Open AccessContained rocket motor burn demonstrations in X-tunnel: Final report for the DoD/DOE Joint Demilitarization Technology Program
Author(s) -
Sarah W. Allendorf,
B. W. Bellow,
R. Boehm
Publication year - 2000
Language(s) - English
Resource type - Reports
DOI - 10.2172/755152
Subject(s) - propellant , rocket (weapon) , solid fuel rocket , aerospace engineering , nike , engineering , burn rate (chemistry) , joint (building) , rocket propellant , aeronautics , nuclear engineering , structural engineering , advertising , business
Three low-pressure rocket motor propellant burn tests were performed in a large, sealed test chamber located at the X-tunnel complex on the Department of Energy's Nevada Test Site in the period May--June 1997. NIKE rocket motors containing double base propellant were used in two tests (two and four motors, respectively), and the third test used two improved HAWK rocket motors containing composite propellant. The preliminary containment safety calculations, the crack and burn procedures used in each test, and the results of various measurements made during and after each test are all summarized and collected in this document