Studies on the influence of testing parameters on dynamic and transient properties of composite solid rocket propellants using a dynamic mechanical analyzer

• Published in: Journal of aerospace technology and management 2012, Vol.4 (4), p.443-452
• Main Authors: Wani, Vilas, Mehilal, Jain, Sunil, Singh, Praveen Prakash, Bhattacharya, Bikash
• Format: Article
• Language: English
• Subjects: ENGINEERING, AEROSPACE
• ISSN: 2175-9146; 2175-9146
• DOI: 10.5028/jatm.2012.04044012

Dynamic mechanical analysis is a unique technique that measures the modulus and damping of materiais as they are deformed under periodic stress. Propellants, which are viscoelastic in nature, are subjected to time, temperature, and frequency effects during the analysis to determine their dynamic and transient properties. The choice of parameters during the experiments like temperature, frequency, strain (%), and stress level is very crucial to the results obtained since the propellant behaves differently under different conditions. A series of experiments like strain and temperature ramp/ frequency sweeps, creep, stress relaxation, etc. have been conducted using high burning rate composite propellant (burn rate ~20 mm/s at 7,000 kPa), in order to determine the precise effects of such parameters on the results obtained. The evaluated data revealed that as the temperature increases the storage modulus, loss modulus, and tan delta curves with respect to the frequency shift towards the lower side. Moreover, there is equivalency between the increase in the temperature and the decrease in the frequency, which can be used for the time-temperature superposition principles. Further, in transient tests, the relaxation modulus has been found to decrease when increasing strain levels in the given time range. Also, relaxation modulus versus time curves were found to shift towards the lower side with increasing temperature while creep compliance decreases with the increase in stress and decrease in temperature. The glass transition value of the composite propellant increases when there is an increase in the heating rate.