Contained rocket motor burn demonstrations in X-tunnel: Final report for the DoD/DOE Joint Demilitarization Technology Program

Technical Report · Mon May 01 00:00:00 EDT 2000

DOI:https://doi.org/10.2172/755152· OSTI ID:755152

Allendorf, S W; Bellow, B W; Boehm, R f

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.

• Research Organization: Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Sandia National Lab. (SNL-CA), Livermore, CA (United States)
• Sponsoring Organization: US Department of Energy (US)
• DOE Contract Number: AC04-94AL85000
• OSTI ID: 755152
• Report Number(s): SAND2000-8238; TRN: AH200021%%7
• Resource Relation: Other Information: PBD: 1 May 2000
• Country of Publication: United States
• Language: English

Related Subjects

37 INORGANIC
ORGANIC
PHYSICAL AND ANALYTICAL CHEMISTRY
ROCKET ENGINES
FUELS
PERFORMANCE TESTING
COMBUSTION PROPERTIES
MEASURING METHODS