doiSerbia

Mechanical characterization of composite solid rocket propellant based on hydroxy-terminated polybutadiene

Gligorijević Nikola I. (Military Technical Institute, Belgrade)
Rodić Vesna Ž. (Military Technical Institute, Belgrade)
Živković Saša Ž. (Military Technical Institute, Belgrade)
Pavković Bojan M. (Military Technical Institute, Belgrade)
Nikolić Momčilo M. (Military Technical Institute, Belgrade)
Kozomara Stevan M. (Military Technical Institute, Belgrade)
Subotić Sredoje D. (Military Technical Institute, Belgrade)

This paper presents the procedure of uniaxial mechanical characterization of composite solid rocket propellant based on hydroxy-terminated polybutadiene (HTPB), whose mechanical properties strongly depend on temperature, strain rate, natural aging and accumulated damage. A method of processing data is presented in order to determine time-temperature shift factor and master curves for tensile strength, ultimate strain and relaxation modulus, depending on reduced time. Functional dependences of these features represent an input for structural analysis of a rocket motor propellant grain. The effects of natural aging on the mechanical properties are also considered.

Keywords: composite propellant, viscoelasticity, mechanical characterization, tensile strength, ultimate strain, time-temperature shift factor, relaxation modulus, safety factor, reduced time

Projekat Ministarstva nauke Republike Srbije, br. TR 36050: Research and development of unmanned aircraft in support of traffic infrastructure monitoring