Fuel slosh has been one of the key problems faced by liquid propellant spacecraft. Fuel slosh can adversely affect a spacecraft’s stability, cause nutation, and affect fuel consumption as well as the ..
Fuel slosh has been one of the key problems faced by liquid propellant spacecraft. Fuel slosh can adversely affect a spacecraft’s stability, cause nutation, and affect fuel consumption as well as the trajectory change especially during change in attitude of the craft or during the stage separation. This research deals with the innovation and use of a hybrid magneto-active membrane, used as a Magneto-active Propellant Management Device (MAPMD) to actively control the free surface effect and reduce fuel slosh. The viability of merging existing diaphragm membrane known as propellant management device with a magneto-active inlay allows us to control the membrane during in-flight conditions. Apart from the system development, the analysis on the control of hybrid membrane and the use of the same to dampen fuel slosh are also performed in order to establish the concept validations. During the development process of the hybrid membrane, the geometric dependency of the meta-smart structure is analyzed to optimize the membrane shape, size and material. Further advancement in the research process could be done using different materials and comparing for inefficiencies to get the best results.
