Research Article
Attitude and Vibration Control of Flexible Spacecraft Using Singular Perturbation Approach
Table 1
Parameters of flexible spacecraft.
| Parameters | Flexible appendage | Piezoelectric layer |
| Young’s Modulus (GPa) | | | Density (kg/m) | | | Thickness (m) | | | Width (m) | | | Length (m) | | | PZT Strain constant (m/V) | — | | PZT Stress constant (Vm/N) | — | | Hub dimension (m) | | Spacecraft moment of inertia (kg·m2) | |
|
|