Pressure-coupled combustion response model for solid propellants based on Zeldovich-Novozhilov approachAn exact analytical solution is given to the problem of long-time propellant thermal response to a specified pressure oscillation. Coupling to the gas phase is made using the quasisteady Zeldovich-Novozhilov approximation. Explicit linear and lowest order (quadratic) nonlinear expressions for propellant response are obtained from the implicit nonlinear solutions. Using these expressions, response curves are presented for an ammonium perchlorate composite propellant and HMX monopropellant.
Document ID
19870035436
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Harstad, K. G. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Strand, L. D. (California Institute of Technology Jet Propulsion Laboratory, Pasadena, United States)