| 摘要 |
Aerodynamic control apparatus which deflects a control-surface-member into the airstream for creating drag on an aircraft. This drag flap mechanism includes a strut and hinge plate which together constrain the control-surface-member to move in a coupled manner about mutually perpendicular axes. There is an actuator from the controls of the pilot which moves the hinge plate which in turn moves the control-surface-member in that coupled manner. It moves between a fully feathered position presenting minimal resistance to the airstream and a fully operative position presenting maximum resistance to the airstream. The preferred embodiment of the drag flap mechanism is as a continuation of the wing tips where two control-surface-members are hinged about a common axis on the hinge plate so they can open like a split flap. The motion of these two control-surface-members are constrained to allow the force of the air opening the two surfaces to assist in pushing the two surfaces more into the airstream. An alternate embodiment is a single flap that opens into the airstream from any surface on the aircraft but most usefully on the top surface of the wing inboard of the ailerons. Either embodiment can be used for both yaw control and for glide slope control as can many prior art drag flaps. The advantage of the present invention is with extremely large drag forces. The augmenting force is a function of the side slip angle and incorrect actuation (pilot error or hydraulic failure) will not be augmented. In fact without any actuation force, this invention can perform the same function as a large fixed vertical stabilizer and with more deflection on both sides, there is more stabilizing effect. |
