Experimental Characterization of Transient Burning Properties of RDX–XLDB Propellant
Author:
Affiliation:
1. Applied Physics Division, Soreq Nuclear Research Center, 81800 Yavne, Israel
2. Solid Propulsion Division, RAFAEL Advanced Defense Systems Ltd., 31021 Haifa, Israel
3. School of Physics and Astronomy, Tel-Aviv University, 69978 Tel Aviv, Israel
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.B34544
Reference16 articles.
1. CulickF. E. C. “Unsteady Motions in Combustion Chambers for Propulsion Systems,” AGARDograph RTO-AG-AVT-039, 2006.
2. T-burner data and combustion instability in solid propellant rockets.
3. Laser-Recoil Combustion Response of RDX
4. Laser-recoil response of AP-HTPB propellants (1-5 atm) - Selective pyrolysis response
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