A COMPARISON OF OPTIMAL LOW-THRUST AEROASSISTED ORBITAL PLANE CHANGE MANEUVERS
- Paper ID
93-iaf-11
- author
- company
Mechanical Dynamics Inc.
- country
U.S.A.
- year
1993
- abstract
The main- objective of this paper is to compare a number of pure propulsive as well as aeroassisted orbital plane change maneuvers to obtain a globally optimal one. We focus on low thrust, constant ejection velocity type propulsion systems. Assuming the same aerodynamic- and propulsive characteristics, we obtain the fuel consumption required for a given plane change angle. We consider both elliptic as well as circular orbits. All the maneuvers are assumed to have the final time free and the consequences of this asumption are studied. The constant ejection velocity type propulsion system leads to three types of optimal thrust sub-arcs: coast, boost and singular (intermediate thrust). We will study all three sub-arcs in conjunction with aeroassisted plane change. Usually while employing thrusting and lifting, the thrust is used to cancel the drag while the lift produces the required plane change. Using the concept of an aerodynamic impulse, we study a maneuver that employs both thrust and the lift forces for plane change. This maneuver is then compared to the others already discussed above. Finally, the results are compared geometrically in the mass-energy space for global optimality.