Flight test hinge assembly configured for calculating exerted forces through strain analysis

A test hinge assembly configured to detect one or more forces exerted into an aircraft component, wherein the test hinge assembly is configured to be secured to the aircraft component, and wherein the test hinge assembly is separate and distinct from the aircraft component, the test hinge assembly comprising:

• at least one beam, wherein the at least one beam comprises:
• a cross beam connected to an extension beam through a first connecting joint;
• and a diagonal beam connected to the extension beam through a second connecting joint and connected to the cross beam through a third connecting joint, wherein the cross beam, the extension beam, and the diagonal beam are fixedly joined together;
• at least one of the first connecting joint, the second connecting joint, and the third connecting joint having a channel configured to receive and retain a fastening member, and configured to connect the test hinge assembly to at least a moveable portion of an aircraft component;
• and
• at least one strain gage secured to an outer surface of the at least one beam, wherein the at least one strain gage is configured to detect one or more strains exerted into the at least one beam.

A system for calculating forces exerted into an aircraft component, the system comprising:

• a test hinge assembly secured to the aircraft component, wherein the test hinge assembly is separate and distinct from the aircraft component, the test hinge assembly including:
• a cross beam connected to an extension beam through a first connecting joint having a first channel configured to receive and retain a first fastening member;
• a diagonal beam connected to the extension beam through a second connecting joint having a second channel configured to receive and retain a second fastening member, and wherein the diagonal beam is connected to the cross beam through a third connecting joint having a third channel configured to receive and retain a third fastening member, wherein the cross beam, the extension beam, and the diagonal beam are fixedly joined together;
• a first strain gage secured to an outer surface of the cross beam, wherein the first strain gage is configured to detect first strains exerted into the cross beam;
• and
• a second strain gage secured to an outer surface of the diagonal beam, wherein the second strain gage is configured to detect second strains exerted into the diagonal beam;
• and
• a monitoring system in communication with the first and second strain gages, wherein the monitoring system is configured to calculate forces exerted into at least one of the fastening members by analyzing the first and second strains.