The Boeing Company

David J Brockmeyer

Tomio Hamatani

Sun Gil Kim

Katsuya Ikeda

Hisao Kondo

A strong helical compression spring biases the plunger of a unidirectional actuator to an extended position. The actuator is a self contained unit having an integral travel stop to limit extension of the plunger and an integral down lock mechanism which locks the plunger when the maximum extended position is reached.

Mechanical actuator with integral travel stop and down lock

An overcenter mechanism (10) includes a housing (12) and a first shaft (14) mounted on the housing. The first shaft has a first axis (34). A second shaft (20) is mounted on the housing and the second shaft has a second axis (41) that parallels the first axis. A lever (16) is attached to the first shaft, and the lever pivots about the first axis in response to a force (F.sub.op) applied to the lever. A cam (18) is attached to the first shaft, and the cam pivots about the first axis. The cam has a cam surface including a first surface portion (58) and a second surface portion (60). The first and second surface portions form a cusp (62) therebetween. A cam follower (21) has a cam follower surface, and the cam follower pivots about the second axis. A biasing member (26) urges the cam follower surface against the cam surface in pressure contact. The cam follower and the pressure contact cooperate with the cam to generate torque (.tau..sub.roller) on the cam until the cam follower surface contacts the cusp. The pressure contact creates an instability about the cusp when the cusp contacts the cam follower surface, and the torque pivots the cam so the cusp and the cam follower move away from each other.

Cam and roller overcenter handle mechanism

A mechanism(10) arms, disarms, and activates an airplane emergency evacuation system having a slide with one end connected to a girt bar (16). The mechanism includes floor fittings (18) mountable below and at each edge of the airplane door (14). Each floor fitting includes a base (32) defining a notch (40) for receiving the girt bar and a pawl (42) mounted to the base. The pawl rotates relative to the base from a locked position preventing removal of the girt bar from the notch, and to an unlocked position permitting removal of the girt bar. Support fittings (20) mountable to the door, engages the floor fittings when the door is closed and locked. A first jaw (58) extends downwardly to one side of the notch, and faces generally towards the notch from the support fitting. First and second linkage members (60) and (70) connect to one another and rotatably mount to the support fitting. A second jaw (94) extends from the second linkage member and faces generally towards the first jaw. The mechanism operates to rotate the second jaw towards the first jaw to capture the girt bar therebetween, and to rotate the pawl to the unlocked position to disarm the system and allow normal use of the door. To arm the system, the second jaw is rotated in the opposite direction which releases the girt bar and causes the pawl to securely lock the girt bar to the floor of the airplane.

Growing community of inventors

Bellevue, WA, United States of America

David J Brockmeyer