Fundamental Burning Characteristics of Double-Base Solid Propellant.

Response of a Burning Propellant Surface to Erosive Transients

Virtual prototyping of solid propellant rockets

cerns in rocket motor design because of the enormous cost of typical payloads and, in the case of the Space Shuttle and other manned vehicles, for the crew’s safety. In the spring of 1999, for example, a series of three consecutive launch failures collectively cost more than US$3.5 billion. The most notorious launch failure, of course, was the tragic loss of the Space Shuttle Challenger and its...

Integrated Simulation of Solid Propellant Rockets

This paper presents an overview of research activities at the Center for Simulation of Advanced Rockets (CSAR) at the University of Illinois at Urbana-Champaign. CSAR is one of five university-based research centers funded by the U. S. Department of Energy as part of the Accelerated Strategic Computing Initiative (ASCI). The purpose of ASCI is to advance the state of the art in computational si...

Use of pyrolysis GC/MS for predicting emission byproducts from the incineration of double-base propellant.

Gas chromatography/mass spectrometry was used to analyze the pyrolytic byproducts from an Army-unique propellant compound (AA2) that is composed of predominantly nitrocellulose and nitroglycerin. Compounds produced by AA2 pyrolysis were compared to compounds detected in the gaseous effluent from AA2 incineration. The light permanent gases and most of the higher molecular weight byproducts produ...

Formulation and Characterization of a New Nitroglycerin- Free Double Base Propellant

Double base propellants composed of nitrocellulose (NC) and nitroglycerin (NG) have been used in rocket and gun applications since the late 1800s [1] . Such propellants offer several benefits over their more modern composite counterparts, including simple formulation, high modulus and strength, and chlorine-free minimum smoke exhaust products [2,3] . Nevertheless, double base propellants are pl...