In the combustion stability assessment of solid propellant rocket motors, several new destabilizing terms are introduced when rotational-flow effects are properly accounted for. Such effects must be included when the wave motion is parallel to the burning surface. A normal fluctuating velocity component then appears in a careful resolution of intrinsic fluid dynamics, including acoustico–vortic...

The objective of this contract was the study of rocket faikire mechanisms in conjunction with the development of nozzle materials for solid propellant motors. Study of graphite comprised the major part of the program, with emphasis on erosion mechanisms. Commercial and experimental graphite grades were tested in an oxy-acetylene torch and the effects of graphite purity, density, orientation and...

A critical review is offered of the commonly implemented flame models for computing transient burning rates and intrinsic combustion stability of solid rocket propellants. After illustrating merits and limitations of each, a new flame model is described, by means of a unified mathematical formalism, incorporatin all of the and closer agreement with experimental information is enforced. #he gene...

Abstract The firing test of variable-thrust Hybrid Rocket Motor (HRM), operated with Hydrogen Peroxide (HP) and Polyethylene (PE), based on closed-loop thrust control, has been carried out in this paper. experiment research instantaneous characteristics HRM is conducted reconstruction techniques. A post-processing software developed to reconstruct the performance parameters during burning stage...