초록 ▼

An apparatus attached to the flight control surface designed to lock the surface in a fixed and generally neutral position when a hydraulic pressure failure occurs. A spring loaded hydraulic actuator is mounted in the fixed wing structure but has an arm with a locking roller extending into a wedge s

An apparatus attached to the flight control surface designed to lock the surface in a fixed and generally neutral position when a hydraulic pressure failure occurs. A spring loaded hydraulic actuator is mounted in the fixed wing structure but has an arm with a locking roller extending into a wedge shaped recess in the adjacent movable control surface. When hydraulic pressure is present the actuator spring is compressed and the locking roller on the actuator arm is moved to the wide end of the wedge, effectively avoiding any contact between the roller and the flight control surface surrounding it irrespective of the control surface orientation. Upon the occurrence of a hydraulic pressure drop, the compressed spring translates the actuator arm drawing the locking roller into a detent in the narrow end of the wedge, thereby inhibiting control surface rotation and flutter.

대표청구항 ▼

A flight control surface rotation and flutter prevention apparatus, comprising: (a) a flight control surface, rotatably mounted to a wing about a hinge axis substantially perpendicular to the chord of said wing, said surface having a wedge shaped recess medial of said wing and said hinge axis which

A flight control surface rotation and flutter prevention apparatus, comprising: (a) a flight control surface, rotatably mounted to a wing about a hinge axis substantially perpendicular to the chord of said wing, said surface having a wedge shaped recess medial of said wing and said hinge axis which has rims that converge sharply to a detent in the direction away from said hinge axis; (b) a spring return hydraulic actuator fixedly mounted in said wing in confronting relationship to said wedge shaped recess, said actuator having a first operating state in which hydraulic pressures forces said actuator to its extreme of travel and compresses a return spring, and a second operating state in which hydraulic pressure is absent and said return spring forces said actuator to its opposite extreme of travel; (c) a translating arm, capable of translation in a direction substantially parallel to the wing chord, connected at its first end to said actuator and extending at its second end into said control surface in the region of said recess; and (d) a means for making contact between said second end of said translating arm and the rims of said wedge shaped recess, said means attached to said second end of the translating arm so that said means is drawn into the detent of the recess when hydraulic pressure is absent, and driven into the wide end of the wedge when hydraulic pressure is present, respectively inhibiting and enabling rotation of the flight control surface about its hinge axis.