Structural Testing of an Ultralight UAV Composite Wing Conference Paper uri icon

abstract

  • This paper describes the design and implementation of a series of experiments to measure the static response and vibration characteristics of a composite wing of an ultralight UAV. All structural components are made of laminated carbon composite materials with uniaxial and biaxial prepreg fabrics. A shaker-table approach is used for the vibration testing. A specially designed track system is used to shake the wing to induce lateral, chordwise or torsional oscillation. Ten dual-axis accelerometers provide information on the wing's dynamic characteristics. Using the swept sine technique, g-load data is obtained for a range of desired frequencies. A whiffletree loading mechanism is designed and used for the static testing. Each wing is instrumented with forty-five strain gages as well as four deflection gages at critical locations. The results of vibration and static tests are presented and discussed.

name of conference

  • 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
    14th AIAA/ASME/AHS Adaptive Structures Conference
    7th

published proceedings

  • 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
    14th AIAA/ASME/AHS Adaptive Structures Conference
    7th

author list (cited authors)

  • Sullivan, R., Rais-Rohani, M., Lacy, T., & Alday, N.

citation count

  • 10

complete list of authors

  • Sullivan, Rani||Rais-Rohani, Masoud||Lacy, Thomas||Alday, Nathan

publication date

  • May 2006