Orbits that are modeled by a relatively small satellite moving in the central force field of a much larger primary body with other forces omitted are termed two-body orbits. Classically, two-body motion in elliptic or hyperbolic orbits is described by transcendental equations requiring extensive calculation to find the precise position as a function of time. This site explores the difficulty of writing algebraic equations for orbital displacement versus time, a challenge known as the Kepler problem.
Consultation Services: Most
space endeavors involve the application of fundamentals of orbital
mechanics, and if the principles described herein can help you with a
mission problem, please make contact with our principal investigator
using the email address below.
This web site is
provided
courtesy of DRD Corporation with motivation by the
mission
statement to:
"Derive equations of orbital
motion that will reduce computation requirements
for prediction, and teach the
results."
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All content of this web site copyright
©
2005 by Douglas H. May*, SaddleBrooke, AZ
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