Pilot Induced Oscillation Suppression Methods And Their Effects On Large Transport Aircraft Handling Qualities PDF Download
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Author | : R. van der Weerd |
Publisher | : IOS Press |
Total Pages | : 176 |
Release | : 2000 |
Genre | : Technology & Engineering |
ISBN | : |
Download Pilot-induced Oscillation Suppression Methods and Their Effects on Large Transport Aircraft Handling Qualities Book in PDF, ePub and Kindle
Author | : J. De Jong |
Publisher | : Delft University Press |
Total Pages | : 155 |
Release | : 2000-01-01 |
Genre | : |
ISBN | : 9789040720949 |
Download Pilot-Induced Oscillation Suppression Methods and Their Effects on Large Transport Aircraft Handling Qualities Book in PDF, ePub and Kindle
Author | : Flight Research Center (U.S.) |
Publisher | : |
Total Pages | : 52 |
Release | : 1975 |
Genre | : Airplanes |
ISBN | : |
Download Analysis of Longitudinal Pilot-induced Oscillation Tendencies of YF-12 Aircraft Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 192 |
Release | : 2001 |
Genre | : |
ISBN | : |
Download Pilot-Induced Oscillation Research: The Status at the End of the Century Book in PDF, ePub and Kindle
Author | : James G. Hanley |
Publisher | : |
Total Pages | : 107 |
Release | : 2003-03 |
Genre | : Air pilots, Military |
ISBN | : 9781423504085 |
Download A Comparison of Nonlinear Algorithms to Prevent Pilot-Induced Oscillations Caused by Actuator Rate Limiting Book in PDF, ePub and Kindle
The objective of this study was to compare the ability of the Feedback-with-Bypass (FWB) and the Derivative-Switching (DS) flight control system filters to prevent PIO during actuator rate limiting, and the filters' effects on aircraft handling qualities. This comparison was conducted in three steps: computer simulation, ground simulation in the Large Amplitude Multimode Aerospace Research Simulator (LAMARS), and flight tests conducted in the Variable Stability In-flight Simulator Test Aircraft (VISTA). During computer simulation, the FWB filter better reduced the phase lag and prevented sustained or divergent oscillations during the closed-loop analysis. During both ground simulation and flight tests, the FWB filter was more effective at preventing divergent PIO and improving handling qualities. Overall the FWB filter performed better during all tests.
Author | : |
Publisher | : |
Total Pages | : 152 |
Release | : 2001 |
Genre | : |
ISBN | : |
Download Pilot-Induced Oscillation Research: Status at the End of the Century Book in PDF, ePub and Kindle
Author | : Donald A. Johnson |
Publisher | : |
Total Pages | : 203 |
Release | : 2002-03-01 |
Genre | : Airplanes |
ISBN | : 9781423512158 |
Download Suppression of Pilot-Induced Oscillation (PIO) Book in PDF, ePub and Kindle
Closed loop instability caused by excess phase lag induced by actuator rate limiting has been suspected in many pilot-induced oscillations (PIOs) and oscillatory departures from controlled flight. As part of the joint AFIT/TPS program, a longitudinal pilot command notch filter activated by a real- time oscillation verifier (ROVER) algorithm was developed to eliminate the PIO source for any developing, severe PIO. Closed loop computer simulations were conducted to prepare for the flight test. The HAVE ROVER flight test project was flown using the NF-16D Variable Stability In-flight Simulator Test Aircraft (VISTA). A programmable heads-up display (HUD) was used to generate a tracking task simulating Category A fighter maneuvers. 6 of the 12 evaluation sorties were flown against an airborne target aircraft. Flight test results showed the stick filter was pivotal in preventing aircraft oscillatory departures and suppressing PIOs. With the original threshold settings, the ROVER algorithm correctly characterized pilot observations of the aircraft motion 72% of the time. Further analysis indicated that a high false detection rate was responsible for this relatively low correct detection rate. These results suggested that the threshold values used by ROVER to detect PIO were set too low. By varying the threshold values as part of a parametric study, a maximum overall correct detection rate of 82% was attained.
Author | : National Research Council |
Publisher | : National Academies Press |
Total Pages | : 221 |
Release | : 1997-03-28 |
Genre | : Transportation |
ISBN | : 0309056888 |
Download Aviation Safety and Pilot Control Book in PDF, ePub and Kindle
Adverse aircraft-pilot coupling (APC) events include a broad set of undesirable and sometimes hazardous phenomena that originate in anomalous interactions between pilots and aircraft. As civil and military aircraft technologies advance, interactions between pilots and aircraft are becoming more complex. Recent accidents and other incidents have been attributed to adverse APC in military aircraft. In addition, APC has been implicated in some civilian incidents. This book evaluates the current state of knowledge about adverse APC and processes that may be used to eliminate it from military and commercial aircraft. It was written for technical, government, and administrative decisionmakers and their technical and administrative support staffs; key technical managers in the aircraft manufacturing and operational industries; stability and control engineers; aircraft flight control system designers; research specialists in flight control, flying qualities, human factors; and technically knowledgeable lay readers.
Author | : |
Publisher | : |
Total Pages | : 702 |
Release | : 1995 |
Genre | : Aeronautics |
ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
Author | : Patrick J. Peters |
Publisher | : |
Total Pages | : 147 |
Release | : 1997-03-01 |
Genre | : Airplanes |
ISBN | : 9781423567370 |
Download The Effects of Elevator Rate Limiting and Stick Dynamics on Longitudinal Pilot-Induced Oscillations Book in PDF, ePub and Kindle
This report presents the results of an investigation into the effects of elevator rate limiting and stick dynamics on longitudinal pilot-induced oscillations (PIO). A simulation study was conducted to prepare for the flight test, but also to gain insight into the effects of rate limiting and stick dynamics. Due to the non-numerical nature of the simulation results, a flexible three-phase flight test plan was developed, first varying the rate limits, then varying the stick dynamics, and finally flying a matrix determined in the first two phases. There were three major conclusions. First, the offset landing task flown was insufficient to consistently uncover handling qualities deficiencies of the aircraft configuration flown. Second, rate limiting did not necessarily cause PIOs. At very low rate limits the problem was lack of pitch response, not PIO. Any oscillations were very low frequency and small in amplitude. Third, for this configuration and task, variations in stick spring constant and natural frequency had negligible effect on the performance of the system with respect to assigned PIO and Cooper-Harper ratings. These conclusions are specific to this system and may not apply to all aircraft, especially aircraft where PIO tendencies are driven by much higher rate limits.