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A comprehensive overview of orbital mechanics, covering the fundamental principles and equations that govern the motion of satellites orbiting the earth. It delves into the laws of planetary motion, the forces acting on satellites, and the mathematical formulations used to describe satellite orbits. Topics such as the determination of look angles, the relationship between satellite mass and acceleration, the concept of centrifugal and centripetal forces, and the derivation of the equation of motion for a satellite in a stable orbit. It also presents detailed calculations and examples related to satellite orbital parameters, including velocity, period, and the transformation between cartesian and polar coordinate systems. The document serves as a valuable resource for understanding the complex dynamics involved in satellite operations and the factors that influence their trajectories.
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Note that the acceleration can be positive or negative, depending on the direction it is acting with respect to the velocity vector.
ME
FIN=GMEM/r^2
FOUT=mv^2 /r
6.672x10-20^ km^3 /kg s^2
Which is the velocity of the satellite in a circular orbit.
Satellite Orbital height (km)
Orbital velocity (km/s)
Orbital period (hr) (min) (s)
Intelsat (GEO) 35,786.03 3.0747 23 56 4. New-ICO(MEO) 10,255 4.8954 5 55 48.
Skybridge (LEO) 1,469 7.1272 1 55 17.
Iridium (LEO) 780 7.4624 1 40 27.
𝐹 = 𝑚 𝑑
(^2) 𝑟 𝑑𝑡^2 ^2
▫ a different set of coordinates can be chosen to describe the location of the satellite such that the unit vectors in the three axes are constant. ▫ The orbital plane coordinate system.
𝑥 0