Deployment/Stationkeeping Dynamics of N Body Orbiting Sat Constellation

The trend to develop small, low-cost spacecraft has
led many to recognize the advantage of flying
multiple spacecraft in formation to achieve the
correlated instrument measurements formerly possible
only by flying many instruments on a single, large
platform. This book explores the techniques for
station keeping an orbiting constellation of
satellites in an elliptical orbit after the initial
deployment is developed. Constellation station
keeping were investigated by: implementing various
propulsive maneuvers at different times based on
Lagrange s planetary equations for impulsive
perturbations; a combination of propulsive strategies
that deliberately shifted the line of apsides and LQR
fb employing the Tschauner and Hempel equations.
Analyses for deploying are developed and evaluated
based on: non-linear two point boundary value problem
via Pontryagin s Prin; numerical techniques using the
shooting method; optimal thrust in near min and min
time. This book sheds light on recent advances in the
field of astronautical sciences and should prove
useful for the practicing professional or for
conducting research in spaceflight mechanics. MATLAB
programs included.