The optimal-control problem arising in coplanar orbital transfer using aeroassist technology is addressed. The maneuver involves the transfer from high earth orbit to low earth orbit with minimum fuel consumption. Simulations are carried out to obtain a corridor of entry conditions which are suitable for flying the spacecraft through the atmosphere. A highlight of the present work is the application of an efficient multiple shooting method for handling the difficult nonlinear two-point boundary value problem resulting from the optimization procedure.
|Original language||English (US)|
|Number of pages||3|
|Journal||Proceedings of the IEEE Conference on Decision and Control|
|State||Published - Dec 1 1988|
|Event||Proceedings of the 27th IEEE Conference on Decision and Control - Austin, TX, USA|
Duration: Dec 7 1988 → Dec 9 1988