公开(公告)号：US20190300145A1

公开(公告)日：2019-10-03

申请号：US16367343

申请日：2019-03-28

申请人： BOMBARDIER INC.

发明人： Menahem BENDAYAN

IPC分类号： B64C5/16 ,  B64C5/08

摘要： An airfoil assembly for an aircraft includes an airfoil body having an internal frame and a skin covering the internal frame to define a cavity of the airfoil body. The airfoil body defines a span between a root and a tip and is deflectable in a deflection direction transverse to the span upon experiencing aerodynamic loading. At least one shaft is attached to the airfoil body and disposed within the cavity adjacent to an inner surface of the skin. The shaft extends along at least part of the span. A shaft measuring device is mounted to the airfoil body within the cavity. The shaft measuring device operates to measure a parameter of the shaft caused by deflection of the airfoil body such that the parameter is indicative of the aerodynamic loading on the airfoil body. A method for determining aerodynamic loading on an airfoil body is also disclosed.