| 摘要 |
1,207,764. Automatic aircraft flight control system. UNITED AIRCRAFT CORP. 31 July, 1968 [11 Sept., 1967], No. 36477/68. Heading B7G. [Also in Division G3] An aircraft control mechanism, illustrated in use for yaw control, comprises a linkage 10 connecting the pilot's control pedals to a bellcrank 12 mounted on the airframe for rotation at 18 and 20, the bellcrank being connected through rods 24, servoactuator 26 and rod 28 to the aircraft yaw control mechanism. The servoactuator 26, which for weight considerations is an electrical type, can be operated in response to control signals from automatic control mechanisms such as a yaw rate gyro, and to prevent the automatic motion of the servoactuator 26 affecting the pilot's controls through the bellcrank 12 and linkage 10 a rotary clutch 30 of the magnetic dry particle type is placed between the bellcrank shaft 16 and the airframe. Rate gyro signals pass via a demodulator and a high-pass filter 48 to a summing amplifier 50, then a preamplifier and an amplifier 52, 54 around which there is a feedback loop which may include lag/lead network 72 to the actuator, whose output is shown at 58. The clutch 30 is operated by signals from the high-pass filter 48, and for automatic control signals of all magnitudes the clutch holds shaft 16 fixed. The electrical linkage between clutch 30 and servoactuator 26 includes the high-pass filter 48 to eliminate steady rate signals and thus to prevent the clutch looking shaft 16 when the servoactuator is moved in response to the pilot's controls. By design of the servoactuator, or by saturation of the amplification 74, 76 linking the clutch and the servoactuator, an upper limit is imposed on the locking forces produced by the clutch 30, as shown at 58, 78, so that at all times the pilot may override the automatic control. An embodiment is described in which the servoactuator is in parallel with the pilot's control, and a linear slip clutch is used. The invention may be used to control pitch and roll as well as yaw; an automatic heading command signal, for example from a gyro compass 86, may be used to operate the servoactuator via the summing amplifier 50, in which case switching on the gyro-compass also energizes the clutch 30 to its maximum looking power to feed the heading signals to the attitude control mechanisms. |
