Research Article

Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

Table 1

Physical parameters of the spacecraft system.

Parameter itemParameter value

Size of the main body (m)1.5 × 1.5 × 2.0
Material density of the main body (kg/m3)2400
Length of panels (m)1.5
Width of panels (m)2.0
Thickness of panels (m)0.06
Material density of panels (kg/m3)100
Young’s modulus of panels (Pa)E1 = 6.78 × 108, E2 = E3 = 4.08 × 108
Poisson’s ratio of panels (-) =  =  = 0.3
Shear modulus of panels (Pa)G12 = G13 = 1.2 × 108, G23 = 4.5 × 108
Layer number of panels (-)4
Fiber angle relative to the Y direction (°)0/90/90/0
Material thickness of panels (m)0.015/0.015/0.015/0.015
Torsional stiffness of spring-damper 1 (N m/rad)0.25
Torsional stiffness of spring-damper 2 (N m/rad)0.085
Damping coefficient of spring-damper 1 (N/(m/s))0.025
Damping coefficient of spring-damper 2 (N/(m/s))0.015
Equivalent cable stiffness of CCL 1 (N m/rad)60
Equivalent cable stiffness of CCL 2 (N m/rad)15
Equivalent stiffness of latch 1 (N m/rad)2.5 × 104
Equivalent stiffness of latch 2 (N m/rad)1 × 104
Damping coefficient of latch 1 (N/(m/s))2.5 × 103
Damping coefficient of latch 2 (N/(m/s))1 × 103
Exponent of latch 1 and latch 2 (-)1.5
Distance depth of latch 1 and latch 2 (°)0.01
Time step (s)0.001
Total time (s)40