Accession Number:

AD0671661

Title:

IN-FLIGHT MEASUREMENT OF ROTOR BLADE AIRLOADS, BENDING MOMENTS, AND MOTIONS, TOGETHER WITH ROTOR SHAFT LOADS AND FUSELAGE VIBRATION, ON A TANDEM ROTOR HELICOPTER. VOLUME 2. CALIBRATIONS AND INSTRUMENTED COMPONENT TESTING

Descriptive Note:

Final rept.

Corporate Author:

BOEING CO MORTON PA VERTOL DIV

Personal Author(s):

Report Date:

1967-05-01

Pagination or Media Count:

135.0

Abstract:

Calibration and instrumented component testing were performed to provide reliable instrumentation for the measurement of dynamic airloads on a large tandem rotor helicopter. All equipment underwent single-load calibration and much of it was calibrated for combined loads. Blade tension instrumentation was calibrated by whirl testing. The combined-loads calibrations represent an extension of the state of the art, especially for elastic structures such as rotor blades. All calibrations were evaluated qualitatively and a summary of the quality of all calibrations is presented. The general error in all calibrations is less than 3 percent. Component testing consisted of whirl tests and dynamic response tests of the rotor blades, and functional testing of the airloads pressure transducers. These tests determined the structural integrity of the blade instrumentation and provided references for isolating the effects of such factors as blade bending, acceleration, and temperature.

Subject Categories:

  • Aerodynamics
  • Helicopters
  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE