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- W4283399095 abstract "Conventional flight test techniques used to estimate the neutral point location are time-consuming and their results are very sensitive to pilot technique. Usually, the tests need to be conducted for three different CG locations, which is not always feasible for two-seater aircraft. When compressibility, aeroelastic or power effects are present, non-standard dependencies arise, such as the CL and Cm dependency on airspeed, thus requiring additional testing. In the present work, system identification techniques were applied to dynamic maneuvers, in order to obtain an aerodynamic model of the longitudinal dynamics of a propeller-driven aircraft, including a model for the elevator hinge moment. As a result, the model allows numerical computation of elevator deflections and stick forces required to trim the aircraft at different flight conditions, including variation of CG location, from which the neutral point location can be computed. The data collected for system identification required a fraction of the flight time used in conventional techniques. Moreover, power effects are automatically embedded into the model. The new method reduced the uncertainty associated with the neutral point location by one order of magnitude, if compared to a conventional technique." @default.
- W4283399095 created "2022-06-25" @default.
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- W4283399095 date "2022-06-20" @default.
- W4283399095 modified "2023-09-27" @default.
- W4283399095 title "Flight Test Determination of Power Effects on Longitudinal Stability using System Identification" @default.
- W4283399095 cites W1971513400 @default.
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- W4283399095 doi "https://doi.org/10.2514/6.2022-3637" @default.
- W4283399095 hasPublicationYear "2022" @default.
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