Mathematical Modeling and software development on pertubation effects towards small satellite mission on low earth orbit (LEO)

The orbit of satellite cannot be calculated using the theoretical method for precise calculation. This is because the orbital elements will deviate from true elements with time. Regression of the lines-of-the-nodes and rotation of the line-of-apsides (major axis) are the two principal effect of the perturbation of low altitude orbits due to the oblate shape of the earth. This gravitational effect of an oblate earth can be modeled by using Spherical Harmonics to satisfy the Laplace’s Equation. A precise calculation of the perturbations is possible only if the orbit is sufficiently well known. The results can be obtained by using Ordinary Differential Equation, i.e., Runge-Kutta method, and Matlab to view the graphs. This paper discusses the development of Mathematical Modeling and Analysis Software on Perturbation Effects Using Cowell’s Method and with the help of Matlab to visualize the Effect.