Noninteracting control for helicopter in straight horizontal flight

Pitch angle and forward velocity are decoupled via a static state feedback law for the case of helicopter in straight horizontal flight. The set of stability derivatives for which decoupling is satisfied, is explicitly determined. The general analytic expression of the feedback controller, satisfying the decoupling design requirement, is derived. The necessary and sufficient conditions for decoupling and simultaneous stability are explicitly determined in terms of the stability derivatives of the helicopter. Simulation results are presented for vertical translation manoeuvre