Rocket motor exhaust thermal environment characterization

Stratospheric Effects of Rocket Exhaust: Heterogeneous Processes

One Dimensional Internal Ballistics Simulation of Solid Rocket Motor

An internal ballistics model has been developed for performance prediction of a solid propellant rocket motor. In this model a 1-D unsteady Euler equation with source terms is considered. The flow is assumed as a non-reacting mixture of perfect gases with space and time varying thermo physical properties. The governing equations in the combustion chamber are solved numerically by using the Steg...

Tin Whisker Horror Story - Rocket Motor Initiator

The failure mechanism was determined to be tin whiskers emanating from the tin plating on the internal pins. The high conductivity, pure tin crystalline whiskers bridged the 10-mil spark gap to cause the test failures. The fusing current of the whiskers was in the range of the source current of the test equipment. This caused inconsistencies during problem identification and verification at the...

A Computational Environment for Exhaust

Design Andrew Gelsey and Don Smith ([email protected], [email protected]) Computer Science Department Rutgers University New Brunswick, NJ 08903 Computing in Aerospace 10, San Antonio, TX, March 1995 AIAA-95-1016-CP Copyright c 1995 by Andrew Gelsey and Don Smith. Published by the American Institute of Aeronautics and Astronautics, Inc. with permission. Abstract The Nozzle Design Associ...

Large Class 1.3 Rocket Motor Detonation Character

Large explosive class 1.3 solid .propellant rocket motors utilizing polybutadiene binder, aluminum fuel, and ammonium perchlorate oxidizer are typically considered explosively vlsafell. That is, the required stimulus is so large that motor detonation is extremely unlikely, even when donored by a sizeable high explosive charge. Two large ground cratering events have occurred during recent years ...