APPROACH AND LANDING SIGNALLING SYSTEMS FOR AIRCRAFT

摘要

1,097,973. Radio navigation. ELLIOTT BROS. (LONDON) Ltd. Aug. 5, 1965 [Aug. 6, 1964], No. 32083/64. Heading H4D. In the aircraft receiver of an I.L.S. the localizer or glide slope beam error signal e is displayed at 13, Fig. 1, and is also applied to a unit 16 which introduces an operation (1/{1+ST 1 }), where ST 1 represents a time integral of signal e, the output being applied to a relay 17; signal e is applied to a unit 19 introducing an operation (K 2 /{1+ST 2 }), where K 2 corresponds to an augmented signal e and ST 2 a time integral of signal e; and when signal e, e.g. as a result of failure of the automatic pilot, is outside limiting combinations of amplitude and frequency, relay 17 is energized, contacts 20 close and the output of unit 19 causes a substantially increased deflection of the display pointer. Units 16 and 19 may comprise an input resistor in series with a D.C. amplifier, the latter being bridged by a parallel combination of resistance and capacitance, Fig. 2 (not shown).