US 12,110,732 B2
Shock absorber configured with a deformable energy absorbing member
Morteza Yadollahi, Fullerton, CA (US); and Alan Manara, Fullerton, CA (US)
Assigned to Adams Rite Aerospace Inc., Fullerton, CA (US)
Filed by Adams Rite Aerospace Inc., Fullerton, CA (US)
Filed on Jul. 11, 2022, as Appl. No. 17/862,106.
Application 17/862,106 is a continuation of application No. 16/250,135, filed on Jan. 17, 2019, granted, now 11,384,585.
Claims priority of provisional application 62/618,546, filed on Jan. 17, 2018.
Prior Publication US 2022/0341236 A1, Oct. 27, 2022
Int. Cl. F16F 7/12 (2006.01); B64C 1/14 (2006.01); E05B 77/54 (2014.01); E05B 81/56 (2014.01); E05F 3/04 (2006.01); E05F 5/06 (2006.01); E05F 5/10 (2006.01); F16F 9/00 (2006.01); F16F 9/19 (2006.01); F16F 9/48 (2006.01); B64C 1/00 (2006.01); F16F 9/16 (2006.01); F16F 9/30 (2006.01)
CPC E05F 5/06 (2013.01) [B64C 1/1469 (2013.01); E05B 77/54 (2013.01); E05B 81/56 (2013.01); E05F 3/04 (2013.01); E05F 5/10 (2013.01); F16F 7/121 (2013.01); F16F 7/125 (2013.01); F16F 9/003 (2013.01); F16F 9/19 (2013.01); F16F 9/48 (2013.01); B64C 2001/009 (2013.01); E05Y 2201/212 (2013.01); E05Y 2900/502 (2013.01); E05Y 2900/531 (2013.01); F16F 9/165 (2013.01); F16F 9/303 (2013.01); F16F 2228/066 (2013.01); F16F 2236/04 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A shock absorber, comprising:
a first end configured to be mechanically fastened to a first component;
a second end configured to be mechanically fastened to a second component;
a main body that is attached to the first end;
a main shaft that is attached to the second end;
a primary piston configured to be received in the main body;
the primary piston being attached to the main shaft and the primary piston being further configured to be movable with the main shaft;
the primary piston configured to move within the main body and further configured to provide a first damping force by movement of a fluid through an orifice in the primary piston while the main shaft moves a first distance;
a deformable solid material arranged in the main body; and
the primary piston configured to further move within the main body and further configured to provide a second damping force by deforming the deformable solid material after the main shaft moves the first distance,
wherein one of the first component and the second component comprises a fixed structure;
wherein another one of the first component and the second component comprises a movable structure;
wherein the movable structure is an aircraft cockpit door, pivotally mounted within a partition separating an aircraft cockpit from an aircraft passenger cabin;
wherein the primary piston is configured to move within the main body and further configured to provide the first damping force to reduce velocity during movement at a first rate of speed of one of the first component and the second component; and
wherein the primary piston configured to further move within the main body and further configured to provide the second damping force to reduce velocity by deforming the deformable solid material after the main shaft moves the first distance during movement at a second rate of speed of one of the first component and the second component, the second rate of speed of one of the first component and the second component being greater than the first rate of speed of one of the first component and the second component.