US 11,851,169 B2
Shock absorbing strut
Robert Chappell, Whitby (CA); Randy Lee, Oshawa (CA); Peter Pisters, Ajax (CA); and Michael Saccoccia, Seagrave (CA)
Assigned to SAFRAN LANDING SYSTEMS
Filed by SAFRAN LANDING SYSTEMS, Velizy-Villacoublay (FR)
Filed on Jul. 26, 2019, as Appl. No. 16/523,777.
Prior Publication US 2021/0024203 A1, Jan. 28, 2021
Int. Cl. B64C 25/60 (2006.01); F16F 13/00 (2006.01); B64C 25/10 (2006.01)
CPC B64C 25/60 (2013.01) [F16F 13/002 (2013.01); B64C 25/10 (2013.01); F16F 2224/04 (2013.01); F16F 2230/06 (2013.01)] 10 Claims
OG exemplary drawing
 
1. An energy absorbing apparatus for an aircraft, the apparatus comprising:
a first load limiter including an oleo-pneumatic strut configured to absorb impact energy exerted on said strut, wherein the oleo pneumatic strut comprises an inner cavity that contains a strut fluid composed of gas and hydraulic fluid, an orifice support tube located within the inner cavity and defining at least one damping orifice, a piston movable within the inner cavity in order to force the strut fluid through the at least one damping orifice, and an outer cylinder configured to slideably receive the piston therein, the inner cavity formed by the piston and the outer cylinder, wherein the orifice support tube is disposed within the outer cylinder and extends from a fixed end at a first end of the outer cylinder to a free end; and
a second load limiter integrally formed within the oleo-pneumatic strut, wherein the second load limiter includes one or more disc springs configured to absorb impact energy exerted on said strut via compression of the one or more disc springs, wherein the one or more disc springs are positioned within the inner cavity and surround the orifice support tube adjacent the first end of the outer cylinder.