The FWB Filter with Real-Time Detector to Suppress Category II Pilot Induced Oscillation

Article Preview

Abstract:

PIO (Pilot Induced Oscillation) is the key factor to damage the flight safety and decrease the quality of manned aircraft. Most of modern PIO records associating with rate limiting or position limiting from actuation systems are defined Category II PIO. The existing compensators, e.g. the Feedback-with-Bypass (FWB) filter, can reduced the oscillation potentiality of the pilot-in-the-loop aircraft system due to rate limiting of control surface, however a negative effect evidently arose which slow the response speed of whole system. This paper uses a Real-Time PIO detector based on Short-time Fourier Transform algorithm as a trigger to determine the switch-off time of the compensator working on the whole system so as to suppress the negative effect on responses of system by FWB. Simulation results show us the positive conclusion that this kind combined FWB filter with Real-Time PIO detector is effectively preventing the Category II PIO without performance decreasing.

You might also be interested in these eBooks

Info:

Periodical:

Pages:

1713-1718

Citation:

Online since:

January 2013

Export:

Price:

Permissions CCC:

Permissions PLS:

Сopyright:

© 2013 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

[1] Dornheim, M.A., Report Pinpoints Factors Leading to YF-22 Crash, Aviation Week & Space Technology, 9 Nov. (1992), pp.53-54.

Google Scholar

[2] Rundqwist, L., Hillgren, R., Phase Compensation of Rate Limiters in JAS 39 Gripen, AIAA Atmospheric Flight Mechanics Conference and Exhibit, AIAA-96-3368, San Diego, (1996).

DOI: 10.2514/6.1996-3368

Google Scholar

[3] Department of Defense. Flying Qualities of Piloted Aircraft. MIL-HDBK-1797. Washington: GPO, 19 December (1997).

Google Scholar

[4] Mitchell, David G. and Roger H. Hoh. Development of a Unified Method to Predict Tendencies fot Pilot-Induced Oscillations. WL-TR-95-3049. Air Force Research Laboratories, Wright-Patterson AFB OH, June (1995).

Google Scholar

[5] David G. Mitchell, Alfredo J. Arencibia. Real-Time Detection of Pilot-Induced Oscillations. AIAA Atmospheric Flight Mechanics Conference and Exhibit. August (2004).

DOI: 10.2514/6.2004-4700

Google Scholar

[6] Chalk, C.R., Calspan Presentation of PIO and the Dffects of Rate Limiting, Flight Vehicle Integration Panel Workshop on Pilot Induced Oscillations, Advisory Group for Aerospace Research & Development, AGARD-AR-335, Feb. (1995), pp.12-1—12-12.

Google Scholar

[7] Klyde, David H. and others. Unified Pilot-Induced Oscillation Theory, Volume 1: PIO Analysis with Linear and Nonlinear Effective Vehicle Characteristics, Including Rate Limiting. WL-TR-96-3028. Air Force Research Laboratories, Wright-Patterson AFB OH, December (1995).

Google Scholar

[8] Michael J. Chapa, Captain, USAF. A Nonlinear Pre-filter to Prevent Departure and/or Pilot Induced Oscillations (PIO) due to Actuator Rate Limiting. Air Force Institute of Technology, (1999).

Google Scholar

[9] Robert Bruce Alstrom, Erik Bollt, Pier Marzocca, Goodarz Ahmadi. The Application of Nonlinear Pre-Filters to prevent Aeroservoelastic Interactions due to Actuator Rate Limiting. 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 23-26 April (2012).

DOI: 10.2514/6.2012-1483

Google Scholar

[10] James G. Hanley, Major, USAF. AComparison of Nonlinear Algorithms to Prevent Pilot-Induced Oscillations caused by Actoator Rate Limiting. AFIT/GAE/ENY/03-4. (2003).

Google Scholar

[11] Fuli TIAN, Zhenghong GAO, Zhigang YU. Determination of Control Characteristic for Detecting the Aircraft Pilot Coupling. Flight Dynamics. Vol. 23 No. 2 June (2005).

Google Scholar