Generic Model of a Satellite Attitude Control System

Table 4

Nominal mode simulation cases.

Case	Initial satellite rates	Commanded attitude; (Initial); (After 100 s)	Initial RW spin	RW configuration
1	0.5°/s	0°; 0°	0	Orthogonal 3 wheels
2	0	0°, 0°, 0°; 120°, 60°, 150	0, 2000, 4000 rpm	Orthogonal 3 wheels
3	0	0°, 0°, 0°; Nadir pointing	0 rpm	Orthogonal 3 wheels
4	0	120°, 60°, 150°	0 rpm	Pyramid 4 wheels
				Tetrahedron 4 wheels