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eBook Prediction of Pilot-Induced Oscillations (PIO) Due to Actuator Rate Limiting Using the Open-Loop Onset Point (OLOP) Criterion download
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Author: Gregory P. Gilbreath
ISBN: 1423530578
Publisher Storming Media (2001)
Language English
Category: No category
Rating: 4.1
Votes: 444
ePUB size: 1218 kb
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eBook Prediction of Pilot-Induced Oscillations (PIO) Due to Actuator Rate Limiting Using the Open-Loop Onset Point (OLOP) Criterion download

by Gregory P. Gilbreath


The main cause of the roll PIO was due to unexpected large pilot input and to increased delay of the aircraft response by its large pilot input.

The main cause of the roll PIO was due to unexpected large pilot input and to increased delay of the aircraft response by its large pilot input. The delay of roll response has much difference between with large input and with small input. That is why the flight control system falls into nonlinear system by actuator rate limit in case of controlling the aircraft with large pilot input. This paper shows analysis of the characteristics of the PIO and its improvement.

Actuator rate limiting has been a causal or contributing factor for Pilot Induced . has been added to your Cart.

Actuator rate limiting has been a causal or contributing factor for Pilot Induced Oscillations (PIO) experienced on highly augmented fighter aircraft. As part of the joint Air Force Institute of Technology-Test Pilot School (AFIT-TPS) program. Then you can start reading Kindle books on your smartphone, tablet, or computer - no Kindle device required.

Rate limiting has been a causal or contributing factor for Pilot Induced Oscillations (PIO). As part of the joint Air Force Institute of Technology/Test Pilot School (AFIT/TPS) program, an examination of the Open-Loop Onset Point (OLOP) criterion, developed by DLR German Aerospace, was conducted to see if it could predict PIO due to rate limiting and to evaluate its potential as a design tool. The criterion was applied to three previous flight test programs involving rate limiting

Prediction of Pilot-in-the-Loop Oscillations Due to Rate Saturation. A new design criterion considering the nonlinear effects of rate limiting is described. The criterion is based on the ‘open loop onset point’ (OLOP) of the rate limiter in a Nichols chart.

Prediction of Pilot-in-the-Loop Oscillations Due to Rate Saturation. J GUID control dynam. The background for the development, and the verification of the OLOP-criterion are presented briefly. The flight control system parameters of a basically unstable aircraft are optimised with respect to the linear design criteria and the OLOP-criterion.

possible pilot-induced oscillations of Category II (with rate and position . Application to actuator rate limiting examples shows intuitive correlation.

possible pilot-induced oscillations of Category II (with rate and position limiting), a phenomenon. usually due to a misadaptation between the pilot and the aircraft response during some tasks in which. tight closed loop control of the aircraft is required from the pilot. For the analysis of Pilot in the Loop. investigated over the last years: Open Loop Onset Point (OLOP) method with a. modified/enhanced version, derived from the describing function method, Robust. Stability Analysis Methods,, also considered in this paper, Time Domain Neal.

Prediction of PIO due to actuator rate limiting using the open-loop onset point (OLOP) criterion

Prediction of PIO due to actuator rate limiting using the open-loop onset point (OLOP) criterion. Msc Thesis, Department of Aeronautics and Astronautics, AirForce Institute of Technology, Ohio, USA (2001)Google Scholar. Liu, . ation detection and mitigation. Thesis, Cranfield University (2012)Google Scholar. 22. Puyou, . Biannic, . M. Boada-Bauxell, . Application of robust antiwindup design to the longitudinal aircraft control to cover actuator loss. In: 19th IFAC Symposium on Automatic Control in Aerospace, University of Wurzburg, W’́urzburg, September 2013Google Scholar.

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Prediction of Pilot-Induced Oscillations (PIO) Due to Actuator Rate Limiting Using the Open-Loop Onset Point (OLOP) Criterion. Gregory P. Gilbreath. Abstract : Rate limiting has been a causal or contributing factor for Pilot Induced Oscillations (PIO). As part of the joint Air Force Institute of Technology/Test Pilot School (AFIT/TPS) program, a. More). The Allen Institute for AIProudly built by AI2 with the help of our.

Two Pilot Models were examined for use with OLOP: the recommended pure gai. ONTINUE READING.

A pilot induced oscillation (PIO) is a complex interaction between the human pilot and the aircraft that leads to sustained and .

A pilot induced oscillation (PIO) is a complex interaction between the human pilot and the aircraft that leads to sustained and sometimes very large amplitude oscillations of the aircraft. It is characterized by a loss of stability margin in the pilot-aircraft closed loop system. These oscillations can occur about any of the aircraft axes of symmetry. The potential occurrence of PIO is amplified by the use of modern control technology including fly-by-wire systems that determine important modification of the airplane response characteristics. For example in heavy aircrafts, the problems result in a faster roll rate than normally expected.

This is a AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH report procured by the Pentagon and made available for public release. It has been reproduced in the best form available to the Pentagon. It is not spiral-bound, but rather assembled with Velobinding in a soft, white linen cover. The Storming Media report number is A861093. The abstract provided by the Pentagon follows: Rate limiting has been a causal or contributing factor for Pilot Induced Oscillations (PIO). As part of the joint Air Force Institute of Technology/Test Pilot School (AFIT/TPS) program, an examination of the Open-Loop Onset Point (OLOP) criterion, developed by DLR German Aerospace, was conducted to see if it could predict PIO due to rate limiting and to evaluate its potential as a design tool. The criterion was applied to three previous flight test programs involving rate limiting. Findings from this analysis led to the HAVE OLOP flight test which was flown on the NF-16D Variable Stability In-flight Simulator Test Aircraft (VISTA). HAVE OLOP evaluated four longitudinal configurations with rate limiting elements inside the feedback loop. OLOP was found to over-predict PIO in some cases when using maximum stick amplitude as DLR suggests. When using actual stick amplitudes, correlation between OLOP predictions and PIO ratings was good. A new metric called stick ratio was developed to help explore the full range of stick amplitudes when using OLOP. OLOP could be a useful design tool, but because of the strong influence of stick amplitude, engineering judgement would have to be exercised. Recommendations on its use as a design tool are presented.