Control device for avoiding the pitching up of missiles or aircr

Details Control device for avoiding the pitching up of missiles or aircr Control device for avoiding the pitching up of missiles or aircr

1074-08-14

1976-06-15

Blix, Trygve M.

Aeronautics and astronautics

Aircraft control

Automatic

340 27SS, B64C 1350

Patent

active

039631974

ABSTRACT:
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.

REFERENCES:
patent: 2584298 (1952-02-01), Seay
patent: 2923499 (1960-02-01), Dinard
patent: 2953327 (1960-09-01), Clement et al.
patent: 2985410 (1961-05-01), Richter et al.
patent: 3015458 (1962-01-01), Marx
patent: 3037725 (1962-06-01), Treffeisen
patent: 3072369 (1963-01-01), Alderson
patent: 3172079 (1965-03-01), Gunson et al.
patent: 3241792 (1966-03-01), Hattendorf
patent: 3260108 (1966-07-01), Kaminskas
patent: 3292882 (1966-12-01), Walsh
patent: 3518621 (1970-06-01), Collett et al.

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