Funksignalverstaerkungsfaktorregelung fuer Flugzeuge

摘要

1,214,672. Radio navigation; gain control. SPERRY RAND CORP. 5 March, 1968 [17 March, 1967], No. 10544/68. Headings H4D and H4R. Relates to a circuit for varying the gain of a radio navigation signal which controls an aircraft automatic pilot or flight director system during an airport approach. According to the invention a distance signal representing the distance between the aircraft and the radio beam transmitter is fed to the gain control circuit and a timing circuit is arranged on failure of the distance signal to control the gain as a function of time whereby gain is reduced as the aircraft approaches the transmitter even when the distance signal fails. The timing circuit may be up-dated by the distance signal. The invention is described with reference to the glide-slope of an I.L.S. system, the gain varying with a predetermined ratio of signal magnitude to altitude from an initial altitude of 1500 ft. to 100 ft. at which point the ratio is changed such that the gain is rapidly reduced to zero at flare altitude e.g. 50ft., Fig. 2 (not shown). For gain with time, the gain is reduced by a first time characteristic from an initial value to a lower gain at the I.L.S. middle marker whereat the gain is reduced by a different time characteristic to substantially zero at or near the runway threshold. Detailed circuit, Fig. 1.-The normal D.C. signal from receiver 10 after modulation is applied to variable gain amplifier 12 comprising a transistor 14 the gain being controlled by a circuit 32 consisting of a transistor 15 the impedance-to-earth of which is connected to the emitter of transistor 14; the gain of amplifier 12 is an inverse function of the emitter impedance-to-ground which in turn is an inverse function of the D.C. current through diodes 17, 18. Distance signal gain variation is derived from radio altimeter 20, a D.C. signal proportional in sense and magnitude to instantaneous altitude appearing on line 27. Circuit 33 comprises a transistor 34 which in association with diode 36 and circuit 40 causes the output of a transistor 41 to decrease with "radio" altitude when in normal glide slope operation; ground depressions are rendered ineffective by resistor 46. If the altimeter fails, loss of voltage on lead 22 actuates transistor switch 47 so as to earth lead 40 and hence turn off transistor 41, gain control then being effected by discharge of capacitors 51, 52 through resistors 53, 57, 58; when the middle marker is reached transistor switch 65 is energized to short potentiometer 66 to ground and transistor switch 63 is energized to afford a further discharge path through resistor 611. The discharge rate is made more rapid when the middle marker is reached. Potentiometer 67 is set to allow zero gain to be reached. If the altimeter fails before the glide slope is engaged, or if there is no altimeter, a twostep timing programme is provided.