US 11,787,552 B2
Engine mount system and elements for reduced force transmission and reduced static motion
Gerald P. Whiteford, Waterford, PA (US); and Jonathan Sacco, Erie, PA (US)
Assigned to LORD Corporation, Cary, NC (US)
Filed by LORD Corporation, Cary, NC (US)
Filed on Dec. 22, 2022, as Appl. No. 18/87,209.
Application 18/087,209 is a continuation of application No. 16/929,794, filed on Jul. 15, 2020, granted, now 11,542,023.
Application 16/929,794 is a continuation of application No. PCT/US2019/013625, filed on Jan. 15, 2019.
Claims priority of provisional application 62/617,395, filed on Jan. 15, 2018.
Prior Publication US 2023/0127420 A1, Apr. 27, 2023
Int. Cl. B64D 27/26 (2006.01); F16F 15/023 (2006.01)
CPC B64D 27/26 (2013.01) [F16F 15/023 (2013.01); B64D 2027/268 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A compliant engine mount system for reacting loads from an engine of an aircraft to an aircraft structure, the system comprising:
a top mount comprising:
an upper link comprising an upper bearing surface;
a housing comprising;
a lower bearing surface disposed along the longitudinal axis of the top mount;
a center structure centrally disposed relative to the longitudinal axis of the top mount and comprising a compression stop configured to carry loads in compression and at least one tension stop configured to carry loads in tension;
wherein the upper link is configured to interlock within the center structure;
a lower mount comprising:
an upper link comprising an upper bearing surface;
a housing comprising:
a lower bearing surface disposed along the longitudinal axis of the lower mount;
a center structure centrally disposed relative to the longitudinal axis of the lower mount and comprising a compression stop configured to carry loads in compression and at least one tension stop configured to carry loads in tension;
wherein the upper link is configured to interlock within the center structure; and
a center trunnion mount comprising:
a pin configured to be received within an engine bearing structure of the engine;
a pivot element disposed on a surface of the pin, the pivot element being configured to react the loads from the engine; and
an elastomeric compliance element disposed inboard on the pin relative to the pivot element.