Abstract
A numerical assessment of the feasibility of aerocapture at Venus is presented, and the mass benefit of aerocapture is compared with propulsive orbit insertion. This paper considers constraints imposed by entry corridor, deceleration loads, and aerodynamic heating on aerocapture for two vehicle control techniques: lift modulation and drag modulation. Feasibility charts are presented to graphically visualize the aerocapture design space spanning interplanetary trajectory and vehicle performance. Results indicate lift modulation aerocapture is feasible at Venus using existing blunt-body aeroshells. Drag modulation technique is also feasible and an attractive option for small satellites, but merits an additional study due to small corridor width and heating constraints. The peak heat rate is within the capability of existing thermal protection system materials for both control techniques. Delivered mass fraction using aerocapture is compared with propulsive insertion with and without aerobraking. Aerocapture allows 90–250% increase in delivered mass to a 400 km circular orbit compared with propulsive insertion.
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