| 摘要 |
1533011 Automatic control of a flying vehicle BOFORS A B 7 Jan 1976 [14 Jan 1975] 00508/76 Heading G3R In an automatic system for guiding a flying vehicle, e.g. a missile, in the vertical and horizontal directions, pitch and yaw oscillations are damped by providing notch filters in each control channel which attenuate the control signals in a narrow frequency band which is automatically adjusted in reponse to vehicle speed to follow in close conformity the natural frequency of the vehicle. The speed signal is derived by itegrating the output of an accelerometer. It is applied to terminal 7 of the filter circuit shown to vary conduction of F.E.Ts. Q1, Q2 and hence the effective resistance in the circuits R1, Cl connecting the control signal at 8 to the inverting terminal of operational amplifier 10, and in the feedback circuit R0, C0. The output to control servos appears at 9. |
