1,043,469. Automatic attitude control. ALBISWERK ZURICH A.G. June 29, 1964 [June 28, 1963], No. 26767/64. Heading G3R. In an error-actuated servo-system at least two error signals having uncorrelated random fluctuations are produced by partly independent measuring units and the smallest error signal is automatically selected for control when the error signals are of the same polarity. In Fig. 2 (not shown), a radar aerial 1, coupled to transmitters 6, 7 operating at different frequencies, makes a conical scan, and associated receivers 8, 9 each produce a pair of D.C. signals corresponding in magnitude and polarity to the magnitude and sense of horizontal and vertical displacement between the axis of the aerial and the direction of a target aircraft. The two horizontal displacement signals are applied to a diode rectifier network 10 which, if the two signals are of opposite polarities, produces no output, but which, if the signals are of the same polarity, applies the smaller of the two to control a follow-up motor 2 eliminating the displacement. A similar diode circuit II eliminates vertical displacement by selecting the smaller of the two vertical displacement signals, if they are of the same polarity, to control a follow-up motor 3. The diode networks, which are described in detail, include a valve amplifier to compensate for attenuation by network resistance.
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