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Abstract

The jettisoning of a nose cone in space from a spinning rocket has been investigated. The spring-assisted separation system is described with its mathematical model. The resulting non-linear equations have been integrated numerically. The geometry for safe separation has been analysed and the influences of various imperfections in the system, such as dynamic asymmetry, dynamic imbalance, separation system imperfection, etc., are studied. The analysis presented here enables a clear understanding to be obtained of the separation dynamics of a nose cone in a spinning environment. A closed-form solution has been obtained for the relative motion between the separating dynamically symmetric bodies devoid of any dynamic imbalance under the influence of a perfect separation system. For the same system, simple design formulae have also been derived for collision avoidance, which can be gainfully utilized for initial sizing of separation systems.

Keywords

separation dynamics nose cone sinning rockets closed-form solution spring-based separation

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Dynamics of nose cone jettisoning from spinning rockets

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