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An airborne glide slope tracking system includes a radio altimeter for producing a signal indicative of the instantaneous altitude of the aircraft and a glide slope error indicator for producing a signal indicative of the angular deviation from glide slope. The two signals are multiplied to produce

An airborne glide slope tracking system includes a radio altimeter for producing a signal indicative of the instantaneous altitude of the aircraft and a glide slope error indicator for producing a signal indicative of the angular deviation from glide slope. The two signals are multiplied to produce a glide slope error signal in feet and fed to a summing device directly and through a lead filter to generate a signal for a throttle servo to increase or decrease the thrust of the aircraft. A longitudinal accelerometer signal is then added to a signal indicative of a difference between an aircraft's reference angle of attack and actual angle of attack to produce a signal to a pitch command to provide an angle which will be sustained by the power of the aircraft.

대표청구항 ▼

1. An airborne glide slope tracking system comprising a computer and program for automatically maintaining an aircraft on its glide slope during a landing maneuver, said system including means for receiving a glide slope error signal which is indicative of angular deviation from flight path, means f

1. An airborne glide slope tracking system comprising a computer and program for automatically maintaining an aircraft on its glide slope during a landing maneuver, said system including means for receiving a glide slope error signal which is indicative of angular deviation from flight path, means for generating a signal indicative of the instantaneous altitude of the aircraft and means for multiplying the glide slope error signal by the signal indicative of the instantaneous altitude of the aircraft to thereby provide a first resulting signal indicative of the glide slope error in distance, a first summing junction and means for multiplying the signal indicative of the glide slope error in distance by a first constant to produce a second resulting signal and feeding the second resulting signal to said first summing device, a lead filter and means for passing the signal indicative of the glide slope error in distance through said lead filter to said first summing device to thereby produce a first combined signal for activating a throttle servo to thereby increase or decrease thrust; a second summing junction, means for generating a signal indicative of the aircraft's longitudinal acceleration and means for multiplying the longitudinal acceleration signal by a second constant to produce a third resulting signal and feeding the third resulting signal to said second summing junction, a third summing junction and means for inputting a signal indicative of the aircraft's reference angle of attack and feeding the signal indicative of the reference angle of attack to said third summing junction, means for generating a signal indicative of the aircraft's actual angle of attack and for feeding that signal to said third summing junction to thereby generate a fourth resulting signal indicative of the difference between the reference angle of attack and the actual angle of attack, means for multiplying the fourth resulting signal by a third constant and adding said fourth resulting signal in said second summing junction to provide a second combined signal and means for multiplying said second combined signal by a fourth constant to thereby produce a pitch command signal to provide a pitch angle that will be sustained by the power of the aircraft. 2. An airborne glide slope tracking system according to claim 1, in which said means for generating a signal indicative of the instantaneous altitude of the aircraft is a radio altimeter. 3. An airborne glide slope tracking system according to claim 2, wherein said pitch command signal is fed to an autopilot. 4. An airborne glide slope tracking system according to claim 2, wherein said pitch command signal is fed to a flight director so that the pilot adjusts the elevator controls to make the actual angle of attack equal to the reference angle of attack.