The Effect of Solar and Lunar Attraction and SRP on the HEO of Satellite

Abstract

The perturbation of a satellite high orbit due to the presence of other
gravitational bodies (such as the Sun and the Moon) and SRP from the conservative
perturbing forces were studied, using our modified model. A precise calculation of
the perturbations is possible only if the initial orbit is sufficiently well known.
Orbital elements that have been entered hp=3000Km., inclination= 63ᵒ, 23ᵒ and
eccentricity= 0.1, longitude of ascending node 30ᵒ, argument of perigee 40ᵒ where
the orbital elements will deviate from initial values with time through 3000 days.
Newton-Rapson method was used to calculate the position and velocity with out
perturbation . The perturbed equation of motion solved numerically using the fourth
order Runge-Kutta method .The results appear that all elements are varies non
linear with time for all inclination 63,23 deg ,the time period was increased, It's
mean value 22.55 hours with i=63ᵒ and 22.52 hours with i=23ᵒ deg. and the orbit
approach to circle .