HELICOPTER FLIGHT SPEED DETERMINATION SYSTEM

摘要

1. System for determining the airspeed of helicopters using the cyclic and collective control signals and the attitude angles for pitch and roll attitude, characterized in that there is supplied a coupled measuring device (11; 21), to which are supplied the cyclic and collective control signals (delta L , delta Q , delta K ), the attitude angles (vphi, THETA) and the rotational velocities (p, q, r) about the axes (x, y, z) of the helicopter and which contains the two models, namely - a model (12; 22) of the input behaviour of the helicopter motion, on which the cyclic and collective control signals (6) act as input parameters and - a model (13/14; 23/24) of the system behaviour of the helicopter, on which the condition parameters act as input parameters, there is a correction arrangement (18; 26/28) for the measured parameters of the rotational velocity and the attitude angle, there is an integration stage (16), in which the estimated condition parameters (x) are obtained by integration of the algebraic sum of see diagramm : EP0249848,P12,F1 of the output signals (x'B , x'S ) of the two models (12, 13/14; 22, 23/24) and the output signals of the correction arrangement (18; 26), said algebraic sum being formed in an addition position (15; 25), and there is an indication (19; 30) of the three estimated velocity components (ûA , va and wA ) for which the values are taken behind the integration stage (16; 29).