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Angle of Attack Determination Using Inertial Navigation System Data from Flight Tests

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Angle of Attack Determination Using Inertial Navigation System Data from Flight Tests University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Masters Theses Graduate School 5-2017 ANGLE OF ATTACK DETERMINATION USING INERTIAL NAVIGATION SYSTEM DATA FROM FLIGHT TESTS Jack Kevin Ly University of Tennessee, Knoxville, [email protected] Follow this and additional works at: https://trace.tennessee.edu/utk_gradthes Part of the Aerodynamics and Fluid Mechanics Commons, Aeronautical Vehicles Commons, Aviation Safety and Security Commons, Dynamics and Dynamical Systems Commons, and the Navigation, Guidance, Control and Dynamics Commons Recommended Citation Ly, Jack Kevin, "ANGLE OF ATTACK DETERMINATION USING INERTIAL NAVIGATION SYSTEM DATA FROM FLIGHT TESTS. " Master's Thesis, University of Tennessee, 2017. https://trace.tennessee.edu/utk_gradthes/4757 This Thesis is brought to you for free and open access by the Graduate School at TRACE: Tennessee Research and Creative Exchange. It has been accepted for inclusion in Masters Theses by an authorized administrator of TRACE: Tennessee Research and Creative Exchange. For more information, please contact [email protected]. To the Graduate Council: I am submitting herewith a thesis written by Jack Kevin Ly entitled "ANGLE OF ATTACK DETERMINATION USING INERTIAL NAVIGATION SYSTEM DATA FROM FLIGHT TESTS." I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the equirr ements for the degree of Master of Science, with a major in Engineering Science. Steve Brooks, Major Professor We have read this thesis and recommend its acceptance: Peter Solies, Trevor Moeller Accepted for the Council: Dixie L. Thompson Vice Provost and Dean of the Graduate School (Original signatures are on file with official studentecor r ds.) ANGLE OF ATTACK DETERMINATION USING INERTIAL NAVIGATION SYSTEM DATA FROM FLIGHT TESTS A Thesis Presented for the Master of Science Degree The University of Tennessee, Knoxville Jack Kevin Ly May 2017 Copyright © 2017 by Jack Kevin Ly All rights reserved. ii Dedication To my family, my friends, and my love, Sonia Joshi. iii Acknowledgements To everyone in the UTSI Flight Research Department, I would like to say thank you for your guidance, feedback, elbow grease, and humanity. Greg Heatherly, Jacob Bowman, and Jonathan Kolwyck for helping to prioritize my thesis over other work. Dr. Steve Brooks, Dr. Peter Solies, and Dr. Trevor Moeller for all your understanding, guidance, input, advice, and knowledge on flight testing, engineering, and academics. Thank you Dr. Borja Martos for providing me with the starting point to launch my thesis. To my mom and dad for always supporting me, even if you do not completely understand what I am doing or why I’m doing it. And with all my heart, to Sonia Joshi, for all your unrelenting support, I can say no more than thank you. iv Abstract Engineers and pilots rely on mechanical flow angle vanes on air data probes to determine the angle of attack of the aircraft in flight. These probes, however, are costly, come with inherent measurement errors, affect the flight characteristics of the aircraft, and are potentially dangerous in envelope expansion flights. Advances in the accuracy, usability, and affordability of inertial navigation systems allow for angle of attack to be determined accurately without direct measurement of the airflow around the aircraft. Utilizing an algorithm developed from aircraft equations of motion, a post- flight data review is completed as the first step in proving the low cost feasibility of utilizing inertial navigation data for such analysis. Flight tests were conducted with the UTSI Cessna 210 research aircraft to calibrate an angle of attack flow angle vane and obtain inertial navigation data from a commercial INS system in typical flight scenarios. The results of the angle of attack algorithm are compared to the measured angle of attack flow angle vane. Discussed in this thesis are the feasibility and potential applications of angle of attack determination from inertial data. v Table of Contents Chapter 1: Introduction........................................................................................................................................ 1 Overview ................................................................................................................................................... 1 Motivation/Purpose .................................................................................................................................. 2 Solution/Approach .................................................................................................................................... 3 Objectives ................................................................................................................................................. 3 Scope/Out-of-scope .................................................................................................................................. 3 Assumptions .............................................................................................................................................. 4 Chapter 2: Theory ................................................................................................................................................. 5 Coordinate Reference Systems, Transformations, and Flow Angles Overview ........................................ 5 Coordinate Reference Systems ............................................................................................................. 5 Coordinate System Transformations .................................................................................................... 6 Flow Angles ........................................................................................................................................... 7 Derivation of the Angle of Attack Algorithm from the Equations of Motion ......................................... 10 Basic Force Equations ......................................................................................................................... 10 Stability Derivative Estimation ............................................................................................................ 14 Air Data and Inertial Navigation System Data Reduction ....................................................................... 19 In-Flight Calibrations – Air Data Flow Angle System ........................................................................... 19 Drag Coefficient Determination .......................................................................................................... 20 Chapter 3: Platform, Equipment, and Instrumentation .................................................................................... 22 UTSI Cessna 210, N33UT ......................................................................................................................... 22 Air Data Boom Assembly (Truth Source) ................................................................................................ 23 Calibration of Air Data System (ADS) Boom Flow Angle Vane ............................................................ 23 Ellipse-N INS System ............................................................................................................................... 25 Chapter 4: Flight Test ......................................................................................................................................... 27 Philosophy/Methodology ....................................................................................................................... 27 Flight Test Technique – Ellipse-N INS Calibration ............................................................................... 27 Flight Test Technique – Power Speed (Piw-Viw), Steady Level Trim Shots ........................................ 27 Flight Test Technique – Level Acceleration and Deceleration ............................................................ 28 Flight Test Technique – Abrupt Pull up ............................................................................................... 28 Flight Test Technique – Windup Turn ................................................................................................. 28 Flight Conditions ..................................................................................................................................... 29 vi Chapter 5: Data Reduction and Results ............................................................................................................. 31 Flow Angle Alpha Vane Calibration ......................................................................................................... 31 Trim Shot ................................................................................................................................................. 33 Level Acceleration and Deceleration ...................................................................................................... 35 Pull Up Maneuver ................................................................................................................................... 39 Chapter 6: Conclusions and Recommendations ................................................................................................ 41 References .......................................................................................................................................................... 43 Appendices ........................................................................................................................................................
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