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Conceptual Design for a Supersonic Advanced Military Trainer

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Conceptual Design for a Supersonic Advanced Military Trainer Conceptual Design for a Supersonic Advanced Military Trainer A project presented to The Faculty of the Department of Aerospace Engineering San José State University In partial fulfillment of the requirements for the degree Master of Science in Aerospace Engineering by Royd A. Johansen May 2019 approved by Dr. Nikos Mourtos Faculty Advisor © 2019 Royd A. Johansen ALL RIGHTS RESERVED ABSTRACT CONCEPTUAL DESIGN FOR A SUPERSONIC ADVANCED MILITARY TRAINER by Royd A. Johansen The conceptual aircraft design project is based off the T-X program requirements for an advanced military trainer (AMT). The design process focused on a top-level design aspect, that followed the classic aircraft design process developed by J. Roskam’s Airplane Design. The design process covered: configuration selection, weight sizing, performance sizing, fuselage design, wing design, empennage design, landing-gear design, Class I weight and balance, static longitudinal and directional stability, subsonic drag polars, supersonic area rule applied to supersonic drag polars, V-n diagrams, Class II weight and balance, moments and products of inertia, and cost estimation. Throughout the process other materials and references are consulted to verify or develop a better understanding of the concepts in the Airplane Design series. ACKNOWLEDGEMENTS I would like to express my deep gratitude to Dr. Nikos Mourtos for his support throughout this project and his invaluable academic advisement throughout my undergraduate and graduate studies. I would also like to thank Professor Gonzalo Mendoza for introducing Aircraft Design to me as an undergraduate and for providing additional insights throughout my graduate studies. My thanks are also extended to Professor Jeanine Hunter for helping me develop my theoretical foundation in Dynamics, Flight Mechanics, and Aircraft Stability and Control. I would also like to thank Heidi Eisips for her help with utilizing Microsoft Word’s capabilities and additional editorial recommendations. My thanks also goes to Reine Dominique Ntone Sike for providing feedback and editorial recommendations. Finally, I would like to thank my friends and family that have continued to give me support and encouragement throughout my academics. v Contents 1. Introduction ......................................................................................................................................... 1 1.1 Mission Requirements ............................................................................................................... 1 1.2 Mission Profile .......................................................................................................................... 1 1.3 Market Analysis ........................................................................................................................ 2 1.4 Technical and Economic Feasibility ......................................................................................... 2 1.5 Comparative Study of Similar Airplanes................................................................................... 3 1.5.1 Mission Capabilities and Configuration Selection .............................................................. 3 1.5.2 Comparison of Important Design Parameters ..................................................................... 5 1.5.3 Discussion and Conclusion ................................................................................................. 5 2. Configuration Design .......................................................................................................................... 7 2.1 Comparative Study of Similar Airplanes................................................................................... 7 2.1.1 Wing Configuration ............................................................................................................ 7 2.1.2 Empennage Configuration .................................................................................................. 7 2.1.3 Propulsion System .............................................................................................................. 8 2.1.4 Landing-Gear ...................................................................................................................... 8 2.1.5 Proposed Configuration ...................................................................................................... 8 3. Weight Sizing ...................................................................................................................................... 9 3.1 Mission Weight Estimates ......................................................................................................... 9 3.1.1 Database for Takeoff and Empty Weights from Similar Airplanes .................................... 9 3.1.2 Determination of Weight Regression Coefficients A and B ............................................... 9 3.1.3 Determination of Mission Weights ................................................................................... 10 3.2 Takeoff Weight Sensitivities ................................................................................................... 13 3.2.1 Manual Calculation of Takeoff Weight Sensitivities ........................................................ 13 3.2.2 Calculation of Takeoff Weight Sensitivities using the AAA Program ............................. 15 3.2.3 Trade Studies .................................................................................................................... 16 3.3 Conclusion ............................................................................................................................... 18 4. Performance Sizing ........................................................................................................................... 19 4.1 Manual Calculation of Performance Constraints ..................................................................... 20 4.1.1 Stall Speed ........................................................................................................................ 20 4.1.2 Takeoff Distance ............................................................................................................... 20 4.1.3 Landing Distance .............................................................................................................. 21 4.1.4 Drag Polar Estimation ....................................................................................................... 21 4.1.5 Climb Constraints ............................................................................................................. 23 4.1.6 Speed Constraint ............................................................................................................... 24 4.1.7 Maneuvering Constraint .................................................................................................... 25 4.2 Calculation of Performance Constraints with the AAA Program............................................ 26 4.2.1 Stall Speed ........................................................................................................................ 26 4.2.2 Takeoff Distance ............................................................................................................... 27 4.2.3 Landing Distance .............................................................................................................. 27 4.2.4 Drag Polar Estimation ....................................................................................................... 28 4.2.5 Climb Constraints ............................................................................................................. 30 4.2.6 Speed Constraint ............................................................................................................... 31 4.2.7 Maneuvering Constraint .................................................................................................... 31 4.3 Summary of Performance Constraints ..................................................................................... 32 4.4 Propulsion System Selection ................................................................................................... 33 4.4.1 Propulsion System Type ................................................................................................... 33 4.4.2 Number of Engines ........................................................................................................... 34 4.5 Summary of Performance Sizing ............................................................................................. 35 5. Fuselage Design ................................................................................................................................ 36 vi 5.1 Layout Design of the Cockpit.................................................................................................. 36 5.1.1 Dimensions and Weights for Crew Members ................................................................... 36 5.1.2 Layout of Cockpit Seating and Cockpit Controls ............................................................. 38 5.1.3 Determination of Visibility from the Cockpit ................................................................... 41 5.1.4 Cockpit Layout ................................................................................................................. 43 5.2 Layout Design of the Fuselage ................................................................................................ 44 5.3 Summary
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