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Modeling Adaptive Control And Flight Testing Of A Lighter Than Air Vehicle Validated Using System Identification
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Book Synopsis Modeling, Adaptive Control, and Flight Testing of a Lighter-than-Air Vehicle Validated Using System Identification by : Steve Messinger
Download or read book Modeling, Adaptive Control, and Flight Testing of a Lighter-than-Air Vehicle Validated Using System Identification written by Steve Messinger and published by . This book was released on 2022 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lighter-than-air vehicles (LTAV), or airships, can be useful platforms to test the autonomy and swarming capabilities of collaborative multi-agent systems. Airships have many advantages compared with other unoccupied aerial vehicles such as simplistic construction, longer flight times, and slower dynamics. The complex dynamic effects due to buoyancy forces can create a challenging control problem with varied size, weight, and power considerations. For autonomous operation, a non-linear model of the system is needed to test the controller performance in simulation and explore model-based control techniques. In this work, a LTAV system is used to compete in the Defend the Republic competition -- an autonomous aerial match where two opposing teams of LTAVs are trying to capture and score neutrally buoyant game balls into opposing team's goals in an indoor arena. The first main contribution of this work is to build and design a prototype LTAV that is highly maneuverable and controllable in unknown environments with many disturbances. The system must have enough actuation for a human operator and an autonomous system to capture and score game balls. Designing an autonomous system requires state estimation and a control system. The corresponding hardware to accommodate the processes needed for autonomous operation must be selected and included on the platform. LTAVs present a challenge due to their low weight budget. Hardware selection was carefully selected to best balance weight, maneuverability, and compute power of the vehicle. The second main contribution of this work is to model the vehicle using system identification techniques. A simple non-linear model is formed using linear least-squares, then sub-sampling based threshold sparse Bayesian regression is used to accurately discover where the simple model is not accurate and update the corresponding coefficients. An analogous simulated model is developed and verified using additional flight testing data captured from the LTAV. The third contribution of this work is the use of the LTAV identified model to develop a neural network model reference adaptive control system. During gameplay, the control system will allow the vehicle to autonomously track a user-provided trajectory. In this work, the control architecture is explained, implemented on the simulated system, and implemented on the real system. Performance of the control system is tuned, assessed, and quantified on both the simulated and real system. The control system is shown to provide tracking of the commanded state in real life and simulation during multiple trajectories used in the Defend the Republic competition.
Book Synopsis Flight Test System Identification by : Roger Larsson
Download or read book Flight Test System Identification written by Roger Larsson and published by Linköping University Electronic Press. This book was released on 2019-05-15 with total page 326 pages. Available in PDF, EPUB and Kindle. Book excerpt: With the demand for more advanced fighter aircraft, relying on unstable flight mechanical characteristics to gain flight performance, more focus has been put on model-based system engineering to help with the design work. The flight control system design is one important part that relies on this modeling. Therefore, it has become more important to develop flight mechanical models that are highly accurate in the whole flight envelope. For today’s modern fighter aircraft, the basic flight mechanical characteristics change between linear and nonlinear as well as stable and unstable as an effect of the desired capability of advanced maneuvering at subsonic, transonic and supersonic speeds. This thesis combines the subject of system identification, which is the art of building mathematical models of dynamical systems based on measurements, with aeronautical engineering in order to find methods for identifying flight mechanical characteristics. Here, some challenging aeronautical identification problems, estimating model parameters from flight-testing, are treated. Two aspects are considered. The first is online identification during flight-testing with the intent to aid the engineers in the analysis process when looking at the flight mechanical characteristics. This will also ensure that enough information is available in the resulting test data for post-flight analysis. Here, a frequency domain method is used. An existing method has been developed further by including an Instrumental Variable approach to take care of noisy data including atmospheric turbulence and by a sensor-fusion step to handle varying excitation during an experiment. The method treats linear systems that can be both stable and unstable working under feedback control. An experiment has been performed on a radio-controlled demonstrator aircraft. For this, multisine input signals have been designed and the results show that it is possible to perform more time-efficient flight-testing compared with standard input signals. The other aspect is post-flight identification of nonlinear characteristics. Here the properties of a parameterized observer approach, using a prediction-error method, are investigated. This approach is compared with four other methods for some test cases. It is shown that this parameterized observer approach is the most robust one with respect to noise disturbances and initial offsets. Another attractive property is that no user parameters have to be tuned by the engineers in order to get the best performance. All methods in this thesis have been validated on simulated data where the system is known, and have also been tested on real flight test data. Both of the investigated approaches show promising results.
Book Synopsis On Subscale Flight Testing by : Alejandro Sobron
Download or read book On Subscale Flight Testing written by Alejandro Sobron and published by Linköping University Electronic Press. This book was released on 2018-11-05 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: Downscaled physical models, also referred to as subscale models, have played an essential role in the investigation of the complex physics of flight until the recent disruption of numerical simulation. Despite the fact that improvements in computational methods are slowly pushing experimental techniques towards a secondary role as verification or calibration tools, real-world testing of physical prototypes still provides an unmatched confidence. Physical models are very effective at revealing issues that are sometimes not correctly identified in the virtual domain, and hence can be a valuable complement to other design tools. But traditional wind-tunnel testing cannot always meet all of the requirements of modern aeronautical research and development. It is nowadays too expensive to use these scarce facilities to explore different design iterations during the initial stages of aircraft development, or to experiment with new and immature technologies. Testing of free-flight subscale models, referred to as Subscale Flight Testing (SFT), could offer an affordable and low-risk alternative for complementing conventional techniques with both qualitative and quantitative information. The miniaturisation of mechatronic systems, the advances in rapid-prototyping techniques and power storage, as well as new manufacturing methods, currently enable the development of sophisticated test objects at scales that were impractical some decades ago. Moreover, the recent boom in the commercial drone industry has driven a quick development of specialised electronics and sensors, which offer nowadays surprising capabilities at competitive prices. These recent technological disruptions have significantly altered the cost-benefit function of SFT and it is necessary to re-evaluate its potential in the contemporary aircraft development context. This thesis aims to increase the comprehension and knowledge of the SFT method in order to define a practical framework for its use in aircraft design; focusing on low-cost, short-time solutions that don’t require more than a small organization and few resources. This objective is approached from a theoretical point of view by means of an analysis of the physical and practical limitations of the scaling laws; and from an empirical point of view by means of field experiments aimed at identifying practical needs for equipment, methods, and tools. A low-cost data acquisition system is developed and tested; a novel method for semi-automated flight testing in small airspaces is proposed; a set of tools for analysis and visualisation of flight data is presented; and it is also demonstrated that it is possible to explore and demonstrate new technology using SFT with a very limited amount of economic and human resources. All these, together with a theoretical review and contextualisation, contribute to increasing the comprehension and knowledge of the SFT method in general, and its potential applications in aircraft conceptual design in particular.
Book Synopsis Flight Dynamics and System Identification for Modern Feedback Control by : J Grauer
Download or read book Flight Dynamics and System Identification for Modern Feedback Control written by J Grauer and published by . This book was released on 2013 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt: Unmanned air vehicles are becoming increasingly popular alternatives for private applications which include, but are not limited to, fire fighting, search and rescue, atmospheric data collection, and crop surveys, to name a few. Among these vehicles are avian-inspired, flapping-wing designs, which are safe to operate near humans and are required to carry payloads while achieving manoeuverability and agility in low speed flight. Conventional methods and tools fall short of achieving the desired performance metrics and requirements of such craft. Flight dynamics and system identification for modern feedback control provides an in-depth study of the difficulties associated with achieving controlled performance in flapping-wing, avian-inspired flight, and a new model paradigm is derived using analytical and experimental methods, with which a controls designer may then apply familiar tools. This title consists of eight chapters and covers flapping-wing aircraft and flight dynamics, before looking at nonlinear, multibody modelling as well as flight testing and instrumentation. Later chapters examine system identification from flight test data, feedback control and linearization. Presents experimental flight data for validation and verification of modelled dynamics, thus illustrating the deficiencies and difficulties associated with modelling flapping-wing flight Derives a new flight dynamics model needed to model avian-inspired vehicles, based on nonlinear multibody dynamics Extracts aerodynamic models of flapping flight from experimental flight data and system identification techniques.
Book Synopsis Flight Dynamics and System Identification for Modern Feedback Control by : Jared A Grauer
Download or read book Flight Dynamics and System Identification for Modern Feedback Control written by Jared A Grauer and published by Elsevier. This book was released on 2013-08-31 with total page 161 pages. Available in PDF, EPUB and Kindle. Book excerpt: Unmanned air vehicles are becoming increasingly popular alternatives for private applications which include, but are not limited to, fire fighting, search and rescue, atmospheric data collection, and crop surveys, to name a few. Among these vehicles are avian-inspired, flapping-wing designs, which are safe to operate near humans and are required to carry payloads while achieving manoeuverability and agility in low speed flight. Conventional methods and tools fall short of achieving the desired performance metrics and requirements of such craft. Flight dynamics and system identification for modern feedback control provides an in-depth study of the difficulties associated with achieving controlled performance in flapping-wing, avian-inspired flight, and a new model paradigm is derived using analytical and experimental methods, with which a controls designer may then apply familiar tools. This title consists of eight chapters and covers flapping-wing aircraft and flight dynamics, before looking at nonlinear, multibody modelling as well as flight testing and instrumentation. Later chapters examine system identification from flight test data, feedback control and linearization. - Presents experimental flight data for validation and verification of modelled dynamics, thus illustrating the deficiencies and difficulties associated with modelling flapping-wing flight - Derives a new flight dynamics model needed to model avian-inspired vehicles, based on nonlinear multibody dynamics - Extracts aerodynamic models of flapping flight from experimental flight data and system identification techniques
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720576815 Total Pages :70 pages Book Rating :4.5/5 (768 download)
Book Synopsis Identification of Low Order Equivalent System Models from Flight Test Data by : National Aeronautics and Space Administration (NASA)
Download or read book Identification of Low Order Equivalent System Models from Flight Test Data written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-31 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: Identification of low order equivalent system dynamic models from flight test data was studied. Inputs were pilot control deflections, and outputs were aircraft responses, so the models characterized the total aircraft response including bare airframe and flight control system. Theoretical investigations were conducted and related to results found in the literature. Low order equivalent system modeling techniques using output error and equation error parameter estimation in the frequency domain were developed and validated on simulation data. It was found that some common difficulties encountered in identifying closed loop low order equivalent system models from flight test data could be overcome using the developed techniques. Implications for data requirements and experiment design were discussed. The developed methods were demonstrated using realistic simulation cases, then applied to closed loop flight test data from the NASA F-18 High Alpha Research Vehicle.Morelli, Eugene A.Langley Research CenterEXPERIMENT DESIGN; DYNAMIC MODELS; SYSTEM IDENTIFICATION; FLIGHT TESTS; DATA PROCESSING; FLIGHT CONTROL; DEFLECTION; AIRCRAFT PERFORMANCE; ERROR ANALYSIS; FLIGHT CHARACTERISTICS; FEEDBACK CONTROL
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author :Ravindra V. Jategaonkar Publisher :AIAA (American Institute of Aeronautics & Astronautics) ISBN 13 : Total Pages :568 pages Book Rating :4.3/5 (91 download)
Book Synopsis Flight Vehicle System Identification by : Ravindra V. Jategaonkar
Download or read book Flight Vehicle System Identification written by Ravindra V. Jategaonkar and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 2006 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt: This valuable volume offers a systematic approach to flight vehicle system identification and exhaustively covers the time domain methodology. It addresses in detail the theoretical and practical aspects of various parameter estimation methods, including those in the stochastic framework and focusing on nonlinear models, cost functions, optimization methods, and residual analysis. A pragmatic and balanced account of pros and cons in each case is provided. The book also presents data gathering and model validation, and covers both large-scale systems and high-fidelity modeling. Real world problems dealing with a variety of flight vehicle applications are addressed and solutions are provided. Examples encompass such problems as estimation of aerodynamics, stability, and control derivatives from flight data, flight path reconstruction, nonlinearities in control surface effectiveness, stall hysteresis, unstable aircraft, and other critical considerations.
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1992 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781793957245 Total Pages :26 pages Book Rating :4.9/5 (572 download)
Book Synopsis Design of Low Complexity Model Reference Adaptive Controllers by : National Aeronautics and Space Adm Nasa
Download or read book Design of Low Complexity Model Reference Adaptive Controllers written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-14 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight research experiments have demonstrated that adaptive flight controls can be an effective technology for improving aircraft safety in the event of failures or damage. However, the nonlinear, timevarying nature of adaptive algorithms continues to challenge traditional methods for the verification and validation testing of safety-critical flight control systems. Increasingly complex adaptive control theories and designs are emerging, but only make testing challenges more difficult. A potential first step toward the acceptance of adaptive flight controllers by aircraft manufacturers, operators, and certification authorities is a very simple design that operates as an augmentation to a non-adaptive baseline controller. Three such controllers were developed as part of a National Aeronautics and Space Administration flight research experiment to determine the appropriate level of complexity required to restore acceptable handling qualities to an aircraft that has suffered failures or damage. The controllers consist of the same basic design, but incorporate incrementally-increasing levels of complexity. Derivations of the controllers and their adaptive parameter update laws are presented along with details of the controllers implementations. Hanson, Curt and Schaefer, Jacob and Johnson, Marcus and Nguyen, Nhan Ames Research Center; Armstrong Flight Research Center NND08RR01B; WBS 284848.02.05.02.02
Author :Mark Brian Tischler Publisher :AIAA (American Institute of Aeronautics & Astronautics) ISBN 13 :9781563478376 Total Pages :0 pages Book Rating :4.4/5 (783 download)
Book Synopsis Aircraft and Rotorcraft System Identification by : Mark Brian Tischler
Download or read book Aircraft and Rotorcraft System Identification written by Mark Brian Tischler and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 2006 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Although many books have been written on the theory of system identification, few are available that provide a complete engineering treatment of system identification and how to successfully apply it to flight vehicles. This book presents proven methods, practical guidelines, and real-world flight-test results for a wide range of state-of-the-art flight vehicles, from small uncrewed aerial vehicles (UAVs) to large manned aircraft/rotorcraft.
Book Synopsis Flight Test of an Adaptive Configuration Optimization System for Transport Aircraft by : Glenn B. Gilyard
Download or read book Flight Test of an Adaptive Configuration Optimization System for Transport Aircraft written by Glenn B. Gilyard and published by . This book was released on 1999 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Test Results from the NF-15B Intelligent Flight Control System (IFCS) Project with Adaptation to a Simulated Stabilator Failure by : National Aeronaut Administration (Nasa)
Download or read book Flight Test Results from the NF-15B Intelligent Flight Control System (IFCS) Project with Adaptation to a Simulated Stabilator Failure written by National Aeronaut Administration (Nasa) and published by . This book was released on 2020-08-05 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Adaptive flight control systems have the potential to be more resilient to extreme changes in airplane behavior. Extreme changes could be a result of a system failure or of damage to the airplane. A direct adaptive neural-network-based flight control system was developed for the National Aeronautics and Space Administration NF-15B Intelligent Flight Control System airplane and subjected to an inflight simulation of a failed (frozen) (unmovable) stabilator. Formation flight handling qualities evaluations were performed with and without neural network adaptation. The results of these flight tests are presented. Comparison with simulation predictions and analysis of the performance of the adaptation system are discussed. The performance of the adaptation system is assessed in terms of its ability to decouple the roll and pitch response and reestablish good onboard model tracking. Flight evaluation with the simulated stabilator failure and adaptation engaged showed that there was generally improvement in the pitch response; however, a tendency for roll pilot-induced oscillation was experienced. A detailed discussion of the cause of the mixed results is presented. Bosworth, John T. and Williams-Hayes, Peggy S. Armstrong Flight Research Center NASA/TM-2007-214629, H-2751, AIAA-2007-2818 ADAPTIVE CONTROL; FLIGHT CONTROL; NEURAL NETS; FORMATION FLYING; AIRCRAFT STABILITY; STABILITY TESTS; ADAPTATION; ROLL; SYSTEM FAILURES; FLIGHT SIMULATION; STABILIZERS; FLIGHT TEST VEHICLES
Download or read book Aeronautical Engineering written by and published by . This book was released on 1991 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analytical Investigation of an Adaptive Flight-control System Using a Sinusoidal Test Signal by : Jack E. Harris
Download or read book Analytical Investigation of an Adaptive Flight-control System Using a Sinusoidal Test Signal written by Jack E. Harris and published by . This book was released on 1961 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis L1 Adaptive Control Theory by : Naira Hovakimyan
Download or read book L1 Adaptive Control Theory written by Naira Hovakimyan and published by SIAM. This book was released on 2010-09-30 with total page 333 pages. Available in PDF, EPUB and Kindle. Book excerpt: Contains results not yet published in technical journals and conference proceedings.
Book Synopsis Identification of Low Order Equivalent System Models from Flight Test Data by : Eugene A. Morelli
Download or read book Identification of Low Order Equivalent System Models from Flight Test Data written by Eugene A. Morelli and published by . This book was released on 2000 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: Identification of low order equivalent system dynamic models from flight test data was studied. Inputs were pilot control deflections, and outputs were aircraft responses, so the models characterized the total aircraft response including bare airframe and flight control system. Theoretical investigations were conducted and related to results found in the literature. Low order equivalent system modeling techniques using output error and equation error parameter estimation in the frequency domain were developed and validated on simulation data. It was found that some common difficulties encountered in identifying closed loop low order equivalent system models from flight test data could be overcome using the developed techniques. Implications for data requirements and experiment design were discussed. The developed methods were demonstrated using realistic simulation cases, then applied to closed loop flight test data from the NASA F-18 High Alpha Research Vehicle.
