Prediction of Internal Ballistic Parameters of Solid Propellant Rocket Motors
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A modular computer program for prediction of internal ballistic performances of solid propellant rocket motors SPPMEF has been developed. The program consists of following modules: TCPSP (Calculation of thermo-chemical properties of solid propellants), NOZZLE (Dimensioning of nozzle and estimation of losses in rocket motor), GEOM (This module consists of two parts: a part for dimensioning the propellant grain and a part for regression of burning surface) and ROCKET (This module provides prediction of an average delivered performance, as well as mass flow, pressure, thrust, and impulse as functions of burning time). Program is verified with experimental results obtained from standard ballistic rocket test motors and experimental rocket motors. Analysis of results has shown that established model enables has high accuracy in prediction of solid propellant rocket motors features in cases where influence of combustion gases flow on burning rate is not significant.Keywords:
Specific impulse
Solid-fuel rocket
Rocket (weapon)
Dimensioning
Characteristic velocity
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Solid-fuel rocket
Rocket (weapon)
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Internal ballistics
Ballistics
Solid-fuel rocket
Rocket (weapon)
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The nozzle geometry affects the performance achieved by a solid propellant rocket motor to a great extent. In order to improve the development of a small home made solid propellant rocket motor these effects on performance from the nozzle geometry need to be understood. This thesis project involves the design of a small solid propellant rocket motor with materials readily available to a hobby rocket enthusiast. A specific investigation is then carried out into the effects that nozzle geometry has on the thrust and impulse performance of the rocket motor. The thrust-time profiles of the rocket motors are achieved by conducting a static firing in a cantilever beam thrust measuring apparatus. A secondary study is also done on these different nozzle geometries using computation fluid dynamics simulations to determine the predicted thrust performance. This also gives the advantage of visualizing the entire flow field and assists in identifying the features that drive the differences in performance. Overall this project develops a high performance nozzle geometry for use on a small home made solid propellant rocket motor as well as outlining various engineering issues involved with the development of a solid propellant rocket motor.
Solid-fuel rocket
Specific impulse
Rocket engine nozzle
Rocket (weapon)
Rocket propellant
Liquid-propellant rocket
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The results of research aimed at improving the predictability of internal ballistics performance of solid-propellant rocket motors (SRM's) including thrust imbalance between two SRM's firing in parallel are presented. Static test data from the first six Space Shuttle SRM's is analyzed using a computer program previously developed for this purpose. The program permits intentional minor design biases affecting the imbalance between any two SMR's to be removed. Results for the last four of the six SRM's, with only the propellant bulk temperature as a non-random variable, are generally within limits predicted by theory. Extended studies of internal ballistic performance of single SRM's are presented based on an earlier developed mathematical model which includes an assessment of grain deformation. The erosive burning rate law used in the model is upgraded and made more general. Excellent results are obtained in predictions of the performances of five different SRM's of quite different sizes and configurations. These SRM's all employ PBAN type propellants with ammonium perchlorate oxidizer and 16 to 20% aluminum except one which uses carboxyl terminated butadiene binder. The only non-calculated parameters in the burning rate equations that are changed for the different SRM's are the zero crossflow velocity burning rate coefficients and exponents. The results, in general, confirm the importance of grain deformation. The improved internal ballistic model makes practical development of an effective computer program for application of an optimization technique to SRM design which is also demonstrated. The program uses a pattern search technique to minimize the difference between a desired thrust-time trace and one calculated based on the internal ballistic model.
Internal ballistics
Ballistics
Solid-fuel rocket
Rocket (weapon)
Ammonium perchlorate
Specific impulse
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This report presents the results of experimental and numerical investigations of the flow field in the head-end star grain slots of the Space Shuttle Solid Rocket Motor. This work provided the basis for the development of an improved solid rocket motor ignition transient code which is also described in this report. The correlation between the experimental and numerical results is excellent and provides a firm basis for the development of a fully three-dimensional solid rocket motor ignition transient computer code.
Solid-fuel rocket
Rocket (weapon)
Transient (computer programming)
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Solid-fuel rocket
Rocket (weapon)
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The sample case presented in this volume is an asymmetrical eight sector thermal gradient performance prediction for the solid rocket motor. This motor is the TC-227A-75 grain design and the initial grain geometry is assumed to be symmetrical about the motors longitudinal axis.
Solid-fuel rocket
Booster (rocketry)
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This paper presents a mathematical-physical model of phenomena occurring in the combustion chamber of a new solid propellant rocket motor.Due to the fact that the geometrical shape of the propellant grain has already been elaborated, the proposal for the modelling of combustion gas generation is a novelty.To solve the system of equations associated with the mathematical model, a computer programme in Turbo Pascal 7.0 was developed.For the solution of ordinary first-order differential equations, the fourth-order Runge-Kutta numerical method was applied.The main results of the completed simulations, i.e. changes in gas pressure, p, in the combustion chamber, and the rocket motor thrust, R, as a function of time, t, of motor operation, are shown graphically.Experimental verification of the parameters of the designed motor shows good agreement with the numerically calculated parameters.
Solid-fuel rocket
Rocket (weapon)
Rocket propellant
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Solid-fuel rocket
Rocket (weapon)
Rocket propellant
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This research aims to optimize the geometric design of slotted propellant grains for solid rocket motors with respect to coupled internal ballistic performance and structural strength criteria. In-house codes such as a zero-dimensional internal ballistic solver and an analytical burnback solver are implemented to compute the variation of chamber pressure and the rocket thrust transiently. Structural analysis of the solid propellant is achieved by using a parametric linear viscoelastic model and a parametric cooldown heat transfer model, both of which are based on the finite element method. The transient temperature distribution data derived from the cooldown process are required inputs for the material properties to be used in the viscoelastic structural analysis. To enable an efficient optimization process, a surrogate heat transfer model that predicts the cooldown time of the system by eliminating expensive iterations is also implemented and validated. Within a coupled analysis approach, the pressure data obtained from the internal ballistic performance analysis are used for the ignition step of the linear viscoelastic analysis. The structural analysis results are evaluated by using a deterministic approach based on the margin of safety with respect to the stress and strain criteria. Finally, the optimum geometrical parameters for a slotted grain subjected to both structural and internal ballistic performance constraints are investigated through multidisciplinary optimization techniques.
Solid-fuel rocket
Solver
Internal ballistics
Rocket (weapon)
Chamber pressure
Internal pressure
Multiphysics
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Citations (15)