Multisegment Scheme Applications to Modified Chebyshev Picard Iteration Method for Highly Elliptical Orbits

Table 1

Classical orbital elements.

Parameter	Symbol	Value	Unit
Semimajor axis			m
Eccentricity		0.7	—
Inclination		60	Degree
Right ascension of the ascending node		45	Degree
Argument of periapsis		30	Degree
Orbit period			s