Abstract
The dynamics associated with the jettisoning of spent ullage rocket systems from the parent launch vehicle is investigated. The analysis considers a spring-based mechanism employed to jettison the system hinged on to an accelerating stage. Closed-form solutions are obtained. Analytical expressions are developed for the hinge reactions. Conditions are derived for optimum separation velocity and guidelines presented for selection of design parameters. The influence of residual thrust of ullage rockets on the separation process is examined and the expressions for its permissible value developed. a b E h
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