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Aircraft Parameter Identification for Application Within a Fault-Tolerant Flight Control System Graduate Theses, Dissertations, and Problem Reports 2011 Aircraft parameter identification for application within a fault- tolerant flight control system Kerri B. Phillips West Virginia University Follow this and additional works at: https://researchrepository.wvu.edu/etd Recommended Citation Phillips, Kerri B., "Aircraft parameter identification for application within a fault-tolerant flight control system" (2011). Graduate Theses, Dissertations, and Problem Reports. 3049. https://researchrepository.wvu.edu/etd/3049 This Dissertation is protected by copyright and/or related rights. It has been brought to you by the The Research Repository @ WVU with permission from the rights-holder(s). You are free to use this Dissertation in any way that is permitted by the copyright and related rights legislation that applies to your use. For other uses you must obtain permission from the rights-holder(s) directly, unless additional rights are indicated by a Creative Commons license in the record and/ or on the work itself. This Dissertation has been accepted for inclusion in WVU Graduate Theses, Dissertations, and Problem Reports collection by an authorized administrator of The Research Repository @ WVU. For more information, please contact [email protected]. AIRCRAFT PARAMETER IDENTIFICATION FOR APPLICATION WITHIN A FAULT- TOLERANT FLIGHT CONTROL SYSTEM by Kerri B. Phillips Dissertation submitted to College of Engineering and Mineral Resources at West Virginia University in partial fulfillment of the requirements for the degree of Doctor of Philosophy in Aerospace Engineering Approved by Dr. Marcello Napolitano, Committee Chairperson Dr. Bojan Cukic Dr. Wade Huebsch Dr. Gary Morris Dr. Mario Perhinschi Department of Mechanical and Aerospace Engineering Morgantown, West Virginia 2011 Keywords: Parameter Estimation, System Identification, Aircraft, UAV, DATCOM Copyright 2011, Kerri B. Phillips Abstract AIRCRAFT PARAMETER IDENTIFICATION FOR APPLICATION WITHIN A FAULT-TOLERANT FLIGHT CONTROL SYSTEM by Kerri B. Phillips A parameter identification study was conducted to identify a detailed aircraft mathematical model for application within a fault-tolerant flight control system that aims to detect, identify, and accommodate for sensor and actuator failures. Specifically, a mathematical model was identified under nominal conditions for two aircraft platforms, and a model was developed for one platform under actuator failure conditions. These models are to be used in flight control law design and to account for actuator failures on the primary control surfaces for one of the research platforms. In order to accurately model the aircraft behavior following a control surface failure, the effects of an individual surface on the aircraft dynamics was estimated. Since an individual control surface deflection – for example in the event of a locked actuator – causes a coupling between the longitudinal and lateral-directional dynamics, additional terms were identified in the state space and stability and control derivative mathematical models. These models were derived from measured flight data acquired from pilot and automated computer-injected maneuvers under both nominal and failure conditions. From this analysis, the stability and control derivatives were extracted to determine the aerodynamic forces and moments on each aircraft. These aerodynamics were next introduced into a simulation environment to validate the accuracy of the identified mathematical models. A Data Compendium (DATCOM) – based analysis was conducted in order to provide a means of comparison of the models obtained through the parameter identification study and to provide constraints on parameter optimization. Finally, a confidence interval analysis was conducted to determine the reliability of the estimated values. Several simulation studies were conducted to validate the accuracy of the models for each research platform, focusing on both nominal and primary control surface failure conditions where applicable. The model outputs were compared to the measured flight data from the two respective research platforms to validate the accuracy of the estimated parameters. Acknowledgements I would first like to thank my parents, Jon and Darla Phillips, for their love and support throughout my graduate work. Thank you to the rest of my family who has also supported me throughout this journey. I would like to thank my committee chairman and research advisor, Dr. Marcello Napolitano, for his guidance and support throughout this research effort. I will be forever grateful for the opportunity to conduct research within the Flight Controls Research Lab and the education I have gained here. I would like to acknowledge and thank my committee members, Dr. Bojan Cukic, Dr. Wade Huebsch, Dr. Gary Morris, and Dr. Mario Perhinschi for reviewing and contributing their thoughts to this research effort. I would like to thank Dr. Giampiero Campa, who has provided me excellent guidance throughout the research project all the way from the coast of California. Thanks for sticking with me. I would also like to thank Dr. Srikanth Gururajan for his support, guidance, and mentorship. Thank you for believing in me even when I doubted myself. I would also like to extend a thank you to Dr. Yu Gu and Dr. Brad Seanor for all of their guidance with this research project. I would like to thank the flight test members who have had a significant impact on the success of this project. Thank you to the three pilots who have flown one or both of the research platforms used in the project: Mike Eden, Mike Spencer, and Dave Ellis. Thank you to the flight testing team, past and present, who have worked diligently on construction, repairs, and instrumentation of the aircraft: Sebastian Sanchez, Jason Gross, Matt Rhudy, Zach Merceruio, Marc Gramlich, Daniele Tancredi, and Frank Barchesky. A special thanks goes to Sergio Tamayo for being a great friend and an excellent support system throughout this research effort. I would like to thank Dr. John Kuhlman and Dr. Wade Huebsch for their support and guidance, not only during my graduate studies, but throughout my entire college career. You both truly have been role models for me. Thank you to the West Virginia Space Grant Consortium for all that they have done for me. The opportunities I had through your programs changed my life – I will never be able to say “thank you” enough. Dr. Majid Jaraiedi, Ms. Candy Cordwell, and Ms. Amy Diznoff, you all are wonderful. Please continue helping students achieve their dreams. I would finally like to thank the West Virginia University College of Engineering and Mineral Resources and the Department of Mechanical and Aerospace Engineering for making the past 8 years the best of my life. I have learned so much throughout my studies, and I will forever be indebted to you. iii Table of Contents Abstract ........................................................................................................................................... ii Acknowledgements ........................................................................................................................ iii Nomenclature ................................................................................................................................. xi 1 Introduction ............................................................................................................................. 1 1.1 Research Background ..................................................................................................... 1 1.2 Project Overview ............................................................................................................ 2 1.3 Research Objective ......................................................................................................... 3 2 Literature Review.................................................................................................................... 5 2.1 Fault-Tolerant Flight Control Systems ........................................................................... 5 2.2 Aircraft Parameter Identification through DATCOM Analysis ................................... 14 2.3 Aircraft Parameter Identification from Flight Data ...................................................... 21 3 Review of Parameter Identification ...................................................................................... 27 3.1 Aircraft Parameter Identification .................................................................................. 27 3.1.1 Experiment Design................................................................................................ 29 3.1.1.1 Selecting Parameter Identification Maneuvers ................................................. 30 3.1.2 Parameter Identification in the Time Domain – Output Error Method ................ 34 3.1.3 Parameter Identification in the Frequency Domain – Fourier Transform Regression Method ............................................................................................................... 36 4 Research Approach and Methodology .................................................................................. 40 4.1 WVU YF-22 Research Platform ................................................................................... 40 4.1.1 WVU YF-22 Aircraft System ............................................................................... 40 4.1.2 WVU YF-22 Onboard Computer.........................................................................
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