Angular Momentum Control in Nonlinear Flight

Abstract

A rational approach to control angular motion of aircraft in highly nonlinear e ight regimes is presented. The method seeks to change the angular velocity by directing the aerodynamic moment so that it is most effective in achieving this objective. Validation of the method is presented by simulating two spins of a light aircraft. The approach is shown to be successful in stopping the rotation for effecting spin recovery. Nomenclature G = moment vector H = angular momentum vector I = moment of inertia L, M, N = moment vector components in body axes P = roll rate Q = pitch rate R = yaw rate u = control vector V = airspeed a = angle of attack b = sideslip angle d A = aileron dee ection d E = elevator dee ection d R = rudder dee ection ! = angular velocity vector