DSpace Repository

Rocket tracking and decoupling eigenstructure control law

Show simple item record

dc.creator Oliva P.
dc.creator Leite Filho W. C.
dc.date 2000
dc.date.accessioned 2013-05-30T11:25:51Z
dc.date.available 2013-05-30T11:25:51Z
dc.date.issued 2013-05-30
dc.identifier http://www.scielo.br/scielo.php?script=sci_arttext&pid=S0100-73862000000200002
dc.identifier http://www.doaj.org/doaj?func=openurl&genre=article&issn=01007386&date=2000&volume=22&issue=2&spage=149
dc.identifier.uri http://koha.mediu.edu.my:8181/jspui/handle/123456789/4591
dc.description A 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.publisher The Brazilian Society of Mechanical Sciences
dc.source Journal of the Brazilian Society of Mechanical Sciences
dc.subject Attitude Control
dc.subject Decoupling
dc.subject Eigenstructure Assignment
dc.title Rocket tracking and decoupling eigenstructure control law

Files in this item

Files Size Format View

There are no files associated with this item.

This item appears in the following Collection(s)

Show simple item record

Search DSpace

Advanced Search


My Account