SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS

A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 43, ISSUE 25 - DECEMBER 16, 2005

28 PROPELLANTS AND FUELS
Includes rocket propellants, igniters, and oxidizers; their storage and handling procedures; and aircraft fuels.

For nuclear fuels see 73 Nuclear Physics.

For related information see also 07 Aircraft Propulsion and Power; 20 Spacecraft Propulsion and Power; and 44 Energy Production and Conversion.

20050242067 Lawrence Livermore National Lab., Livermore, CA USA

Drop Test Results for the Combustion Engineering Model No. ABB-2901 Fuel Pellet Package

Hafner, R. S.; Mok, G. C.; Apr. 27, 2004; 12 pp.; In English Report No.(s): DE2005-15014142; UCRL-CONF-203811; No Copyright; Avail.: Department of Energy Information Bridge

The U.S. Nuclear Regulatory Commission (USNRC) contracted with the Packaging Review Group (PRG) at Lawrence Livermore National Laboratory (LLNL) to conduct a single, 30-ft shallow-angle drop test on the Combustion Engineering ABB-2901 drum-type shipping package. The purpose of the test was to determine if bolted-ring drum closures could fail during shallow-angle drops. The single test clearly demonstrated the vulnerability of the bolted-ring drum closure to shallow-angle drops-the test package's drum closure was easily and totally separated from the drum package. NTIS

Combustion Physics; Drop Tests; Impact Tests; Pellets

20050243241 Pennsylvania State Univ., University Park, PA USA

Fundamental Understanding of Propellant/Nozzle Interaction for Rocket Nozzle Erosion Minimization Under Very High Pressure Conditions

Kuo, Kenneth K.; Brezinsky, Kenneth; Hanagud, Sathyanaraya; Irle, Stephan; Koo, Joseph H.; Lin, M. C.; Menon, Suresh; Morral, John; Musaev, Jamal; Seitzman, Jerry; Aug. 31, 2005; 108 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): N00014-04-1-0683 Report No.(s): AD-A439823; No Copyright; Avail.: CASI: A06, Hardcopy

To substantially increase the operating pressures of future missiles, this MURI project addresses scientific understanding and methods for mitigation of rocket nozzle erosion by solid-propellant combustion products.

Several processes can affect the nozzle erosion rate at high pressure and temperature conditions. Three approaches have been used to reduce the thermochemical/mechanical erosion rates of nozzle materials, including improving the thermochemical resistance of the nozzle materials, modifying the solid propellant formulation, and/or introducing boundary-layer control methods. The experimental efforts of the program are guided by state-of-the-art theoretical calculations.

During the past year, great progress has been made on the development of both numerical codes and new experimental test facilities. Test rigs have been designed for simulating ultra high-pressure rocket nozzle conditions; with X-ray radiography for erosion rate measurements. A vortex combustor was also designed to simulate propellant product species and to evaluate their effects on nozzle erosion process. A nozzle erosion code has been updated to include comprehensive heterogeneous surface reaction mechanism at high-pressure conditions. The reaction kinetics of nozzle materials has been studied and calculations have been performed using quantum-mechanical and molecular dynamics models. A micro-scale dynamics sub-grid model has been adopted in a parallel LES code to determine the effect of surface shear forces on physical erosion of nozzle throat. Phase diagrams of the W-O-C-H-Cl systems have been obtained to acquire insight into tungsten reaction mechanisms with gaseous mixtures at high-pressure conditions. From equilibrium calculations, tungsten-based nozzles are suitable for aluminized propellants since tungsten oxide and tungsten oxychloride formation are significantly reduced due to the strong affinity of oxygen for aluminum. DTIC

Corrosion Resistance; Erosion; High Pressure; High Temperature; Optimization; Propellants; Rocket Nozzles; Rocket Propellants

Source: NASA.