Army Research Laboratory 

Aberdeen Proving Ground, MD 21005-5066 

* U-l-R-2326 September 2000 

Minimizing Life-Cycle Costs of Gun 

Propellant Selection Through 

Model-Based Decision Making: 

A Case Study in Environmental I 

Screening and Performance Testing 

Ronald D. Anderson and Betsy M. Rice 

Weapons and Materials Research Directorate, ARL 

Approved for public release; distxibution is unlimited. 
Abstract 

This work demonstrates the first phases of a newly proposed gun propellant formulation 

process that will minimize life-cycle costs through science-based design. This new approach 

proposes maximal use of modeling and simulation in the earliest phases of the developmental 

cycle to screen candidate formulations, resulting in elimination of probable poor performers and 

identification of the most promising test candidates. The screening and identification of 

propellant formulations are demonstrated under the assumption of a specific weapon platform 

and user requirements. The process of selecting a propellant for the assumed gun system 

application has been distilled into measurable steps, leading from a set of candidate materials, 

through logical and numerical filters, to a shorter list of energetic materials demonstrated as 

viable weapon platform choices. Environmental filtering and performance modeling are used 

to screen propellants through a well-defined sequence of tests designed to weed out materials not 

meeting safety, energy, or manufacturability standards. Because much of the testing is performed 

by computer modeling, the gun systems and energetic materials need not be present (or even 

existent) in order to be described and matched against performance requirements for future 

applications. The calculations demonstrate that utilizing computer models rather than physical 

testing in the early developmental stages of the formulation process can produce enormous 

savings in labor, material, and environmental costs, along with a tremendous reduction in the 

time required to select a “best candidate” propellant. 
Acknowledgments 

This work was supported by the Strategic Environmental Research and Development 

Program under Project CPO/S. The authors would like to thank Dr. Randall J. Cramer of the 

Naval Surface Warfare Center, Indian Head Division, for his guidance and valuable discussions. 
hl-ENl'IONALLYLEFTBLANK. 

iv 
1. Introduction .*..,...~..~......*.~.....~~.........~~.~.....~~.*.... . ..*.*....*......*.......**.*..*.....**.* . . . . . . ...*.*.. 1 

2. Performance Testing Description . . . ..*............*...........*.........*..~~.........*....*.....*...*.... 3 

2.1 Propellant Database ............................................................................................. 3 

2.2 Ingredient Environmental Screening ................................................................... 3 

2.3 Tbermodynarnic Properties ................................................................................. 3 

2.4 Estimate of Available Energy .............................................................................. 5 

2.5 Propellant Grain Geometry ................................................................................. 5 

2.6 Low-Zone Charge Applications .......................................................................... 5 

2.7 Propellant Suitability ........................................................................................... 6 

3. Example Performance Screening .. . . . . . . . . . ..*~.....*..*............*......*......*.*...*.......*........*. 6 

3.1 User Requirements .............................................................................................. 6 

3.2 Propellant Database ............................................................................................. 7 

3.3 Ingredient Environmental Screening ................................................................... 7 

3.4 Thermodynamic Properties ................................................................................. 9 

3.5 Estimate of Available Energy .............................................................................. 11 

3.6 Propellant Grain Geometry ................................................................................. 12 

3.7 Propellant Zoning ................................................................................................ 17 

3.8 Propellant Suitability ........................................................................................... 17 

3.9 Next Step ............................................................................................................. 19 

4. 

5. 

6. 

.Table of Contents 

Acknowledgments-~ . . . . . . . . . . *. . . ..~~.....~~.*..*.~........*...~~......~..*. . . . . . . ..*....*....*....e..*..*....*.. 111 

List of Figures ..*......**..*...**...~.....,.*............ ..~.....~*..*.~~.........*.~........~...*.......~..*....-....~. vii 

List of Tables . . . . . . . ..*...~.*.....*............*.**....*.. . . . . . . . ..~.........*.*.........*.*...*.~...*.........~-...... vii 

Lessons Learned atid Tools Needed ..~.~...*,.....~..~...~..l*~...~..........**~..~...........*..~...~..*~ 20 

Summary ~...~.......*...~..~~.....**..~~~.....~...* . . . . . . . . . . . . ..**............**..**.*........* . . . . . . ..*.*.*~~........*.. 21 

Appendix A: BLAKE Calculations for Generic Ml Propellant ..*............... e . . . . . 27 

Appendix B: IBHVG2 Constant-Pressure Calculations Using M26El 

Propellant . ..*.............~....~.......*......~.~....~.~*. ..*.....................*..............* 33 

V 
Appendix C: IBHVG2 Performance Calculations for M30Al Propellant . . . . . . . 43 

Appendix D: Performance Calculations Varying Charge Mass of M30Al 

Propellant . . . . . ..~......*.......*.....*...**........*......*..*..**.....*...**.*.......**.......... 69 

Distribution List *.**..............*..*.........*...*.............~~**....**..~..........~.~**....... ...........~.. 85 

Report Documentation Page .. ..~.~...............** ........*.*.*..............*......***.............*~..~.... 87 

vi 
List of Figures 

Figure Page 

1. Master Optimization Algorithm ..*......*......*....*.......*. . . . . . . . ..**...*..~.....~.**.....~.............~.. 4 

2. Propellant Grain Types . ..*...........**..**..**......~.**.............~.. . . . . . . . . . ..****...~*.*.....***.*........... 6 

List of Tables 

Table 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

8. 

Ingredients of Propellants *.....*..*...**.......*.*..***....*.*. . ..~......*..........~*.~..~~..**.....~* *.....*..**. 

Thermodynamic Properties of Propellants . . . . . . ..*..***.*.~...~.......**.*..............~..*......*...... 

Ingredients and Their Relative Percentages for Ml Propellant ..*............*..........*.*...~ 

Ml Thermodynamic Data Calculated by BLAKE and From Virginia Reference..... 

Constant-Pressure Calculations of Exit Velocity f,.~~..~.......~.**........~.~...~....*..*..,*~......~ 

Computed M30Al Simulations With Different Gram Geometries and Web Sizes.. 

M30Al Charge Weight Variations for 19-Perf Granulation .-......... ** . . . . . . . . . . . . . . . . . . . . . 

Summary of Gun System Study Performance Calculations ..*...*..*....~..~****..*..*.~.~...~.. 

Page 

8 

9 

10 

10 

12 

14 

15 

16 

9, Charge Zoning Applications With 19-Perf JA2 Propellant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 

vii 
mN’TTONaLY LEFT BLANK. 

.,. 

Vlll 
1. Introduction 

The attainment of proposed future war-fighting capabilities [l] will depend on the 

performance of new weapons platforms and the energetic materials that are used by them. In 

order to efficiently and effectively meet the requirements of the future weapons systems, a 

mechanism must be in place for the rapid design and manufacture of advanced chemical fuels. 

Presently, there is no single formal procedure in place for the design and development of a new 

propellant; rather, the overall procedure includes any number of steps leading to deployment of a 

new energetic material. The inclusion of steps varies among individuals according to 

experience, philosophy, and training. Also, the overall procedure relies heavily on 

experimentation and measurement and often proceeds through lengthy cut-and-try processes. 

Significant waste sueams in terms of time, manpower, and materials are generated from 

implementation of such unstructured developmental procedures, and they often exact 

unacceptably large time and environmental penalties. Current fiscal realities and increased 

environmental constraints necessitate a revision in existing strategies for energetic material 

design, development, and manufacture. The most obvious revision that must be made is to 

minimize the waste created during the process. In order to do this, a formal mechanism must be 

established to estimate the waste associated with each part of the procedure and, thus, assign 

costs to each step in the mechanism. The assignment of costs will depend upon the priorities that 

drive the development of the material and could include pecuniary, environmental, or 

performance considerations. Then refinements to the steps and overall mechanism can be made 

to minimize the cost and maximize the efficiency of the process. 

The Strategic Environmental Research and Development Program (SERDP), in recognizing 

the need to counter extreme waste generation in energetic materials development, is supporting a 

project whose goal is to establish a new developmental procedure that will minimize waste 

generation throughout the entire process. The project is currently limited to gun propellant 

formulations; however, the .same developmental procedures could be applied to other classes of 

energetic materials, including rocket propellants, explosives, or pyrotechnics. The 

developmental procedure that is being advanced under this project is model-based. In other 

1 
words, the goals of the project can ideally be achieved through replacement (where possible) of 

measurement and testing with computer modeling or through optimal reduction of 

experimentation by the exercise of predictive methodologies. This new approach to gun 

propellant formulation is outlined in a parallel report [2] that describes a science-based activity 

where the earliest possible steps utilize modeling and simulation of all stages that might occur 

during development of a gun propellant. Although modeling of the complete process cannot be 

implemented at this time since there are several areas in which models do not currently exist, the 

work described here is an attempt to exercise the developmental procedure using available 

models. 

Part of the propellant assessment involves determination of whether its performance in a 

cannon will meet the military requirements of projectile velocity (which governs effective range 

of the weapon) within the limitations of pressure and acceleration peculiar to the gun system and 

projectile. Predictive performance models [3-S] have been available in the military for many 

years and are well-suited for computing expected solutions of the interior ballistic cycle for 

known (measurable) guns and for gun systems as yet only imagined. These computer models 

require a priori information describing the physical parameters of the gun chamber and tube, of 

the projectile, of the propellant charge, and of critical interactions during the gun firing. This 

report explains how to use available computer programs to model the performance testing of a 

proposed set of gun propellants in a large-caliber artillery weapon. Additionally, since the 

proposed developmental approach incorporates environmental screening procedures at each 

stage of the development process, we have attempted to include such in our demonstration. A 

prototypical simulation was performed in which minimal user requirements for maximum 

pressure and minimum muzzle energy were assigned for a specific weapon platform using a set 

of 10 existing propellant formulations. Using performance modeling and database information 

on environmental hazards, 6 of the 10 formulations were eliminated as candidates due to 

environmental constraints and failure to meet energy requirements. This demonstration shows 

that application of computer models based on scientific principles during gun propellant design 

and formulation will result in cost savings through decreases in labor, equipment, and 

environmental issues. 

2 
3 

2. Performance Testing Description 

2.1 Propellant Database. A generalized flow chart of the necessary steps in testing the 

performance of a new gun propellant is shown in Figure 1, representing the early screening steps 

of the science-basedesign process outlined in the study of Miller, Rice, and Cramer [2]. The 

Master Optimization Algorithm (MOPTA) starts with a database of new and/or known 

propellants to be tested and screened for suitability to a “virtual gun’system.” This gun system 

may be a computer model of a known weapon or a model of a completely theoretical gun system 

to be analyzed for possible manufacture and deployment. From its chemical and thermodynamic 

description, each propellant is to be characterized in the weapon without ever having physically 

been placed in the chamber, or perhaps without ever having been actually created in a laboratory. 

The portion of the algorithm to be described in this report is highlighted with a gray background 

in Figure l-the other blocks contain steps where either models are not yet available or else the 

authors do not have the expertise necessary to use current programs or databases. 

2.2 Ingredient Environmental Screening. Those propellants containing known 

environmental hazards may be screened out of the performance testing process here. Legacy 

propellants may include ingredients that have been identified, in the years since original 

production, as carcinogens or as substances toxic to one or more environmental systems. This 

could include not only the ingredients themselves but also the manufacturing processes involved 

in creating the material. 

23 Thermodynamic Properties. Each propellant must be described by a suite of 

measurable physical parameters in order to be acceptable to the interior ballistic (IB) computer 

programs. Required values include isochoric flame temperature, density, internal chemical 

energy, and others depending on which computer code will be used for performance modeling. 

Several programs are available to estimate these parameters (except for density and burning rate) 

from the initial chemical description. These programs include CHEETAH [6], BLAKE [7], and 

TRAN72 [S] and CEA [9]. Part of the output generated by these codes can include a list of 

combustion products (both gaseous and condensed), which can be scanned to determine 

3 
I USER REQUIREMENTS 

MuiTle vemty, pojecble design, gun design, 

excid wlnerabiltv and 8ntironmen$r consbhts 

. 

MASTER OPTlMlZAflON ALGORITHM -b I!?..mm Cm-I- 

-,;fq [rziE&-[ 

--~ltiERMED/ATE EVALUATION MODELS 

Figure 1. Master Optimization Algorithm. 
if toxic or corrosive materials are predicted. Propellant density and burning rates must be 

physically measured or estimated from other sources. 

, 

2.4 Estimate of Available Energy. Given a gun system model and the thermodynamic 

properties of each propellant, an estimate can be made of how much energetic material can be 

placed in the gun chamber. A calculation can then be made to determine if enough kinetic 

energy can be transferred to the projectile in order to meet the exit velocity requirements. By 

assuming that the highest allowable pressure is continuously maintained by propellant 

combustion (until the charge is exhausted), an estimate of maximum achievable projectile exit 

velocity can be calculated. If this velocity does not meet or exceed user requirements, then the 

propellant will not be a candidate for further testing. Computer codes that can estimate this 

maximum are IBHVG2 [lo] and CONPRESS [ll]. 

2.5 Propellant Grain Geometry. Actual energy transferred to a projectile will be 

somewhat less than that calculated in the previous step because propellant grain design cannot 

provide a continuous, unwavering pressure level for the life of the burning charge. Standard 

grain geometries (lPperf, 7-per& and single-perf, shown in Figure 2) can be parametrically 

computed and tested within the gun system model. In general, a multiperforated gram design is 

more efficient in transferring energy to a projectile; this rule of thumb may be untrue for certain 

“virtual” gun systems where databases may be varied to experiment with nontraditional 

dynamics in chamber sizes, projectile/bore interactions, and other physical parameters. Interior 

ballistic calculations can determine if one or more propellant grain designs used as charges in the 

real (or future) gun system can meet requirements for muzzle energy and complete charge 

burnout within maximum pressure limitations. A first-pass IB program is IBHVG2; if 

predictions of pressure waves within the gun chamber are required, then XNOVAKTC [12] or 

NGEN [ 131 may be used. 

2.6 Low-Zone Charge Applications. Artillery guns are routinely loaded with a 

less-than-maximum charge when targets are located at relatively short ranges. These “zoned’ 

applications allow optimum trajectories for higher kill probabilities. Lowest-zoned charges are 

5 
19 Peti. 7 Perf. 1 Peff. 

Y 

Web 

Figure 2. Propellant Grain Types. 

still required to bum completely before the projectile exits the gun muzzle; unburned and 

partially burned propellant particles and gases can be major causes of secondary muzzle blast 

and flash. If low-zone applications are defined, then the grain geometry meeting minimum 

energy requirements at maximum charge weights must still show complete burnout when used at 

lower loading densities. The same IB programs that previously calculated acceptable propellant 

grain geometries may also be used here. 

2.7 Propellant Suitability. Other conditions may screen out propellants that meet muzzle 

energy requirements. Cost, manufacturing limitations, burning temperature (a major factor in 

gun tube life expectancy), grain size, or any number of user-defined stipulations may preclude 

propellants from final consideration. More likely, the list of remaining propellants will be 

ranked according to importance of these additional factors. 

3. Example Performance Screening 

3.1 User Requirements. As a test system, the Navy S-inch 54-caliber gun was chosen to be 

the vehicle for exercising the propellant performance analysis. User-supplied guidelines 

included a maximum pressure limitation of 65 ksi (448 MPa) and a minimum muzzle energy of 

6 
18 MJ with a 1 lo-lb (49.9 kg) projectile. From the kinetic energy formula (KE = ‘/z Mv2), it can 

be determined that projectile velocity needs to be at least 848 m/s to meet the requirement. A 

general description of the weapon specifies a chamber volume of approximately 0.015 1 m3 

(919 in3) and a projectile travel of 6.84 m (269 inches). 

3.2 Propellant Database. A mixture of old and new propellant formulations, from both 

Army and Navy sources, provided a well-rounded sample for the analysis. All propellants are 

real-no theoretical materials have been added to the study, although it certainly could be done 

in further tests. The standard Army propellants include Ml, MlO, M26E1, M30A1, M31E1, and 

JA2; Navy propellants are NACO, EX99 (called LOVA in the reference noted in Table l), 

HELP42, and BAMO/AMMO (abbreviated as BAMO in the rest of this report). No particular 

method was used for propellant selection other than an attempt to include the several classes 

(single-base, double-base, and triple-base propellants), along with some newer formulations not 

fitting neatly into such descriptions. 

3.3 Ingredient Environmental Screening. Table 1 shows the proposed propellants and 

lists their ingredients. A quick scan reveals’ that NACO contains lead carbonate (PblC&)-a 

known toxic substance and suspected carcinogen (141. For this reason, NACO was dropped 

from further analysis. (If a cost of manufacture with suitable biohazard controls and increased 

demilitarization expenses would be computed, then such a material could be included in the 

complete performance appraisal; the extra factors would be added to a final figure for overall life 

cycle costs.) 

L 

Dinitrotoluene (DNT) is an ingredient of the Army Ml propellant. The International 

Chemical Safety Card (ICSC 0727) [ 151 describes this substance as able to be absorbed through 

human skin and ingested through inhalation of fumes when it is heated. For humans, it is an 

irritant to the eyes and skin and may cause effects on the central nervous system, cardiovascular 

system, and blood. It is also extremely toxic to aquatic organisms. The environmental costs 

from DNT can be very high; as an example of the type of chemical ingredient to be avoided, 

mixtures with DNT (specifically Ml) will be removed from the list of propellants under 

consideration. 

7 
Table 1. Ingredients of Propellants 

The ingredient definitions in Table 1 and in text are as follows: 

l 

. 

. 

. 

l 

. 

. 

l 

. 

. 

. 

. 

l 

l 

. 

. 

. 

l 

. 

. 

. 

. 

. 

l 

AKAR2 

ALC 

AMMO 

BAMO 

BDN-PA 

BDNPF 

BS 

C 

CAB 

DBP 

DEGDN 

DNT 

DPA 

EC 

H20 

KS 

MGO 

NCxx.yy 

NDPA 

NG 

NQ 

PB2C04 

RDX 

Akardite II 

Ethanol (ethyl alcohol) 

Azidomethylenemethyl oxetane 

Azidomethyl oxetane 

Bisdinitropropyl acetal 

Bisdinitropropyl formal 

Barium sulfate 

Graphite 

Cellulose acetate butyrate 

Butyl phthalate 

Diethyleneglycol dinitrate 

Dinotrotoluene 

Diphenylamine 

Ethyl centralite 

Water 

Bisdihydrazinotetrazine 

Potassium sulfate 

Magnesium oxide 

Nitrocellulose with a nitration percentage of xx.@% 

2ktrodiphenylamine 

Glyceryl @initiate 

Nitroguanidine 

Basic lead oxide 

Cycle-1,3,5-trimethylene-2,4,6-trinitramine 

8 
I 3.4 Thermodynamic Properties. The U.S. Army Research, Development, and Engineering. 

Center (ARDEC) Report “Interior Ballistics Firing Data Library of Closed Breech, Single 

. Combustion Chamber Tank Guns, Artillery Guns and Howitzers Cannon,” by author Frank J. 

Virginia, Jr. [20], is a valuable source of existing military propellant data including many 

measured burning rates. All data are taken from testing of individual propellant lots. A second 

reference is the chapter “Thermodynamic Properties of Military Gun Propellants” written by E. 

Freedman in the book Gun Propulsion Technology [14], from which many of the ingredient 

listings in Table 1 have been taken. The data in this reference pertain to generic compositions 

rather than the variations found in individual lots of propellant. 

Table 2 contains thermodynamic values required to model the remaining propellants. As 

shown, there is a wide range of isochoric flame temperatures (from lowest at 2,555 K to highest 

at 3,410 K). Estimated temperature within the gun chamber will affect modeling of product gas 

expansion due to the (simplified) nonideal equation of state p(V-b)=RT [2 l], where T is a direct 

factor in the pressure calculation; in turn, the force of pressure on the base of the projectile will 

govern acceleration through F=ma. Propellant burning rates will also be a major factor; rates in 

this study were gamed either from the aforementioned Virginia reference or from other sources 

as noted in Ahneyda [ 183 and Cramer [ 19 3. The propellant property labeled as Force in Table 2 

is a measure of the energy contained in a unit weight of material. 

Table 2. Thermodynamic Properties of Propellants 

9 
If there were no published or experimental thermodynamic values, computer programs are 

available to calculate estimates. CHEETAH, BLAKE, and TRAN72 have all been used for this 

purpose. As an example, the formulation for Ml (extracted from the Freedman chapter, and 

shown in Table 3) has been used for an input to the BLAKE program. The output is reproduced 

in Appendix A; the thermodynamic values are listed in Table 4, along with comparable data from 

the Virginia report. The fluctuation of values is not unexpected because any particular lot of Ml 

may vary slightly from the composition of the generic propellant-manufacturing methods are 

not so precise as to guarantee final composition in a production lot of propellant to within a 

fraction of a percent. 

Table 3. Ingredients and Their Relative Percentages for Ml Propellant 

Table 4. Ml Thermodynamic Data Calculated by BLAKE and From Virginia Reference 

Source 1 Lot Number 1 Gamma ) Temperature 1 Covolume 1 Force 1 6) (cm3k> (J/g) II Blak(_ t , (Generic) 1.2675 2,447 1 1.105 I 919.2 

Virginia 1 JAN-P-369 1 1.2593 1 23413 I 1.1044 I 911.7 I 

Part of the calculation of thermodynamic parameters includes estimation of final combustion 

gases and their relative amounts. A section of Appendix A titled “Constituent Concentrations” 

shows gases (and possible solid or liquid products) expected to be created by each mole of 

burned energetic material. If relatively large amounts of toxic or corrosive products are noted, 

the propekurt could be dropped from further analysis or else flagged for special consideration 

later in the study. 

10 
The computation of burning rate parameters is not yet so straightforward as is the case with 

thermodynamic values, since there is no computer program to calculate rates fiorn chemical 

composition. Obviously the best source is through experimental data from closed-bomb analysis 

of the actual propellant [22-241. Estimates of burning rates and propellant densities could be 

taken from a member of the “family” of propellants if the formulation of the unknown material is 

similar (within a percentage point or two) to the major ingredients of a known propellant, but the 

user should he aware that it is only an estimate and needs to be proven through experimental 

means. 

3.5 Estimate of Available Energy. IBHVG2 computations were used to evaluate the 

potential energy of each propellant in the gun system model. An assumption made for this step 

was that there would he a constant charge weight for the various energetic materials. Since most 

fielded granular charges have maximum loading densities (amount of propellant mass per unit 

chamber volume) in the range of 0.80 g/cm3 to 0.90 g/cm3, a suitable value for this study was 

chosen at 0.85 g/cm3 so that the interior ballistics program now has all the necessary parameters 

to proceed with a constant-pressure calculation. The purpose of this step is to quickly determine 

whether the charge could meet the minimum requirement of projectile exit velocity while 

keeping chamber pressure no higher than the user-defined maximum. The program artificially 

ties breech pressure to a given value (by converting the necessary amount of propellant to gas at 

each time step) until the charge is completely burned; then the gases are allowed to continue 

expanding (and accelerating the projectile) until maximum travel is accomplished. This process 

approximates what would be the perfect combination of propellant surface area and burning rate 

in order to transfer maximum energy to the projectile. CONPRESS does not require estimates 

for either grain geometry or burning rate; IBHVG2 requires either burning rate or grain 

geometry; although this is just a formality-both can be made to vary in order to complete the 

calculation. 

Computed projectile exit velocities using IBHVG2 are listed in Table 5 for each of the 

remaining candidate propellants. The user-required velocity is 848 m/s; each velocity in the 

table is compared to that value via a percentage of minimum requirement. All considered 

11 
Table 5. Constant-Pressure Calculations of Exit Velocity 

II ~ Propellant I Exit Velocity Comparison 11 

propellants except M3 1El attained over 100% of minimum and will be passed on to the next step 

in the study. 

A sample output from the constant-pressure computation for M26El is included as 

Appendix B of this report. 

3.6 Propellant Grain Geometry. A parametric feature allows lBHVG2 to vary propellant 

gram dimensions in order to calculate how each geometry will perform in the modeled gun 

system. By adjusting one grain measurement (in this case the web, or bum-through distance 

between grain perforations and between the outer grain surface and closest perforations) the 

program can compute entire ballistic cycles for a series of grain sizes and can find the maximum 

pressure and the expected projectile exit velocity for each situation. Appendix C is the printout 

from the performance calculations for M30Al; it includes a table of input and output values for 

each set of dimensions. A short summary of that information is shown in Table 6, where the 

computed maximum pressure is closest to 448 MPa at a web size of 3.06 mm for the grain with 

19 perforations; for the 7-perf grain the targeted pressure is reached at a web size of 3.38 mm; 

the single-perf simulations show maximum pressure of 448 Mica at the web thickuess of 4.72 

mm. Projectile exit velocities are 861 m/s, 856 m/s, and 812 m/s, respectively, showing that the 

multiperforated grains transferred more energy to the projectile than did the mono-perforated 

grain. Both the 19-per-f and 7-perf solutions exceeded minimum required projectile velocity, 

12 
while the single did not. Other grain dimension sizes (length 18.3 mm and perforation diameter 

0.457 mm) were held constant during the parametric variations of we&this means the 

computed grain diameter of the 1Pperf solution is 

3.06 * 6 + 0.457 * 5 = 20.6 mm, 

which would make the grain length slightly shorter than its width. By increasing the perforation 

diameter, the gram could be longer (perforation length is restricted by the ability of combustion 

gases to escape confinement, dependent on diameter and expected burning rates of the 

propellant)-but this is an exercise best left to expert ballisticians. For current purposes, it is 

enough to realize that the multiperforated M30Al grains can satisfy system requirements. 

Table 6 also contains information about pressure felt on the projectile base at the time of 

muzzle exit. The W@Exit” column is an estimate of the mass fraction burned at projectile exit. 

The last column is an estimated length of projectile travel when computed charge burnout 

occurs. Jn the bottom two rows of single-perf data, the charge is not expected to bum completely 

by the time the projectile exits the gun muzzle; this could be a clue to the possibility of 

unacceptable secondary muzzle blast and flash should the charge consist of this grain geometry. 

For the 19-perf granular solution in Table 6, projectile travel is only slightly more than 2/3 

maximum allowable-suggesting that there is yet more flexibility in charge manipulation in 

order to get even higher exit velocities within user limitations. For example, with a slightly 

larger loading density (assuming more propellant can be loaded into the chamber) and a larger 

grain web in order to keep down the maximum pressure for the increased charge, the results are 

as in Table 7. As charge mass increases from 12.50 kg to 13.50 kg, the web size is increased 

from 3.0168 mm to 3.3527 mm in order to keep maximum pressure at the 448~Mica limitation. 

(Increased grain web size results in a lower surface-to-mass ratio; thus the pressure peak can be 

maintained even though the greater charge mass transfers more energy to the 

projectile-assuming all the propellant still burns out within the gun tube.) Loading densities for 

the different charge weights are printed in the second column. Values in the right-most column, 

13 
Table 6. Computed M30Al Simulations With Different Grain Geometries and Web Sizes 

14 
Table 7. M30Al Charge Weight Variations for 19-Perf Granulation 

Charge Loading 

Weight Density Web 

(kg) (g/cm3> Cm@ 

12.50 0.838 3.017 

12.75 0.855 3.097 

13.00 0.872 3.179 

13.25 0.888 3.264 

1350 0.905 3.353 

Maximum Exit 

Pressure Velocity Z Trav @ B-0. 

(MM Ws) (m> 

448 857.1 1.0 4.410 

448 862.4 1.0 4.473 

448 867.3 1.0 5.144 

448 871.6 1.0 5.561 

448 875.2 1.0 6.070 

projectile travel at the point of charge burnout, grow larger as the charge weight and web size 

increase-since there is no change in maximum pressure it requires a longer burning cycle to 

completely consume the charge. The lBHVG2 computation for this study is in Appendix D. 

For direct comparison of the different propellants, the major analysis kept a constant loading 

density of approximately 0.85 g/cm3 for the gun simulation. The results are summarized in 

Table 8-each propellant is listed with the three grain types, their corresponding web sizes for 

448 MPa maximum pressure, and the calculated projectile exit velocity in each situation. 

Propellant types with a superscript “a” after the name included at least one granulation satisfying 

the minimum user requirements. M30A1, JA2, and EX-99 each met the velocity goal with one 

or more multiperf granulations, while BAMO was the only propellant type to qualify with all the 

grain types. The rest of the formulations, although they all had potential for 848 m/s as shown in 

the constant-pressure calculations, could not reach that level when simulated as a standard charge 

consisting of single-, 7-, or 1Pperf grams. BAMO exhibited the highest computed velocity in 

both constant-pressure and granular configurations; JA2 was the next-best computed velocity in 

both simulations. 

c 

Unlike the majority of propellants listed in Table 8, EX-99 shows higher computed velocities 

for the 7-per-f grain type than for the 19-perf. This is because of “two-tiered” burning rate data 

and their effect in the gun model. Many IB programs (including lBHVG2) represent the 

15 
Table 8. Summary of Gun System Study Performance Calculations 

Propellant 

Ml0 

M26El 

M30Ala 

JA2” 

BAMO’ 

HELP-42 

EX-99a 

19-P& 

844mfs 

(2.56 mm) 

836 m/s 

(3.48 mm) 

861 m/s 

(3.06 mm) 

875 m/s 

(4.42 mm) 

881 m/s 

(3.13 mm) 

807 m/s 

(0.883 mm) 

845 m/s 

(2.29 mm) 

Grain Geometry 

7-Perf 

841 m/s 

(2.76 mm) 

835 m/s 

(3.76 mm) 

856 m/s 

(3.34 mm) 

867 m/s 

(4.91 mm) 

877 m/s 

(3.47 mm) 

813 rnls 

(0.980 mm) 

858 m/s 

(2.52 mm) 

1 -Per-f 

807 ds 

(3.82 mm) 

806 m/s 

(5.20 mm) 

812 m/s 

(4.72 mm) 

812 m/s 

(7.20 nun) 

859 m/s 

(5.06 mm) 

836 III/S 

(1.375 mm) 

845 m/s 

(3.57 InIn) 

at least one granulation satisfying the minimum user requirements. 

propellant burning rate equation in the form R=aPn, where P is the instantaneous pressure, n is 

its exponent, and a is the coefficient used to calculate R as the rate of linear regression of the 

propellant surface. Usually the values of a and n do not change for the entire range of pressures 

encountered during the JB calculation, as is the case for the first five propellants in Table 8 

(although each propellant has its own unique values for a and n). The EX-99 data were supplied 

with experimental burning rate values -three different pressures (PI, P2, PJ) and a corresponding 

rate (1-1, 1-2, 75) for each. lBHVG2 used these values to create an aP” representation between the 

first two pressures, and again between the last two pressures. The solution values for a and n 

were not the same over the two pressure regions for EX-99. In effect, the IB code used values aI 

and nr for pressures between PI and P2 (and for all pressure levels below PI), and values aj and nj 

for pressures between P2 and P3 (and for all pressure levels above PJ). The “two-tier” rates can 

produce effects such as the higher exit velocity for the 7-perf EX-99 charge than for its 

counterpart 19- and single-perf granular charges when the breakpoint (P-J) is in the range of 

pressures experienced during the II3 cycle. 

16 
The exponent n for HELP-42 was much higher than that of the other propellants; its effect on 

the model was to produce the highest projectile exit velocity for the single-pexf Help-42 

L propellant and the lowest velocity for its corresponding 19-per-f charge. This result is an 

interaction with the projectile/bore resistance profile and the timing of gas production by the 

* burning granular surface. 

3.7 Propellant Zoning. Although there was no requirement for a lower-velocity charge in 

this study, a calculation of lighter charge weights for the JA2 19-perf grain solution gave the 

information in Table 9. The “Charge Burned” column shows the fraction of main charge 

consumed at the time of projectile exit-none of the charge weights smaller than 11 .O kg burned 

out. If a low-zone artillery application had been a requirement with velocity at or below 

760 m/s, then this propellant granulation (web of 4.43 mm and no changes in either length or 

perforation diameter) would not meet specifications unless incomplete charge burnout was 

acceptable to the user. 

3.8 Propellant Suitability. The fmal step in the first round of propellant performance 

testing could be as simple as listing data such as that in Table 8 and providing it to the original 

requesting authority. In this study, BAMO appears to be the most suitable propellant, since it 

gives the highest muzzle energy and has the flexibility of using any of the three granulations. 

M30Al and JA2 both provided solutions with the multiperforated grain types but fell short with 

the single-perf geometry. More likely, there will be additional constraints put on final selection, 

such as the following: 

l Propellants will be ranked according to highest calculated velocities within a particular 

grain geometry; 

l Environmental and economic costs due to manufacturing or. demilitarization will 

determine rankings; 

L 

l Additional performance details, such as computed chamber combustion temperatures, 

will be factored in with velocities to produce a ranking scheme; 

17 
Table 9. Charge Zoning Applications With 19-Perf JA2 Propellant 

II Charge 

Weight 

0%) 

8.000 

8.200 

8.400 

8.6008 

MW 

136.723 

144.193 

160.176 168.724 

ws 

552.40 

566.44 

594.40 60833

ZFraction) 

0.95 1 

0.957 

0.96772 

Cm> 

6.840 

6.840 

6.840 I 

152.005 I 580.44 I 0.962 I 6.840 II 

9.000 177.670 I.30 03 I 

9.200 187.032 636.11 I 

II 9.400 I 196.837 I 649.97 1 0.984 I 6M-o II 

I 10.002 229.151 240.985 691.42 705190.9953 6.840 I 

10.40 253.402 718.98 0.997 6.840 

10.60 266.441 732.71 0.998 6.840 

10.80 280.142 746.48 0.999 6.840 

11.00’ 294.547 760.18 0.999 6.840 

11.20 309.701 773.96 !. -000 6.820 

11.40 325.660 787.63 1.000 6.840 

II 11.60 I 342.479 I 801.36 I 1.000 I 6.545 II 

I 11.8020 360.222 378.957 

813.U 

828.91 m.m _A I 

1. 

- 1.000 000 5.973 6.187 I 

12.20 398.759 842.70 1 .ooo 5.664 

12.40 419.717 856.6 1 1 .ooo 5.422 

12.60 441.926 870.48 1 .ooo 5.167 

I 12.8030 465.492 490.528 884.45986 1 .ooo 4.702 4.982 I 

l Further testing, such as supplemental calculations with other projectile weights or 

secondary propelling charges, will be indicated; 

l Temperature variations should be considered if the propellant is to be used in climatic 

extremes of desert, tropical, or polar regions; 

18 
l If no candidate propellants survive the process, the requester may ask for variations in 

ingredient ratios in order to find a viable charge; 

l Follow-on calculations with one-, two-, or higher-dimensional IB programs may be 

indicated so that pressure waves or other secondary interior ballistic effects might be 

discovered [12, 131. 

The comment concerning the choice of IB code should be addressed before this report could 

be considered complete. IBHVG2 was used because of its automatic input-varying feature. 

Most of the currently available one- or multi-dimensional IB programs lack the ability to 

automatically vary any of the input parameters. In order to complete several of the process steps 

(finding web size versus grain geometry, computing various charge weights and noting amount 

burned at time of projectile exit, etc.), the number of individual 113 cycles to be calculated can be 

very large. The labor required to modify input data, compute each situation, tabulate output 

values, and analyze the results could be extremely large if each calculation is done separately. 

Therefore, the use of a code with an automated parametric function is crucial, especially during 

the initial phase of propellant screening. The same type of reasoning can lead to tremendous 

savings in time and labor in virtually all steps of the propellant developmental process where 

automated models can be.fitted with parameter variation [25]. 

3 

3.9 Next Step. Other “tools” in the propellant production and testing flow diagram will 

need the information from a performance analysis, whether the results are used for reformulation of a new propellant or for additional filtering of existing choices. Before the user 

elects an energetic material, he will require more data about manufacturing costs, vulnerability, 

shelf life, environmental compatibility, and a host of other factors dealing with propellants. The 

initial performance comparisons are a small but important part of the overall formulation and 

selection process. 

19 
4. Lessons Learned and Tools Needed 

The example test case is a simplistic exercise: no variations of gun hardware were 

considered; no propellant reformulation was envisioned; no multidimensional II3 analysis was 

performed. Yet it is clear that some functions are necessary and others are nonexistent. To be 

complete, the model-based performance process still requires software tools to estimate density 

and burning rates of virtual propellants-semi-empirical and first-principle burning rate models 

are currently under development at the Army Research Laboratory [26], and models exist to 

predict crystal densities within a subset of crystalline space groups [27]. Automated search 

methods for IE! solutions are absolutely necessary for minimization of the labor involved in 

computation and analysis. As the overall propellant ereation and testing methods become 

formalized, there will certainly be other areas where software tools need to be developed or 

utilized for individual and composite steps in the sequencmstimation of processing costs, 

toxicity hazards, mechanical properties, disposal and demilitarization requirements, and many 

other activities. 

Along with the computer programs is a critical need for databases to be assembled with the 

parameters required for software tools. With enough data, the missing tools for estimation of 

propellant density and burning rates might be created; vulnerability, compatibility, temperature 

sensitivity, and a dozen other empirical methods could follow. At the least, such gathered data 

would make the tasks of modelers much easier and faster. 

Clear and complete performance and environmental requirements might shorten the 

performance modeling too. A standardized questionnaire could alert the modeler to additional 

factors in zoning, temperature maximums, projectile acceleration limits, and other stipulations 

not apparent during construction of an initial set of performance requirements. Ideally, a 

database of existing environmental regulations and constraints should be incorporated into the 

process to flag the user about possible problems with manufacture, movement, and disposal of 

energetic materials. 

20 
5. Summary 

We have demonstrated the preliminary steps in a new formulation process for gun 

propellants that can minimize life-cycle costs by science-basedesign. The earliest steps in this 

process use modeling and simulation of the properties, processing, and performance of the 

candidate in order to screen potential candidates, eliminate probable poor performers, and 

identify candidates that show promise. In this exercise, user requirements of maximum pressure 

limitation and minimum muzzle energy for a Navy 5-inch M-caliber gun were presented. The 

most promising candidate(s) to meet the user requirement from a set of 10 existing formulations 

representing single-, double- and triple-based propellants, as well as other novel energetic 

mixtures, was determined. Since not all performance and properties models exist, it was 

necessary to use limited empirical information to perform parts of the exercise. Down-selection 

of the propellants proceeded first through consideration of ingredient toxicity, then calculation of 

thermodynamic properties, estimation of theoretical maximum energy, determination of actual 

granular solutions, and listing of additional final considerations. At the end of the exercise, 4 of 

the 10 original formulations survived the simulation, and information is available at this point for 

a user to rank the suitability of the propellant according to his requirements. 

The number of steps in a complete screening analysis would seemingly be endless, just as the 

infinite amount of propellant variations to be considered might appear when first contemplated. 

But the list of available propellant formulations is small when compared to current computer 

capabilities, and a performance testing sequence with defined steps and parametric searching 

methods can quickly determine which propellants can meet user requirements without extensive 

firing range exercises. When compared to cost of experimental tests of the same materials, the 

amount of resources saved by model-based filtering is enormous. 

21 
-ONALLY LEFT BLANK. 

22 
1. 

2. 

3. 

4. 

5. 

6. 

7. 

8. 

9. 

10. 

11. 

6. References 

Cohen, W. S. “Report of the Quadrennial Defense Review.” U.S. Department of Defense, 

http://www.defenselink.mil/quad.html, May 1997. 

Miller, M. S., B. M. Rice, and R. J. Cramer. “A New Approach to Propellant Formulation: 

Minimizing Life-Cycle Costs Through Science-Based Design.” Memorandum report, 

U.S. Army Research Laboratory, Aberdeen Proving Ground, MD, to be published. 

Baer, P., and J. Frankle. “The Simulation of Interior Ballistic Performance of Guns by 

Digital Computer Program.” BRLR 1183, U.S. Army Ballistic Research Laboratory, 

Aberdeen Proving Ground, December 1962. 

Voltis, P. M. “Digital Computer Simulation of the Interior Ballistic Process in Guns.” 

TR-6615, Watervliet Arsenal, Waverliet, NY, 1966. 

Baer, P. G., I. W. May, and J. M. Frankle. “A Comparison of Several Predictive 

Approaches in Charge Establishment for ktrge Caliber Artillery Systems.” I I th JANNAF 

Combustion Meeting, Chemical Propulsion Information Agency, publ. 261, vol. 1, 

pp* 55-66,1974. 

Fried, L. E., W. M. Howard, and P. C. Souers. “Cheetah 2.0 User’s Manual.” Energetic 

Materials Center, Lawrence Liverrnore National Laboratory, Livennore, CA, August 1998. 

Freedman, E. “B LAKE-A Thermodynamics Code Based on TIGER: Users’ Guide to the 

Revised Program.” ARL-CR-422, U.S. Army Research Laboratory, Aberdeen Proving 

Ground, MD, July 1998. 

Svehla, R. A., and B. J. McBride. “FORTRAN IV Computer Program for Calculation of 

Thermodynamic and Transport Properties of Complex Chemical Systems.” NASA 

TD-7056, NASA Lewis Research Center, Cleveland, OH, 1973. 

McBride, B. J., and S. Gordon. “Computer Program for Calculation of Complex Chemical 

Equilibrium Compositions and Applications, II: User’s Manual and Program Description.” 

NASA RP-,13 11, NASA Lewis Research Center, Cleveland, OH, 1996. 

Anderson, R. D., and K. D. Fickie. “IBHVG2-A User’s Guide.” BRL-TR-2829, 

U.S. Army Ballistic Research Laboratory, Aberdeen Proving Ground, MD, July 1987. 

Oberle, W. F. “Constant Pressure Interior Ballistics Code CONPRESS: Theory and User’s 

Manual.” ARLTR-199, U.S. Army Research Laboratory, Aberdeen Proving Ground, MD, 

September 1993. 

23 
12. Gough, P. S, “The XNOVAKTC Code.” BRL-CR-627, U.S. Army Ballistic Research 

Laboratory, Aberdeen Proving Ground, MD, February 1990. 

13. Nusca, M. 5. (Army Research Laboratory), and P. S. Gough (Paul Gough Associates). 

“Numerical Model of Multiphase Flows Applied to Solid Propellant Combustion in Gun 

Systems.” AIAA 983695, 34th AIAAIASME/SAE/ASEE Joint Propulsion Conference & 

Exhibit, Cleveland, OH, 13-15 July 1998. 

14. Mallincktrodt Baker, Inc. “Lead Carbonate-MSDS Number L2650.” Material Safety Data 

Sheet, http://www.jtbaker.com/msds/12650.htm, December 1996. 

15. International Chemical Safety Cards. “2,4Dinitrotoluene-ICSC: 0727.” 

http://hazard.com/msds/mfYc~ds/file/O727.html, 1993. 

16. Freedman, E. “Thermodynamic Properties of Gun Propellants.” Chapter 5 of Gun 

Propulsion Technology, edited by L. Stiefel and M. Summerfield, vol. 109 of Progress in 

Astronautics and Aeronautics, American Institute of Aeronautics and Astronautics, Inc., 

pp. 103-132,1988. 

17. Miller, M. S. “Thennophysical Properties of Six Solid Gun Propellants.” ARL-TR-1322, 

U.S. Army Research Laboratory, Aberdeen Proving Ground, MD, March 1997. 

18. Almeyda, N. Personal communication. Naval Surface Warfare Center, Indian Head, MD, 

November 1998. 

19. Cramer, R. J. “Advanced Gun Propellants.” CPIA Publication 675, vol. II, pp. 145-148, 

July 1998e 

20. Virginia, F. J., Jr. “Interior Ballistics Firing Library of Closed Breech, Single Combustion 

Chamber Tank Guns, Artillery Guns, and Howitzers Cannon.” Report 87-027, U.S. Army 

Research, Development, and Engineering Center, March 1987. 

21. Van der Waals, J. D., Sr. “Over de Continuiteit van Den Gas-en Vloestoftoestand.” Ph.D. 

dissertation, Leiden, Netherlands, 1873. 

22. Robbins, F. W., and F. R. Lynn. “Analytic Solutions to the Closed Bomb.” BRLTR-2892, 

U.S. Army Ballistic Research Laboratory, Aberdeen Proving Ground, MD, March 1988. 

23. Oberle, W. F., III, and D. E. Kooker. “BRLCB: A Closed Chamber Data Analysis Program 

With Provisions for Deterred and Layered Propellants.” BRL-TR-3227, U.S. &my Ballistic 

Research Laboratory, Aberdeen Proving Ground, MD, April 1991. 

24. Price, C., and A. Juhasz. “A Versatile User-Oriented Closed Bomb Data Reduction 

Program (CBRED).” BRL-TR-2018, U.S. Army Ballistic Research Laboratory, Aberdeen 

Proving Ground, MD, September 1977. 

24 
I * 

I 

i * 

. 

25. Murphy, Michael J. “GLO-Global Local Optimizer User’s Manual.” UCRL-MA-133858, 

Lawrence Livermore National Laboratory, Liverrnore, CA, April 1999. 

26. Miller, M. S., and W. R. Anderson. “Energetic-Material Combustion Modeling With 

Elementary Gas-Phase Reactions: A Practical Approach.” Journal of Propulsion and 

Power, to be published. 

27. Holder, J. R., 2. Du, and H. L. Ammon. “Prediction of Possible Crystal Structures for C-, 

H-, N-, 0-, and F-Containing Organic Compounds.” Journal of Computational Chemistry, 

vol. 14, no. 4, p. 422, 1993. 
hl-ENTIONALLY LEFT BLANK. 

26 
. 

Appendix A: 

BLAKE Calculations for Generic Ml Propellant 

27 
h”TWlTONALLY LEFT BLANK. 

28 
l ** BLAKE Version 221.50 l ** 

Tyger! Tyger! Burning bright/ In the forests of the night. 

What immortal hand or eye/ Dare frame thy fearful symmetry? 

---William Blake (1757-1827) 

16:07:20 6-APR-1999 

> TITLE, GENERIC Ml 

> COM,NC1315,83.11,DNT,9.77,DBP,4.89,DPA,OC,~.75 

*******************~**t*t***************~~~~~~~~~~~~~~~~~~~~~*~~~~~ 

<<< The binary library being used is based on >>> 

<<< SBLAKLYB.LIB dated 11 August 1998 >>> 

<i< >>> 

<<< This binary library was created on 24-SEP-1998 >>> 

*****~t+**************************************~~*****************~* 

16:07:20 

GENERIC Ml 

THE COMPOSITION IS 

Name Pet wt Pet Mole Delta H (J/mol) 

NC1315 83.110 .244 

DNT 9.770 44.210 

6-APR-1999 Page 1. 

FORMULA 

-6.88903+08 C H 0 N 

6000 7364 10271 2636 

-6.59003+04 C H 0 N 

7 6 4 2 

29 
DBP 4.890 14.480 -8.42603+05 C H 0 

16 22 4 

DPA .980 4.773 1.1190E+05 C N H 

12 1 11 

H20 .500 22.875 -2.85833+05 H 0 

2 1 

ALC .750 13.418 -2,7710E+05 C H 0 

2 6 1 

The Elements and their Atom Percentages 

C 25.597 

H 31.357 

0 34.025 

N 9.022 

Formula Weight = 1009.775 

The Heat of Formation is -2340.7 J/g = -2.3643+06 J/mol 

= -559.46 Cal/g r -5.6493+05 cal/mol 

> GUN,0.05,0.05,0.4 

CONSTITUENT CONCENTRATIONS - MOLES PER KGM OF COMPOUND 

NAME 1) 2) 3) 4) 

co GAS 2.297753+01 2.298413+01 2.297213+01 2.293763+01 

H2 GAS 9.507573+00 9.442883+00 9.358973+00 9.249953+00 

H20 GAS 5.988653+00 6.023453+00 6.057323+00 6.092153+00 

N2 GAS 4.460413+00 4.452143+00 4.441573+00 4.428483+00 

co2 GAS 2.361383+00 2.339473+00 2.326193+00 2.322763+00 

H GAS 1.698233-02 1.121913-02 8.567693-03 6.966433-03 

OH GAS 2.065963-03 1.369083-03 1.051323-03 8.632533-04 

NH3 GAS 8.100153-03 1.814433-02 3.036833-02 4.493153-02 

HCN GAS 4.779703-03 1.105743-02 1.916183-02 2.943333-02 

CH4 GAS 1.629973-03 7.661323-03 2.01363E-02 4.134603-02 

0 GAS 2.489823-06 1.133173-06 6.92114E-07 4.824393-07 

02 GAS 6.373023-07 2.903233-07 1.778203-07 1.246513-07 

NO GAS 9.002473-05 6.157283-05 4.886003-05 4.155203-05 

CHO GAS 6.858513-04 1.038233-03 1.364223-03 1.696593-03 

CH20 GAS 1.453793-03 3.216543-03 5.336723-03 7.862463-03 

30 
c 

HNCO 

NH2 

CH3 

NH 

C2H2 

HNO 

HO2 

C2H4 

N 

CN 

N20 

NC0 

HNO2 

CH2 

C 

NO2 

FORMAC 

C(S) 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

SOLID 

4.067873-04 9.262683-04 1.583143-03 2.406383-03 

4.645013-05 6.856643-05 8.760483-05 1.056623-04 

7.312423-05 2.392033-04 5.067363-04 8.950923-04 

6.039413-07 6.111973-07 6.198873-07 6.330443-07 

1.259303-05 6.410523-05 1.831323-04 4.109103-04 

3.971273-07 4.009103-07 4.062773-07 4.155253-07 

1.216783-08 8.173843-09 6.387573-09 5.380383-09 

1.047613-06 1.109993-05 4.932353-05 1.520203-04 

1.005723-07 6.938933-08 5.55090E-08 4,759713-08 

5.847213-07 9.186933-07 1.253113-06 1.619863-06 

3.613153-08 3.74717E-08 3.903763-08 4.108173-08 

2.730963-07 4.283493-07 5.843003-07 .7.573053-07 

0.00000E+00 0.00000E+00 0.00000E+00 0.00000E+00 

2.55410E-07 5.746413-07 9.698753-07 1.457503-06 

0.00000E+00 0.00000E+00 0.00000E+00 0.00000E+00 

0.00000E+00 0.00000E+00 0.00000E+00 0.00000E+00 

5.420353-04 1.198803-03 1.992083-03 2.948453-03 

0.00000E+00 0.00000E+00 0.00000E+00 0.00000E+00 

TOTAL GAS (MOLES/KG) 45.3324 45.2984 45.2466 45.1710 

CONSTITUENT CONCENTRATIONS - MOLES PER KGM OF COMPOUND 

NAME 5) 6) 7) 8) 

co 

H2 

H20 

N2 

co2 

H 

OH 

NH3 

HCN 

CH4 

0 

02 

NO 

CHO 

CH20 

HNCO 

NH2 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

GAS 

2.287773+01 2.278783+01 2.266653+01 2.251363+01 

9.11047E+OO 8.93571E+OO 8.724713+00 8.479603+00 

6.129973+00 6.171143+00 6.216033+00 6.264143+00 

4.413233+00 4.395173+00 4.374453+00 4.351163+00 

2.330743+00 2.351063+00 2.384573+00 2.431463+00 

5.880893-03 5.097193-03 4.508133-03 4.051133-03 

7.401953-04 6.561383-04 5.979053-04 5.576193-04 

6.189103-02 8.114973-02 1.024863-01 1.255833-01 

4.219543-02 5.770903-02 7.616663-02 9.768923-02 

7.346023-02 1.179843-01 1.753403-01 2.447283-01 

3.656743-07 2.952643-07 2.510693-07 2.228883-07 

9.538613-08 7.812143-08 6.772533-08 6.161553-08 

3.701153-05 3.420023-05 3.260633-05 3.192803-05 

2.052003-03 2.442283-03 2.877403-03 3.365683-03 

1.083793-02 1.429603-02 1.82605E-02 2.274493-02 

3.429233-03 4.687503-03 6.220343-03 8.069453-03 

1.236443-04 1.420493-04 1.611953-04 1.812423-04 

31 
CH3 GAS 

NH GAS 

C2H2 GAS 

HNO GAS 

HO2 GAS 

C2H4 GAS 

N GAS 

CN GAS 

N20 GAS 

NC0 GAS 

HN02 GAS 

CH2 GAS 

C GAS 

NO2 GAS 

FORMAC GAS 

C(S) SOLID 

1.424663-03 2.112223-03 2.968433-03 3.996493-03 

6.525913-07 6.799443-07 7.161523-07 7.616973-07 

8.026483-04 1.426233-03 2.359083-03 3.683903-03 

4.30369E-07 4.522663-07 4.825293-07 5.221833-07 

4.783663-09 4.452513-09 4.317023-09 4.338423-09 

3.791413-04 8.174893-04 1.578273-03 2.788833-03 

4.275293-08 3.983613-08 3.828213-08 3.775443-08 

2.039883-06 2.532233-06 3.116453-06 3.812213-06 

4.383313-08 4.751973-08 5.238363-08 5.866373-08 

9.595873-07 1.203743-06 1.504173-06 1.877243-06 

0.00000E+00 0.00000E+00 1.808113-09 2.040883-09 

2.056553-06 2.787523-06 3.671813-06 4.730063-06 

0.00000E+00 0.00000E+00 0.00000E+00 0.00000E+00 

0.00000E+00 0.00000E+00 0.00000E+00 0.00000E+00 

4.100093-03 5.483433-03 7.140353-03 9.117163-03 

0.00000E+00 0.00000E+00 0.00000E+00 0.00000E+00 

TOTAL GAS (MOLES/KG) 45.0694 44.9350 44.7670 44.5666 

* * SUMMARY OF PROPELLANT THERM0 PROPERTIES l l 

Truncated virial equation of state with L-J 6,12 potential is being used 

RhO/L TOP 

g/cc K 

1).05000 2436. 

2).10000 2439. 

3).15000 2443. 

4).20000 2447. 

5).25000 2454. 

6).30000 2462. 

7).35000 2471. 

8).40000 2483. 

Press Imptus Mel Wt Co-V01 Frozen Balrgy U PHI 

MPa J/9 Gas cc/g Gamma J/g J/g 

48.79 918.2 22.059 1.181 1.2630 3490.9 -2340.7 1.0627 

103.9 918.7 22.076 1.158 1.2639 3480.9 -2340.7 1.1310 

166.1 919.0 22.101 1.133 1.2654 3462.4 -2340.7 1.2047 

236.0 919.2 22.138 1.105 1.2675 3436.0 -2340.7 1.2838 

314.5 919.5 22.188 1.077 1.2702 3402.9 -2340.7 1.3683 

402.4 919.7 22.254 1.048 1.2734 3364.1 -2340.7 1.4583 

500.2 919.9 22.338 1.018 1.2770 3320.9 -234.0.7 1.5536 

608.9 920.1 22.438 . 989 1.2810 3274.3 -2340.7 1.6545 

> QUIT 

Run time = 1.15 seconds 

32 
Appendix B: 

IBHVG2 Constant-Pressure Calculations 

Using M26El Propellant 

33 
hTENllONALLY LEFl- BLANK. 

34 
ERRTOL 1.1920929&07 

1 IBHVG2.505 DATE 

0 CARD 1 --> SCOMM 

CARD 2 --> GREEN GUN TEST CASE - INDIAN HEAD SYSTEM 

CARD 3 --> SGUN 

CARD 4 --> TRAV = 6:840 CHAM = 0.01506 $ 919 CUBIC INCHES 

CARD 5 --> GRVE = 0.12852 LAND = 0.127 TWST = 24 G/L = 1.66 $ ESTIMATES 

CARD 6 --> $ CPTS = 6 

CARD 7 --> $ DIST = 0.0, 0.04455, 0.14732, 0.8260, 0.8913, 1.0592 

CARD 8--r $ DIAM- 0.12965, 0.13655, 0.13929, 0.132588, 0.12852, 0.12852 

CARD 9 --> SPROY 

CARD 10 --> PRWT = 49.895 

CARD 11 --> SRESI 

CARD 12 --> NPTS = 5 

CARD 13 --> TRAV = 0.0, 0.00508, 0.04318, 0.1397, 7.62 

CARD 14 --> PRES = 3.4474, 0.6894757, 0.6894757, 8.2737, 8.2737 

CARD 15 -9 $1~~0 

CARD 16 --> E-OPT = l,l,l,O 

CARD 17 --> RUN - 'GREEN GUN TEST CASE - M26E1’ 

CARD 10--> $ GRAD-3 

CARD 19 --> CONP = 2 PRES = 448 

CARD 20 --> SCOMM PRIM 

CARD 21 --> NAME - 'PRIMER' CHWT = 0.12637 FORC = 146140 

CARD 22 --> GAMA - 1.2015 cov = 0.0010838 TEMP = 3377 

CARD 23 --> SPROP 

CARD 24 --> NAME = 'M26El' CHWT - 11,567 FORC = 1085031 

CARD 25 --> GAMA = 1.2384 COV ='0.0010383 TEMP = 3132 

CARD 26 --> FORM = '7P' 

CARD 27 --> LEN = 0.018288 PD = 0.0004572 WEB = 0.003467 RHO = 1611 

CARD 28 --> ALPH = 0.7466 BETA = 0.0033776 

CARD 29 --> $COMM PARA 

CARD 30 --> VARY = 'CHWT DECK = 'PROP' NTH = 1 

CARD 31 --> FROM = 11.5 

czdm 32 --> SEND 

IGREEN GUN TEST cAsE - ~26~1 

- GUN TUBE - 

TY!?E: 

(Ml: 6.84000 

GROOVE DIAMETER (M): 

GROOVE/LAND RATIO (-): 

BY = 0.1 TO = 15.01 

IBHVG2.505 DATE 

TIME 

TIME 

CHAMBER VOLUME (M3): 0.01506 TRAVEL 

0.12852 LAND DIAMETER (M): 0.12700 

1.660 

35 
TWIST (CALS/TURN): 24.0 BORE AREA (M2): 0.01286 HEAT-LOSS 

OPTION : 1 

SHELL THICKNESS (M): 0.000102 SHELL CP (J/KG-K): 460 _ 3163 SHELL 

DENSITY (KG/M3): 7861.0918 

INITIAL SHELL TEMP (K): 233. AIR HO (W/M**2-K): 11.3482 

- PROJECTILE - 

TYPE: 

PREDICTOR OPTION: 

- RESISTANCE - 

TOTAL WEIGHT (KG): 49.895 WEIGHT 

AIR RESISTANCE OPTION: 1 WALL HEATING FRACTION: 0.000 

RESISTIVE PRESSURE MULT INDEX: 3 RESISTIVE FACTOR 1.000 FRICTION 

TABLE LENGTH: 5 

I TRAVEL (M) PRESSURE (MPA) I TRAVEL (M) PRESSURE (MPA) I 

TRAVEL (M), PRESSURE (MPA) 

1 0.000 3.447 

7.620 8.274 

2 0.005 0.689 

3 0.043 0.689 

4 0.140 a.274 

5 

- GENERAL - 

MAX TIME STEP (S): 0.000100 PRINT STEP (S): 

RELATIVE ERROR (-): 0.00200 

PRINT OPTIONS: 111011 STORE OPTION: 

PRESSURE OPTION: 2 

GRADIENT MODEL: LAGRANGIAN 

0.000000 MAX 

0 CONSTANT- 

- RECOIL - 

_____*--__ 

RECOIL OPTION: 0 TYPE: 

WEIGHT (KG): 0 

36 

RECOILING 
- CONSTANT-PRESSURE RUN - 

MAINTAIN PRESSURE (MPA): 448. 

VARYING: PROPELLANT SURFACE AREA 

1GREEN GUN TEST CASE - M26El 

WITHIN (MPA): 

IBHVG2.505 DATE 

0.0 BY 

TIME 

TYPE: M26El GRAINS : 1.0000 ?P WEIGHT 

(KG): 11.5670 

EROSIVE COEFF (-): 0.000000 CHARGE IGN CODE: 

AT (S): 0.00000E+OO 

PROPERTIES AT LAYER BOUNDARIES OF LAT SURFACES 

3RD 4TH 

------ 0.00000 

_----- 100.000 

------ 1611.000 

_----- 1.2384 

_--___ 1085031. 

-+e--- 1.03833-03 

_____- 3132.0 

__---- 0.7468 

__-___ 3.37783-03 

IBHVG2.505 DATE TIME 

0 CHARGE IGN 

- CHARGE 1 - 

-----_------ 

1ST 2ND 

AT DEPTH (M): ------ _____- 

ADJACENT LAYER WT %: ___--- ------ 

DENSITY (KG/M3): ------ 

GAMMA (-): _-____ ------ 

FORCE (J/KG): ---___ ------ 

COVOLUME (M3/KG): --__-_ ------ 

FLAME TEMP (K): ------ ___-+- 

BURNING RATE EXPS: _*____ ------ 

BURNING RATE COEFFS: -----_ ------ 

1GREEN GUN TEST CASE - M26El 

TIME TRAV VEL ACC BREECH MEAN 

(MS) CM) W/S) (G) PRESS PRESS 

WA) (Mph) 

0 0.000 0.000 0.00 10469. 448.000 432.608 

0.100 0.001 10.27 10475. 448.000 432.598 

BARREL RESISTANCE OVERCOME - PROJECTILE MOVING 

0.200 0.002 20.55 10495. 448.000 432.569 

0.300 0.005 30.86 10527. 448.000 432.521 

0.400 0.008 41.19 10533. 448.000 432.513 

0.500 0.013 51.53 10533. 448.000 ,432.513 

0.600 0.019 61.86 10533. 448.000 432.513 

0.700 0.025 72.19 10533. 448.000 432.513 

0.800 0.033 82.52 10533. 448.000 432.514 

0.900 0.042 92.85 10533. 448.000 432.514 

BASE MEAN 

PRESS TEMP 

CM=) (K) 

401.823 3132. 

401.794 3131. 

FRAC 

BURN 

1 

0.233 

0.233 

SURFACE BURNING 

AREA 

(M'*2) 

0.223 

0.056 

RATE 

W/S) 

0.314 

0.314 

401.708 3128. 

401.563 3124. 

401.538 3118. 

401.539 3110. 

401.539 3101. 

401.540 3091. 

401.540 3079. 

401.541 3066. 

1.000 0.052 103.17 10517. 448.000 432.537 401.610 3052. 

0.234 

0.235 

0.237 

0.239 

0.242 

0.245 

0.249 

0.253 

0.258 

0.169 

0.283 

0.402 

0.519 

0.. 634 

0.749 

0.864 

0.979 

1.097 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

37 
1.100 0.062 

1.200 0.074 

1.300 0.087 

1.400 0.101 

1.500 0.116 

1.600 0.132 

1.700 0.149 

1.800 0.167 

1.900 0.186 

2.000 0.206 

2.100 0.227 

2.200 0.249 

2.300 0.272 

2.400 0.296 

2.500 0.321 

2.600 0.347 

2.700 0.374 

2.800 0.403 

2.900 0.432 

3.000 0.462 

3.100 0.493 

3.200 0.525 

3.300 0.559 

3.400 0.593 

3.500 0.628 

3.600 0.664 

3.700 0.702 

3.800 0.740 

3.900 0.779 

4.000 0.820 

4.100 0.861 

4.200 0.903 

4.300 0.947 

4.400 0.991 

4.500 1.036 

4.600 1.083 

4.700 1.130 

4.800 1.179 

4.900 1.228 

5.000 1.279 

5.100 1.330 

5.200 1.383 

5.300 1.436 

113.48 

123.77 

134.03 

144.27 

154.48 

164.66 

174.82 

184.97 

195.13 

205.28 

215.43 

225.59 

235.74 

245.89 

256.05 

266.20 

276.35 

286.50 

296.65 

306.80 

316.96 

327.11 

337.26 

347.41 

357.56 

367.71 

377.'86 

388.00 

398.15 

408.30 

418.45 

428.60 

430.74 

448.89 

459.04 

469.18 

479.33 

489.48 

499.62 

509.77 

519.91 

530.06 

540.20 

10497. 448.000 432.566 401.699 3038. 0.263 1.212 

10475. 448.000 432:599 401.796 3022. 0.269 1.326 

10451. 448.000 432.634 401.902 3006. 0.275 1.440 

10425. 448.000 432.672 402.017 2990. 0.282 1.554 

10397. 448.000 432.713 402.139 2973. 0.290 1.667 

10367. 448.000 432.757 402.270 2957. 0.297 1.779 

10353. 448.000 432.778 402.334 2940. 0.306 1.888 

10353. 448.000 432.778 402.335 2923. 0.314 1.997 

10352. 448.000 432.779 402.336 2906. 0.324 2.107 

10352. 448.000 432.779 402.337 2890. 0.333 2.218 

10352. 448.000 432.779 402.337 2874. 0.343 2.328 

10352. 448.000 432.779 402.338 2858. 0.354 2.439 

10352. 448.000 432.780 402.339 2842. 0.365 2.549 

10351. 448.000 432.700 402.340 2827. 0.377 2.659 

10351. 448.000 432.780 402.341 2812. 0.389 2.768 

10351. 448.000 432.781 402.342 2798. 0.402 2.878 

10351. 448.000 432.781 402.343 2704. 0.415 2.987 

10351. 448.000 432.781 402.344 2771. 0.428 3.096 

10350. 448.000 432.782 402.345 2758. 0.442 3.206 

10350. 448.000 432.702 402.346 2745. 0.457 3.315 

10350. 448.000 432.782 402.347 2733. 0.472 3.424 

10350. 448.000 432.783 402.348 2722. 0.487 3.533 

10349. 448.000 432.783 402.349 2711. 0.503 3.642 

10349. 448.000 432.783 402.350 2700. 0.520 3.750 

10349. 448.000 432.704 402.352 2690. 0.537 3.859 

10349. 448.000 432.784 402.353 2680. 0.554 3.968 

10348. 448.000 432.785 402.354 2671. 0.572 4.077 

10348. 448.000 432.785 402.355 2662. 0.590 4.186 

10348. 448.000 432.705 402.356 2653. 0.609 4.295 

10347. 448.000 432.786 402.358 2645. 0.628 4.404 

10347. 448.000 432.786 402.359 2637. 0.648 4.513 

10347. 448.000 432.787 402.360 2629. 0.668 4.622 

10346. 448.000 432.787 402.362 2622. 0.689 4.731 

10346. 448.000 432.700 402.363 2615. 0.710 4.841 

10346. 448.000 432.788 402.365 2608. 0.732 4.950 

10345. 448.000 432.709 402.366 2602. 0.754 5.059 

10345. 448.000 432.789 402.368 2595. 0.777 5.169 

10345. 448.000 432.790 4024.369 2589. 0.800 5.278 

10344. 448.000 432.790 402.371 2584. 0.823 5.388 

10344. 448.000 432.791 402.372 2578. 0.847 5.497 

10344. 448.000 432.791 402.374 257?. 0.872 5.607 

10343. 448.000 432.792 402.376 2568. 0.897 5.717 

10343. 448.000 432.792 402.377 2563. 0.922 5.827 

IGREEN GUN TEST CASE - M26El IBHVG2.505 DATE 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

0.314 

TIME 

TIME TRAV VEL ACC BREECH MEAN BASE MEAN FRAC SURFACE BURNING 

38 
(MS) CM) P/S) (G) 

0 5.400 1.491 550.34 

5.500 1.546 560.49 

5.593 1.599 569.96 

PROPELLl ht?T 1 Bl URNED OUT 

5.600 1.603 570.65 

5.700 1.660 580.57 

5.800 1.719 590.10 

5.900 1.778 599.27 

6.000 1.839 608.10 

6.100 1.900 616.61 

6.200 1.962 624.80 

6.300 2.025 632.70 

6.4'00 2.088 640.32 

6.500 2.153 647.68 

6.600 2.218 654.78 

6.700 2.284 661.64 

6.800 2.350 668.27 

6.900 2.417 674.69 

7.000 2.485 680.89 

7.100 2.554 686.90 

7.200 2.623 692.72 

7.300 2.692 698.35 

7.400 2.762 703.82 

7.500 2.833 709.12 

7.600 2.904 714.26 

7.700 2.976 719.25 

7.800 3.048 724.10 

7.900 3.121 728.81 

8.000 3.194 733.38 

8.100 3.267 737.83 

8.200 3.341 742.16 

8.300 3.416 746.37 

8.400 3.491 750.47 

8.500 3.566 754.45 

8.600 3.641 758.34 

8.700 3.717 762.13 

8.800 3.794 765.81 

8.900 3.871 769.41 

9.000 3.948 772.92 

9.100 4.025 776.34 

9.200 4.103 779.60 

9.300 4.181 782.94 

9.400 4.260 786.12 

9.500 4.338 789.23 

10343. 448.000 

10342. 448.000 

10342. 448.000 

10314. 446.810 431.645 401.316 2548. 1.000 0.000 0.000 

9915. 429.871 415.293 386.138 2528. 1.000 0.000 0.000 

9536. 413.800 399.779 371.738 2509. 1.000 0.000 0.000 

9176. 398.549 385.057 358.073 2490. 1.000 0.000 0.000 

8835. 384.073 371.083 345.103 2472. 1.000 0.000 0.000 

8511. 370.330 357.816 332.788 2454. 1.000 0.000 0.000 

8203. 357.277 345.215 321.093 2436. 1.000 0.000 0.000 

7911. 344.875 333.243 309.981 2419. 1.000 0.000 0.000 

7633. 333.087 321.864 299.418 2402. 1.000 0.000 0.000 

7369. 321.877 311.043 289.374 2385. 1.000 0.000 0.000 

7117. 311.212 300.748 279.819 2369. 1.000 0.000 0.000 

6878. 301.060 290.948 270.723 2354. 1.000 0.000 0.000 

6650. 291.393 281.615 262.060 2338. 1.000 0.000 0.000 

6433. 282,181 272.723 253.807 2323. 1.000 0.000 0.000 

6225. 273.398 264.245 245.938 2308. 1.000 0.000 0.000 

6028. 265.021 256.158 238.432 2294. 1.000 0.000 0.000 

5839. 257.026 248.440 231.268 2280. 1.000 0.000 0.000 

5659. 249.391 241.070 224.428 2266. 1.000 0.000 0.000 

5487. 242.096 234.028 217.892 2252. 1.000 0.000 0.000 

5323. 235.123 227.297 211.644 2239. 1.000 0.000 0.000 

5165. 228.453 220.858 205.669 2226. 1.000 0.000 0.000 

5015. 222.070 214.697 199.950 2213. 1.000 0.000 0.000 

4871. 215.959 208.797 194.474 2201. 1.000 0.000 0.000 

4733. 210.103 203.145 189.228 2189. 1.000 0.000 0.000 

4600. 204.491 197.727 184.199 2177. 1.000 0.000 0.000 

4473. 199.108 192.531 179.376 2165. 1.000 0.000 0.000 

4351. 193.943 187.545 174.749 2153. 1.000 0.000 0.000 

4234. 188.985 182.759 170.306 2142. 1.000 0.000 0.000 

4122. 184.222 178.161 166.039 2131. 1.000 0.000 0.000 

4014. 179.645 173.743‘ 161.939 2120. 1.000 0.000 0.000 

3910. 175.245 169.495 157.996 2109. 1.000 0.000 0.000 

3810. 171.012 165.409 154.204 2099. 1.000 0.000 0.000 

3714. 166.938 161.477 150.554 2089. 1.000 0.000 0.000 

3622. 163.016 157.691 147.040 2078. 1.000 0.000 0.000 

3533. 159.237 154.043 143.655 2069. 1.000 0.000 0.000 

3447. 155.596 150.529 140.393 2059. 1.000 0.000 0.000 

3364. 152.086 147.140 137.248 2049. 1.000 0.000 0.000 

3284. 148.700 143.871 134.215 2040. 1.000 0.000 0.000 

3207. 145.432 140.717 131.287 2030. 1.000 0.000 0.000 

3132. 142.278 137.672 128.461 2021. 1.000 0.000 0.000 

PRESS 

(MPA) 

PRESS PRESS TEMP BURN AREA RATE 

CM=) WPA) (K) 1 (M**2) (M/S 1 

432.793 402.379 2558. 0.948 5.937 0.314 

432.794 402.381 2554. 0.975 6.047 0.314 

432.794 402.382 2550. 1.000 0.000 0.314 

39 
9.600 4.417 792.27 3060. 

9.700 4.497 795.23 2991. 

9.800 4.576 798.13 2924. 

9.900 4.656 800.97 2859. 

10.000 4.737 803.74 2796. 

10.100 4.817 806.45 2735. 

10.200 4.698 809.11 2676. 

10.300 4.979 811.70 2619. 

10.400 5.060 814.24 2564. 

10.500 5.142 816.73 2511. 

10.600 5.224 819.17 2459. 

~GREEN GUN TEST CASE - ~26~1 

TIME TRAV VEL 

(MS) (Ml (M/S) 

0 10.700 5.306 821.56 

10.800 5.388 823.89 

10.900 5.470 826.18 

11.000 5.553 828.43 

11.100 5.636 830.63 

11.200 5.719 832.79 

11.300 5.803 834.90 

11.400 5.886 836.98 

11.500 5.970 839.01 

11.600 6.054 841.01 

11.700 6.138 842.97 

11.800 6.223 844.89 

11.900 6.307 846.78 

12.000 6.392 848.63 

12.100 6.477 850.45 

12.200 6.562 852.24 

12.300 6.647 854.00 

12.400 6.733 855.72 

12.500 6.819 857.41 

12.525 6.840 857.83 

PROJECTILE EXIT 

ACC 

(G) 

2409. 

2360. 

2312. 

2267. 

2222. 

2179. 

2136. 

2096. 

2056. 

2017. 

1979. 

1943. 

1907. 

1872. 

1839. 

1806. 

1774. 

1742. 

1712. 

1704. 

139.231 134.732 

136.288 131.890 

133.443 129.144 

130.692 126.489 

128.032 123.921 

125.457 121.435 

122.964 119.029 

120.551 116.699 

118.212 114.442 

115.947 112.255 

113.750 110.135 

125.732 2012. 1.000 0.000 0.000 

123.095 2003. 1.000 0.000 0.000 

120.546 1995. 1.000 0.000 0.000 

118.082 1986. 1.000 0.000 0.000 

115.698 1978. 1.000 0.000 0.000 

113.392 1969. 1.000 0.000 0.000 

111.159 1961. 1.000 0.000 0.000 

108.996 1953. 1.000 0.000 0.000 

106.902 1945. 1.000 0.000 0.000 

104.872 1937. 1.000 0.000 0.000 

102.904 1930. 1.000 0.000 0.000 

IBHVG2.505 DATE TIME 

BREECH MEAN BASE 

PRESS PRESS PRESS 

(MPA) (MPA) IMPA) 

111.620 108.079 100.996 

109.554 106.084 99.145 

107.549 104.149 97.349 

105.603 102.270 95.605 

103.713 100.446 93.912 

101.878 98.674 92.268 

100.094 96.953 90.670 

98.361 95.280 89.118 

96.676 93.654 87.609 

95.038 92.072 86.141 

93.445 90.534 84.713 

91.894 89.037 83.324 

90.385 87.581 81.973 

88.916 86.163 80.657 

87.486 84.782 79.375 

86.092 83.437 78.127 

84.735 82.127 76.911 

83.412 80.850 75.726 

82.123 79.606 74.572 

81.806 79.300 74.287 

IGREEN GUN TEST CASE - M26El 

CONDITIONS AT: PI-i&X MUZZLE 

TEMP 

(K) 

1922. 

1915. 

1907. 

1900. 

1893. 

1886. 

1879. 

1872. 

1865. 

1859. 

1852. 

1846. 

1839. 

1833. 

1827. 

1820. 

1814. 

1808. 

1802. 

1801. 

FRAC SURFACE BURNING 

BURN AREA RATE 

1 (Wf2) (M/S 1 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

1.000 0.000 0.000 

IBHVG2.505 DATE TIME 

TIME (MS): '5.593 12.525 

TRAVEL (M): 1.5988 6.8400 

VELOCITY (M/S) 569.96 857.83 

4-o 
ACCELERATION (G): 10342. 1704. 

BREECH PRESS (MPA): 447.9999 81.8058 

MEAN PRESS (MPA)! 432.7940 79.2997 

BASE PRESS (MPA): 402.3822 74.2075 

MEAN TEMP (K): 2550. 1801. 

Z CHARGE 1 (-): 1.000 1.000 

ENERGY BALANCE SUMMARY JOULE % 

TOTAL CHEMICAL: 52645464. 100.00 

(1) INTERNAL GAS: 

(2) WORK AND LOSSES: 

30269280. 

22376184. 

57.50 

42.50 

(A) PROJECTILE KINETIC: 10350272. 34.87 

(B) GAS KINETIC: 1418647. 2.69 

(C) PROJECTILE ROTATIONAL: 157282. 0.30 

(D) FRICTIONAL WORK TO TUBE: 0. 0.00 

(E) OTHER FRICTIONAL WORK: 718839. 1.37 

(F) WORK DONE AGAINST AIR: 69870. 0.13 

(G) HEAT CONVECTED TO BORE: 1653274. 3.14 

(H) RECOIL ENERGY: 0. 0.00 

LOADING DENSITY (KG/hi3): 768.061 

CHARGE WT/PROJECTILE WT: 0.232 

PIEZOMETRIC EFFICIENCY: 0.466 

EXPANSION RATIO: 6.840 

41 
hTENTIONALLY LEFTBLANK. 

42 
Appendix C: 

lBHVG2 Performance Calculations 

for M30Al Propellant 

43 
44 
ERRTOL 1.1920929E-07 

1 IBHVG2.505 DATE 

0 CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

& 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

XREEN GUN TEST CASE - M30Al 19F PERFORMANCE IBHVG2.505 DATE 

1 --> $COMM 

2 --> GREEN GUN TEST CASE - INDIAN HEAD SYSTEM 

3 -9 SGUN 

4 --> TRAV = 6.840 CHAM = 0.01506 $ 919 CUBIC INCHES 

5 --> GRVE = 0.12852 LAND = 0.127 TWST = 25 G/L = 1.49 $ ESTIMATES 

6 --> SPROJ 

7 --> PAWT = 49.895 

8 --> $RESI 

9 --> NPTS = 5 

10 --> TRAV = 0.0, 0.0050B, 0.04318, 0.1397, 7.62 

11 --> PRES = 3.4474, 0.6894757, 0.6094757, 8.2737, 8.2737 

12 --> $1~~0 

13 --> POPT = l,l,l,O DELP=0.0005 

14 --> RUN = 'GREEN GUN TEST CASE - M30Al 19P PERFORMANCE' 

15 --> SPRIM 

16 --> NAME = 'PRIMER' CHWT = 0.12637 FORC = 146140 

17 --> GAMA = 1.2015 COV = 0.0010838 TEMP = 3377 

ia --> $pROP 

19 --> NAME = 'M30Al' CHWT = 12.65 FORC = 1073374 

20 --> GAMA = 1.2375 COV = 0.00105239 TEMP = 3036 

21 --> LEN = 0.018288 PD = 0.0004572 WEB = 0.003467 RHO = 1683 

22 --> ALPH = 0.8063 BETA = 0.00196836 

23 --> FORM = '19P' 

24 --> SPARA 

25 --> VARY = 'WEB' DECK = 'PROP' NTH = 1 

26 --> FROM = 0.0030 BY = 0.00002 TO = 0.00501 

27 --> SEND 

TIME 

I * 

<11 . 

TIME 
- _ - _ - - - - - - - - 

- GUN TUBE - 

--_--------- 

TYPE: CHAMBER VOLUME (M3): 0.01506 

GROOVE DIAMETER (M): 0.12852 LAND DIAMETER (M): 0.12700 

TWIST (CALS/TURN): 25.0 BORE AREA (M2): 0.01285 

SHELL THICKNESS (M): 0.000102 SHELL CP (J/XG-K): 460.3163 

INITIAL SHELL TEMP (K): 293. AIR HO (W/M**2-K): 11.3482 

-------------- 

- PROJECTILE - 

-------------- 

TYPE: TOTAL WEIGHT (KG): 

& ---- 

________-_ 

- RESISTANCE - 

------ -------- 

49.895 WEIGHT PREDICTOR OPTION: 

TRAVEL (M): 6.84000 

GROOVE/LAND RATIO (-): 1.490 

HEAT-LOSS OPTION: 1 

SHELL DENSITY (KG/M3): 7861.0918 

AIR RESISTANCE OPTION: 1 WALL HEATING FRACTION: 0.000 

RESISTIVE PRESSURE MULT INDEX: 3 RESISTIVE FACTOR 1.000 FRICTION TABLE LENGTH: 5 

I TRAVEL (M) PRESSURE (MPA) I TRAVEL (M) PRESSURE (MPA) I TRAVEL (M), PRESSURE (MPA) 

1 0.000 3.447 3 0.043 0.689 

2 0.005 0.689 4 0.140 8.274 

5 7.620 a.274 

I. * 

* I 

I 

- GENERAL - 
MAX TIME STEP (S): 0.000100 

PRINT OPTIONS: 111011 

GRADIENT MODEL: LAGRANGIAN 

PRINT STEP (S): 

STORE OPTION: 

0.000500 

0 

MAX RELATIVE ERROR (-): 0,00200 

CONSTANT-PRESSURE OPTION: 0 

__-_-___-_ 

- RECOIL - 

---------- 

RECOIL OPTION: 

---------- 

- PRIMER - 

_____-_--- 

0 TYPE: RECOILING WEIGHT (KG): 0 

TYPE: PRIMER GAMMA (-): 1.2015 

COVOLUME (M3/KG): l.O838E-03 FLAME TEMP (K): 3377 .o 

alGREEN GUN TEST CASE - M30Al 19P PERFORMANCE IBHVG2.505 DATE 

4 

__-_---_-___ 

- CHARGE 1 - 

------------ 

FORCE (J/KG): 

WEIGHT (KG): 

TIME 

146140. 

0.126370 

TYPE: M30Al 

EROSIVE COEFF (-): 

GRAIN LENGTH (M): 

INNER WEB (M): 

,o .oooooo 

0.01828l3 

0.003000 

GRAINS: 1284.0 19P WEIGHT (KG): 12.6500 

CHARGE IGN CODE: 0 CHARGE IGN AT (S): 0.00000E+00 

GRAIN DIAMETER (M): 0.020286 PERF DIAMETER (M): 0.000457 

MIDDLE WEB (M): 0.003000 OUTER WEB (Mf: 0.003000 

PROPERTIES AT LAYER BOUNDARIES OF PERF SURFACES PROPERTIES AT LAYER BOUNDARIES OF END SURFACES 

1ST 2ND 3RD QTH UT 2ND 3RD 4TH 

AT DEPTH (M): ------ -_---- _-_--- 0.00000 ______ ___-_- ____-_ 0.00000 
ADJACENT LAYER WT %: 

DENSITY (KG/M3): 

GAMMA (-): 

FORCE (J/KG): 

COVOLUME (M3/KG): 

FLAME TEMP (K): 

BURNING RATE EXPS: 

BURNING RATE COEFFS: 

------ 

------ 

----__ 

----_- 

------ 

--_-__ 

---___ ------ 

-_-_-_ 

-----_ 

------ 

100.000 

1683.000 

1.2375 

1073374. 

1.05243-03 

3036.0 

0.8063 

1.9684E-03 

-----_ 

------ 

------ 100.000 

----__ ---___ 

---_-_ 1683.000 

----_- ----__ 

----__ 1.2375 

------ 

------ -----_ 1073374. 

-----_ ----_- 

-----_ 1.05243-03 

------ ------ 

-----_ 3036.0 

-----_ ----_- 

----__ 0.8063 

----__ ---___ 

------ 1.9684E-03 

PROPERTIES AT LAYER BOUNDARIES OF LAT SURFACES 

1ST 2ND 3RD 4TH 

AT DEPTH (M): _____- 

------ 

ADJACENT LAYER WT %: ---__- 

------ 

DENSITY (KG/M3): ------ 

---___ 

GAMMA I-): ------ 

--*--- 

$ 

FORCE (J/KG): ------ 

------ 

COVOLUME (M3/KG): ------ -__-__ 

FLAME TEMP (K): ----__ ------ 

BURNING RATE EXPS: --____ 

------ 

BURNING RATE COEFFS: ------ 

------ 

IGREEN GUN TEST CASE - M30Al 19P PERFORMANCE 

-----_ 0.00000 

---"-- 100.000 

------ 1683.000 

------ 1.2375 

------ 1073374. 

------ 1.0524E-03 

------ 3036.0 

------ 0.0063 

-----_ 1.96843-03 

IBHVG2.505 DATE TIME 

TIME TRAV VEL ACC 

(MS 1 (M) (M/S) (G) 

0 0.000 0.000 0.00 0. 

0.277 0.000 0.00 0. 

SHOT-START PRESSURE ACHIEVED 

0.500 0.000 0.02 23. 

1.000 0.000 0.30 96. 

1.500 0.000 1.02 206. 

BREECH MEAN 

PRESS PRESS 

(MPA) IMPA) 

2.493 2.493 

3.447 3.447 

4.448 4.410 4.334 3234 0.001 

7.515 7.360 7.049 3156 0.003 

12.078 11.743 11.075 3112 0.005 

BASE 

PRESS 

(Mph) 

2.493 

3.447 

MEAN 

TEMP 

(K) 

3377. 

3287. 

FRAC 

BURN 

1 

0.000 

0.001 
2.000 0.001 2.41 369. 18.664 18.064 16.863 3084. 0.008 

2.500 0.003 4.77 607. 27.925 26.939 24.965 3066. 0.013 

3.000 0.006 8.51 929. 40.612 39.102 36.082 3052. 0.020 

3.500 0.012 13.99 1323. 57.536 55.386 51.085 3040. 0.029 

4.000 0.021 21.69 1838. 79.654 76.667 70.692 3027. 0.041 

4.500 0.034 32.25 2493. 107.798 103.747 95.643 3011. 0.057 

5.000 0.053 46.37 3282. 142.481 137.147 126.481 2992. 0.077 

5.500 0.081 64.63 4189. 183.637 176.826 163.212 2967. 0.103 

6.000 0.119 87.64 5208. 230.353 221.890 204.965 2,937. 0.136 

6.500 0.169 115.87 6340. 280.646 270.343 249.738 2901. 0.177 

7.000 0.236 149.87 7519. 331.295 319.077 294.641 2859. 0.226 

7.500 0.320 189.46 8611. 378.243 364.249 336.263 2813. 0.285 

8.000 0.426 234.02 9527. 417.611 402.130 371.167 2764. 0.352 

8.500 0.555 282.49 10200. 446.570 429.994 396.844 2714. 0.426 

9.000 0.709 333.60 10602. 463.912 446.682 412.223 2664. 0.500 

9.500 0.889 386.04 10744. 470.072 452.612 417.691 2617. 0.594 

P 9.555 0.910 391.85 10746. 470.129 452.667 417.743 2612. 0.604 

W LOCAL PRESSURE MAX DETECTED 

10.000 1.095 438.61 10664. 

10.500 1.327 490.34 10412. 

11.000 1.585 540.51 10011. 

11.500 1.867 587.38 9047. 

12.000 2.172 629.02 7937. 

12.500 2.495 665.36 6914. 

13.000 2.836 697.07 6048. 

13.500 3.192 724.86 5299. 

14.000 3.560 749.21 4651. 

14.500 3.940 770.63 4100. 

14.911 4.260 786.34 3710. 

PROPELLANT 1 BURNED OUT 

15.000 4.331 789.55 3632. 

15.500 4.730 806.37 3237. 

466.677 

455.930 

438.775 

397.438 

349.841 

305.970 

268.841 

236.727 

208.957 

185.341 

168.618 

165.275 

148.339 

449.348 414.689 2572. 0.683 

439.010 405.170 2529. 0.774 

422.506 389.970 2488. 0.863 

382.737 353.334 2431. 0.917 

336.943 311.148 2367. 0.948 

294.734 272.264 2304. 0.967 

259.013 239.357 2246. 0.983 

228.116 210.894 2191. 0.992 

201.399 186.282 2137. 0.997 

178.678 165.351 2086. 0.999 

162.589 150.530 2047. 1.000 

159.372 

143.079 

147.567 

132.559 

2038, 

1994. 

1.000 

1.000 
16.000 5.137 821.40 2902. 134.007 129.291 119.057 1953. 

16.500 5.551 834.91 2617. 121.770 117.517 109.012 1915. 

17.000 5.971 847.13 2371. 111.236 107.383 99.677 1879. 

17.500 6.398 858.22 2158. 102.099 98.593 91.581 1846. 

18.000 6.029 868.33 1971. 94.120 90.917 84.510 1815. 

18.012 6.840 868.56 1967. 93.939 90.742 84.350 1814. 

PROJECTILE EXIT 

1.000 

1.000 

1.000 

1.000 

1.000 

1.000 

1GREEN GUN TEST CASE - M30Al 19P PERFORMANCE IBHVG2.505 DATE TIME 

CONDITIONS AT: 

TIME (MS): 

TRAVEL (M): 

VELOCITY (M/S) 

3 ACCELERATION (G): 

BREECH PRESS (MPA) 

MEAN PRESS (WA): 

BASE PRESS (MPA): 

MEAN TEMP (X): 

Z CHARGE 1 (-}: 

PMAX MUZZLE 

9.555 18.012 

0.9102 6.8400 

391.85 860.56 

10746. 1967. 

470.1292 93.9389 

452.6669 90.7424 

417.7426 04.3496 

2612. 1814. 

0.604 1.000 

ENERGY BALANCE SUMMARY JOULE % 

TOTAL CHEMICAL: 57251044. 100.00 

(1) INTERNAL GAS: 34206272. 59.75 

(2) WORK AND LOSSES: 23044770. 40.25 

(A) PROJECTILE KINETIC: 18820410. 32.87 

,I r 
(B) GAS KINETIC: 1606417. 2.81 

(C) PROJECTILE ROTATIONAL: 148600. 0.26 

(D) FRICTIONAL WORK TO TUBE: 0. 0.00 

(E) OTHER FRICTIONAL WORK: 718397, 1.25 

(F) WORK DONE AGAINST AIR: 68561. 0.12 

(G) HEAT CONVECTED TO BORE: 1682386. 2.94 

(H) RECOIL ENERGY: 0. 0.00 

LOADING DENSITY (KG/M3): 848.365 

CHARGE WT/PROJECTILE WT: 0.256 

PIEZOMETRIC EFFICIENCY: 0.455 

EXPANSION RATIO: 6.036 

mlGREEN GUN TEST CASE - M30Al 19P PERFORMANCE 

- 

PARAMETRIC VARIABLES: / 1/ PROP 1 WEB 

/I/ PMAX VMUZ PMUZ Z(1) X@Z=l 

0 0.3000E-02 470.129 868.56 84.350 1.000 3.940 

0.30203-02 463.022 866.16 04.667 1.000 4.274 

0.304OE-02 456.125 863.60 04.946 1.000 4.218 

0.30603-02 449.431 860.93 85.206 1.000 4.553 

0.30803-02 442.933 858.40 85.503 1.000 4.495 

0.3100E-02 436.620 855.71 05.764 1.000 4.832 

0.31203-02 430.480 853.11 B6.053 1.000 4.773 

0.314OE-02 424.527 850.57 B6.356 1.000 5.111 

0.31603-02 410.731 847.84 86.613 1.000 5.051 

0.31803-02 413.094 845.20 86.902 1.000 5.390 

0.32003-02 407.608 842.51 87.181 1.000 5.328 

IBRVG2.505 DATE TIME 
0.32203-02 402.270 

0.32403-02 397.071 

0.32603-02 392.008 

0.3280E-02 387.078 

0.3300E-02 382.273 

0.3320E-02 377.590 

0.33403-02 373.022 

0.33603-02 368.567 

0.33803-02 364.221 

0.34003-02 359.980 

0.34203-02 355.841 

0.34403-02 351.801 

0.34603-02 347.1353 

0.34803-02 343.997 

0.35003-02 340.230 

0.35203-02 336.548 

G 0.35403-02 332.952 

0.35603-02 329.434 

0.35803-02 325.993 

0.36003-02 322.628 

0.36203-02 319.337 

0.3640E-02 316.115 

0.36603-02 312.963 

0.36803-02 309.876 

0 37003-02 306.854 

0 37203-02 303.894 

0 3740E-02 300.995 

0 37603-02 298.155 

0 37803-02 295.373 

0 38003-02 292.646 

0 3820E-02 289.972 

0.3840E-02 287.351 

839.91 87.408 1.000 5.668 

837.15 87.756 1.000 5.605 

834.42 88.035 1.000 5.945 

831.82 88.358 1.000 5.882 

820.99 88.616 1.000 6.222 

826.23 88.903 1.000 6.564 

823.55 89.217 1.000 6.498 

020.72 89.405 1.000 6.840 

817.91 89.753 1.000 6.840 

815.13 90.027 1.000 6.840 

812.29 90.269 0.999 6.840 

809.52 90.526 0.999 6.840 

806.65 90.743 0.999 6.840 

803.85 90.976 0.990 6.840 

800.94 91.163 0.997 6.840 

798.11 91.365 0.997 6.840 

795.1'9 91.524 0.996 6.840 

792.32 91.694 0.995 6.840 

789.39 91.825 0.994 6.840 

786.50 91.966 0.993 6.840 

783.57 92.073 0.992 6.840 

780.67 92.179 0.990 6.840 

777.77 92.270 0.909 6.640 

774.01 92.310 0.987 6.640 

771.89 92.333 0.985 6.840 

760.98 92.344 0.983 6.640 

766.03 92.325 0.901 6.840 

763.11 92.323 0.979 6.840 

760.1B 92.308 0.977 6.840 

757.26 92.302 0.975 6.840 

754.31 92.271 0.973 6.840 

751.38 92.244 0.971 6.840 
0.38603-02 284.782 748.46 92 221 0.969 6.1340 

0.38803-02 282.262 745.53 92 186 0.967 6.840 

0.3900E-02 279.791 742.59 92 150 6.964 6.840 

0.392OE-02 277.367 739.67 92 112 0.962 6.840 

0.39403-02 274.987 736.74 92 070 0.960 6.840 

0.39603-02 272.653 733.81 92 024 0.958 6.840 

0.390OE-02 270.361 730.88 91 971 0.955 6.840 

0.4000E-02 268.112 727.95 91 910 0.953 6.840 

0.4020E-02 265.904 725.03 91 829 0.951 6.840 

0.40403-02 263.736 722.10 91 730 0.948 6.840 

0.4060E-02 261.607 719.17 91 613 0.945 6.840 

~GREEN GUN TEST CASE - M30Al 19P PERFORMANCE 

PARAMETPIC VARIABLES: / 1/ PROP 1 WEB 

/I/ PMAX 

~10 0.4080E-02 259.515 

w 

0.4100E-02 257.460 

0.4120E-02 255.442 

0.414OE-02 253.45B 

0.4160E-02 251.509 

0.4180E-02 249.595 

0.42003-02 247.712 

0.4220E-02 245.860 

0.42403-02 244.041 

0.42603-02 242.251 

0.42803-02 240.491 

0.43003-02 238.760 

0.43203-02 237.057 

0.43403-02 235.381 

0.43603-02 233.733 

0.43803-02 232.111 

VMUZ PMCIZ Z(l) X@Z-1 

716.26 91.482 0.943 6.840 

713.34 91.329 0.940 6.840 

710.43 91.158 0.937 6.840 

707.54 90.983 0.934 6.840 

704.64 90.767 0.930 6.840 

701.75 90.542 0.927 6.840 

698.87 90.290 0.923 6.840 

696.00 90.032 0.920 6.840 

693.14 89.740 0.916 6.840 

690.30 89.431 0.912 6.840 

687.47 89.104 0,908 6.840 

684.65 88.749 0.903 6.840 

681.84 88.377 O.B99 6.840 

679.05 87.970 0.895 6.840 

676.28 87.542 O.B90 6.840 

673.53 87.077 0.885 6.840 

IBHVG2.505 DATE TIME 
0.4400E-02 230.514 

0.44203-02 228.943 

0.44403-02 227.396 

0.44603-02 225.874 

0.44803-02 224.375 

0.45003-02 222.898 

0.45203-02 221.444 

0.45403-02 220.012 

0.45603-02 218.601 

0.45803-02 217.212 

O.Q600E-02 215.844 

0.46203-02 214.497 

0.46403-02 213.168 

0.46603-02 211.858 

0.46803-02 210.568 

0.47003-02 209.296 

E 0.47203-02 208.042 

0.47403-02 206.806 

0.47603-02 205.587 

0.47803-02 204.386 

0.48003-02 203.201 

0.48203-02 202.033 

0.48403-02 200.880 

0.4860E-02 199.744 

0.4880E-02 198.622 

0.4900E-02 197.516 

0.4920E-02 196.426 

0.4940E-02 195.349 

0.49603-02 194.287 

0.49803-02 193.23B 

0.5000E-02 192.204 

IGREEN GUN TEST CASE - 

670.80 86.580 0.880 6.840 

668.10 86.041 0.874 6.840 

665.42 85.413 0.868 6.840 

662.77 84.725 0.862 6.840 

660.15 84.047 0.855 6.840 

657.56 83.379 0.849 6.840 

655.00 82.722 0.843 6.840 

652.47 82.075 0.837 6.840 

649.97 81.438 0.831 6.840 

647.50 80.811 0.825 6.840 

645.06 80.194 0.819 6.840 

642.64 79.586 0.814 6.840 

640.26 78.987 0.808 6.840 

637.09 78.397 0.802 6.840 

635.56 77.816 0.797 6.840 

633.25 77.244 0.792 6.040 

630.97 76.680 0.786 6.840 

628.71 76.124 0.781 6.840 

626.48 75.577 0.776 6.840 

624.27 75.038 0.771 6.840 

622.08 74.506 0.766 6.840 

619.92 73.982 0.761 6.840 

617.78 73.465 0.756 6.840 

615.67 72.956 0.751 6.840 

613.57 72.454 0.746 6.840 

611.50 71.959 0.742 6.840 

609.45 71.471 0.737 6.840 

607.43 70.990 0.732 6.840 

605.42 70.516 0.728 6.840 

603.43 70.04B 0.723 6.840 

601.47 69.586 0.719 6.840 

M30A1 19P PERFORMANCE IBHVG2.505 DATE TIME 
0 CARD 28 --> SSAVE 

CARD 29 --> $INFO 

CARD 30 --> POPT - l,O,O,O $ PRINT INPUT ECHO, MINIMIZE TRAJ PRINT 

CARD 31 --> RUN = ‘GREEN GUN TEST CASE - M30Al ?P PERFORMANCE' 

CARD 32 --> $PROP 

CARD 33 --> FORM = '7P' 

CARD 34 --> SEND 

1GREEN GUN TEST CASE - M30Al 7P PERFORMANCE IBHVG2.505 DATE TIME 

- GUN TUBE - 

TYPE: CHAMBER VOLUME (M3): 0.01506 TRAVEL (M): 6.84000 

GROOVE DIAMETER (M): 0.12852 LAND DIAMETER (M): 0.12700 GROOVE/LAND RATIO (-): 1,490 

E 

TWIST (CALS/TURN): 25.0 BORE AREA (M2): 0.01285 HEAT-LOSS OPTION: 1 

SHELL THICKNESS (M): 0,000102 SHELL CP (J/KG-K): 460.3163 SHELL DENSITY (KG/M3): 7861.0918 

INITIAL SHELL TEMP (K): 293. AIR HO (W/M**2-K): 11.3482 

- PROJECTILE - 

TYPE: 

---____-_-____ 

- RESISTANCE - 

----___-_-____ 

TOTAL WEIGHT (KG): 49.895 WEIGHT PREDICTOR OPTION: 

AIR RESISTANCE OPTION: 1 WALL HEATING FRACTION: 

RESISTIVE PRESSURE MULT INDEX: 3 RESISTIVE FACTOR 

0.000 

1.000 FRICTION TABLE LENGTH: 5 

0 
‘I TRAVEL (M) PRESSURE (MPA) I TRAVEL (M) PRESSURE (MFA) 

1 0.000 

2 0.005 

3.447 3 0.043 0.689 

0.689 4 0.140 8.274 

____-_____- 

- GENERAL - 

- - - - - - - - - - - 

I TRAVEL (M), PRESSURE (MPA) 

5 7.620 8.274 

MAX TIME STEP (S): 0.000100 PRINT STEP (S): 

PRINT OPTIONS: 10 0 0 1.1 STORE OPTION: 

GRADIENT MODEL: LAGRANGIAN 

---------- 

- RECOIL - 

- - - - - - - - - - 

2 

RECOIL OPTION: 0 TYPE: 

---------- 

- PRIMER - 

0.000500 

0 

TYPE: PRIMER GAMMA (-): 1.2015 

COVOLUME (M3/KG): 1.08383-03 FLAME TEMP (K): 3377.0 

~GREEN GUN TEST CASE - M30Al 7P PERFORMANCE IBHVG2.505 DATE 

MAX RELATIVE ERROR (-): a.oo20Q 

CONSTANT-PRESSURE OPTION: 0 

RECOILING WEIGHT (KG): 0 

FORCE (J/KG): 

WEIGHT (KG): 

TIME 

146140. 

0.126370 

- CHARGE 1 - 
TYPE: M30Al GRAINS: 2950.9 7P 

EROSIVE COEFF (-) : 0 .oooooo CHARGE IGN CODE: 0 

GRAIN LENGTH (M): 0.018288 GRAIN DIAMETER (M): 0.013372 

INNER WEB (M): 0.003000 OUTER WEB (M): 0.003000 

WEIGHT (KG): 12.6500 

CHARGE IGN AT (S): O.00000Et00 

PERF DIAMETER (M): 0.000457 

PROPERTIES AT LAYER BOUNDARIES OF PERF SURFACES PROPERTIES AT LAYER BOUNDARIES OF END SURFACES 

1ST 2ND 3RD 4TH NT 2ND- ~RD 4TH 

AT DEPTH (M): 

ADJACENT LAYER WT %: 

DENSITY (KG/M3): 

GAMMA (-1: 

FORCE (J/KG): 

COVOLUME (M3/KG): 

FLAME TEMP (K): 

BURNING RATE EXPS: 

Y 

BURNING RATE COEFFS: 

----_- ______ -_---- 0.00000 -_---- ---__- 

-_____ 0.00000 

----_- 

------ ----_- 100.000 _____- ------ ------ 100.000 

------ ------ ------ 1683.000 --___- ------ -----_ 16EI3.000 

--_--- ------ ------ 1.2375 -----_ ------ ------ 1.2375 

______ ____-_ ______ 1073374. ------ ----__ ______ 1073374. 

--_--- _----- ------ 1.05243-03 __---- _-____ -----_ 1.05243-03 

------ 

______ 

-_--__ 3036.0 

_____- ------ ------ 0.8063 

-_--_- ______ ----__ 3036.0 

_-_--_ ______ ---_-- 0.8063 

_-_--- ______ ______ 1.9684E-03 ------ _---_- ______ 1.96043-03 

PROPERTIES AT LAYER BOUNDARIES OF LAT SURFACES 

1ST 2ND 3RD 4TH 

AT DEPTH (M): ------ ------ 

ADJACENT LAYER WT %: -____- ___-_- 

DENSITY (KGjM3): _--_-- 

GAMMA (-): ---_-- ------ 

FORCE (J/KG): ____-- ----_- 

COVOLUME (M3/KG): ____-_ ------ 

FLAME TEMP (K): ______ ___-_- 

BURNING RATE EXPS: ___-__ ___-__ 

BURNING RATE COEFFS: --_--_ ______ 

~GREEN GUN TEST CASE - ~30~1 7~ PERFORMANCE 

------ 0.00000 

------ 100.000 

______ 1683.000 

____-_ 1.2375 

------ 10?33?4. 

------ l.OS24E-03 

------ 3036.0 

------ 0.8063 

------ 1.96843-03 

IBHVG2.505 DATE TIME 
PARAMETRIC VARIABLES: / 1/ PROP 1 WEB 

/I/ PMAX 

0 0.3000E-02 554.378 

0.30203-02 546.707 

0.3040&-02 539.250 

0.30603-02 532.000 

0.30BOE-02 524.946 

0.3100E-02 518.081 

0.31203-02 511.396 

0.31403-02 504.889 

0.31603-02 498.548 

0.31803-02 492.369 

0.32003-02 486.349 

0.32203-02 480.477 

0.32403-02 474.750 

k2 

0.32603-02 469.163 

0.32803-02 463.710 

0.33003-02 458.389 

0.33203-02 453.193 

0.33403-02 448.116 

0.33603-02 443.157 

0.33803-02 438.312 

0.34003-02 433.576 

0.34203-02 428.946 

0.34403-02 424.419 

0.34603-02 419.990 

0.34803-02 415.657 

0.35003-02 411.418 

0.35203-02 407.270 

0.35403-02 403.209 

0.35603-02 399.234 

VMUZ mm Z(l) X@Z=l 

895.63 01.329 1.000 3.058 

893.39 81.584 1.000 3.396 

891.14 81.839 1.000 3.351 

888.88 02.094 1.000 3.694 

886.62 82.351 1.000 3.648 

884.36 82.611 1.000 3.603 

882.10 82.876 1.000 3.947 

879.91 83.161 1.000 3.900 

877.63 83.426 1.000 3.054 

875.24 83.667 1.000 4.199 

872.86 83.912 1.000 4.151 

870.40 84.160 1.000 4.499 

868.12 84.418 1.000 4.450 

865.78 84.684 1.000 4.800 

863.37 84.931 1.000 4.750 

8fiO.98 85.192 1.000 4.700 

858.73 85.494 1.000 5.050 

856.24 85.729 1.000 4.999 

853.78 85.979 1.000 5.351 

851.36 86.244 1.000 5.298 

048.90 86.498 1.000 5.651 

046.55 86.795 1.000 5.598 

844.01 87.033 1.000 5.952 

841.55 87.301 1.000 5.897 

839.03 87.555 1.000 6.252 

036.59 87.840 1.000 6.609 

034.04 88.091 1.000 6.552 

831.50 88.349 1.000 6.840 

829.03 88.625 1.000 6.840 
c . 

0.35803-02 395.330 826.44 88.850 1.000 6.840 

0.36003-02 391.522 823.87 89.079 0.999 6.840 

0.36203-02 387.705 821.34 89.315 0.999 6.840 

0.36403-02 384.123 818.75 09.524 0.999 6.840 

0.36603-02 380.534 816.22 89.750 0.999 6.840 

0.3680E-02 377.016 813.57 09.922 0.998 6.840 

0.3700E-02 373.566 810.97 90.108 0.997 6.840 

0.3720E-02 370.183 808.36 90.283 0.997 6.840 

0.37403-02 366.865 805.74 90.448 0.996 6.840 

0.37603-02 363,610 803.11 90.607 0.995 6.840 

0.37803-02 360.416 800.48 90.756 0.994 6.840 

0.38003-02 357.282 797.85 90.895 0.993 6.840 

0.38203-02 354.207 795.23 91.042 0.993 6.840 

0.38403-02 351.188 792.55 91.144 0.991 6.840 

0.38603-02 348.225 789.90 91.258 0.990 6.840 

0.3880E-02 345.315 787.23 91.351 0.989 6.840 

2 0.3900E-02 342.457 784.57 91.449 0.988 6.840 

0.3920E-02 339.651 781.90 91.535 0.987 6.840 

0.39403-02 336.894 779.22 91.597 0.985 6.840 

0.39603-02 334.185 776.54 91.667 0.984 6.840 

0.39803-02 331.522 773.86 91.719 0.982 6.840 

O.QOOOE-02 328.905 771.19 91.775 0.981 6.840 

0.4020E-02 326.335 768.48 91.794 0.979 6.840 

0.404OE-02 323.807 765.80 91.823 0.978 6.840 

0.4060E-02 321.322 763.11 91.836 0.976 6.840 

IGREEN GUN TEST CASE - M30Al 7P PERFORMANCE 

PARAMETRIC VARIABLES: / l/ PROP 1 WEB 

IBHVG2.505 DATE TIME 

/I/ PMAX V-Mm PMUZ Z(l) X@Z=l 

0 0.40803-02 318.879 760.41 91.835 0.974 6.840 

0.4100E-02 316.477 757.73 91.820 0.972 6.840 
0.4120E-02 314.113 755.04 91.788 0.970 6.840 

0.414OE-02 311.787 752.35 91.739 0.968 6.840 

0.41603-02 309.500 749.65 91.658 0.965 6.840 

0.41803-02 307.249 746.96 91.570 0.963 6.840 

0.42003-02 305.035 744.28 91.465 0.961 6.840 

0.42203-02 302.857 741.60 91.345 0.958 6.840 

0.42403-02 300.713 738.93 91.214 0.955 6.840 

0.42603-02 298.602 736.26 91.052 0.952 6.840 

0.428OE-02 296.523 733.60 90.872 0.949 6.840 

0.4300E-02 294.477 730.94 90.674 0.946 6.840 

0.4320E-02 292.462 728.30 90.462 0.943 6.840 

0.43406-02 290.478 725.66 90.223 0.940 6.840 

0.43608-02 288.523 723.03 89.971 0.936 6.840 

0.438OE-02 286.599 720.41 89.696 0.932 6.840 

0.4400E-02 284.703 717.81 89.397 0.929 6.840 

0.44203-02 282.833 715.22 89.070 0.925 6.840 

0.44403-02 280.993 712.64 88.725 0.921 6.040 

0.44603-02 279.179 710.08 88.346 0.916 6.840 

0.44BOE-02 277.392 707.54 87.939 0.912 6.840 

0.45003-02 275.630 705.01 87.484 0.907 6.840 

0.45203-02 273.093 702.51 86.977 0.902 6.840 

0.454OE-02 272.182 700.03 86.379 0.896 6.840 

0.4560E-02 270.494 697.5B 85.786 0.690 6.040 

0.4580E-02 268.829 695.15 85.202 0.885 6.840 

0.46003-02 267.188 692.75 84.626 0.879 6.840 

0.46203-02 265.571 690.38 84.058 0.874 6.840 

0,4640E-02 263.975 688.03 83.498 0.868 6.840 

0.46603-02 262.401 685.70 82.945 0.863 6.840 

0.46803-02 260.849 683.40 82.401 0.858 6.840 

0.4700E-02 259.319 681.13 81.863 0.852 6.840 

0.47203-02 257.808 678.88 81.333 0.847 6.840 

0.47403-02 256.317 676.65 80.810 0.842 6.840 

l ’ 
0.4760E-02 254.846 674.44 80,294 0.837 6 840 

0.4780E-02 253.394 672,26 79.785 0.032 6 040 

0.48003-02 251.962 670.10 79.283 0.020 6 040 

0.48203-02 250.548 667.95 78.707 0.823 6 040 

0.48403-02 249.153 665.04 78.290 0.818 6 840 

0.4860E-02 247.776 663.74 77.815 0.013 6 040 

0.48803-02 246.416 661.66 77.339 0.809 6 840 

0,49OOE-02 245.074 659.61 76.869 0.804 6 840 

0.49203-02 243.748 657.57 76.405 0.800 6 840 

0.4940E-02 242.439 655,55 75.946 0.795 6 040 

0.4960E-02 241.147 653.56 75.494 0.791 6 840 

0.49803-02 239.870 651.58 75.047 0.786 6 840 

0.5000E-02 238.610 649.62 74.606 0.782 6 840 

1GREEN GUN TEST CASE - M30A1 7P PERFORMANCE IBHVG2.505 DATE 

0 CARD 35 --> $SAVE 

m CARD 36 --> $YNFO 

e 

CARD 37 --> RUN = 'GREEN GUN TEST CASE - M3OA1 1P PERFORMANCE' 

CARD 38 --> SPROP 

CARD 39 --> FORM = '1P' 

CARD 40 --> SEND 

1GREEN GUN TEST CASE - M30Al 1P PERFORMhNCE IBHVG2.505 DATE 

- _ _ _ - - _ _ _ - - - 

- GUN TUBE - 

-- ---- - ----- 

TYPE: CHAMBER VOLUME (M3): 0.01506 

GROOVE DIAMETER (M): 0.12852 LAND DIAMETER (M): 0.12700 

TWIST (CALS/TURN): 25.0 BORE AREA (M2): 0.01285 

SHELL THICKNESS (M): 0.000102 SHELL CP (J/KG-K): 460.3163 

TIME 

TIME 

TRAVEL (M): 6.84000 

GROOVE/LAND RATIO (-): 1.490 

HEAT-LOSS OPTION: 1 

SHELL DENSITY (KG/'N3): 7861.0918 
INITIAL SHELL TEMP (K): 293. AIR HO (W/N**2-K): 11.3482 

- PROJECTILE - 

TYPE: TOTAL WEIGHT (KG): 49.895 WEIGHT PREDICTOR OPTION: 0 

___________--- 

- RESISTANCE - 

_- ----_- -_---- 

AIR RESISTANCE OPTION: 1 WALL HEATING FRACTION: 0.000 

RESISTIVE PRESSURE MULT INDEX: 3 RESISTIVE FACTOR 1.000 FRICTION TABLE LENGTH: 5 

I TRAVEL (M) PRESSURE (MPA) I TRAVEL (M) PRESSURE (MPA) I TRAVEL (M), PRESSURE (MPA) 

c 

1 0.000 3.447 3 0.043 0.609 5 7.620 8.274 

2 0.005 0.689 4 0.140 8.274 

_____--_--- 

- GENERAL - 

MAX TIME STEP (S): 0.000100 

PRINT OPTIONS: 1OOOll 

GRADIENT MODEL: LAGRANGIAN 

PRINT STEP (S): 

STORE OPTION: 

__-_-_____ 

- RECOIL - 

____---___ 

0.000500 MAX RELATIVE ERROR (-): 0.00200 

0 CONSTANT-PRESSIIRE OPTION: 0 
. I 

. I. 

RECOIL OPTION: 

- PRIMER 

---------- 

0 TYPE: 

TYPE: PRIMER GAMMA (-): 1.2015 

COVOLUME (M3/KG): 1.083BE-03 FLAME TEMP (K): 3377.0 

IGREEN GUN TEST CASE - M30Al 1P PERFORMANCE IBHVG2.505 DATE 

______ -_-_-_ 

- CHARGE 1 - 

--____ - --_-_ 

TYPE: M3OAl 

E 

EROSIVE COEFF (-): 

GRAIN LENGTH (M): 

INNER WEB (M): 

AT DEPTH (M): 

ADJACENT LAYER WT % 

DENSITY (KG/M3): 

GAMMA (-): 

FORCE (J/KG): 

COVOLUME (M3/KG): 

FLAME TEMP (K): 

BWRNING RATE EXPS: 

BURNING RATE COEFFS 

RECOILING WEIGHT (KG): 

FORCE (J/KG): 

WEIGHT (KG): 

TIME 

0. 

146140. 

0.126370 

GRAINS: 12614. 1P WEIGHT (KG): 12.6500 

0.000000 CHARGE IGN CODE: 0 CHARGE IGN AT (S): 0.00000Et00 

0.018288 GRAIN DIAMETER (M): 0.006457 PERF DIAMETER (M): 0.000457 

0.003000 WEB RATIO: 1.0000 

PROPERTIES AT LAYER BOUNDARIES OF PERF SURFACES PROPERTIES AT LAYER BOUNDARIES OF END SURFACES 

1ST 2ND 3RD 4TH 1ST 2ND 3RD 4TH 

----_- __---- ---___ 0 .ooooo 

----_- --_--- ------ 100.000 

-_---- -----_ ------ 1683.000 

_-_--- _____- ------ 1.2375 

------ _____- ---* -- 1073374. 

------ ------ ----__ l.O524E-03 

------ _-_--- ------ 3036.0 

_----- __-_-- ------ 0.8063 

__--_- _____- ------ 1.96843-03 

_-____ -__--- ____-- 0.00000 

------ -__--- ------ 100.000 

------ ------ _---_- 1683.000 

------ --_--- ___-_- 1.2375 

__-___ -_---- ______ 1073374. 

_--_-_ ------ __---- 1.05243-03 

---___ -_---- ___--- 3036.0 

---___ -__--- -_--_- 0.8063 

------ ------ _----- 1.9684E-03 
AT DEPTH (M): 

ADJACENT LAYER WT a: 

DENSITY (KG/M3): 

GAMMA (-): 

FORCE (J/KG): 

COVOLUME (M3/KG): 

FLAME TEMP (K): 

BURNING RATE EXPS: 

BURNING RATE COEFFS: 

PROPERTIES AT LAYER BOUNDARIES OF LAT SURFACES 

1ST 2ND 3RD 4TH 

-----_ __-___ 

------ 0.00000 

------ 

---___ ----__ 100.000 

------ 

-----_ ------ 1683.000 

-----_ ------ ------ 1.2375 

------ ------ ------ 1073374. 

______ ______ _----- 1.05243-03 

------ ------ 

---_-- 3036.0 

----__ -_____ 

--__-_ 0.8063 

------ ------ ------ 1.96843-03 

IGREEN GUN TEST CASE - M30Al 1P PERFORMANCE IBHVGZ.505 DATE TIME 

PARAMETRIC VARIABLES': / I/ PROP 1 WEB 

$ 

/I/ PMAX vuuz PMUZ Z(l) X@Z=l 

0 0.3000E-02 913.691 963.31 73.056 1.000 0.968 

0.30203-02 902.632 962.34 73.348 1.000 0.952 

0.30403-02 891.834 961.39 73.647 1.000 0.936 

0.30603-02 881.294 958.71 73.605 1.000 0.921 

0.30803-02 871.006 958.31 74.021 1.000 0.906 

0.3100E-02 860.959 956.54 74.163 1.000 1.185 

0.31203-02 851.144 954.00 74.140 1.000 1.166 

0.31403-02 841.554 952.85 74.411 1.000 1.149 

0.31603-02 832.178 951.66 74.678 1.000 1.131 

0.31803-02 823.008 950.43 74.940 1.000 1.114 

0.32003-02 814.042 947.96 74.924 1.000 1.098 

0.32203-02 805.271 946.70 75.182 1.000 1.082 

0.32403-02 796.690 945.40 75.435 1.000 1.370 

0.32603-02 788.293 944.07 75.684 1.000 1.352 

1 II * I 

I 
0.32803-02 780.073 941.68 75.676 1.000 1.333 

0.33003-02 772.026 940.32 75.922 1.000 1.315 

0.33203-02 764.144 930.94 76.164 1.000 1.297 

0.3340E-02 756.422 937.52 76.402 1.000 1.279 

0.3360E-02 748.858 936.06 76.637 1.000 1.579 

0.33803-02 741.445 933,76 76.637 1.000 1.559 

0.34003-02 734.101 932.30 76.869 1.000 1.539 

0.3420E-02 727.061 930.82 77.098 1.000 1.520 

0.34403-02 720.082 929.32 77.324 1.000 1.501 

0.34603-02 713.234 928.06 77.626 1.000 1.482 

0.34803-02 706.517 926.25 77.766 1.000 1.789 

0.35003-02 699.929 924.77 78.011 1.000 1.769 

0.3520E-02 693.466 923.12 78.204 1.000 1.748 

0.3540E-02 687.122 921.46 78.397 1.000 1.728 

0.3560E-02 680.896 919.28 78.421 1.000 1.708 

0.3580E-02 674.704 917.67 78.631 1.000 1.689 

E 0.36003-02 668.782 916.04 78.839 1.000 2.002 

0.36203-02 662.887 914.40 79.044 1.000 1.980 

0.36403-02 657.099 912.75 79.247 1.000 1.959 

0.36603-02 651.413 911.08 79.449 1.000 1.938 

0.36803-02 645.825 909.40 79.647 1.000 1.918 

0.37003-02 640.335 907.71 79.845 1.000 2.238 

0.37203-02 634.941 906.00 80.040 1.000 2.216 

0.37403-02 629.640 904.29 80.233 1.000 2.193 

0.3760E-02 624.426 902.56 00.425 1.000 2.172 

0.3780E-02 619,299 900.03 80.615 1.000 2.150 

0.38003-02 614.259 099.08 80.804 1.000 2.476 

0.38203-02 609.305 897.33 80.991 1.000 2.452 

0.38403-02 604.431 895.91 81.330 1.000 2.429 

0.38603-02 599.637 094.12 81.509 1.000 2.407 

0.38803-02 594.920 092.41 81.727 1.000 2.739 

0.39003-02 590.279 890.52 81.869 1.000 2.714 
0.39203-02 585.709 880.87 82.124 1.000 2.690 

0.3940E-02 581.214 886.90 82.224 1.000 2.667 

0.39603-02 576.789 885.08 82.401 1.000 2.644 

0.39803-02 572.433 883.53 82.722 1.000 2.978 

0.4000E-02 568.144 881.66 82.880 1.000 2.954 

0.40203-02 563.921 879.81 83.052 1.000 2.929 

O.Q040E-02 559.763 877.96 83.223 1.000 2.905 

0.40603-02 555.668 876.31 83.524 1.000 3.244 

IGREEN GUN TEST cAsE - M30Al 1P PERFORMANCE IBHVG2.505 DATE 

PARAMETRIC VARIABLES: / 1/ PROP 1 WEB 

/I/ PMAX VMUZ PMUZ Z(l) X@Z=l 

0 0.4060E-02 551.633 874.42 83.683 1.000 3.218 

0.4100E-02 547.658 872.67 83.927 1.000 3.193 

0,4120E-02 543.742 870.66 84.017 1.000 3.168 

Fl 0.4140E-02 539.883 868.99 84.331 1.000 3.511 

0.4160E-02 536.081 867.14 84.534 1.000 3.484 

0.41803-02 532.335 865.29 04.737 1.000 3.458 

0.42003-02 528.642 863.37 84.893 1.000 3.805 

0.4220E-02 525.004 861.45 85.055 1.000 3.770 

0.42403-02 521.417 059.65 85.318 1.000 3.750 

0.42603-02 517.880 057.81 B5.552 1.000 3.724 

0.42803-02 514.392 855.89 85.735 1.000 4.073 

0.43003-02 510.953 853.95 85.894 1.000 4.045 

0.43203-02 507.562 852.10 86.146 1.000 4.017 

0.4340E-02 504.217 850.14 86.302 1.000 4.369 

0.43603-02 500.917 848.29 86.579 1.000 4.340 

0.43803-02 497.663 846.29 86.705 1.000 4.312 

0.44003-02 494.453 844.39 86.949 1.000 4.667 

0.44203-02 491.285 042.49 87.199 1.000 4.637 

0.44403-02 480.159 840.54 87.407 1.000 4.608 

TIME 
0.44603-02 485.075 838.59 87.615 1.000 4.965 

0.44803-02 482.032 836.62 87.B13 1.000 4.934 

0.4500E-02 479.028 834.65 88.033 1.000 4.904 

0.4520E-02 476.063 032.67 88.244 1.000 5.263 

0.454OE-02 473.136 830.69 88.454 1.000 5.232 

0.45603-02 470.248 828.69 88.665 1.000 5.201 

0.45803-02 467.396 826.66 08.803 1.000 5.562 

0.4600E-02 464.580 824.68 89.090 1.000 5.530 

0.46203-02 461.798 822.66 89.303 1.000 5.498 

0.46403-02 459.051 820.62 89.473 1.000 5.860 

0.4660E-02 456.340 818.59 89.694 1.000 5.828 

0.4680E-02 453.663 816.55 89,949 1.000 6.192 

0.4700E-02 451.018 814.50 90.133 1.000 6.158 

0.47203-02 448.406 812.44 90.351 1.000 6.125 

0.47403-02 445.826 810.37 90.607 1.000 6.490 

0.47603-02 443.278 808.29 90.788 1.000 6.456 

0:47803-02 440.759 806.21 90.854 0.999 6.840 

0.4BOOE-02 438.270 804.13 90.480 0.995 6.840 

0.4820E-02 435.810 802.07 90.110 0.990 6.840 

0.484OE-02 433.380 800.03 89.743 0.906 6.840 

0.48603-02 430.978 798.00 89.380 0.982 6.840 

0.4880E-02 428.605 795.99 89.020 0.978 6.840 

0.49003-02 426.258 794.00 88.662 0.975 6.840 

0.49203-02 423.940 792.02 88.308 0.971 6.840 

0.494OE-02 421.649 790.05 87.957 0.967 6.840 

0,4960E-02 419.384 788.11 87.608 0.963 6.840 

0.49803-02 417.144 706.17 07.263 0.959 6.840 

0.5000E-02 414.930 784.25 86.921 0.955 6.040 
hTENlTONALLY LEFT BLANK. 

68 
Appendix D: 

Performance Calculations Varying Charge Mass 

of M30Al Propellant 

69 
hl-ENTIONALLY LEFT BLANK. 

70 
ERRTOk l.l920929E-07 

1 

0 CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

2 

CARD 

CARD 

CARD 

CARD 

CARD 

CARD 

IBHVG2.505 DATE 

1 --> $COMM 

2 --> GREEN GUN TEST CASE - INDIAN HEAD SYSTEM 

3 --> $GUN 

4 --> TRAV = 6.840 CHAM = O.OlSO6 $ 919 CUBIC INCHES 

5 --> GRVE = 0.12852 LAND = 0.127 TWST = 25 G/L = 1.49 $ ESTIMATES 

6--> $ CPTS=~ 

7 --> $ DIST = 0.0, 0.04455, 0.14732, 0.0260, 0.8913, 1.0592 

8--> $ DIAM- 0.12965, 0.13655, 0.13929, O.l325BB, 0.12852, 0.12852 

9 --> $E'ROJ 

10 --> PRWT = 49.895 

11 --> SRESI 

12 --> NPTS = 5 

13 --> TRAV - 0.0, 0.00508, 0.04318, 0.1397, 7.62 

14 --> PRES = 3.4474, 0.6894757, 0.6094757, 8.2737, 8.2737 

15 --> $INFO 

16 --> POPT = 1,1,1,0,2 

17 --> RUN = 'GREEN GUN TEST CASE - M30A1 19P PERFORMANCE' 

18 --> $ GRAD = 3 

19 --> $ CONP = 2 PRES = 448 TOL = 0.1 

CARD 20 --> $PDIS 

CARD 21 --> SHOW = 'CRWT ' DECK = 'PROP' NTH = 1 REMK ='CHWI (KG)' 

CARD 22 --> $PDIS 

CARD 23 --> SHOW = 'LDEN' DECK = 'OUT' RRMK = 'L/D (G/CC)' MOLT = 0.001 

CARD 24 --> $PDIS 

CARD 25 --> SHOW = 'WEB' DECK = 'PROP' NTH = 1 REMK ='WEB(MM)' MULT = 1000. 

CARD 26 --> $PDIS 

CARD 27 --> SHOW = 'PMAX' DECK = 'OUT' REMK = 'PMAX (MPA' 1' 

CARD 28 --> SPDIS 

CARD 29 --> SHOW = 'VMUZ DECK = 'OUT' REMK = 'VMUZ (M/S 1' 

TIME 
(1)’ DECK = 'OUT' REMK = '2 @ EXIT' 

CARD 30 --> $PDIS 

CARD 31 --> SHOW '= ' ZMUZ 

CARD 32 --> $PDIS 

CARD 33 --> SHOW = 'X@BO 

CARD 34 --> $PRIM 

(1) ' DECK = 'OUT' REMU = 'X @ B.O.' 

CARD 35 --> NAME = 'PRIMER' CHWT = 0.12637 FORC = 146140 

CARD 36 --> GhMA = 1.2015 cov = 0.0010838 TEMP = 3377 

CARD 37 --> SPROP 

CARD 38 --> NAME = 'M3oAl' CHWT = 12.65 FORC = 1073374 

CARD 39 --> GhMA = 1.2375 COV = 0.00105239 TEMP = 3036 

CARD 40 --> LEN = 0.018288 PD = 0.0004572 WEB = 0.003467 RHO = 1683 

CARD 41 --> ALPH = 0.8063 BETA = 0.00196836 

CARD 42 --> FORM = '19P' 

CARD 43 --> SPMAX 

CARD 44 --> VARY = 'WEB' NTH = 1 TRY~ = 0.003 ~Ry2 = 0.0031 PMAX = 448. 

CARD 45 --> SPARA 

2 

CARD 46 --> VARY = 'CHNT' DECK = 'PROP' NTH = 1 

CARD 47 --> FROM = 12.5 BY = 0.25 TO = 13.6 

CARD 48 --> SEND 

~GREEM GON TEST CASE - M30Al 19p PERFORMANCE IBHVG2.505 DATE 

------------ 

- GUN TUBE - 

------------ 

TYPE: CHAMBER VOLUME (M3): 0.01506 

GROOVE DIAMETER (M) 0.12852 LAND DIAMETER (M): 0.12700 

TWIST (CALS/TURN): 25.0 BORE AREA (N2): 0.01285 

SHELL THICKNESS (M) 0.000102 SHELL Cp (J/KG-K): 460.3163 

INITIAL SHELL TEMP ( K): 293. AIR HO (W/M**2-K): 11.3482 

TIME 

TRAVEL (M) : 6.04000 

GROOVE/LAND RATIO (-): 1.490 

HEAT-LOSS OPTION: 1 

SHELL DENSITY (KG/M3): 7861.0918 
0 

c 

. 

73 

0 
_ _ _ - - - - - _ _ 

- PRIMER - 

TYPE: PRIMER GAMMA (-): 1.2015 FORCE (J/KG): 146140. 

COVOLUME (M3/KG): 1.08383-03 FLAME TENP (K): 3377.0 WEIGHT (KG): 0.126370 

1GREEN GUN TEST CASE - M30AI 19P PERFORMANCE IBHVG2.505 DATE TIME 

- CHARGE 1 - 

____----- --- 

TYPE: M30Al GRAINS: 1256.2 19P WEIGHT (KG): 12.5000 

EROSIVE COEFF (-): 0.000000 CHARGE IGN CODE: 0 CHARGE IGN AT (2.): 0.00000E+00 

GRAIN LENGTH (M): 0.018288 GRAIN DIAMETER (M): 0.020387 PERF DIAMETER (M): 0.000457 

4 INNER WEB (M): 0.003017 MIDDLE WEB (M): 0.003017 OUTER WEB (M): 0.003017 

P 

PROPERTIES AT LAYER BOUNDARIES OF PERF SURFACES PROPERTIES AT LAYER BOUNDARIES OF END SURFACES 

1ST 2ND 3RD 4TH 1ST 2ND 3RD 4TH 

AT DEPTH (M): ------ -_---- ------ 0.00000 ------ 

--_--_ 

-____- 0.00000 

ADJACENT LAYER WT %: _----_ ------ ------ 100.000 _----- 

------ -___-- 100.000 

DENSITY (KG/M3): _----- ------ ------ 1683.000 _-_--_ --_--- -___-- 1683.000 

GAMMA (-): ------ ------ ------ 1.2375 __--__ --_--_ ------ 1.2375 

FORCE (J/KG): ------ -_---_ -__--- 1073374. ------ 

-__--_ ------ 1073374. 

COVOLUME (M3/KG): ------ -----_ ___--- l.O524E-03 __---- 

------ ---_-- 1.05243-03 

FLAME TEMP (K): ------ -_---- ------ 3036.0 __---- ___--_ ------ 3036.0 

BURNING RATE EXPS: _--__- ___--- ------ 0.8063 _----_ --_--- -___-- 0.8063 

BURNING RATE COEFFS: _----- ------ ------ 1.96843-03 ------ 

--_--_ 

------ 1.9684E-03 

PROPERTIES AT LAYER BOUNDARIES OF LAT SURFACES 

1 . . 

* Q 
1ST 2ND 3RD 4TH 

AT DEPTH (M) : _----- ------ 

ADJACENT LAYER WT 8: _-____ ______ 

DENSITY (KG/M): ____-_ ______ 

GAMMA (-): ______ ______ 

FORCE (J/KG): _____- __-___ 

COVOLUME (M3/KG): ____-_ _----_ 

FLAME TEMP (K): ------ ______ 

BURNING RATE EXPS: ____-_ ______ 

BURNING RATE COEFFS: -----_ _----- 

IGREEN GUN TEST CASE - ~30~1 19p PERFORMANCE 

------ 0.00000 

-_---- 100.000 

-_-_-_ 1683.000 

_-___- 1.2375 

------ 1073374. 

------ l.O524E-03 

------ 3036.0 

------ 0.8063 

-__-_- 1.96843-03 

IBHVG2.505 DATE 

TIME TRAV VEL ACC 

(MS) (Ml (M/S) (G) 

40 0.000 0.000 0.00 0. 

wl 

0.100 0.000 0.00 0. 

0.200 0.000 0.00 0. 

0.295 0.000 0.00 0. 

SHOT-START PRESSURE ACHIEVED 

0.300 0.000 0.00 0. 

0.400 0.000 0.01 10. 

0.500 0.000 0.02 21. 

0.600 0.000 0.05 32. 

0.700 0.000 0.00 45. 

0.800 0.000 0.13 50. 

0.900 0.000 0.20 73. 

1.000 0.000 0.28 89. 

1.100 0.000 0.37 107. 

1.200 0.000 0 I49 125. 

1.300 0.000 0.62 146. 

BREECH 

PRESS 

(Mph) 

2.464 

2.768 

3.102 

3.448 

MEAN 

PRESS 

(MPA) 

2.464 

2.760 

3.102 

3.448 

BASE MEAN FRAC 

PRESS TEMP BURN 

IMPA) (K) 1 

2.464 3377. 0.000 

2.760 3342. 0.000 

3.102 3311. 0.000 

3.448 3284. 0.001 

3.463 3.466 3.464 3283. 0.001 

3.880 3.063 3.831 3259. 0.001 

4.330 4.297 4.231 3237. 0.001 

4.820 4.760 4.665 3218. 0.001 

5.352 5.200 5.137 3201. 0.002 

5.929 5.836 5.649 3185. 0.002 

6.555 6.438 6.204 3172. 0.002 

7.233 7.090 6.804 3159. 0.003 

7.965 7.794 7.452 3148. 0.003 

a.755 8.554 8.151 3139. 0.003 

9.608 9.373 8.904 3130. 0.004 

TIME 
1.400 

1.500 

1.600 

1.700 

1.800 

1.900 

2.000 

2.100 

2.200 

2.300 

2.400 

2.500 

2.600 

2.700 

2.000 

2.900 

2 

3 * 000 

3.100 

3.200 

3.300 

3.400 

3.500 

3.600 

3.700 

3. BOO 

3.900 

4.000 

4.100 

4.200 

4.300 

4.400 

4.500 

0.000 

0.000 

0.000 

0.001 

0.001 

0.001 

0.001 

0.001 

0.002 

0.002 

0.002 

0.003 

0.003 

0.004 

0.004 

0.005 

0.006 

0.007 

0.008 

0.009 

0.010 

0.011 

0.012 

0.014 

0.015 

0.017 

0.019 

0.021 

0.024 

0.026 

0.029 

0.032 

0.77 

0.95 

1.15 

1.38 

1.64 

1.92 

2.24 

2.60 

3.00 

3.43 

3.92 

4.45 

5.03 

5.66 

6.36 

7.11 

7.93 

8.02 

9.76 

10.70 

ll.B7 

13.03 

14.28 

15.61 

17.03 

18.55 

20.16 

21.88 

23.71 

25.65 

27.71 

29.90 

168. 

192. 

219. 

247. 

277. 

310. 

345. 

383. 

424. 

468. 

515. 

565. 

620. 

678. 

740. 

806. 

867. 

932. 

1000. 

1072. 

1148. 

1229. 

1313, 

1403. 

1496. 

1595. 

1699. 

1607. 

1921. 

2041. 

2165. 

2295. 

10.526 

11.514 

12.575 

13.715 

14.937 

16.247 

17.646 

19.147 

20.747 

22.456 

24.277 

26.218 

28.203 

30.479 

32.812 

35.288 

37.099 

40.663 

43.589 

46.681 

49.946 

53.395 

57.029 

60.057 

64.085 

69.120 

73:566 

78.230 

B3.117 

88.233 

93.580 

99.164 

10.256 

11.205 

12.224 

13.319 

14.492 

15.749 

17.094 

18.531 

20.066 

21.704 

23.450 

25.310 

27.288 

29.391 

31.624 

33.994 

36.506 

39.167 

41.903 

44.959 

48.104 

51.422 

54.920 

58.605 

62.482 

66.558 

70.838 

75.327 

80.032 

84.955 

90.103 

95.478 

9.715 

10.587 

11.523 

12.527 

13.602 

14.754 

15.985 

17.301 

18.705 

20.202 

21.796 

23.493 

25.298 

27.214 

29.249 

31.406 

33.720 

36.174 

30.771 

41.516 

44.416 

47.476 

50.702 

54.100 

57.676 

61.435 

65.382 

69.522 

73.860 

78.401 

83.148 

88.105 

3122. 

3114. 

3100. 

3102. 

3096. 

3091. 

3006. 

3082. 

3078. 

3075. 

3071. 

3068. 

3065. 

3062. 

3059. 

3057. 

3054. 

3051. 

3049. 

3047. 

3044. 

3042. 

3039. 

3037. 

3034. 

3032. 

3029. 

3026. 

3oi3. 

3020. 

3017. 

3014. 

0.004 

0.005 

0.005 

0.006 

0.007 

0.007 

0.008 

0.009 

0.010 

0.011 

0.012 

0.013 

0.014 

0.015 

0.016 

0.018 

0.019 

0.020 

0.022 

0.024 

0.025 

0.027 

0.029 

0.031 

0.034 

0.036 

0.039 

0.041 

0.044 

0.047 

0.050 

0.053 
4.600 0.035 32 

4.700 0.038 34 

4.800 0.042 37 

4.900 0.045 40 

5.000 0.050 42 

5.100 0.054 45 

5.200 0.059 49 

1GREEN GUN TEST CASE 

TIME 

(MS) 

TRAV 

(Ml 

VEL 

(M/S) 

0 5.300 

5.400 

5.500 

5.600 

-4 5.700 

4 

5.800 

5.900 

6.000 

6.100 

6.200 

6.300 

6.400 

6.500 

6.600 

6.700 

6.000 

6.900 

7.000 

7.100 

7.200 

0.064 

0.069 

0.075 

0.081 

0.088 

0.095 

0.102 

0.110 

0.118 

0.127 

0.136 

0.146 

0.157 

0.168 

0.179 

0.191 

0.204 

0.217 

0.232 

0.246 

52.47 

55.96 

59.66 

63.52 

67.56 

71.77 

76.17 

80.76 

85.54 

90.51 

95.68 

101.04 

106.62 

112.42 

118.43 

124.66 

131.11 

137.78 

144.65 

151.74 

21 2431. 104.907 101.083 93.274 3011 

67 2572. 111.052 106.920 98.658 3007 

26 2719. 117.359 112.992 104.257 3004 

00 2060. 123.904 119.298 110.086 3000 

89 3018. 130.685 125.838 116.143 2996 

92 3174. 137.707 132.610 122.416 2992 

11 3334. 144.968 139.613 128.903 2987 

- M30Al 19P PERFORMANCE IBHVG2 

0 

0 

0 

0 

0 

0 

0 

505 

ACC 

tG) 

3500. 

3670. 

3844. 

4023. 

4206. 

4393. 

4582. 

4775. 

4971. 

5168. 

5367. 

5580. 

5800. 

6022. 

6243. 

6465. 

6605. 

6904. 

7120. 

7333. 

BREECH 

PRESS 

(MPA) 

152.462 

160.184 

168.128 

176.284 

184.644 

193.195 

201.924 

210.816 

219.854 

229.020 

238.294 

247.675 

257.132 

266.628 

276.138 

285.634 

295.069 

304.473 

313.756 

322.910 

MEAN 

PRESS 

IMPA) 

146.841 

154.290 

161.954 

169.823 

177.889 

186.140 

194.564 

203.147 

211.871 

220.720 

229.674 

238.714 

247.817 

256.958 

266.112 

275.253 

284.353 

293.386 

302.322 

311.133 

BASE 

PRESS 

(MPA) 

135.600 

142.503 

149.606 

156.901 

164.380 

172.032 

179.846 

187.808 

195.905 

204.120 

212.435 

220.792 

229.186 

237.616 

246.059 

254.489 

262.082 

271.212 

279.453 

287,579 

MEAN 

TEMP 

(K) 

2983. 

2970. 

2973. 

2968. 

2962. 

2957 * 

2951. 

2945. 

2938. 

2932. 

2925. 

2918. 

2911. 

2903. 

2096. 

2888. 

2880. 

2871. 

2863. 

2054. 

057 

060 

064 

068 

072 

077 

OBl 

DATE TIME 

FRAC 

BURN 

1 

0.086 

0.091 

0.096 

0.102 

0.108 

0.114 

0.120 

0.127 

0.133 

0.141 

0.148 

0.156 

0.164 

0.172 

0.181 

0.190 

0.199 

0.209 

0.219 

0.229 
7.300 

7.400 

7.500 

7.600 

7.700 

7.800 

7.900 

8.000 

8.100 

8.200 

8.300 

8.400 

8.500 

0.600 

8.700 

8.800 

8.900 

9.000 

9.100 

9.200 

9.300 

9.400 

9.500 

9.600 

9.700 

9.749 

0.262 

0.278 

0.295 

0.313 

0.332 

0.351 

0.371 

0.393 

0.414 

0.437 

0.461 

0.406 

0.511 

0.538 

0.565 

0.594 

0.623 

0.654 

0.685 

0.717 

0.751 

0.785 

0.820 

0.857 

0.B94 

0.913 

159.03 

166.53 

174.23 

182.12 

190.20 

198.45 

206.89 

215.49 

224.25 

233.15 

242.20 

251.39 

260.69 

270.11 

279.63 

289.25 

298.95 

308.73 

318.57 

328.47 

330.42 

340.40 

358.41 

368.44 

378.48 

383.41 

7543. 

7748. 

7948. 

8142. 

8330. 

8512. 

8686. 

8851. 

9009. 

9150. 

9297. 

9428. 

9549. 

9660. 

9761. 

9852. 

9933. 

10005. 

10067. 

10119. 

10162. 

10195. 

10220. 

10236. 

10243. 

10244. 

331.904 

340.710 

349.299 

357.644 

365.719 

373.499 

380.962 

388.065 

394.850 

401.240 

407.241 

412.040 

418.029 

422.801 

427.149 

431.073 

434.573 

437.650 

440.309 

442.557 

444.401 

445.851 

446.919 

447.616 

447.955 

447.996 

319.790 295.564 

328.267 303.381 

336.535 311.007 

344.568 318.415 

352.341 325.584 

359.830 332.491 

367.013 339.115 

373.869 345.439 

3B0.3Bl 351.445 

386.533 357.119 

392.309 362.446 

397.700 367.418 

402.695 372.025 

407.287 376,261 

411.474 380.123 

415.251 383.607 

418.620 3B6.714 

421.582 309.447 

424.142 391.809 

426.306 393.805 

428.082 395.443 

429.478 396.732 

430.506 397.681 

431.177 398.301 

431.505 398.603 

431.544 398.640 

2846. 

2837. 

2828. 

2818. 

2809. 

2800. 

2790. 

2781. 

2771. 

2761. 

2752. 

2742. 

2732. 

2722. 

2713. 

2703. 

2693. 

2684. 

2674. 

2665. 

2655. 

2646. 

2637. 

2628. 

2619. 

2614. 

0.240 

0.251 

0.262 

0.274 

0.286 

0.298 

0.311 

0.324 

0.337 

0.351 

0.364 

0.379 

0.393 

0.408 

0.422 

0.438 

0.453 

0.468 

0.484 

0.500 

0.516 

0.533 

0.549 

0.566 

0.582 

0.591 . 

LOCAL PRESSURE MAX DETECTED 

9.800 0.932 388.53 10243. 447.952 431.502 398.602 2610. 0.599 

9.900 0.972 398.57 10235. 447.621 431.184 398.309 2601. 0.616 

10.000 1.012 408.60 10220. 446.977 430.565 397.739 2592. 0.633 

10.100 1.054 418.61 10198. 446.037 429.660 396.906 2583. 0.650 

10.200 1.096 428.60 10169. 444.017 420.486 395.825 2575. 0.667 
*- . 

I cc 

10.300 1.139 438.56 10134. 443.333 427.058 394.508 2566. 0.685 

10.400 1.104 448.47 10093. 441.600 425.391 392.972 2558. 0.702 

10.500 1.229 458.35 10047. 439.637 423.501 391.231 2550. 0.719 

IGREEN GUN TEST CASE - M30~1 19p PERFORMANCE IBHVG2.505 DATE TIME 

TIME TRAV VEL 

(MS) (Ml (M/S) 

ACC 

(G) 

0 10.600 

10.700 

10.000 

10.900 

11.000 

11.100 

11.200 

11.300 

3 

11.400 

11.500 

1.275 

1.323 

1.371 

>1.420 

1.470 

1.521 

1.574 

1.627 

1.681 

1.736 

11.600 1.791 

11.700 I.048 

11.000 1.906 

11.900 1.964 

12.000 2.023 

12.100 2.083 

12.200 2.144 

12.300 2.206 

12.400 2.260 

12.500 2.331 

12.600 2.395 

12.700 2.460 

12.800 2.525 

12.900 2.591 

468.18 9996. 

477.95 9940. 

487.67 9880. 

497.33 9816. 

506.92 9748. 

516.45 9677. 

525.90 9603. 

535.20 9521. 

544.56 9309. 

553.69 9231. 

562.66 9056. 

571.45 0870. 

500.05 0677. 

500.47 0470. 

596.68 8277. 

604.70 8075. 

612.52 7872. 

620.14 7671. 

627.57 7472. 

634.00 7275. 

641.04 7085. 

640.69 6899. 

655.37 6720. 

661.80 6546. 

BREECH MEAN BASE 

PRESS PRESS PRESS 

(MPA) (Mph) (MPAl 

437.458 421.404 389.298 

435.070 419.115 387.187 

432.514 416.647 3B4.913 

429.701 414.017 3B2.488 

426.B92 411.237 379.925 

423.862 400.320 377.237 

420.704 405.281 374.435 

417.190 401.907 371.325 

411.555 396.476 366.317 

404.769 309.945 360.296 

397.202 382.739 353.651 

389.321 375.076 346.586 

381.038 367.103 339.234 

372.545 356.929 331.697 

363.930 350.637 324.051 

355.262 342,294 316.359 

346.597 333.954 308.660 

337.979 325.659 301.020 

329.445 317.445 293.445 

321.030 309.346 285.97B 

312.852 301.474 270.719 

304.923 293.843 271.682 

297.241 286.449 264.864 

209.801 279.280 250.261 

TEMP 

(K) 

2s41. 

2533. 

2525. 

2517. 

2510. 

2502. 

2495. 

2487. 

2477. 

2467. 

2456. 

2445. 

2433. 

2422. 

2410. 

2397. 

2305. 

2373. 

2361. 

2348. 

2336. 

2324. 

2313. 

2301. 

FRAC 

BURN 

I 

0.737 

0.754 

0.771 

0.789 

0.006 

0.023 

0.041 

0.858 

0.071 

0.083 

0.894 

0.904 

0.912 

0.920 

0.927 

0.933 

0.939 

0.944 

0.940 

0.953 

0.956 

0.960 

0.964 

0.967 
13.000 2.657 66a.il 

13.100 2.725 674.39 

13.200 2.792 680.40 

13.300 2.661 686.27 

13.400 2.930 691.99 

13.500 2.999 697.56 

13.600 3.069 703.00 

13.700 3.140 708.30 

13.800 3.211 713.47 

13.900 3.282 718.51 

14.000 3.354 723.43 

14.100 3.427 728.22 

14.200 3.500 732.89 

14.300 3.574 737.45 

14.400 3.647 741.90 

14.500 3.722 746.23 

g 

14.600 3.797 750.47 

14.700 3.872 754.60 

14.800 3.948 758.63 

14.900 4.024 762.57 

15.000 4.100 766.41 

15.100 4.177 770.16 

15.200 4.254 773.83 

15.300 4.332 777.41 

15.400 4.410 780.91 

15.467 4.462 783.20 

PROPELLANT 1 BURNED OUT 

15.500 4.408 784.33 

15.600 4.567 787,68 

15.700 4.645 790.95 

15.800 4.725 794.14 

6378. 

6215. 

6058. 

5905. 

5758. 

5615. 

5476. 

5339. 

5205. 

5075. 

4948. 

4825. 

4706. 

4590. 

4478. 

4369. 

4264. 

4161. 

4062. 

3966. 

3a73. 

3703. 

3695. 

3610. 

3528. 

3475. 

3448.' 

3371. 

3296. 

3224. 

282.597 

275.625 

268.878 

262.350 

256.035 

249.925 

243.961 

238.091 

232.362 

226.785 

221.365 

216.102 

210.995 

206.040 

201.236 

196.578 

192.063 

187.687 

183.445 

179.333 

175.347 

171.483 

167.738 

164.106 

160.584 

158.300 

157.169 

153.865 

150.669 

147.578 

272.354 

265.644 

259;150 

252.867 

246.788 

240.907 

235.167 

229.517 

224.003 

218.635 

213.419 

208.353 

203.437 

198.669 

194.045 

169.562 

185.216 

181.004 

176.921 

172.963 

169.127 

165.408 

161.803 

158.308 

154.918 

152.720 

151.631 

148.451 

145.375 

142.400 

251.869 

245.681 

239.693 

233.900 

228.294 

222.872 

217.579 

212.370 

207.285 

202.336 

197.526 

192.855 

188.323 

183.926 

179.662 

175.529 

171.522 

167.638 

163.873 

160.224 

156.687 

153.258 

149.934 

146.711 

143.586 

141.559 

140.555 

137.623 

134.707 

132.044 

2290. 

2278. 

2267. 

2256. 

2245. 

2235. 

2224. 

2214. 

2203. 

2192. 

2182. 

2172. 

2161. 

2151. 

2141. 

2131. 

2121. 

2111. 

2102. 

2092. 

2003. 

2073. 

2064. 

2055. 

2046. 

2040. 

2037. 

2028. 

2019. 

2011. 

0.970 

0.973 

0.976 

0.979 

0.982 

0.984 

0.986 

0.9B8 

0.990 

0.991 

0.993 

0.994 

0.995 

0.996 

0.997 

0.997 

0.998 

0.998 

0.999 

0.999 

0.999 

1.000 

1.000 

1.000 

1.000 

1.000 

1.000 

1.000 

1.000 

1.000 

~GREEN GUN TEST CASE - M30Al 19p PERFORMANCE IBHVG2.505 DATE TIME 
TIME' TRAV VEL 

(MS) (M) (M/S) 

0 15.900 4.804 

16.000 4.884 

16 .I00 4.964 

16.200 5.045 

16.300 5.126 

16.400 5.207 

16.500 5.288 

16.600 5.370 

16.700 5.451 

16.800 5.534 

16.900 5.616 

17.000 5.699 

17.100 5.782 

00 17.200 5.865 

w 

17.300 5.948 

17.400 6.032 

17.500 6.115 

17.600 6.199 

17.700 6.284 

17.800 6.368 

17.900 6.453 

18.000 6.538 

18.100 6.623 

18.200 6.708 

18.300 6.794 

18.354 6.840 

PROJECTILE EXIT 

797.27 

800.33 

803.32 

806.26 

809.13 

811.94 

814.69 

817.39 

820.03 

822.62 

825.16 

827.65 

830.09 

832.40 

034.83 

B37.13 

B39.40 

841.62 

043.79 

845.93 

848.03 

850.10 

852.12 

854.11 

856.07 

857.11 

ACC 

(GJ 

3154. 

3087. 

3021. 

2957. 

2896. 

2836. 

2778. 

2722. 

2668. 

2615. 

2563. 

2514. 

2465. 

2418. 

2372. 

2328. 

2204. 

2242. 

2201. 

2161. 

2122. 

2084. 

2048. 

2012. 

1977. 

1958. 

BREECH MEAN BASE MEAN FRAC 

PRESS PRESS PRESS TEMP BURN 

(MPA) (MPA) (MPA) CR) 1 

144.506 139.520 129.389 2002. 1.000 

141.689 136.732 126.818 1994. 1.000 

138.883 134.032 124.328 1986. 1.000 

136.16i 131.415 121.916 1978. 1.000 

133.531 128.880 119.578 1970. 1.000 

130.977 126.422 117.312 1962. 1.000 

128.500 124.038 115.114 1954. 1.000 

126.097 121.725 112.982 1947. 1.000 

123.766 119.481 110.913 1939. 1.000 

121.502 117.303 108.905 1932. 1.000 

119.305 115.188 106.954 1925. 1.000 

117.170 113.134 105.060 1917. 1.000 

115.097 111.138 103.220 1910. 1.000 

113.0131 109.198 101.432 1903. 1.000 

111.122 107.313 99.693 1897. 1.000 

109.217 105.479 98.003 1890. 1.000 

107.364 103.696 96.359 1883. 1.000 

105.562 101.961 94.759 1876. 1.000 

103.807 100.272 93.203 1870. 1.000 

102.100 98.629 91.687 1863. 1.000 

100.437 97.029 90.212 1857. 1.000 

98.818 95.470 0B.775 1851. 1.000 

97.240 93.952 07.376 lS45. 1.000 

95.703 92.473 66.012 1838. 1.000 

94.205 91.031 84.682 1832. 1.000 

93.413 90.269 83.980 1829. 1.000 

1GREEN GDN TEST CASE - M30A1 l9P PERFORMANCE IBHVG2.505 DATE TIME 
CONDITIONS AT: PMAX MUZZLE 

TIME (MS): 

TRAVEL (M): 

VELOCITY (M/S) 

ACCELERATION (G): 

BREECH PRESS (MPA): 

MEAN PRESS (MPA): 

BASE PRESS (MPA): 

MEAN TEMP (K): 

2 CHARGE 1 (-): 

9.749 

0.9128 

383.41 

10244. 

447.9955 

431.5436 

398.6397 

2614. 

0.591 

18.354 

6.13400 

857.11 

1958. 

93.4133 

90.26BEI 

83.9790 

1829. 

1.000 

ENERGY BALANCE SUMMARY 

TOTAL CHEMICAL: 

e (1) INTERNAL GAS: 

(2) WORK AND LOSSES: 

(A) PROJECTILE KINETIC: 

(B) GAS KINETIC: 

(C) PROJECTILE ROTATIONAL: 

(D) FRICTIONAL WORK TO TUBE: 

(E) OTHER FRICTIONAL WORK: 

(F) WORK DONE AGAINST AIR: 

(G) HEAT CONVECTED TO BORE: 

(I-I) RECOIL ENERGY: 

LOADING DENSITY (KG/M3): 838.404 

CHARGE WT/PROJECTILE WT: 0.253 

JOULE 

56586656. 

34086580. 

22500076. 

lB327256. 

1545958. 

144706. 

0. 

718397. 

66574. 

1697185. 

0. 

% 

100.00 

60.24 

33.76 

32.39 

2.73 

0.26 

0.00 

1.27 

0.12 

3.00 

0.00 
PIEZOMETRIC EFFICIENCY: 0.465 

EXPANSION RATIO: 6.836 

IGREEN GUN TEST CASE - M30Al 19P PERFORMANCE IBHVG2.505 DATE TIME 

PARAMETRIC VARIABLES: / l/ PROP 1 CHWT 

/ 2/ OUT 1 LDEN 

/ 3/ PROP 1 WEB 

/ 4/ OUT 1 PMAX 

/ 5/ OUT 1 wmz 

/ 6/ OUT 1 ZMUZ(1) 

/ 7/ OUT 1 X@BO(l) 

CNWT (KG) 

L/D (WCC) 

WEB(MM) 

PMAX (MPA) 

VMUZ (M/S) 

2 @ EXIT 

x @ B.O. 

/ 1/ / 2/ / 3/ / Q/ / 5/ / 6/ / 7/ 

co 12.500 0.83840 3.0168 448.00 857.11 1.0000 4.4097 

12.750 0.85500 3.0966 440.00 862.41 1.0000 4.7334 

13.000 0.87160 3.1791 448.00 067.33 1.0000 5.1440 

13.250 0.88821 3.2643 448.00 871.55 1.0000 5.5614 

13.500 0.90401 3.3527 448.00 875.17 1.0000 6.0699 
&TEN’TTONALLY LEFT BLANK. 

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85 
hTENl-'lONALLYLEFTBLANK. 

86 
inimizing Life-Cycle Costs of Gun Propellant Selection Through Model-Based 

on Making: A Case Study in Environmental Screening and Performance 

Ronald D. Anderson and Betsy M. Rice 

U.S. Army Research Laboratory 

A’ITN: AMSRL-WM-BE 

Strategic Environmental Research and Development Program 

901 North Stuart Street, Suite 303 

Arlington, VA 22203 

11. SUPPLEMENTARY NOTES 

12a. DISTRIBUTIONIAVAILABlLilY STATEMENT 

Approved for public release; distribution is unlimited. 

12b. DISTRIBUTION CODE 

13. ABSTRA~(Maximum 200 wvrds) 

This work demonstrates the first phases of a newly proposed gun propellant formulation process that will 

minimize life-cycle costs through science-based design. This new approach proposes maximal use of modeling and 

simulation in the earliest phases of the developmental cycle to screen candidate formulations, resulting in elimination of 

probable poor Performers and identification of the most promising test candidates. The screening and identification of 

propellant formulations are demonstrated under the assumption of a specific weapon platform and user requirements. 

The process of selecting a propellant for the assumed gun system application has been distilled into measurable steps, 

leading from a set of candidate materials, through logical and numerical filters, to a shorter list of energetic materials 

demonstrated as viable weapon platform choices. Environmental filtering and performance modeling are used to screen 

propellants through a well-defmed sequence of tests designed to weed out materials not meeting safety, energy, or 

manufacturability standards. Because much of the testing is performed by computer modeling, the gun systems and 

energetic materials need not be present (or even existent) in order to be described and matched against performance 

requirements for future applications. The calculations demonstrate that utilizing computer models rather than physical 

testing in the early developmental stages of the formulation process can produce enormous savings in labor, material, 

and environmental costs, along with a tremendous reduction in the time required to select a ‘best candidate” propellant. 

14. SUBJECT TERMS 

propellant, cost minimization, gun, performance 

15. NUMBER OF PAGES 

78 

16. PRICE CODE 

17. SECURITY CLASSlFlCAtlON 18. SECURlTY CLASSlFlCAflON 19. SECURlTY CLASSIRCATION 20. LlMlTAflON OF ABSTRACT 

OF REPORT OF THIS PAGE OF ABSTRACT 

UNCLASSlF.CED UNCLASSIFIEZD UNCLASSIFIED UL 

N4N 7-,-9wm C.adad Es.- cm* /El*.. 1.mo\ 

81 Pnsuibed by ANSI Std. 239-18 29ai02 
88 
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