The optimal control problem arising in coplanar, orbital transfer employing aeroassist technology is addressed. The maneuver involves the transfer from high Earth orbit to low Earth orbit via the atmosphere with the object of minimizing the total fuel consumption. Simulations are carried out for obtaining the fuel optimal trajectories for flying the spacecraft through the atmosphere. A highlight is the application of an efficient multiple shooting method for taming the notorious nonlinear, two-point boundary value problem resulting from the optimization procedure.
|Original language||English (US)|
|Number of pages||8|
|Journal||IEEE Transactions on Aerospace and Electronic Systems|
|State||Published - Mar 1990|