Publicado 6 números por año
ISSN Imprimir: 2150-766X
ISSN En Línea: 2150-7678
Indexed in
MODELING OF A SHORT ACTION MOTOR DISCHARGING A WEIGHT
SINOPSIS
This paper investigates the interior ballistics of a unique concept for short action motors, based on a rocket-type combustion chamber discharging a weight through an exhaust tube. Depending on the overall system requirements, different kinds of propellant and weight may be considered. In the current study a system comprising a granular solid propellant and a solid weight is considered in order to capture the basic mechanisms of the impulse augmentation. A simplified lumped parameters model and a detailed two-phase flow model have been formulated and the fundamental characteristics of the propulsion system have been computed and analyzed. The study reveals that for certain system parameters with a given propellant mass the total impulse as well as the specific impulse may be significantly larger than those generated by a conventional rocket motor. The theoretical parametric investigation provides a good understanding on how different system parameters influence the in-terior ballistics processes, and can provide guidelines to the design of thrusters. Such short action motors may be beneficial for spacecraft and missile station keeping and trajectory correction, applying mini-thrusters of this kind, as well as for separating large space bodies such as missiles/launcher stages, satellites, etc.
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Michaels Dan, Gany Alon, Theoretical and experimental study of a thruster discharging a weight, Acta Astronautica, 99, 2014. Crossref