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Prediction Of Pilot Induced Oscillations Pio Due To Actuator Rate Limiting Using The Open Loop Onset Point Olop Criterion
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Book Synopsis Prediction of Pilot-Induced Oscillations (PIO) Due to Actuator Rate Limiting Using the Open-Loop Onset Point (OLOP) Criterion by : Gregory P. Gilbreath
Download or read book Prediction of Pilot-Induced Oscillations (PIO) Due to Actuator Rate Limiting Using the Open-Loop Onset Point (OLOP) Criterion written by Gregory P. Gilbreath and published by . This book was released on 2001-03-01 with total page 169 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Prediction of Pilot-induced Oscillations (PIO) Due to Actuator Rate Limiting Using the Open-loop Onset Point (OLOP) by : Gregory P. Gilbreath
Download or read book Prediction of Pilot-induced Oscillations (PIO) Due to Actuator Rate Limiting Using the Open-loop Onset Point (OLOP) written by Gregory P. Gilbreath and published by . This book was released on 2001 with total page 169 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Space Engineering by : Giorgio Fasano
Download or read book Space Engineering written by Giorgio Fasano and published by Springer. This book was released on 2016-12-31 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book presents a selection of advanced case studies that cover a substantial range of issues and real-world challenges and applications in space engineering. Vital mathematical modeling, optimization methodologies and numerical solution aspects of each application case study are presented in detail, with discussions of a range of advanced model development and solution techniques and tools. Space engineering challenges are discussed in the following contexts: •Advanced Space Vehicle Design •Computation of Optimal Low Thrust Transfers •Indirect Optimization of Spacecraft Trajectories •Resource-Constrained Scheduling, •Packing Problems in Space •Design of Complex Interplanetary Trajectories •Satellite Constellation Image Acquisition •Re-entry Test Vehicle Configuration Selection •Collision Risk Assessment on Perturbed Orbits •Optimal Robust Design of Hybrid Rocket Engines •Nonlinear Regression Analysis in Space Engineering •Regression-Based Sensitivity Analysis and Robust Design •Low-Thrust Multi-Revolution Orbit Transfers •Modeling and Optimization of Balance Layout Problems •Pilot-Induced Oscillations Alleviation •Modeling and Optimization of Hybrid Transfers to Near-Earth Objects •Probabilistic Safety Analysis of the Collision Between Space Debris and Satellite •Flatness-based Low-thrust Trajectory Optimization for Spacecraft Proximity Operations The contributing authors are expert researchers and practitioners in either the space engineering and/or in the applied optimization fields. Researchers and practitioners working in various applied aspects of space engineering will find this book practical and informative. Academics, graduate and post-graduate students in aerospace engineering, applied mathematics, operations research, optimization, and optimal control, will find this book useful.
Book Synopsis Model-Reference Adaptive Control by : Nhan T. Nguyen
Download or read book Model-Reference Adaptive Control written by Nhan T. Nguyen and published by Springer. This book was released on 2018-03-01 with total page 453 pages. Available in PDF, EPUB and Kindle. Book excerpt: This textbook provides readers with a good working knowledge of adaptive control theory through applications. It is intended for students beginning masters or doctoral courses, and control practitioners wishing to get up to speed in the subject expeditiously. Readers are taught a wide variety of adaptive control techniques starting with simple methods and extending step-by-step to more complex ones. Stability proofs are provided for all adaptive control techniques without obfuscating reader understanding with excessive mathematics. The book begins with standard model-reference adaptive control (MRAC) for first-order, second-order, and multi-input, multi-output systems. Treatment of least-squares parameter estimation and its extension to MRAC follow, helping readers to gain a different perspective on MRAC. Function approximation with orthogonal polynomials and neural networks, and MRAC using neural networks are also covered. Robustness issues connected with MRAC are discussed, helping the student to appreciate potential pitfalls of the technique. This appreciation is encouraged by drawing parallels between various aspects of robustness and linear time-invariant systems wherever relevant. Following on from the robustness problems is material covering robust adaptive control including standard methods and detailed exposition of recent advances, in particular, the author’s work on optimal control modification. Interesting properties of the new method are illustrated in the design of adaptive systems to meet stability margins. This method has been successfully flight-tested on research aircraft, one of various flight-control applications detailed towards the end of the book along with a hybrid adaptive flight control architecture that combines direct MRAC with least-squares indirect adaptive control. In addition to the applications, understanding is encouraged by the use of end-of-chapter exercises and associated MATLAB® files. Readers will need no more than the standard mathematics for basic control theory such as differential equations and matrix algebra; the book covers the foundations of MRAC and the necessary mathematical preliminaries.
Book Synopsis In-Flight Simulators and Fly-by-Wire/Light Demonstrators by : Peter G. Hamel
Download or read book In-Flight Simulators and Fly-by-Wire/Light Demonstrators written by Peter G. Hamel and published by Springer. This book was released on 2017-03-15 with total page 359 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book offers the first complete account of more than sixty years of international research on In-Flight Simulation and related development of electronic and electro-optic flight control system technologies (“Fly-by-Wire” and “Fly-by-Light”). They have provided a versatile and experimental procedure that is of particular importance for verification, optimization, and evaluation of flying qualities and flight safety of manned or unmanned aircraft systems. Extensive coverage is given in the book to both fundamental information related to flight testing and state-of-the-art advances in the design and implementation of electronic and electro-optic flight control systems, which have made In-Flight Simulation possible. Written by experts, the respective chapters clearly show the interdependence between various aeronautical disciplines and in-flight simulation methods. Taken together, they form a truly multidisciplinary book that addresses the needs of not just flight test engi neers, but also other aeronautical scientists, engineers and project managers and historians as well. Students with a general interest in aeronautics as well as researchers in countries with growing aeronautical ambitions will also find the book useful. The omission of mathematical equations and in-depth theoretical discussions in favor of fresh discussions on innovative experiments, together with the inclusion of anecdotes and fascinating photos, make this book not only an enjoyable read, but also an important incentive to future research. The book, translated from the German by Ravindra Jategaonkar, is an extended and revised English edition of the book Fliegende Simulatoren und Technologieträger , edited by Peter Hamel and published by Appelhans in 2014.
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1998 with total page 984 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation Relating Longitudinal Pilot-Induced Oscillation Tendency Rating to Describing Function Predictions for Rate-Limited Actuators by : Joel B. Witte
Download or read book An Investigation Relating Longitudinal Pilot-Induced Oscillation Tendency Rating to Describing Function Predictions for Rate-Limited Actuators written by Joel B. Witte and published by . This book was released on 2004-03-01 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this study was to investigate pilot-induced oscillations (PIO) and determine a method by which PIO tendency rating could be predicted. In particular, longitudinal PIO in the presence of rate-limited actuators were singled out for examination. Sinusoidal input/triangular output describing function techniques using Nichols charts were used. A new criterion dubbed Gap Criterion was calculated for PIO sensitivity. This criterion consists of the product of pilot gain necessary to cause PIO and the normalized maximum amplitude of the commanded actuator. These results were paired with simulator and flight test PIO tendency rating data. The PIO rating scale used was the PIO tendency classification of MIL-HDBK-1797. This concept was applied to two historical test databases, HAVE PREVENT and HAVE OLOP. Additional PIO data was gathered in the Large Amplitude Multimode Aerospace Simulator (LAMARS) at the Air Force Research Laboratory (AFRL), Wright-Patterson AFB, Ohio and the USAF NF-16D Variable In-flight Stability Test Aircraft (VISTA) at Edwards AFB, California. Correlation between PIO tendency rating and Gap Criterion was determined for each dataset. Most datasets exceeded a confidence level of 95% that a correlation existed. Follow-on analysis for best curve fit was also accomplished with a logarithmic fit deemed best. Datasets were combined with success to demonstrate the universality of Gap Criterion for correlating PIO tendency ratings for longitudinal PIO involving rate-limited actuators.
Book Synopsis Journal of Guidance, Control, and Dynamics by :
Download or read book Journal of Guidance, Control, and Dynamics written by and published by . This book was released on 2008 with total page 760 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation Relating Longitudinal Pilot-Induced Oscillation Tendency Ratings to Describing Function Predictions for Rate-Limited Actuators (Project MAX GAP). by :
Download or read book An Investigation Relating Longitudinal Pilot-Induced Oscillation Tendency Ratings to Describing Function Predictions for Rate-Limited Actuators (Project MAX GAP). written by and published by . This book was released on 2003 with total page 135 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of Project MAX QAP, a method of predicting pilot induced oscillations (PIO) caused by actuator rate limiting. The overall test objective was to correlate, if possible, Pilot-induced Oscillation Tendency Ratings with a new preflight calculation called the Gap Criterion. The Air Force Institute of Technology, Engineering Department (AFIT/ENY) requested this testing. The USAF Test Pilot School (TPS), Class 03A, conducted 8 flight test totaling 10.8 hours at Edwards AFB, California, from 16 to 22 October 2003.
Author :American Institute of Aeronautics and Astronautics Publisher :AIAA (American Institute of Aeronautics & Astronautics) ISBN 13 : Total Pages :838 pages Book Rating :4.3/5 (91 download)
Book Synopsis Atmospheric Flight Mechanics Conference Held August, 1997 at New Orleans, Louisiana by : American Institute of Aeronautics and Astronautics
Download or read book Atmospheric Flight Mechanics Conference Held August, 1997 at New Orleans, Louisiana written by American Institute of Aeronautics and Astronautics and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 1997 with total page 838 pages. Available in PDF, EPUB and Kindle. Book excerpt: This volume is the proceedings of the Atmospheric Flight Mechanics Conference, which took place in New Orleans, August 1997. It focuses on the technical progress, issues and challenges associated with atmospheric flight. Technical papers address stability and control, flying qualities (including one session dedicated to pilot-induced oscillations), unsteady and vortex aerodynamics, system and parameter identification, aircraft flight dynamic re-entry and aero assist technologies, and reusable launch vehicles.
Book Synopsis Pilot-induced Oscillation Suppression Methods and Their Effects on Large Transport Aircraft Handling Qualities by : R. van der Weerd
Download or read book Pilot-induced Oscillation Suppression Methods and Their Effects on Large Transport Aircraft Handling Qualities written by R. van der Weerd and published by IOS Press. This book was released on 2000 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unified Pilot-Induced Oscillation Theory. Volume 1. PIO Analysis with Linear and Nonlinear Effective Vehicle Characteristics, Including Rate Limiting by :
Download or read book Unified Pilot-Induced Oscillation Theory. Volume 1. PIO Analysis with Linear and Nonlinear Effective Vehicle Characteristics, Including Rate Limiting written by and published by . This book was released on 1995 with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work was conducted as part of a USAF initiative to develop a comprehensive theory to predict pilot-induced oscillation (PIO) tendencies due to the combined effect of all influencing elements. A PIO is a very complicated phenomenon stemming from a dynamic interaction between the pilot and the aircraft. When tight control is required from the pilot, an undesired oscillation can result. However, the adaptive nature of the human pilot makes such oscillations difficult to predict. The independent research of STI included: compilation of available PIO time histories and references as an initial step toward a comprehensive PIO database; refinement of the proposed PIO categories defined in NASA CR-4683; development of PIO theories based on these categories; development of methods to handle the higher frequency and nonlinear aspects of PIO analysis with an emphasis on rate limiting; and a review of existing and proposed linear PIO criteria.
Book Synopsis A Nonlinear Pre-Filter to Prevent Departure And/or Pilot-Induced Oscillations (PIO) Due to Actuator Rate Limiting by : Michael Chapa
Download or read book A Nonlinear Pre-Filter to Prevent Departure And/or Pilot-Induced Oscillations (PIO) Due to Actuator Rate Limiting written by Michael Chapa and published by . This book was released on 1999-03-01 with total page 155 pages. Available in PDF, EPUB and Kindle. Book excerpt: Closed loop instability caused by excess phase lag induced by actuator rate limiting has been suspected in many aircraft departures from controlled flight and pilot-induced oscillations (PIO). As part of the joint Air Force Institute of Technology Test Pilot School (AFITITPS) program, a nonlinear rate limiter pre-filter (RLPF) was developed to minimize the phase lag induced by rate limiting. RLFF performance was evaluated inside the feedback path, but primary emphasis was on the pilot command path. Closed loop computer and motion- based flight simulation were conducted to prepare for the flight test. The HAVE FILTER flight test project was flown using the NF-16D Variable Stability in- flight Simulator Test Aircraft (VISTA) aircraft and evaluated using a software rate limit (SWRL) with and without an RLPF on the pilot command path. A programmable heads-up-display (HUD) was used to generate a fighter tracking task. Flight test results showed the SWRL was useful in preventing departure and/or PIO. However, with low SWRL settings (
Book Synopsis Results of Attempts to Prevent Departure And/or Pilot-Induced Oscillations (PIO) Due to Actuator Rate Limiting in Highly-Augmented Fighter Flight Control Systems (HAVE FILTER). by :
Download or read book Results of Attempts to Prevent Departure And/or Pilot-Induced Oscillations (PIO) Due to Actuator Rate Limiting in Highly-Augmented Fighter Flight Control Systems (HAVE FILTER). written by and published by . This book was released on 1999 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this effort was to evaluate the effects of software rate limiting the pilot command with and without a software pre-filter on a highly-augmented fighter aircraft flight control system. The software rate limiter and software pre-filter were designed to provide protection from departure and/or pilot-induced oscillation (PIO). In statically unstable aircraft stabilized with feedback, elevator/stabilator actuator rate limiting may lead to PIOs and/or departure during aggressive maneuvers. This project examined the use of a software rate limiter (SWRL) on the pilot command and compared the results with those for the unprotected airframe. Additionally, a nonlinear rate limiter pre-filter (RLPF) was used in conjunction with the SWRL. Previous attempts to suppress PIO and/or departure tendencies using similar technologies have encountered difficulty with noise-in-the-loop and out-of-trim bias development during filter operation. This project attempted to improve previous designs using a different algorithm for the RLPF. The SWRL was found to help prevent PIO and/or departure. The RLPF plus SWRL was generally found to be more helpful than the SWRL alone at preventing PIO and/or departure. However, handling qualities deficiencies arose when using low SWRL settings and worsened with low SWRL settings used in conjunction with the RLPF.
Book Synopsis A Nonlinear Pre-filter to Prevent Departure And/or Pilot-induced Oscillations (PIO) Due to Actuator Rate Limiting by : Michael J. Chapa (CAPT, USAF.)
Download or read book A Nonlinear Pre-filter to Prevent Departure And/or Pilot-induced Oscillations (PIO) Due to Actuator Rate Limiting written by Michael J. Chapa (CAPT, USAF.) and published by . This book was released on 1999 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Comparison of Nonlinear Algorithms to Prevent Pilot-Induced Oscillations Caused by Actuator Rate Limiting by : James G. Hanley
Download or read book A Comparison of Nonlinear Algorithms to Prevent Pilot-Induced Oscillations Caused by Actuator Rate Limiting written by James G. Hanley and published by . This book was released on 2003-03 with total page 107 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Suppression of Pilot-Induced Oscillation (PIO) by : Donald A. Johnson
Download or read book Suppression of Pilot-Induced Oscillation (PIO) written by Donald A. Johnson and published by . This book was released on 2002-03-01 with total page 203 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
