Numerical simulation is used to perform parametric analysis to assess the feasibility of aerocapture at Titan over arrival of , vehicle lift-to-drag ratio of 0–1, and vehicle ballistic coefficient of 90 and . Aerodynamic forces, peak heat rate, and total heat load are evaluated. It is shown that aerocapture at Titan requires a lifting vehicle with a minimum lift-to-drag ratio of 0.2 and an arrival of , an equivalent propulsive of about , which is higher than what is realistically possible. Results show that aerocapture requires different interplanetary trajectories from propulsive options, and aerocapture with a vehicle of lift-to-drag ratio of 0.3 enables an arrival of and higher. The peak heat rate is well within the capability of the state-of-the-art technologies of thermal protection system materials. In addition, the vehicle can achieve an inclination change up to 20 deg via an aerocapture maneuver.
Feasibility Assessment of Aerocapture for Future Titan Orbiter Missions
Journal of Spacecraft and Rockets ; 55 , 5 ; 1125-1135
2018-06-28
11 pages
Article (Journal)
Electronic Resource
English
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