Pitch drop-back is the phenomena by which an aircraft which is perturbed in flight path angle from its trim position by a step input exhibits an output which is indicative of a second order system.[1]

A pilot who actuates an elevator input may find that the aircraft then "droops" or "drops back" to a position further toward the start position. The phenomenon is particularly marked in tilt-rotor aircraft.[2] Pitch drop-back may be controlled using a Stability Augmentation System or Stability Control and Augmentation System.[3]

See also

References

  1. ↑ "Longitudinal stability and control of large tilt-rotor aircraft". IFAC-PapersOnLine. 2008-10-17. Retrieved 2010-10-05.
  2. ↑ Mark Voskuijl, Daniel J. Walker. "Active Control of Flight Path and Critical Loads in Tilt-Rotor Aircraft" (PDF). Engineering Department: University of Liverpool. Retrieved 5 October 2010.
  3. ↑ "Measuring Simulation Fidelity through an Adaptive Pilot Model" (PDF). Retrieved 2010-10-05.


This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.