Erosion sensitivity of graphitic nozzles for solid-propellant rocket motors
Abstract
A parametric study on the erosion sensitivity of graphitic nozzle throats in small-scale solid propellant rocket motors is presented. The parameters considered are the aluminum content of the solid propellant, combustion gas products of a wide range of composite solid propellants, two propellant configurations (tubular and end-burning), two propellant burning rates for each configuration, and nozzle geometry. Pressure decrease caused by the erosion at the nozzle throat is estimated for each of the two propellant configurations and burning rates. The estimations are performed for pressure values of 0.5-3.0 megapascal at the throat section. The convergence half angle of the nozzle is in the range 30-75 degrees, and the graphitic throat inserts considered are of densities 1.80-1.90 grams per cubic cm. The results obtained and the parameters defined in the work are significant tools for the designer of the design procedure for the rocket motors. The erosion rate or the recession of the nozzle throat can be predicted in each design step of the rocket motor.
- Publication:
-
Israel Society of Aeronautics and Astronautics, 32nd Annual Conference on Aviation and Astronautics
- Pub Date:
- February 1992
- Bibcode:
- 1992isaa.conf..404S
- Keywords:
-
- Erosion;
- Erosive Burning;
- Graphite;
- Nozzle Inserts;
- Propellant Combustion;
- Solid Propellant Rocket Engines;
- Solid Rocket Propellants;
- Throats;
- Aluminum;
- Burning Time;
- Parameter Identification;
- Pressure Dependence;
- Spacecraft Propulsion and Power