Patent ID: 7853369

Claim:
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 1 ; c) calculating a deflection command δq using the following expressions: { δ ⁢ ⁢ q = ( Q ⁢ ⁢ 1 - F + Δ ⁢ ⁢ RMI ) ⁢ / ⁢ G F = ρ · V 2 · S · l · Cm ⁢ / ⁢ 2 · I G = ρ · V 2 · S · l ⁡ ( ∂ Cm ⁢ / ⁢ ∂ δ ⁢ ⁢ q ) ⁢ / ⁢ 2 · I Δ ⁢ ⁢ RMI = K · ( - Q ⁢ ⁢ eff + ∫ ( F + G · δ ⁢ ⁢ q ⁢ ⁢ eff - Δ ⁢ ⁢ RMI ) · ⅆ t ) wherein: Q 1 represents said pitch acceleration instruction; 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.