| 摘要 |
FIELD: physics; control. ^ SUBSTANCE: invention relates to automatic control systems. Aircraft, method and system for controlling flight of the aircraft assume a selected value of a first parametre which is either airspeed or inertial speed of the aircraft. A primary feedback loop generates a primary error signal which is proportional to difference between the selected value and the measured value of the first parametre. A secondary feedback loop generates a secondary error signal which is proportional to difference between the selected value of the first parametre and the measured value of the second flight parametre which is the remaining parametre: either airspeed or inertial speed. The primary and secondary error signals are summed to generate a speed error signal, and this speed error signal and the integrated value of the primary error signal are summed to generate an actuation control signal, which is then used to actuate aircraft devices to control the first parametre in order to minimise the primary error signal. ^ EFFECT: minimisation of undesirable accelerations acting on aircraft passengers. ^ 16 cl, 24 dwg |
