GB860793A - Device for controlling and coordinating the controls of an aircraft - Google Patents

Abstract

860,793. Automatic steering-control systems. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. April 11, 1958 [April 17, 1957], No. 11610/58. Class 38 (4). Aerodynamic steering controls of an aircraft are rendered inoperative by the pilot during substantially vertical flight when the angular attitude of the aircraft is automatically controlled by control of a jet, and rendered operative by the pilot during substantially horizontal flight when the automatic control is inoperative. In Fig. 1, D.C. signals of reversible polarity, derived from a potentiometer-type pick-off (not shown) in a bridge circuit associated with a gyro 34 responsive to the pitch attitude of an aircraft during vertical take-off, are applied through a magnetic amplifier 11 to control an A.C. servomotor 9 which adjusts, through fluid-pressure servo-systems 8, jet spoilers 5 in opposite directions to maintain a desired vertical attitude. Positional and rate follow-up signals derived from movement of the jet spoilers are applied to amplifier 11 through channels 15 and 17, the latter including a resistance-capacity delay unit 42. Signals from a rate gyro 35 are also applied to amplifier 11. The desired attitude may be trimmed by signals applied to amplifier 11 in consequence of movement of a manual controller 31. Change from vertical to horizontal flight is effected by moving switches 41 to position b and closing a switch 40. Gyro 34 is thus disconnected and a fixed signal introduced for a predetermined time from a source 38 to cause a predetermined rate of change of pitch until the aircraft is level. Manual controller 31 is now also effective to trim the pitch by signals applied to an amplifier 10 to control an A.C. servomotor 4 which adjusts, through a fluid-pressure servo-system 3, a control surface 1. Positional follow-up signals derived from movement of control surface 1 are applied to amplifier 10 through a channel 14. Finally, to continue horizontal flight, switches 41 are moved to position c to cut out delay unit 42. Change from horizontal flight to vertical flight prior to landing is effected by returning switches 41 to position band operating manual controller 31 to produce nose lifting. Vertical flight may then be maintained automatically by moving switches 41 to position a to reintroduce gyro 34. Signals to control control-surface 1 may alternatively be derived from the spoiler control system or both control systems may be controlled by separate automatically-produced signals.