Differential sensor rotations relative to the mean inertia axes usually are neglected in simulations of the quasisteady frequency response, For control-configured flying-wing aircraft, however, this aeroelastic effect may be significant as demonstrated by analyses of the U.S. Air Force-Northrop B-2 aircraft. A correction for the axes rotation has been provided by Redden and Love who formulated the unaugmented vehicle equations in terms of motion variables measured in a structurally restrained system, This article, while retaining the original mean axes formulation, extends the Redden-Love concept to the sensor output equations, which are required for modeling of aeroservoelastic effects, By applying the modified equations, longitudinal maneuver analyses are performed and correlated with flight test data.
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