylate is added at 60° F., the rate at which the bismuth ion is formed is reduced significantly. The hydroxyl-isocyanate reaction rate is dramatically affected by the bismuth ion concentration. Therefore, a dramatic increase in propellant potlife is gained. Potlife data of a gallon mix containing bismuth salicylate is shown in Table 10 hereinbelow. The propellant end of mix viscosity was 3.5 kilopoise at 60° F. Higher propellant solids loadings appear possible without adversely affecting propellant castability at this temperature. 
     The above propellant mixing procedure applies to the use of bismuth salicylate. Bismuth citrate does not accelerate the propellant cure reaction the same as bismuth salicylate. Using the above procedure, dibutyltin dilaurate was necessary for adequate propellant cures with bismuth citrate. Ballistic properties of propellant containing bismuth salicylate are superior to properties of propellants containing bismuth citrate. Because of the processing advantage when using the bismuth citrate, this ingredient shows promise for non-lead containing propellants. 
     PROPELLANT MECHANICAL PROPERTIES 
     Typical mechanical properties of the proposed lead-free propellant are shown in Table 11 hereinbelow. Significant work has been done with Orp-2 polymer by this author and others. The propellant properties as reported are typical for Orp-2 in this type formulation. These propellant mechanical properties are superior to reported properties of a currently fielded propellant in ambient stress, strain and modulus. The propellant mechanical property data reported here is not optimized and may vary slightly when 9DT-NIDA is used. Both pre-polymers ORP-2 and 9DT-NIDA can produce propellants with excellent mechanical properties when used with this combination of ingredients. 
     PROPELLANT COMBUSTION PROPERTIES 
     The strand burning rate data of the ORP-2 propellant containing bismuth salicylate are shown in Table 1. Thermax carbon was used in the initial evaluations. The propellant burning rate properties are comparable to currently fielded propellants. The strand burning rate data are plotted in FIG.  1 . The propellant burning rate curve is relatively flat with an exponent less than 0.3 to 1400 psi. Above 1400 psi the burning rate pressure exponent approaches one. The 2×4 motor burning rate data are shown in Table 2. The 2×4 motor burning rate data are plotted in FIG.  2 . The 2×4 motor data curve is similar to the strand data curve with the exponent break appearing at approximately 1400 psi. This is undesirable for tactical missile systems with an MEOP anywhere above 1300 psi. Typically, minimum signature propellant burning rate pressure exponent breaks occur above 2000 psi. 
     The same propellant formulation was evaluated using the Sterling R carbon. The propellant strand burning rate data are shown in Table 3. The strand burning rate data are plotted in FIG.  3 . Sterling R carbon shifted the burning rate pressure exponent break to above 2000 psi in both the strand and 2×4 motor data. The 2×4 motor data using the Sterling R carbon are shown in Table 4. The 2×4 motor data are plotted in FIG.  4 . The burning rate pressure exponents for the strand and 2×4 motor data are 0.3 and 0.45, respectively. The 2×4 motor data appears to be the same as for the strands. The burning rates are slightly lower which is normal. The trend appears clear that bismuth salicylate and bismuth citrate in the presence of zirconium carbide and Sterling R carbon result in the desired ballistic properties for tactical missile applications. 
     
       
         
               
             
               
               
               
               
               
               
               
               
               
               
               
               
               
               
               
               
             
           
               
                 TABLE 1 
               
               
                   
               
               
                 PROPELLANT GALLON MIX STRAND DATA-THERMAX AND BISMUTH SALICYLATE 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                 PSI 
                  750 
                  900 
                 1000 
                 1100 
                 1200 
                 1300 
                 1400 
                 1500 
                 1600 
                 1700 
                 1800 
                 1900 
                 2000 
                 2500 
                 3000 
               
               
                 Rb 
                 .280 
                 .288 
                  .290 
                  .290 
                  .297 
                  .309 
                  .325 
                  .346 
                  .364 
                  .380 
                  .409 
                  .417 
                  .440 
                  .550 
                  .660 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
               
               
               
             
           
               
                 TABLE 2 
               
               
                   
               
               
                 BISMUTH SALICYLATE AND THERMAX 
               
               
                 2 × 4 MOTOR BURN RATE DATA 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                 Psi 
                  682 
                  914 
                 1117  
                 1136  
                 1151  
                 1199  
                 1346  
                 2305  
               
               
                 Rb, ips 
                 .260 
                 .279 
                 .292 
                 .291 
                 .291 
                 .296 
                 .318 
                 .504 
               
               
                 Nozzle, in. 
                 .300 
                 .269 
                 .247 
                 .247 
                 .245 
                 .241 
                 .237 
                 .229 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
               
               
               
               
               
               
               
               
               
             
           
               
                 TABLE 3 
               
               
                   
               
               
                 BISMUTH SALICYLATE AND STERLING R PROPELLANT STRAND BURN RATE DATA 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                 Psi 
                 750 
                 1000 
                 1100 
                 1200 
                 1300 
                 1400 
                 1500 
                 1600 
                 1700 
                 1800 
                 1900 
                 2000 
                 2500 
                 3000 
               
               
                 Rh 
                  .37 
                   .46 
                   .50 
                   .49 
                   .52 
                   .53 
                  .535 
                   .54 
                   .56 
                   .57 
                   .57 
                  .575 
                   .77 
                   .85 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
             
           
               
                 TABLE 4 
               
               
                   
               
               
                 BISMUTH SALICYLATE AND STERLING R PROPELLANT 
               
               
                 2 × 4 BURN RATE DATA 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                   
                 Pressure, psi 
                  844 
                 1078 
                 1624 
                 1952 
               
               
                   
                 Burn rate, R b , ips 
                 0.38 
                  0.44 
                  0.55 
                  0.57 
               
               
                   
                   
               
             
          
         
       
     
     PRELIMINARY AGING PROPERTIES 
     Another critical propellant property is aging, determined by the depletion rate of N-methyl para nitroaniline, MNA. MNA is added to the propellant to scavenge nitrogen dioxide (NO 2  ) released from the nitrate esters BTTN and TMETN. If NO 2  accumulation is left unchecked, a loss of propellant mechanical and safety properties is the result. MNA scavenges the NO 2  gas to prevent this from occurring. Preliminary results of MNA depletion rates were determined for a propellant containing bismuth salicylate and bismuth citrate as shown in Table 5 and Table 6 below. See FIG.  5  and FIG. 6 for the graphical presentation of the data. Points a, b, c, and d represent MNA @50° C., 60° C., 70° C., and linear MNA @70° C. respectively for FIG.  5  and FIG.  6 . The results are excellent. From these findings neither the bismuth salicylate or citrate accelerate the decomposition of the nitrate esters significantly. The results were comparable to previous data of propellants containing lead compounds and the results are comparable. 
     
       
         
               
             
               
               
               
               
             
           
               
                 TABLE 5 
               
             
             
               
                   
               
               
                 MNA Depletion for 2% Bismuth Citrate Propellant 
               
             
          
           
               
                   
                 % MNA 
                 Times in Days 
                 Temperature 
               
               
                   
                   
               
               
                   
                 0.31 
                 28 
                 50 
               
               
                   
                 0.30 
                 28 
                 60 
               
               
                   
                 0.28 
                 14 
                 70 
               
               
                   
                 0.26 
                 28 
                 70 
               
               
                   
                 0.25 
                 42 
                 70 
               
               
                   
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
             
           
               
                 TABLE 6 
               
             
             
               
                   
               
               
                 MNA Depletion for 2% Bismuth Salicylate Propellant 
               
             
          
           
               
                   
                 % MNA 
                 Times in Days 
                 Temperature 
               
               
                   
                   
               
               
                   
                 0.38 
                 28 
                 50 
               
               
                   
                 0.37 
                 28 
                 60 
               
               
                   
                 0.35 
                 28 
                 70 
               
               
                   
                 0.34 
                 42 
                 70 
               
               
                   
                   
               
             
          
         
       
     
     EVALUATION OF 9DT-NIDA POLYMER 
     9DT-NIDA, like ORP-2 is a nitramine polymer. Both give similar properties when used in the formulation as described previously for evaluating ORP-2. The propellant performance, ballistic, processing, mechanical, signature and aging properties are very similar. The 9DT-NIDA propellant bum rate data are outlined in Table 7 and Table 8. Data plots are shown in FIG.  7 and FIG.  8 . Propellant burning rates and rate exponent values are close to the same as those reported for ORP-2 propellant. Ballistic properties are also adequate for tactical missile applications. Other 9DT-NIDA propellant properties such as mechanical, aging and signature are expected to be the near the same or better than with ORP-2 polymer. 
     
       
         
               
             
               
               
               
               
               
               
               
               
               
               
               
               
             
           
               
                 TABLE 7 
               
               
                   
               
               
                 PROPELLANT GALLON MIX STRAND DATA-9DT-NIDA/STERLING 
               
               
                 R/BISMUTH SALICYLATE/ZrC 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                 PSI 
                 1000 
                 1100 
                 1200 
                 1300 
                 1400 
                 1500 
                 1600 
                 1700 
                 1800 
                 1900 
                 2000 
               
               
                 Rb 
                  0.40 
                  0.42 
                  0.44 
                  0.46 
                  0.48 
                  0.49 
                  0.50 
                  0.51 
                  0.52 
                  0.53 
                  0.64 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
               
             
           
               
                 TABLE 8 
               
               
                   
               
               
                 PROPELLANT GALLON MIX 2 × 4 MOTOR 
               
               
                 DATA-9DT-NIDA/STERLING R/BISMUTH 
               
               
                 SALICYLATE/Zrc 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                   
                 PSI 
                 1161 
                 1317 
                 1516 
                 1671 
                 1865 
               
               
                   
                 Rb, ips 
                  0.42 
                  0.45 
                  0.48 
                  0.49 
                  0.51 
               
               
                   
                   
               
             
          
         
       
     
     PRELIMINARY SIGNATURE EVALUATION 
     The propellant formulation evaluated for signature contained two percent bismuth salicylate, and one and one half percent zirconium carbide. These two ingredients are expected to produce smoke during the combustion process. Four 2×2 motors were fired in the Propulsion Laboratory&#39;s smoke chamber facility. The average transmittances in the photopic and infrared regions are ninety four and ninety eight percent, respectively. Transmittance greater than 90 percent is considered passing for minimum signature classification. The data summary of the four 2×2 motors fired in the smoke chamber facility is shown in Table 9. 
     
       
         
               
             
               
               
               
               
               
               
               
             
           
               
                 TABLE 9 
               
             
             
               
                   
               
               
                 BISMUTH SALICYLATE PROPELLANT SIGNATURE DATA 
               
             
          
           
               
                   
                 Test # 
                 1 
                 2 
                 3 
                 4 
                 Average 
               
               
                   
                   
               
               
                   
                 Photopic, % T 
                  96 
                 91 
                 95 
                 93 
                 94 
               
               
                   
                 Infrared, % T 
                 100 
                 95 
                 99 
                 99 
                 98 
               
               
                   
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
               
             
           
               
                 TABLE 10 
               
             
             
               
                   
               
               
                 GALLON MIX POTLIFE DATA OF 
               
               
                 BISMUTH SALICYLATE PROPELLANT 
               
             
          
           
               
                 Time, hrs 
                 0 
                 1 
                 3 
                 4 
                 &gt;18 
               
               
                   
               
               
                 Viscosity, Kp (amb.) 
                 3.5 
                 3.0 
                 4.5 
                 4.5 
                 firm 
               
               
                   
               
             
          
         
       
     
     
       
         
               
             
               
               
               
               
               
             
           
               
                 TABLE 11 
               
             
             
               
                   
               
               
                 MECHANICAL PROPERTY DATA OF 
               
               
                 TYPICAL ORP-2 PROPELLANT 
               
             
          
           
               
                   
                   
                   
                   
                 Corrected 
               
               
                 Temperature 
                 Stress 
                 Strain 
                 Modulus 
                 Stress 
               
               
                 ° F. 
                 Psi 
                 % 
                 Psi 
                 Psi 
               
               
                   
               
               
                 140 
                 38 
                 220 
                 111 
                 109 
               
               
                  75 
                 66 
                 271 
                 169 
                 245 
               
               
                 −40 
                 650  
                  34 
                 4667  
                 1108  
               
               
                   
               
             
          
         
       
     
     The advantages of environmentally friendly high performance lead-free propellant formulations using bismuth citrate or bismuth salicylate as replacements for lead citrate or lead salicylate are recognized. Both bismuth compounds are readily available and are inexpensive. The optimum concentrations of the bismuth compounds are the same as for lead compounds; therefore propellant performance levels are not adversely affected. When using bismuth salicylate or bismuth citrate ambient cures are possible eliminating the need for expensive ovens to cure propellants at 140 degrees F. Ambient propellant cures will eliminate a safety hazard during the propellant curing process, and will increase propellant service life. Both processes could result in substantial cost savings to the Army over the long term.