摘要
The control problem for aircraft in rapid roll is analyzed. A 5-DOF modelis used to derive a decoupling control law of roll, pitch and sideslip angular velocitiesaccording to the nonlinear decoupling theory. The stability of the closed-loop system isdiscussed. A method to stabilize the whole system when some fixed dynamics areunstable is given. Simulations are perfonned.
The control problem for aircraft in rapid roll is analyzed. A 5-DOF modelis used to derive a decoupling control law of roll, pitch and sideslip angular velocitiesaccording to the nonlinear decoupling theory. The stability of the closed-loop system isdiscussed. A method to stabilize the whole system when some fixed dynamics areunstable is given. Simulations are perfonned.
