Perturbation analysis for low earth orbits

Reddy, Suryakiran B (2014) Perturbation analysis for low earth orbits. Masters thesis, Manipal Institute of Technology, Manipal.

[img] PDF
Suryakiran.pdf - Submitted Version
Restricted to Registered users only

Download (3MB) | Request a copy


A satellite in an orbit around the earth experiences many perturbing forces classified as conservative and non-conservative. Conservative forces include gravitational effects, tidal effects, attraction by sun and moon and other planets. While non-conservative forces are atmospheric drag and solar radiation pressure. The consequences of these forces are change in the nominal orbital elements. The special perturbation techniques Cowell’s Method and Encke’s Method are studied and the phenomenonal changes in the orbital parameters are calculated. But certain limitations are present in these methods. A better method simplified general perturbations model is developed to overcome these limitations. SGP4 takes into account all the disturbing forces and its effect on the orbital elements. This model is used to propagate orbital parameters over time. This theory uses two line mean element set (TLE) to determine the orbit parameter and satellite mean motion. The scope of the present work is to do a thorough analytical study of the SGP4 model and implement the same using MATLAB. The results of the MATLAB model shall be compared with the results obtained from Systems Tool Kit (STK).

Item Type: Thesis (Masters)
Subjects: Engineering > MIT Manipal > Instrumentation and Control
Depositing User: MIT Library
Date Deposited: 13 Nov 2014 10:58
Last Modified: 13 Nov 2014 10:58

Actions (login required)

View Item View Item