Aeroelastic Stability Analysis of Electric Aircraft Wings with Distributed Electric Propulsors
نویسندگان
چکیده
In this paper, the effect of distributed electric propulsion on aeroelastic stability an aircraft wing was investigated. All propulsors, which are different properties, attached to in positions. The structural dynamics modelled by using geometrically exact beam equations, while aerodynamic loads were simulated unsteady theory. propulsors a concentrated mass wing, and motor’s thrust angular momentum taken into account. each propulsor as follower force acting exactly at centre gravity propulsor. nonlinear governing equations discretised time–space scheme, obtained results verified against available very good agreement observed. Two case studies considered throughout resembling two flight conditions aircraft. numerical show that tip thrust, mass, had most impact wing. addition, it observed high-lift motors minimal
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ژورنال
عنوان ژورنال: Aerospace
سال: 2021
ISSN: ['2226-4310']
DOI: https://doi.org/10.3390/aerospace8040100