| 摘要 |
<p>A control column 102 for an aircraft comprises a control stick 110 pivotable about a pitch axis 136 and a roll axis 130. An autopilot lockout mechanism 246 is associated with a selected one of pitch or roll, the autopilot lockout mechanism 246 providing increased resistance that must be overcome to manipulate the control stick 110 about the selected one of the pitch axis 136 or roll axis 130 when autopilot is activated. The autopilot lockout 246 may include first and second autopilot plates 254,256 and a resistance spring 252 biasing ends of the autopilot plates 254,256 angularly toward one another about an autopilot axis 250. A main link 248, pivotable about the autopilot axis 250 and coupled to the control stick 110, engages the first autopilot plate 254 when rotated in a first direction and engages the second autopilot plate 256 when rotated in a second direction. When autopilot is activated, a grounding arrangement 272 selectively grounds the second autopilot plate 256 when the main link 248 is rotated in the first direction and selectively grounds the first autopilot plate 254 when the main link 248 is rotated in the second direction.</p> |
