أعرض تسجيلة المادة بشكل مبسط
| 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 |
|
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أعرض تسجيلة المادة بشكل مبسط