FLIGHT TEST HINGE ASSEMBLY

A system for calculating forces exerted into an aircraft component (12) may include a test hinge assembly (10) and a monitoring system (18). The test hinge assembly (10) may be a triangular shaped assembly, and may include at least one beam 22, 24, 28, at least one connecting joint 26, 34, 42 having...

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Bibliographic Details
Main Authors WILLIAMS, JAMES A, OELKE, BRIAN S, DICKERSON, MATT R, JOHNSON, ROBERT, AMINZADEH, SHAHZAD
Format Patent
LanguageEnglish
French
German
Published 13.01.2016
Subjects
MEASURING
MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER,MECHANICAL EFFICIENCY, OR FLUID PRESSURE
PHYSICS
TESTING
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Summary:A system for calculating forces exerted into an aircraft component (12) may include a test hinge assembly (10) and a monitoring system (18). The test hinge assembly (10) may be a triangular shaped assembly, and may include at least one beam 22, 24, 28, at least one connecting joint 26, 34, 42 having a channel (46, 48, 50) configured to receive and retain a fastening member, and at least one strain gage (60) secured to an outer surface of the beam(s) (22, 24, 28). The strain gage(s) (60) is configured to detect one or more strains exerted into the beam(s) (22, 24, 28). The monitoring system (18) is in communication with the strain gage(s) (60). The monitoring system (18) may be configured to calculate forces exerted into the fastening member(s) by analyzing the strain(s) (60) exerted into the beam(s) (22, 24, 28).
Bibliography:Application Number: EP20150174392