Compound actuation system design for an advanced space transportation reusable orbiter

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dc.contributor.authorZare Shahneh, Amir
dc.date.accessioned2018-09-12T13:34:53Z
dc.date.available2018-09-12T13:34:53Z
dc.date.issued2018-09-11
dc.description.abstractThe SL-12 is a reusable space orbiter which offers the capability to go beyond the notion of a second generation space shuttle, and is targeted to be in operation in the year 2020. SL-12 Orbiter utilizes gimballing of the main rocket engines for control during ascent and typical aerodynamic surfaces for control during re-entry, approach, and landing. Power by wire (PBW) Actuation system is used for SL-12 based on All Electric Aircraft (AEA) approach. Electro Hydrostatic Actuators have been used for Primary Flight Control surfaces (Elevon, Body Flap and Rudder) and Thrust Vector Control for Main Engine Module, Electro Mechanical actuators have been used for Thrust Vector Control of Orbital Maneuvering System and Payload bay door. Dual redundant electric power supply channels are used for redundancy. Actuation System Safety and Reliability analysis has been done to ensure compliance and specification requirements.en_UK
dc.identifier.citationAmir Zare Shahneh. Compound actuation system design for an advanced space transportation reusable orbiter. Aeronautics and Aerospace Open Access Journal, 2018, Volume 2, Issue 5, pp264-268en_UK
dc.identifier.issn2576-4500
dc.identifier.issnhttps://doi.org/10.15406/aaoaj.2018.02.00059
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/13479
dc.language.isoenen_UK
dc.publisherMedCrave Groupen_UK
dc.rightsAttribution-NonCommercial 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc/4.0/*
dc.titleCompound actuation system design for an advanced space transportation reusable orbiteren_UK
dc.typeArticleen_UK

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