Font Size:
Artificial Satellites: Orbital Perturbations
Rodolpho V. Moraes
Last modified: 2010-05-29
Abstract
A brief comment about some scientific applications of artificial satellites is presented showing the necessity of precise orbital determination for the success of the mission.
The main orbital perturbations: geopotential, atmospheric drag, tides, solar radiation pressure (direct and reflected), electric drag, third body perturbation, are described. Resonance’s effects are discussed. The equations describing the motion of artificial satellites are given considering conservative and non-conservative perturbations. Some original analytical solutions for the equations of motion are presented. Applications are done for real and hypothetical satellites. Orders of magnitudes for the perturbations are exhibited. Simulations show that resonance can produce important long period terms in the time variation of the orbital elements. For intervals shorter than one fourth of the period of the resonant term this could be regarded as a secular variation.
The main orbital perturbations: geopotential, atmospheric drag, tides, solar radiation pressure (direct and reflected), electric drag, third body perturbation, are described. Resonance’s effects are discussed. The equations describing the motion of artificial satellites are given considering conservative and non-conservative perturbations. Some original analytical solutions for the equations of motion are presented. Applications are done for real and hypothetical satellites. Orders of magnitudes for the perturbations are exhibited. Simulations show that resonance can produce important long period terms in the time variation of the orbital elements. For intervals shorter than one fourth of the period of the resonant term this could be regarded as a secular variation.