A New Erosive Burning Model of Solid Propellant Based on Heat Transfer Equilibrium at Propellant Surface

Response of a Burning Propellant Surface to Erosive Transients

A novel design of MEMS based solid propellant

As the development of small satellites, more commonly referred to as ‘microsats’ with masses in the range of 10-100 kg and ‘nanosats’ featuring masses from 1-10 kg, there emerge several new kinds of space missions, such as the formation flying and constellations of micro satellites, distributed onboard carrier wave radar, high resolution synthetic aperture remote sensing etc. Due to the continu...

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...

A critical review of solid rocket propellant transient flame models

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...