A Flight Load Test Method for Helicopter Rotor Blade

This paper studies a flight load test method for helicopter blade, including the structural force of strain gauge bridge modification, calibration and establishment equation in typical maneuvers. First, blade structure was analyzed gauges were pasted profile which considered to be important positions analysis safe helicopter. Second, Load equations obtained by ground test, would used convert time curve curve. The flighted different maneuvers, such as hovering, horizontal climbing. At same time, parameters recorded, altitude, pitch angle, roll angle yaw Angle. can conditions. Then maneuvers analyzed. result that time-domain waveform neat, good periodicity, strong regularity, no hybrid interference jump point. It illustrated data accurate reliable, met accuracy requirements Engineering. through fatigue design.