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

Abstract

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.

Study of Initial Pressure Rise in Multi Grain Solid Propellant Rocket Motor

“…In his study, the author investigated the grain burn back analysis for 3D star grain geometries for solid rocket motor. Shekhar [12] has carried out regression and burn back analysis for the various grain configurations such as taper convex star grain, high volumetric loading single-grain dualthrust rocket propellant configuration [13] and funnel port tubular grain [14]. Abdelaziz et al [15], investigated the design process involved with parametric geometry modelling in CAD, MATLAB, coding of performance prediction and 2D star grain ignition experiment.…”