Aircraft nose-up warning method

摘要

The angles mentioned are converted into voltages and the left angle of attack sensor (10) gives an alpha1 signal, the right angle of attack sensor (20) an alphar signal and the slide angle sensor (30) a beta signal, and these are stored in the calculator (40) that provides the parameter alpha, where alpha = alpha1 + alphar/2. The calculator generates a warning modulation value delta, controlling the warning tone generator (50), while beta = M1 (alpha1-alphar)-M2, where M1 and M2 are constants depending on the aircraft. Values of beta are periodically compared and, if a threshold is exceeded, there is a warning lift from the interface (80), with values of constants (and so on) given to interface (70), in cockpit.