Patent US 3,963,197

A controller for avoiding the pitching up of aircraft. A device is provided which, at a predetermined combination of the angle of attack and the aerodynamic rate of change of the angle of attack, supplied by a pitch rate gyro in connection with an electrical network, interrupts the pilot's command signal and transfers the control of the aircraft to the control device. The control device causes the aircraft to move through its change command by the pilot at primarily an optimum permissible limit for the angle of attack (.alpha.) and an optimum permissible limit for the aerodynamic rate of change for the rate of attack (.omega..sub.7 *). An optimum permissible limit which corresponds to the optimum permissible limit (.alpha. permissible) for the angle of attack (.alpha.) is also provided so that all control operations commanded by the pilot which would exceed .alpha. permissible are stopped prematurely.