Automatic landing systems for aircraft

Claim 1

AN AUTOMATIC AIRCRAFT LANDING SYSTEM COMPRISING MEANS FOR DERIVING A FIRST CONTROL SIGNAL AS A FUNCTION OF THE BANK ANGLE OF THE AIRCRAFT, MEANS FOR DERIVING A SECOND CONTROL SIGNAL AS A FUNCTION OF THE DEPARTURE OF THE AIRCRAFT HEADING ANGLE FROM THE RUNWAY ANGLE, MEANS FOR DERIVING A THIRD CONTROL SIGNAL AS AN INTEGRAL FUNCTION OF SUCH DEPARTURE, MEANS FOR DERIVING A FOURTH CONTROL SIGNAL AS A FUNCTION OF THE LATERAL DISPLACEMENT OF THE AIRCRAFT RELATIVE TO THE RUNWAY, MEANS FOR DERIVING A FIFTH CONTROL SIGNAL AS AN INTEGRAL FUNCTION OF SUCH DISPLACEMENT, RUDDER CONTROL MEANS RESPONSIVE TO THE SECOND, THIRD, FOURTH AND FIFTH CONTROL SIGNALS TO CONTROL THE RUDDER IN THE SENSE TO REDUCE THE SECOND CONTROL SIGNAL TO ZERO AND CAUSE THE AIRCRAFT TO HEAD ALONG THE RUNWAY AND AILERON CONTROL MEANS RESPONSIVE TO THE FIRST, SECOND, FOURTH AND FIFTH SIGNALS TO CONTROL THE AILERONS IN THE SENSE TO REDUCE THE FOURTH CONTROL SIGNAL TO ZERO AND CAUSE THE AIRCRAFT TO ASSUME OR MAINTAIN A BANK ANGLE SUFFICIENT TO COMPENSATE FOR ANY TENDENCY TO DRIFT DUE TO WIND.