Conceptual Development of AeroDrop: Aerocapture and Direct Entry for Two Spacecraft on a Common Approach Trajectory

Abstract

The ability to deliver an orbiter and a lander from the same cruise stage and approach trajectory is desirable. However, the use of propulsive maneuvers to accomplish these objectives is operationally risky. AeroDrop provides the ability for an orbiter and a probe to reach their desired states from a single set of entry conditions due to differences in geometry and control approach. In this investigation, the concept of AeroDrop is introduced and its performance assessed. AeroDrop is shown to be feasible for a small range of entry conditions for uncontrolled ballistic vehicles and for a larger range of entry conditions when at least one vehicle is lift-modulated. The feasibility of AeroDrop is shown for both Earth and Mars entry.

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