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Completed TRL 3 (started at 2, targeting 3)
Ames will perform a concept study in fall to formulate a baseline mission. ARC will then conduct trajectory analyses to define the entry environments. This will feed into TPS analysis, CFD simulations exploring the separation dynamics of the drag modulation event, and the mechanical design of a feasible vehicle. Ballistic range models reflecting this vehicle configuration will be designed and fabricated. In year 2, a ballistic range test will be executed to verify that the transition event is aerodynamically stable and validate the CFD predictions. Results from this CIF and the parallel work at JPL and CU-Boulder will likely result in sounding rocket flight test that can lead to a mission proposal for a small (~100 kg) secondary payload, Venus science mission.
The goal is to enable a simple, single-event drag modulated aerocapture at Venus for a small satellite science mission. Aerocapture can significantly enhance orbital missions to Mars, Venus, Titan, Uranus, and Neptune. The use of aerocapture instead of propulsive orbit insertion can increase delivered payload by 15% at Mars, 70% at Venus, more than 200% at Titan and Uranus, and an estimated greater than 800% at Neptune. An alternative approach is aerocapture that employs drag instead of lift as a means to modulate the trajectory. Drag modulated aerocapture is a simple, scalable, and likely to be cost-effective way to enhance planetary science missions. The focus of this proposal is to address some of the key entry technology challenges for the single-stage discrete-event architecture.
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