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contributor authorHu, Qinglei
contributor authorZhang, Jian
contributor authorFriswell, Michael I.
date accessioned2017-05-09T01:16:31Z
date available2017-05-09T01:16:31Z
date issued2015
identifier issn0022-0434
identifier otherds_137_06_061012.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/157541
description abstractIn this paper, finitetime attitude coordinated control for spacecraft formation flying (SFF) subjected to input saturation is investigated. More specifically, a bounded finitetime state feedback control law is first developed with the assumption that both attitude and angular velocity signals can be measured and transmitted between formation members. Then, a bounded finitetime output feedback controller is designed with the addition of a filter, which removes the requirement of the angular velocity measurements. In both cases, actuator saturation is explicitly taken into account, and the homogeneous system method is employed to demonstrate the finitetime stability of the closedloop system. Numerical simulation results are presented to illustrate the efficiency of the proposed control schemes.
publisherThe American Society of Mechanical Engineers (ASME)
titleFinite Time Coordinated Attitude Control for Spacecraft Formation Flying Under Input Saturation
typeJournal Paper
journal volume137
journal issue6
journal titleJournal of Dynamic Systems, Measurement, and Control
identifier doi10.1115/1.4029467
journal fristpage61012
journal lastpage61012
identifier eissn1528-9028
treeJournal of Dynamic Systems, Measurement, and Control:;2015:;volume( 137 ):;issue: 006
contenttypeFulltext


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