TY - JOUR
T1 - Transient combustion response of AP/HTPB composite propellant to acoustic oscillations in a rocket motor
AU - Cai, Weidong
AU - Thakre, Piyush
AU - Yang, Vigor
N1 - Funding Information:
Received 26 June 2008; revised 24 November 2008; accepted 5 December 2008. This work was sponsored partly by the Pennsylvania State University and partly by the California Institute of Technology Multidisciplinary University Research Initiative under ONR grant number N00014-95-1-1338, Program Manager Dr. Judah Goldwasser. Address correspondence to Vigor Yang, The Pennsylvania State University, 104 Research Building East, University Park, PA 16802, USA. E-mail: vigor@psu.edu
PY - 2009/4
Y1 - 2009/4
N2 - A comprehensive theoretical/numerical model is developed to investigate the transient combustion response of AP/HTPB composite propellant to acoustic excitation in a rocket-motor environment. The work extends our previous analysis of AP/HTPB combustion at steady-state to include flow oscillations and their subsequent influence on the flame structure and propellant burning behavior. Detailed information about the flame-zone physiochemistry near the propellant surface is obtained at different locations in the motor for the first three modes of longitudinal acoustic waves. In addition, various mechanisms dictating the characteristics of the propellant combustion response, including microscale motions in the flame zone and macroscale motions in the bulk flow, are explored. The effects of mean and oscillatory flowfields in determining the propellant combustion response are also examined. Furthermore, a large flow velocity fluctuation often leads to a nonlinear response of the heat feedback to the propellant surface and the resultant burning rate.
AB - A comprehensive theoretical/numerical model is developed to investigate the transient combustion response of AP/HTPB composite propellant to acoustic excitation in a rocket-motor environment. The work extends our previous analysis of AP/HTPB combustion at steady-state to include flow oscillations and their subsequent influence on the flame structure and propellant burning behavior. Detailed information about the flame-zone physiochemistry near the propellant surface is obtained at different locations in the motor for the first three modes of longitudinal acoustic waves. In addition, various mechanisms dictating the characteristics of the propellant combustion response, including microscale motions in the flame zone and macroscale motions in the bulk flow, are explored. The effects of mean and oscillatory flowfields in determining the propellant combustion response are also examined. Furthermore, a large flow velocity fluctuation often leads to a nonlinear response of the heat feedback to the propellant surface and the resultant burning rate.
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U2 - 10.1080/00102200802693781
DO - 10.1080/00102200802693781
M3 - Article
AN - SCOPUS:70449562585
VL - 181
SP - 597
EP - 617
JO - Combustion Science and Technology
JF - Combustion Science and Technology
SN - 0010-2202
IS - 4
ER -