US 12,263,934 B2
Aircraft plug door with in-plane load transfer capacity and methods of use
James M. Curry, Snohomish, WA (US); and Randolph Schemkes, Snohomish, WA (US)
Filed by James M. Curry, Snohomish, WA (US); and Randolph Schemkes, Snohomish, WA (US)
Filed on May 23, 2022, as Appl. No. 17/664,613.
Application 17/664,613 is a continuation of application No. 15/932,777, filed on Apr. 23, 2018, granted, now 11,338,900.
Claims priority of provisional application 62/602,403, filed on Apr. 21, 2017.
Prior Publication US 2022/0281580 A1, Sep. 8, 2022
Int. Cl. B64C 1/14 (2006.01)
CPC B64C 1/143 (2013.01) [B64C 1/1415 (2013.01); B64C 1/1461 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A door assembly for a door opening in a fuselage of an airplane comprising an airframe, the door opening defining an opening upper edge, an opening lower edge, an opening first side edge, and an opening second side edge, the door assembly comprising:
a door configured to fit within the door opening in the fuselage of the airplane;
a first plurality of engagement assemblies positioned and configured to releasably couple an upper edge of the door to the opening upper edge and a lower edge of the door to the opening lower edge, and further configured to transfer in-plane stresses between the door and the airframe, and to transfer radial stresses from the door to the airframe; and
a second plurality of engagement assemblies positioned and configured to releasably couple first and second side edges of the door to the opening first side edge and the opening second side edge, respectively, wherein at least one of the second plurality of engagement assemblies comprises a frame connecting element configured to be coupled to the airframe, the frame connecting element defining at least one frame contact surface, and a door connecting element coupled to the door, the door connecting element defining at least one door contact surface wherein the at least one frame contact surface bears against the at least one door contact surface such that the frame and door contact surfaces transfer radial stresses from the door to the fuselage.