Patent ID: 8046118

Claim:
A converter, for aircraft, for converting a load factor command N zc into a longitudinal attitude deviation instruction Δθ c comprising a longitudinal attitude deviation generator circuit with: a variable-gain integrator applying the flight mechanics relation linking the load factor N zc to the longitudinal attitude deviation Δθ c : Δ ⁢ ⁢ θ c = α TAS · ∫ ( N zc + τ γ · ⅆ N zc ⅆ t ) ⁢ ⅆ t α=180/π being a coefficient for converting radians into degrees, τ γ the aircraft's trajectory constant, and TAS the true air speed of the aircraft considered, and a high-pass filter restoring in the long term, to a constant value, the longitudinal attitude deviation instruction value provided by the integrator.