| 摘要 |
1,181,685. Automatic control. VEREINIGTE FLUGTECHNISCHE WERKE G.m.b.H. April 6, 1967 [April 6, 1966], No.15922/67. Heading G3R. In a system in which a control member for a variable is automatically regulated to eliminate error between the magnitude of the variable and a desired magnitude, input and/or feedback impedance associated with an operational electronic control amplifier is automatically varied in dependence on the magnitude of the error or variations of the control member. In Fig.7, deviations in the attitude of an aerial body 14 are detected by a gyro 13 signals from which are applied through one resistor R 1 to an amplifier 15 in opposition to signals, representing a desired attitude, applied through another input resistor R 1 . The output of amplifier 15, which thus varies with the attitude error, is applied to a rudder 17, having a limited range of movement, which corrects the attitude. Input and feedback impedances provide differential and integral components of control. The amplifier feedback is derived from a potential divider which includes a resistor 19 having two sliders, one, 20, of which is moved in dependence on attitude as detected by the gyro, and the other, a double slider 22, 22a, of which is moved in dependence on the desired attitude setting. The sliders occupy the position shown when the attitude is correct but more relative to one another, when there is error, to increase the feedback and reduce the gain with increase of error so that the gain is as high as possible without instability. In another arrangement, without an integral component of control, the amplifier feedback is through a fixed resistor and the input resistors are each provided with two sliders which are moved in dependence on the actual and desired values of attitude to vary the gain. Variation of the amplifier input and/or feedback impedance in dependence on deflection or rate of deflection of a control member such as a rudder is referred to. |
