|
Abstract
|
|
|---|---|
| A specific modal analysis performed about a flexible spacecraft leads to identify rigid modes and bending modes. One of the main problems of this kind of vehicles is the mechanical coupling existing between rigid and flexible spacecraft parts. In spacecraft with fine attitude pointing requirements it is very important to take into account possible misalignments for the whole vehicle. In designing the attitude controller it is necessary to consider the possible vibrations of the solar panels, and how they influence on the rest of the vehicle. Spacecraft in their orbits with large flexible appendages are susceptible to perturbations and non desired attitude motions. In this paper, the modelling of flexible spacecraft is taken as the preliminary phase of the controller design by the Eigenstructure Assignment (EA) method. The design process is closed by an assignment of the robustness performances of the spacecraft. | |
|
International
|
Si |
|
Congress
|
EUCASS |
|
|
960 |
|
Place
|
Versalles |
|
Reviewers
|
Si |
|
ISBN/ISSN
|
978-2-930389-47-9 |
|
|
|
|
Start Date
|
06/07/2009 |
|
End Date
|
09/07/2009 |
|
From page
|
0 |
|
To page
|
0 |
|
|
no disponible |