초록 ▼

An actuator load path monitoring system for an aircraft having an aircraft structure, a control surface, and, an actuator connected between the aircraft structure and the control surface to support and position the control surface as desired relative to the aircraft structure. The actuator is of a t

An actuator load path monitoring system for an aircraft having an aircraft structure, a control surface, and, an actuator connected between the aircraft structure and the control surface to support and position the control surface as desired relative to the aircraft structure. The actuator is of a type including a) an upper actuator assembly securely connected to the aircraft structure, including a motor assembly and gear assembly; b) a ball screw assembly operatively connected to the gear assembly; c) a tie-rod assembly positioned within the ball screw assembly; and, d) a lower actuator assembly securely connected to the control surface, wherein actuation of the ball screw provides selected positioning of the control surface. The actuator load path monitoring system includes an upper load sensing assembly positioned in an upper load path between the upper actuator assembly and the aircraft structure. The upper load sensing assembly provides upper indications of the applied forces in the upper load path when the upper load path is disconnected. A lower load sensing assembly is positioned in a lower load path between the lower actuator assembly and the control surface. The lower load sensing assembly provides upper indications of the applied forces in the lower load path when the lower load path is disconnected. A computer system receives the upper and lower indications of applied forces and analyzes the upper and lower indications, thereby monitoring the structural integrity and safety of the upper and lower load paths by annunciating the detection of a failed portion thereof.

대표청구항 ▼

The invention claimed is: 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 struct

The invention claimed is: 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:i. an upper actuator assembly housing;ii. a gear assembly supported by said upper actuator assembly housing;iii. a motor assembly operatively associated with said gear assembly;iv. an upper primary gimbal assembly mounted to said upper actuator assembly housing, said upper primary gimbal assembly being securely connected to a primary aircraft structure; and,v. an upper load sensing assembly securely attached to a secondary aircraft structure;b) a ball screw assembly operatively connected to said gear assembly, said ball screw assembly, comprising:i. a ball screw;ii. a ball nut assembly translatable along said ball screw; and,iii. a secondary inverted thread nut in an unloaded standby mode operatively positioned about said ball nut assembly;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:i. a lower primary gimbal assembly operatively connected to said ball screw assembly, defining a lower portion of the primary load path;ii. a lower secondary gimbal assembly positioned about said lower primary gimbal assembly and securely connected to the control surface;iii. a yoke assembly operatively connected to said secondary inverted thread nut and to said lower secondary gimbal assembly; and,iv. a lower load sensing assembly securely attached to said yoke assembly for providing said operative connection between said yoke assembly and said lower secondary gimbal assembly, wherein,1. a lower portion of said primary load path is defined by the load from said ball screw to said ball nut assembly to said lower primary gimbal assembly to said control surface;2. a lower portion of said secondary load path is defined by the load from said ball screw to said secondary inverted thread nut to said yoke assembly to said lower load sensing assembly to said lower secondary gimbal assembly to said control surface; and,3. said lower load sensing assembly provides lower indications of the applied forces in said lower portion of said secondary load path when the lower portion of said primary load path is disconnected; and,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.