US 12,084,169 B2
Retractable body mounted landing gear with secondary crash attenuation
Michael Saccoccia, Seagrave (CA)
Assigned to Safran Landing Systems Canada Inc., Ajax (CA)
Filed by SAFRAN LANDING SYSTEMS CANADA INC., Ajax (CA)
Filed on Oct. 26, 2022, as Appl. No. 18/049,941.
Prior Publication US 2024/0140594 A1, May 2, 2024
Int. Cl. B64C 25/20 (2006.01); B64C 25/26 (2006.01); B64C 25/34 (2006.01); B64C 25/58 (2006.01)
CPC B64C 25/20 (2013.01) [B64C 25/26 (2013.01); B64C 25/34 (2013.01); B64C 25/58 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A vehicle, comprising:
a fuselage; and
a landing gear assembly, comprising:
a linkage coupled to the fuselage and configured to reciprocate between a stowed position and a deployed position, the linkage comprising a shock strut;
a side brace configured to provide a driving force that reciprocates the linkage between the stowed and deployed position, the side brace including:
a lower brace with a first end coupled to the linkage; and
an upper brace with a first end rotatably coupled to the fuselage, a second end of the upper brace being rotatably coupled to a second end of the lower brace about a first axis, the upper brace having an energy attenuation system that enables the first end of the upper brace to move toward the second end of the upper brace to dissipate energy when a compressive load on the side brace exceeds a predetermined threshold; and
an actuator assembly including:
an upper toggle link with a first end rotatably coupled to the first end of the upper brace;
a lower toggle link with a first end rotatably coupled to the second end of the upper brace, a second end of the lower toggle link being rotatably coupled about a second axis to a second end of the upper toggle link; and
a linear actuator rotatably coupled at a first end to the fuselage and rotatably coupled at a second end to at least one of the upper toggle link and the lower toggle link.