A Method to Derive Angle of Pitch, Flight-Path Angle and Angle of Attack from Measurements in Nonsteady Flight

摘要

A method is described to determine the angle of pitch, the flight-path angle and the angle of attack of an air craft during steady or nonsteady flight. These angles are determined by integration of the rate of pitch and the specific forces, and not by directly measuring these angles. Errors in the estimates of the initial conditions of the integra tions and of the zero shifts in the measurements are corrected by comparing the computed and the measured values of the change in altitude and airspeed. An error analysis is carried out, to determine the accuracy with which the angles of pitch, flight path, and attack are determined by the described method for steady as well as for nonsteady flight. (Author)