Quaternion-Based Attitude Control System Design of Single and Cooperative Spacecrafts: Boundedness of Solution Approach

Table 1

Parameter simulation for single spacecraft case.

Parameters	Value
𝐽, [22]	1.490.0540.04420.0541.5100.044201.56
𝑞𝑑𝑙	1000^𝑇
𝑞𝑏𝑙(0)	−1/301/31/3^𝑇
𝜔^𝑏𝑏𝑙(0); 𝜔^𝑏𝑑𝑙(𝑡), 𝑡≥0	000^𝑇
𝑘	1
𝐿	100010001
𝜙	0.57