Fig 1.
Schematic of Spacecraft Motion.
Fig 2.
Schematic diagram of the proposed control system.
Table 1.
Simulation parameters.
Fig 3.
Response of the attitude quaternion vector part .
(a) represent the proposed controller; (b) represent the fixed-time anti-unwinding controller from [21]. (c) represent the finite-time anti-unwinding controller from [17].
Fig 4.
(a) represent the proposed controller; (b) represent the fixed-time anti-unwinding controller from [21]. (c) represent the finite-time anti-unwinding controller from [17].
Fig 5.
(a) represent the proposed controller; (b) represent the fixed-time anti-unwinding controller from [21]. (c) represent the finite-time anti-unwinding controller from [17].
Fig 6.
Response of the attitude error.
(a) represent the proposed controller; (b) represent the fixed-time anti-unwinding controller from [21]. (c) represent the finite-time anti-unwinding controller from [17].
Fig 7.
Response of the angular velocity error .
(a) represent the proposed controller; (b) represent the fixed-time anti-unwinding controller from [21]. (c) represent the finite-time an-ti-unwinding controller from [17].
Fig 8.
Response of the control torque .
(a) represent the proposed controller; (b) represent the fixed-time anti-unwinding controller from [21]. (c) represent the finite-time anti-unwinding controller from [17].
Fig 9.
Interevent interval.