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)	𝐸=39.72	𝐸𝑝=68
Density (kg/m)	𝜌𝑏=4	𝜌𝑝=2.31
Thickness (m)	𝑡𝑏=0.01	𝑡𝑝=0.003
Width (m)	𝑏=0.5	𝑏=0.1
Length (m)	𝐿𝑏=2	𝐿𝑝=0.1
PZT Strain constant (m/V)	—	𝑑31=125×10^−12
PZT Stress constant (Vm/N)	—	𝑒31=10.5×10^−3
Hub dimension (m)	𝑎=1
Spacecraft moment of inertia (kg·m^2)	200000210000180