Results of an experimental investigation of the flow field in the head-end star slot section of a Solid Rocket MotorCold flow tests of a one-tenth scale model based on the geometry of the Space Shuttle Solid Rocket Motor, SRM, head-end section and its single-port igniter, along with two models of a four port igniter, have been conducted. The tests were done to establish quantitative as well as qualitative data on the behavior of the flow inside the star slot during the early part of the ignition transient. This paper presents the data obtained from these tests and discusses the implications of the data with respect to ignition transients of solid rocket motors which have head-end star grains.
Document ID
19920066084
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ciucci, A. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Foster, Winfred A., Jr. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Jenkins, Rhonald M. (Auburn University AL, United States)