Patent ID: 7853369
Filing Date: 2010-12-14
Classification: G05D

Abstract:
1. An active pitch control method for an aircraft, comprising: a) generating a pitch objective which is expressed in the form of a pitch rate and which must be applied to the aircraft; b) from said pitch objective, calculating a pitch acceleration instruction Q c) calculating a deflection command δq using the following expressions: wherein: Q ρ is the volumic mass of air; V is the speed of the aircraft; S is a reference surface of the aircraft; l is a reference length of the aircraft; Cm represents a pitch coefficient; I represents a pitch inertia; ∂Cm/∂δq represents an efficiency coefficient; K is a predetermined coefficient; Qeff represents an effective pitch rate of the aircraft; ∫ illustrates an integration function; and δqeff is an effective deflection angle of the elevators of the aircraft; and d) applying said deflection instruction δq to the elevators of the aircraft.