A Review of Analytical Methods for Solid Rocket Motor Grain Analysis

Hartfield, Roy J.; Jenkins, Rhonald M.; Burkhalter, John E.; Foster, Winfred A.

doi:10.2514/6.2003-4506

Cited by 36 publications

(25 citation statements)

References 5 publications

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“…It is observed that propellant can be manufactured by both casting and extrusion methods. Since geometric details of grain design are missing in most of the recent texts, analytical methods for determining burn surface area and port area as a function of burn distance for a variety of cylindrically-perforated solid rocket motor grains has been reviewed 16 . Star, long-spoke wagon wheel, dendrite grains are considered, but the simple grain design is not visited in open literature exclusively.…”

Section: Configuration Detailsmentioning

confidence: 99%

Burn-back Equations for High Volumetric Loading Single-grain Dual-thrust Rocket Propellant Configuration

Shekhar¹

2011

DSJ

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Dual-thrust mode is adopted in solid propellant rocket propulsion through tailoring of burning area, nozzle, rocket motor chamber, propellant type, multiple propellant blocks. In the present study, mathematical formulation has been evolved for generation of burning surface area with web burnt for a simple central blind hole in a solid cylindrical propellant geometry with proper partial inhibition on external and lateral surfaces. The burn-back equation has been validated by static firing and parametric study was conducted to understand effect of various control geometrical parameters. The system is utilised for high volumetric loading, single propellant, single composition, single-chamber, single nozzle dual-thrust mode of burning profiles in rocket application.

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Section: Configuration Detailsmentioning

confidence: 99%

Burn-back Equations for High Volumetric Loading Single-grain Dual-thrust Rocket Propellant Configuration

Shekhar¹

2011

DSJ

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“…The coefficients of determination were high for response surfaces, and indicated that the fitted quadratic models accounted for more than 92% of the variance in the experimental data. Base on p values, the regression coefficient that was significant at p < 95% were selected for the models that resulted in Equations (9) to (13). Analyses of variance (ANOVA) were conducted to evaluate the adequacy and consistency of the models using F-statistic.…”

Section: Performance Equation For Composite Formulationmentioning

confidence: 99%

“…Therefore optimizing the composite formulation to enhance good performance becomes an essential issue. The need to apply process optimization as an essential tool demonstrated high efficiency in selecting optimal process variables in many chemical processes [13]. Among process optimization tools that have been effectively applied to chemical processes is response surface methodology (RSM) [7].…”

Section: Introductionmentioning

confidence: 99%

Optimal design of a composite propellant formulation using response surface methodology

Hamed¹,

Ogunleye

Osheku³

2017

Advances in Materials Science

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There is a continuous demand for high performance composite propellant formulations to meet mission requirements. The performance of composite propellant formulations can be enhanced by optimizing propellant formulation. However, the main objective of this study is to formulate a composition for composite propellant by optimizing the specific impulse which is the measure of propellant performance. A central composite design (ccd) consisting five ingredients (ammonium nitrate, powdered aluminum, polyester resin, ammonium dichromate and powdered charcoal) at five levels was used to formulate optimum propellant formulation from composite materials of ammonium nitrate based propellant verified for propellant characteristics using propellant performance evaluation programme (propep 3). The responses evaluated are specific impulse, characteristic velocity, density, temperature and molecular weight. Response surface methodology was used to analyze the results of the ccd of the composite formulations. The optimum values for specific impulse, characteristic velocity, density, temperature and molecular weight of the mixture from the surface plot are 212.178 s, 1335.81 m/s, 1640.6 k g/m3, 1968.73 k and 21.7722 g/mol respectively. The optimum predicted specific impulse was 212.178 s at composite composition of 73.61% ammonium nitrate, 4.36% powdered aluminum, 14.39% polyester resin, 5.10% ammonium dichromate and 2.54% powdered charcoal. The propellant optimum composition validated with propep 3 are in good agreement with each other in their accompany propellant characteristics. Therefore, the optimal propellant formulation enhanced the performance of solid propellants.

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“…In the design and development of solid propellant rocket motors, an accurate and reliable internal ballistics model provides a physical understanding of the main internal ballistic driving phenomena, besides being used for design optimisation through parametric analysis of the available design options [1][2][3][4] . A good internal ballistics model is also required for the characterisation of the solid rocket motor performance and mission capabilities for both nominal and non-nominal behaviour.…”

Section: Introductionmentioning

confidence: 99%

“…are generally carried out using analytical methods 1,5 . The grain geometry evolution of a complex initial geometry grains like conocyl or finocyl require use of generalised three-dimensional computer programs using different algorithms and grain burnback evaluation methodology 5 .…”

Section: Introductionmentioning

confidence: 99%

Internal Ballistic Code for Solid Rocket Motors using Minimum Distance Function for Grain Burnback

Javed¹,

Sundaram²,

Chakraborty³

2015

DSJ

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A computer code has been developed for internal ballistic performance evaluation of solid rocket motors, using minimum distance function (MDF) approach for prediction of geometry evolution. This method can handle any complex geometry without the need to define different geometrical shapes and their evolution as used in several existing analytical geometry evolution-based methodologies. The code is validated with both experimental results published in literature, as well as for solid rocket motors of tactical and strategic missiles and a very good match is obtained with static test results. The output of the code gives pressure-time (p-t) curve as well as the detailed parameters of the flow along the axial direction, and geometries in the form of mesh file, which can be further used as input to codes for CFD analysis.

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A Review of Analytical Methods for Solid Rocket Motor Grain Analysis

Cited by 36 publications

References 5 publications

Burn-back Equations for High Volumetric Loading Single-grain Dual-thrust Rocket Propellant Configuration

Burn-back Equations for High Volumetric Loading Single-grain Dual-thrust Rocket Propellant Configuration

Optimal design of a composite propellant formulation using response surface methodology

Internal Ballistic Code for Solid Rocket Motors using Minimum Distance Function for Grain Burnback

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