Please use this identifier to cite or link to this item: http://dspace.mediu.edu.my:8181/xmlui/handle/123456789/4591
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dc.creatorOliva P.-
dc.creatorLeite Filho W. C.-
dc.date2000-
dc.date.accessioned2013-05-30T11:25:51Z-
dc.date.available2013-05-30T11:25:51Z-
dc.date.issued2013-05-30-
dc.identifierhttp://www.scielo.br/scielo.php?script=sci_arttext&pid=S0100-73862000000200002-
dc.identifierhttp://www.doaj.org/doaj?func=openurl&genre=article&issn=01007386&date=2000&volume=22&issue=2&spage=149-
dc.identifier.urihttp://koha.mediu.edu.my:8181/jspui/handle/123456789/4591-
dc.descriptionA control law was designed for a satellite launcher ( rocket ) vehicle using eigenstructure assignment in order that the vehicle tracks a reference attitude and also to decouple the yaw response from roll and pitch manoeuvres and to decouple the pitch response from roll and yaw manoeuvres. The design was based on a complete linear coupled model obtained from the complete vehicle non linear model by linearization at each trajectory point. After all, the design was assessed with the vehicle time varying non-linear model showing a good performance and robustness. The used design method is explained and a case study for the Brazilian satellite launcher ( VLS Rocket ) is reported.-
dc.publisherThe Brazilian Society of Mechanical Sciences-
dc.sourceJournal of the Brazilian Society of Mechanical Sciences-
dc.subjectAttitude Control-
dc.subjectDecoupling-
dc.subjectEigenstructure Assignment-
dc.titleRocket tracking and decoupling eigenstructure control law-
Appears in Collections:Technology and Engineering

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