| 摘要 |
An aircraft flight control system has wing-mounted flight control output devices employed in a multipurpose role. The system in one form includes wing-mounted port and starboard output assemblies 24, 25 of yaw and roll control surface components 26, 27, 28; 29, 30, 31 and port and starboard flight control actuators 32, 33 which in response a yaw demand input cause the components 26, 27; 29, 30 of the assemblies 24, 25 to produce asymmetric yawing forces on the wings 12, 13 and yawing of the aircraft 10 and in response to a roll demand input cause the components 28, 31 to produce rolling forces on the wings 12, 13 and rolling of the aircraft 10. In addition, the actuators 32, 33 in response to an air-braking demand input cause the components 26, 27; 29, 30 to produce symmetric air-braking forces on the wings (12, 13) (Figure 4) and aerodynamic braking of the aircraft. In other forms the control surface components of the wing-mounted output assemblies may be inclined (figure 5) or provide simply for yawing and air-braking forces to be applied to the aircraft (figure 7). <IMAGE> |
