The transient burning parameters of an RDX–XLDB propellant were determined experimentally using a strand burner. Experiments were conducted under various conditions ( of 0.1–15 MPa, and of , 25, and 65°C). A few distinct burning regimes were observed. At pressures between 0.1 and 1.5 MPa, the pressure exponent was found to be around 0.7. Between 1.5 and 2.5 MPa, there was a drop in the burn rate that could not be fitted to burn laws. In the range of 2.5–8 MPa, the exponent was 0.4. Between 8 and 12 MPa, a plateau regime was detected, whereas the exponent recovered its positive value above 12 MPa. A stability analysis based on the Zeldovich–Novozhilov approach was performed for various conditions. For operating pressures around 7 MPa, the propellant response was rather low (about 20% of the steady-state value). At lower pressures, the propellant exhibited a higher response (up to 400% of the steady-state value) at acoustic frequencies under 1 kHz. The diversity of burning regimes was attributed to the differences in the deflagration process of XLDB with nitramine oxidizer over a wide pressure range.
Experimental Characterization of Transient Burning Properties of RDX–XLDB Propellant
Journal of Propulsion and Power ; 29 , 2 ; 305-312
2013-02-27
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Experimental Characterization of Transient Burning Properties of RDX-XLDB Propellant
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