Cool-down Problem of a Solid Propellant Rocket Motor Incorporating Dewetting
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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The thesis undertook a macroscopic, theoretical analysis of a long, circular, solid propellant, rocket motor undergoing thermal loading. It was shown that classical plasticitys von Mises yield condition adequately described dewetting of solid propellant which was modeled to have linear strain hardening characteristics. The mechanical properties of the propellant permitted a closed-form solution for the stresses and the strains resulting from cooling the motor from 160 deg F to -60 deg F.
- Solid Rocket Propellants