Adaptive Fuzzy Modified Fixed-Time Fault-Tolerant Control on SE(3) for Coupled Spacecraft

Table 1

Initial orbital elements of the leader.

Orbital element	Value
Semimajor axis (km) (km)	26628
Eccentricity	0.7417
Inclination (deg)	63.4
RAAN (deg)	0
Argument of perigee (deg)	270
True anomaly (deg)	120