Theses - Daytona Beach Dissertations and Theses Fall 2009 Determination of Stability and Control Derivatives for a Modern Light Composite Twin Engine Airplane Monica M. Londono Embry-Riddle Aeronautical University - Daytona Beach Follow this and additional works at: https://commons.erau.edu/db-theses Part of the Aerodynamics and Fluid Mechanics Commons, and the Aviation Commons Scholarly Commons Citation Londono, Monica M., "Determination of Stability and Control Derivatives for a Modern Light Composite Twin Engine Airplane" (2009). Theses - Daytona Beach. 124. https://commons.erau.edu/db-theses/124 This thesis is brought to you for free and open access by Embry-Riddle Aeronautical University – Daytona Beach at ERAU Scholarly Commons. It has been accepted for inclusion in the Theses - Daytona Beach collection by an authorized administrator of ERAU Scholarly Commons. For more information, please contact [email protected]. DETERMINATION OF STABILITY AND CONTROL DERIVATIVES FOR A MODERN LIGHT COMPOSITE TWIN ENGINE AIRPLANE by Monica M. Londono A Thesis Submitted to the Graduate Studies Office In Partial Fulfillment of the Requirements for the Degree of Master of Science in Aerospace Engineering Embry-Riddle Aeronautical University Daytona Beach, Florida Fall 2009 UMI Number: EP31998 INFORMATION TO USERS The quality of this reproduction is dependent upon the quality of the copy submitted. Broken or indistinct print, colored or poor quality illustrations and photographs, print bleed-through, substandard margins, and improper alignment can adversely affect reproduction. In the unlikely event that the author did not send a complete manuscript and there are missing pages, these will be noted. Also, if unauthorized copyright material had to be removed, a note will indicate the deletion. UMI® UMI Microform EP31998 Copyright 2011 by ProQuest LLC All rights reserved. This microform edition is protected against unauthorized copying under Title 17, United States Code. ProQuest LLC 789 East Eisenhower Parkway P.O. Box 1346 Ann Arbor, Ml 48106-1346 Copyright by Monica M. Londono 2009 All Rights Reserved II DETERMINATION OF STABILITY AND CONTROL DERIVATIVES FOR A MODERN LIGHT COMPOSITE TWIN ENGINE AIRPLANE by Monica M. Londono This thesis was prepared under the direction of the candidate's thesis committee chairman, Dr. Richard "Pat" Anderson, Department of Aerospace Engineering, and has been approved by the members of her thesis committee. It was submitted to the Department of Aerospace Engineering and was accepted in partial fulfillment of the requirements for the degree of Master of Science in Aerospace Engineering. THESIS COMMITTEE: 'Richard "Pat" Anderson Chairman Dr. Maj Mirmirani Member Professor Charles Eastlake Member Coordinator^ MS AE Program Date pL James CunnmghaHj^ssociate VP for Academics Date 3 ACKNOWLEDGEMENTS I would like to thank everyone who helped me and supported me in my thesis work. This project has been very important to me and its success can largely be attributed to the support I have received. I want to start by thanking my parents, brother and family. They have been a model of love, responsibility and hard work. Thank you for all the support and for always believing in me. I would like to thank Dr. Anderson for all of his help during my time at Embry-Riddle. Thank you for everything you have taught me and for giving me the opportunity to experience so many different and exciting projects. I would also like to thank Prof. Eastlake and Dr. Mirmirani for all of their advice and knowledge which was put to good use for this thesis. I also include thanks to all the faculty and ERAU community for my growth as a person and the knowledge I have gained. I would also like to thank my friends, classmates and all the students who supported my work. I learned a great deal from all of you and I am lucky to have such wonderful help. Dick, thank you for your help during my initial work; your programming expertise was essential. You were patient and always willing to make everything work. Brett, I thank you for our numerous discussions on everything involving flight testing that greatly clarified my understanding. Your motivation was endless and you were always willing to help; thanks for all of your support. Thank you all for sharing this process with me which has helped me grow into the person I am today. I could not have done it without you. 4 ABSTRACT Author: Monica M. Londono Title: Determination of stability and control derivatives for a modern light composite twin engine airplane Institution: Embry-Riddle Aeronautical University Degree: Master of Science in Aerospace Engineering Year: 2009 To develop and compare full envelope stability and control derivatives and their associated errors for a modern light composite twin engine airplane from flight test data and digital DATCOM (Data Compendium). This development is to serve three purposes 1) to provide data for validation of newer analytical techniques such as Computational Fluid Dynamics (CFD), 2) to provide public domain static and dynamic stability and control derivatives for a modern twin engine airplane, 3) to analyze the relationship between test design and error for both output error and equation error methods. A flight test program was conducted on a Diamond Twin Star DA42 with Thielert engines and on a DA42 with Lycoming engines by Embry-Riddle Aeronautical University. For the theoretical verification the equation error and output error methods in both time and frequency domain within System Identification Programs for AirCraft (SIDPAC), were used. The DATCOM analysis was based on airplane drawings and direct measurement on the DA42 airframe. The results for both methods and error associated with SIDPAC were compared to Digital DATCOM results. 5 TABLE OF CONTENTS 1. INTRODUCTION 13 1.1 PID Background 14 1.1.1 SIDPAC Background 14 1.1.2 Digital DATCOM Background 15 1.2 Airplane Information 15 1.3 Sign Convention 17 1.4 Literature Review 18 1.4.1 PID methods 18 1.4.2 Equation error 18 1.4.3 Output error 20 1.4.4 Data compatibility 22 2. METHODS 25 2.1 PID analysis 25 2.2 Test Input Design 26 2.2.1 Longitudinal Inputs 26 2.2.2 Lateral-directional Inputs 28 2.3 Flight test data and Instrumentation 30 2.3.1 Instrumentation 30 2.3.2 Derived Parameters 32 2.3.3 Mass Properties 32 2.3.4 Test Points 33 2.4 Flight Test Data Corrections 35 2.4.1 Flight test Data Calibrations 35 2.5 Data Compatibility Results 37 2.6 Modification to SIDPAC model 44 2.7 Linear Models 44 2.8 Correlation 45 2.9 Digital DATCOM analysis 48 2.10 Flight Conditions (FLTCON) 49 2.11 Reference Parameters (OPTENS) 49 2.12 Synthesis Parameters (SYNTHS) 50 2.13 Body Geometric Data (BODY) 51 6 2.14 Wing Planform (WGPLNF) 51 2.15 Wing Airfoil (WGSCHR) 52 2.16 Horizontal Tail Planform (HTPLNF) 53 2.17 Horizontal Tail Airfoil (HTSCHR) 54 2.18 Vertical Tail Planform (VTPLNF) 55 2.19 Vertical Tail Airfoil (VTSCHR) 55 2.20 Ventral Fin (VFPLNF) 56 2.21 Wingtips - Twin vertical panels (TVTPAN) 57 2.22 Propeller Power Parameters 58 2.23 Elevator - Symmetrical Flaps (SYMFLP) 60 2.24 MATLAB model 63 3. ANALYSIS AND RESULTS ,... 64 3.1 Longitudinal 64 3.1.1 Lift force 64 3.1.2 Pitching Moment 66 3.2 Lateral Directional 71 3.2.1 Side Force 71 3.2.2 Rolling Moment 73 3.3 Yawing Moment 77 4. CONCLUSION AND CORRELATION 81 4.1 Longitudinal Mode 81 4.2 Lateral-Directional Mode 82 4.3 Future work 84 5. REFERENCES 85 6. APPENDIX 1: STEPWISE REGRESSION 86 7 TABLE OF FIGURES Figure 1 Control Surface Sign Convention 17 Figure 2 Airplane Notation and Sign Convention 17 Figure 3 PID Analyses Flowchart 25 Figure 4 DA42TDI/DA42L360 Longitudinal PID Input 27 Figure 5 Longitudinal regressors during 3-2-1-1 maneuver 28 Figure 6 DA42TDI Lateral-Direction PID input 29 Figure 7 DA42L360 Lateral-Directional PID Input 30 Figure 8 Flight Test Data Corrections Flowchart 35 Figure 9 Elevator String Pot 36 Figure 10 Elevator Calibration 36 Figure 11 Elevator Deflection Angle vs. Voltage Ratio 37 Figure 12 Longitudinal parameter reconstruction before DCMP corrections 42 Figure 13 AoA scale factor from Longitudinal DCMP 43 Figure 14 Beta scale factor from Lateral-Directional DCMP 43 Figure 15 Aileron and roll rate time histories 48 Figure 16 Reference drawings for Synthesis Parameters 51 Figure 17 Digital DATCOM body model 51 Figure 18 Reference drawing for wing planform parameters 52 Figure 19 Wing airfoil model 53 Figure 20 Reference drawing for horizontal tail parameters 54 Figure 21 Horizontal tail airfoil model 54 Figure 22 Reference drawing for vertical tail parameters 55 Figure 23 Vertical tail airfoil model 56 Figure 24 Reference drawing for Ventral Fin parameters 57 Figure 25 Reference drawings for Wingtip parameters 58 Figure 26 Reference drawing for Propeller Power parameters 60 Figure 27 Reference drawings for Elevator parameters 62 Figure 28 Three view model comparison 63 Figure 29 CLa Results 65 8 Figure 30 Cma results 66 Figure 31 Static Margin Results 67 Figure 32 Cm<, Results 68 Figure 33 Alpha Reconstruction 69 Figure 34 Cmge Results 70 Figure 35 CYP Results 72 Figure 36 Clp Results 73 Figure 37 Clp Results 74 Figure 38 Clr Results 75 Figure 39 Cl8a Results 76 Figure 40 Cnp Results .... 77 Figure 41 Cnp Results 78 Figure 42 Cnr Results 79 Figure 43 Cn5r Results 80 9 LIST OF ACRONYMS AFM Airplane Flight Manual AMM Airplane Maintenance Manual C.G. Center of Gravity CFD Computational Fluid Dynamics DA42 L360 Twin Star DA42 with Lycoming Engines DA42 TDI Twin Star DA42 with Thielert Engines DATCOM Data Compendium EE Equation Error