A system for calculating forces exerted into an aircraft component may include a test hinge assembly and a monitoring system. The test hinge assembly may be a triangular shaped assembly, and may include at least one beam, at least one connecting joint having a channel configured to receive and retain a fastening member, and at least one strain gage secured to an outer surface of the beam(s). The strain gage(s) is configured to detect one or more strains exerted into the beam(s). The monitoring system is in communication with the strain gage(s). The monitoring system may be configured to calculate forces exerted into the fastening member(s) by analyzing the strain(s) exerted into the beam(s).
FLIGHT TEST HINGE ASSEMBLY
30.06.2016
Patent
Elektronische Ressource
Englisch
IPC: | G01L Messen von Kraft, mechanischer Spannung, Drehmoment, Arbeit, mechanischer Leistung, mechanischem Wirkungsgrad oder des Drucks von Fluiden , MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
Flight test hinge assembly configured for calculating exerted forces through strain analysis
Europäisches Patentamt | 2017
|AIAA | 1991
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