Patent ID: 8033500
Filing Date: 2011-10-11
Classification: B64C

Abstract:
1. An actuator system for an aircraft of a type having a primary aircraft structure, a secondary aircraft structure and a control surface positionable relative to said primary and secondary aircraft structures, the load path between the primary and secondary aircraft structure and the control surface defining a dual load path, said actuator system, comprising: a) an upper actuator assembly, comprising: b) a ball screw assembly operatively connected to said gear assembly, said ball screw assembly, comprising: c) a tie-rod assembly positioned within said ball screw assembly, said tie-rod assembly having an upper end securely attached to said upper load sensing assembly, wherein said upper load sensing assembly defines an upper portion of a secondary load path of a dual load path between the secondary aircraft structure and a control surface, said dual load path including a primary load path acting and reacting the applied aerodynamic load to the control surface and said secondary load path in a stand-by, unloaded mode, said upper load sensing assembly providing upper indications of the applied forces in said upper portion of said secondary load path when an upper portion of the primary load path is disconnected; d) a lower actuator assembly, comprising: e) a computer system for receiving said upper and lower indications of applied forces and analyzing said upper and lower indications, thereby monitoring the structural integrity and safety of said dual load path by annunciating the detection of a failed portion thereof.