Burnback Analysis of 3-D Star Grain Solid Propellant (original) (raw)

CAD-Based 3D Grain Burnback Analysis for Solid Rocket Motors

Lecture Notes in Mechanical Engineering, Springer Link, 2020

Propellant grain burnback analysis is crucial for solid rocket motor design and performance prediction. Unlike 2D grain configurations, 3D configurations are complex, hence, simulating their burnback inside the rocket combustion chamber is a tedious and time-consuming process. This study proposes a fast and simple approach for modeling, and evaluating the burning area of 3D propellant grains, based on particular features available in a commercial CAD software. A common 3D Finocyl grain configuration available in the literature has been taken as a test case. The results obtained from the proposed approach were compared with the published experimental data and showed good agreement. The proposed approach can handle any arbitrary complex grain geometry and provide fast and reliable analysis for the preliminary design stage of solid propellant rocket motors.

IJERT-To Evaluate the Burn-Perimeter of Star-Shaped Propellant Grain of A Solid Rocket Motor using Dimensionless Equations

International Journal of Engineering Research and Technology (IJERT), 2021

https://www.ijert.org/to-evaluate-the-burn-perimeter-of-star-shaped-propellant-grain-of-a-solid-rocket-motor-using-dimensionless-equations https://www.ijert.org/research/to-evaluate-the-burn-perimeter-of-star-shaped-propellant-grain-of-a-solid-rocket-motor-using-dimensionless-equations-IJERTV10IS060016.pdf The main idea of my work is to discuss and evaluate the geometrical parameter like burn perimeter of the starshaped propellant grain in detail. Whenever, solid propellant comes into the discussion, the grain design is one of the most important topics to be studied and evaluated. Because the thrust output as per requirement can be obtained by varying the shape of grain. Many scholars did lot of research on different sizes and shapes of grains that can provide the burn rate as per wanted. The star-shaped propellant grain design parameter like burn perimeter by using non-dimensional equations is evaluated. A MATLAB code is written in order to plot the non-dimensional burn-perimeter (S/l) versus burnt distance (y + f)/l for star-shaped propellant grain having star point, n = 6 for  = 65-75. The obtained graphs for star points with different opening of star point angle in MATLAB are compared with burn perimeter values measured in CATIA V5 designing tool for corresponding set of values. Later, by taking the geometrical inputs like inner radius(l), fillet radius(f), web thickness(w) for star-shaped grain having star point, n = 6, the grain area regressive is modelled by using CATIA V5 design tool.

Parametric Study of Solid Propellant Axisymmetric Grains for Space Motors

Solid rocket motors have been the mainstay of launch vehicle boosters, they offer high propulsive power with low cost and simple construction compared to liquid motor boosters. As space motors are characterized by low motor case mass with high volumetric loading, the most commonly used grains are axisymmetric grains which offer the advantages of easy fabrication and high volumetric loading. A well-designed grain should be made to fulfill the intended objective of a certain motor. To do so, various tests and simulations must be done, which is costly and time-consuming. Thus, other ways are implemented; these methods should be reliable and accurate in predicting the performance of a specific grain based on its design parameters. The current effort seeks to explore the impact of each design parameter of axisymmetric grains. In this paper, a parametric study is performed on the solid propellant axisymmetric grains used in space motors; the burnback analysis is applied using the level set method which is a numerical technique used for tracking moving interfaces and then the thrust profile is generated using an internal ballistic prediction module. The parametric study is conducted using a single-parameter-at-a-time technique to investigate the effect of changing each parameter; the results of the different cases are introduced and finally, the main design merits are compared.

Parametric Studies of Solid Propellant Axisymmetric Grains for Space Motors

AIAA SCITECH 2023 Forum, 2023

Solid rocket motors have been the mainstay of launch vehicle boosters, they offer high propulsive power with low cost and simple construction compared to liquid motor boosters. As space motors are characterized by low motor case mass with high volumetric loading, the most commonly used grains are axisymmetric grains which offer the advantages of easy fabrication and high volumetric loading. A well-designed grain should be made to fulfill the intended objective of a certain motor. To do so, various tests and simulations must be done, which is costly and time-consuming. Thus, other ways are implemented; these methods should be reliable and accurate in predicting the performance of a specific grain based on its design parameters. The current effort seeks to explore the impact of each design parameter of axisymmetric grains. In this paper, a parametric study is performed on the solid propellant axisymmetric grains used in space motors; the burnback analysis is applied using the level set method which is a numerical technique used for tracking moving interfaces and then the thrust profile is generated using an internal ballistic prediction module. The parametric study is conducted using a single-parameter-at-a-time technique to investigate the effect of changing each parameter; the results of the different cases are introduced and finally, the main design merits are compared.

Burn Back Analysis & CFD Simulation of Finocyl Grain in Solid Propellant Rocket Motor

2016

Design and analysis of propellant grain configurations for determination of the grain geometry which is an important and critical step in the design of solid propellant rocket motors, because accurate calculation of grain geometrical properties plays a vital role in performance prediction. The performance prediction of the solid rocket motor can be achieved easily if the burn back steps of the grain are known. In this study, grain burnback analysis for 3-D grain geometries was investigated. The method used was solid modeling of the propellant grain for predefined intervals of burnback. In this method, the initial grain geometry was modeled parametrically using Creo parametric software. For every burn step, the parameters were adapted and the new grain geometry was modeled. By analyzing these geometries, burn area change of the grain geometry was obtained. CFD simulation of the core flow 3D grain of solid propellant rocket motor. And the field of SRMs various types of CFD models were...