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- W2320987582 abstract "A general method is presented for modeling inertial hinge moments on aircraft control surfaces that result from maneuver loads on the aircraft. Inertial hinge moments are used to accurately model the loads experienced by actuators or control linkages in dynamic flight conditions. The calculations use quaternion rotations and properties of vector arithmetic applied to hinge vectors to simplify the transformations between coordinate systems. The intent of the paper is to allow the reader to apply this method to any aircraft configuration as part of an aircraft simulation. Sample calculations are included for a simple aircraft configuration." @default.
- W2320987582 created "2016-06-24" @default.
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- W2320987582 date "2016-01-01" @default.
- W2320987582 modified "2023-09-24" @default.
- W2320987582 title "Modeling of Inertial Control Surface Hinge Moments Using Quaternion Calculations" @default.
- W2320987582 doi "https://doi.org/10.2514/6.2016-1185" @default.
- W2320987582 hasPublicationYear "2016" @default.
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