Vision Autonomous Relative Positioning and Orientating Algorithm for Distributed Micro/Nanosatellite Earth Observation System Based on Dual Quaternion

Table 1

The initial parameters of the simulations.

	Active spacecraft A	Target spacecraft B	Initial parameters
Ascending node/deg	0.0	0.0	x/m	0.0
Inclination of orbit/deg	57.5	57.5	y/m	0.0
Argument of perigee/deg	0.0	0.0	z/m	7.0505710682868
Eccentricity	0.000001	0	Vx/(m/s)	0.0150364992
Semimajor axis/km	7051.004	7051.004	Vy/(m/s)	0.0000007894
Time of perigee passage/s	0	0.0	Vz/(m/s)	0.0
Yaw/deg	0.5	0.5	q 0	1
Pitch/deg	0.2	0.2	q 1	0
Roll/deg	0.4	0.5	q 2	0
Yaw angle velocity/(deg/s)	5×10^−7	5×10^−7	q 3	0
Pitch angle	5×10^−7	5×10^−7	Wx/(deg/s)	−0.000000000864246
Velocity/(deg/s)			Wy/(deg/s)	0.000000000876427
Roll angle velocity/(deg/s)	5×10^−7	5×10^−7	Wx/(deg/s)	−0.000000000010665