CAD-Based 3D Grain Burnback Analysis for Solid Rocket Motors (original) (raw)

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...

Burnback Analysis of 3-D Star Grain Solid Propellant

International Journal of Advanced Trends in Computer Science and Engineering, Vol.2 , No.1, Pages : 215-223 (2013)

Determination of the grain geometry 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 burn back analysis for 3-D star grain geometries for solid rocket motor was investigated. The design process involves parametric modeling of the geometry in CAD software through dynamic variables that define the complex configuration. Initial geometry is defined in the form of a surface which defines the grain configuration. Grain burn back is achieved by making new surfaces at each web increment and calculating geometrical properties at each step. Equilibrium pressure method is used to calculate the internal ballistics. The procedure adopted can be applied to any complex geometry in a relatively simple way for preliminary designing of grain configuration.

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.

Accurate Computation of Grain Burning Coupled with Flow Simulation in Rocket Chamber

Inthispaper,wepresentanovelnumericalapproachforpredictingthefluidflowinasolidrocketmotorchamberwith burning propellant grain. We use a high-order technique to track the regressing grain surface. Spectral convergence toward the exact burning surface is achieved thanks to Fourier differentiation. For the computation of the internal chamber fluid flow, we make use of a body-fitted volume mesh deforming with the grain surface. We describe several methods to deform the volume mesh and to keep good mesh element quality without global remeshing. We then couple the surface and volume approaches and integrate them into a complex code for compressible, multispecies, turbulent flow simulations. Thanks to these methods, we are able to exhibit one of the first three-dimensional simulations of the internal flow in a realistic solid rocket motor coupled to complex grain surface regression. In prior work, burning grain surface methods have only been coupled with one-dimensional internal ballistics solvers.