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. A performance index is chosen the minimize the fuel consumpltion for the transfer. Simulations are carried out for establishing a corridor of entry conditions which are suitable for flying the spacecraft through the atmosphere. A highlight of the paper is the application of an efficient multiple shooting method for taming the notorious nonlinear, two-point, boundary value problem resulting from optimization procedure.
Guidance and control strategies for aerospace vehicles
1988-07-01
Report
Keine Angabe
Englisch
Guidance and Control Strategies for Aerospace Vehicles
NTIS | 1990
|Guidance and control strategies for aerospace vehicles
NTRS | 1989
|Guidance and control strategies for aerospace vehicles
NTRS | 1990
|Guidance and control of aerospace vehicles
TIBKAT | 1963
|