System to measure unsteady signals (AMIS III)


Measured values

  • Voltage
  • Pressure
  • Force
  • Acceleration

Description of facility

Facility is in service since 2008. It is used to measure voltage signals and to control test procedures (mobile operation world-wide possible). Ground based operation and in-flight operation possible (permission for DLR-ATRA A320).

  • 24bit delta-sigma A/D-converter with 512-times oversampling
  • 204,8MHz sampling frequency per channel
  • 1000 synchronized channels
  • 200 ksamples/second/channel continuously data throughput
  • Unlimited measurement time
  • Signal-to-noise ratio 108 dB
  • Channel separation 120dB @10kHz, 105dB @ 50kHz
  • Analogue low-pass filter 86 dB decrease at nyquist frequency
  • 0.001 dB peak-ripple factor in the passband
  • Realtime visualization of preprocessed data for control of test procedure (e.g. cp(x), cl, cd, cm)
  • Synchronisation of all Channels by internal or external link, GPS or IRIG-B
  • Input for synchronization by clock and 0° phase
  • Software trigger
  • Output for synchronization on measurement start/stop
  • Output of real time sampling clock

Located at DLR Göttingen/Germany


  • Measurement of unsteady pressure distributions at helicopter models in DNW-LLF
  • Measurement of unsteady pressures, accelerations and forces in wind tunnel tests at:
    • Helicopter models
    • Transport aircraft wings
    • Wind energy converters
    • Building models
  • Measurement of unsteady acoustic signals in flight tests

Literature / References

  • Hebler, A. and Thormann, R.: Flutter Prediction of a Laminar Airfoil Using a Doublet Lattice Method Corrected by Experimental Data, Notes on Numerical Fluid Mechanics and Multidisciplinary Design Vol. 132, pp. 445-455 (2016)
  • Lütke, B., Nuhn, J., Govers, Y. and Schmidt, M.: Design of a Rotor Blade Tip for the Investigation of Dynamic Stall in the Transsonic Wind Tunnel Göttingen, The Aeronautical Journal (RAE) Vol. 120, No. 1223, pp. 123-456 (2016)
  • Wiggen, S.: Unsteady pressure distributions at the wind tunnel model of a pitching Lambda wing with development of vortical flow, Aerospace Scienence and Technology Vol 47, pp. 396-405 (2015)
  • Lübker, J.: Experimental Investigations on dynamic aeroelastic Stability of Panels in the Transonic Domain, 14th European Conference on Space Structures, Materials, and Environmental Testing, Sep., 27th-30th, Toulouse, France (2016)

Institute / Organization

DLR Institute for Aeroelasticity


Dr.rer.nat. Holger Mai
DLR Institute for Aeroelasticity

Dr. Frank Holtmann
Technology Marketing

Similar Measures

Subsequent references to data sheets are given which describe with high probability similar measured values. The selection is made on the basis of semantic affinity:

Voltage :: more

Pressure :: more

Force :: more

Acceleration :: more