Verfahren zur Schätzung des Anstellwinkels eines Rotorblatts für ein Flugzeug und Rotor für ein Flugzeug

Details

Veröffentlichungs-Nr.

EP4768387

Anmeldetag

31. Dezember 2024

Veröffentlichung

1. Juli 2026

Rechtsraum

EP

Abstract

A method is described for estimating the pitch angle (γ) of the blades (25) of a rotor (10, 10') of an aircraft (1) capable of hovering comprising a motor member (16) with a stator (14) and an output shaft (18) rotatable about the stator (14); a hub (19) rotatable about the axis (B) and operatively connected with the output shaft (18) so as to be rotatable with an angular velocity (ω) about the axis (B); at least two blades (25) rotatable about the axis (B) and about corresponding second axes (D) of extension of the blades (25), so as to adjust the pitch angles (γ) of the blades (25) between a first value (α) and a second value (β) different from each other; the method comprises the steps of: i) computing a third value associated with the torque (τ_EM) generated by the motor (16); ii) computing a fourth value associated with the torque (τ_tr) required, in use, by the rotor (10, 10'); iii) computing a fifth value associated with the thrust coefficient (C_P) and a sixth value associated with the thrust coefficient (C_T) of the rotor (10, 10'), also based on the fourth value; iv) comparing the fifth and sixth values with seventh and eighth threshold values (Th_P, Th_T); and v) estimating a ninth value of the pitch angle (γ), based on the result of step iv). (Figure 2)

Anmelder

Firma

Leonardo S.p.a.

Land

🇮🇹 Italien