Detail publikace

Possibilities and methods of in-flight loading measurement

Originální název

Possibilities and methods of in-flight loading measurement

Anglický název

Possibilities and methods of in-flight loading measurement

Jazyk

en

Originální abstrakt

This article provides information about in-flight measurement of a small sport aircraft. Firstly the strain gauges were installed into the wing structure and then the calibration procedures were done. After the calculation of strain gauge coefficients the equations for calculating of bending moments and other variables were established. The data acquisition system was installed into the aircraft for measurement responses from strain gauges and other variables as speed, altitude, load factor and temperature. Many flights were performed with this way equipped aircraft and after that the recorded data were analyzed and those results were compared with the calculation and with the static strength tests performed before.

Anglický abstrakt

This article provides information about in-flight measurement of a small sport aircraft. Firstly the strain gauges were installed into the wing structure and then the calibration procedures were done. After the calculation of strain gauge coefficients the equations for calculating of bending moments and other variables were established. The data acquisition system was installed into the aircraft for measurement responses from strain gauges and other variables as speed, altitude, load factor and temperature. Many flights were performed with this way equipped aircraft and after that the recorded data were analyzed and those results were compared with the calculation and with the static strength tests performed before.

Dokumenty

BibTex


@article{BUT94474,
  author="Ivo {Jebáček} and Marek {Horák}",
  title="Possibilities and methods of in-flight loading measurement",
  annote="This article provides information about in-flight measurement of a small sport aircraft. Firstly the
strain gauges were installed into the wing structure and then the calibration procedures were done.
After the calculation of strain gauge coefficients the equations for calculating of bending moments and
other variables were established.
The data acquisition system was installed into the aircraft for measurement responses from strain
gauges and other variables as speed, altitude, load factor and temperature. Many flights were
performed with this way equipped aircraft and after that the recorded data were analyzed and those
results were compared with the calculation and with the static strength tests performed before.",
  address="Vilnius Gediminas Technical University",
  chapter="94474",
  institution="Vilnius Gediminas Technical University",
  number="2",
  volume="16",
  year="2012",
  month="june",
  pages="47--50",
  publisher="Vilnius Gediminas Technical University",
  type="journal article - other"
}