Patent ID: 8442705
Filing Date: 2013-05-14
Classification: G01M

Abstract:
1. A method for determining aerodynamic characteristics of an aircraft: (a) detecting forces and mechanical flight parameters by sensors on aerofoils and a horizontal tail plane of the aircraft at various detection instants during at least one non-stationary flight manoeuvre of the aircraft; and (b) evaluation of a system of equations by a calculation unit, the system comprising, for each detection instant, a pitch movement moment balance equation, which has the detected forces and mechanical flight parameters, to calculate the aerodynamic characteristics of the aircraft; wherein a spindle force in a trimming spindle of the horizontal tail plane and bearing forces in a left and right rotary bearing of the horizontal tail plane are detected by sensors during the flight manoeuvre; and wherein a vertical ascending force F wherein co is a predetermined carry over factor, g is the gravitational constant, m is the mass of the aircraft, m m n n n F F