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- W4312685657 abstract "For future helicopter-only Mars missions, NASA-JPL has proposed a novel entry, descent, and landing technique, in which the rotorcraft is deployed from the aeroshell in mid-air before landing. However, this approach is likely to subject the rotorcraft to unfavorable vortex ring state aerodynamics during deployment. To address this, the performance of a variable-pitch multirotor in axial descent was investigated using two parallel approaches: an experimental free-flight wind tunnel campaign and analogous computational efforts utilizing the tool RotCFD. Results indicated significant mean thrust losses of up to 20% compared to hover conditions, as well as heavily amplified rotor thrust fluctuations and vehicle attitude oscillations with increasing descent rate. Meanwhile, discrepancies between computations and experiments were observed, primarily regarding the descent rates where maximum thrust losses occur. Additional studies performed within the computational environment indicated that the vehicle fuselage and rotor-rotor interactions have significant impacts on the rotor performance in descent." @default.
- W4312685657 created "2023-01-05" @default.
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- W4312685657 date "2021-05-10" @default.
- W4312685657 modified "2023-09-26" @default.
- W4312685657 title "Axial Descent of Variable-Pitch Multirotor Configurations: An Experimental and Computational Study for Mars Deployment Applications" @default.
- W4312685657 doi "https://doi.org/10.4050/f-0077-2021-16697" @default.
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