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AVIAVIS Short Range High Capacity Transport Aircraft Design

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AVIAVIS Short Range High Capacity Transport Aircraft Design AV I AV I S SHORT RANGE,HIGH CAPACITY AIRCRAFT DESIGN UNIVERSITY OF CALIFORNIA,DAV I S Design Report June 10, 2020 Authors: Nahom Benyam Emre Mengi Christopher Pribilo Zachary Price Yashdeep Sidana Faculty Advisors: C.P. ”Case” van Dam, PhD Jared Sagaga Ryan Han 2020 AIAA Design Competition Team Members AIAA Number Signature Nahom Benyam 1109268 Emre Mengi 984297 Christopher Pribilo 1082933 Zachary Price 1109176 zachhim Yashdeep Sidana 1109292 1 Abstract This report includes a detailed design of a short-range high capacity aircraft as well as a post-design analysis in accordance with the research for proposal given by the American Institute of Aeronautics and Astronautics. The report includes the work of the AVIAVIS student design team at the University of California, Davis who designed the SRHC-530G aircraft. The designed aircraft aims to reduce the problem of overcrowded airports at major economic hubs without the size and cost that comes with long range capability. The SRHC-530G includes a twin-engine layout mounted on the back of the fuselage with a cruciform tail configuration, ensuring structural stability and clearance for the large GE9x engine nacelles. The aircraft is designed to carry 414 passengers in a two-class configuration with a twin-aisle setup and is optimized for short-haul routes of 700 nautical miles. The maximum range of the aircraft is 3700 nautical miles with maximum payload at 35,000 ft cruise altitude and cruising speed of Mach 0.8. The maximum take-off weight of the aircraft is 566,000 pounds with a take-off ground roll of 7500 feet to clear a 35 foot obstacle. The SRHC-530G will also utilize hydrogen as a fuel source to reduce the carbon footprint, revolutionize air travel, and save money on operational costs. With its capabilities, the SRHC-530G is expected to lead the commercial aviation market in efficiency and reducing congestion at airports around the world. 3 Contents 1 Detailed Design - Hydrogen Storage 1 2 Introduction 12 2.1 Report Outline . 13 3 Concept Evolution & Final Configuration 14 3.1 Design Goals . 14 3.2 Market Study . 15 3.3 Baseline Aircraft Specifications . 17 3.4 Preliminary Sizing . 18 3.4.1 Weight Estimation . 18 3.4.2 Stall Speed, Takeoff, & Landing Sizing . 18 3.4.3 Preliminary Drag Polar . 19 3.4.4 Climb Sizing . 19 3.4.5 Sizing Diagram . 21 3.5 Carpet Plots . 23 3.6 Trade Study . 25 3.6.1 Fuselage Configuration . 25 3.6.2 Wing Location [33] . 26 3.6.3 Tail Configuration [30] . 27 3.7 Chosen Design Parameters . 30 3.7.1 Fuselage . 30 3.7.2 Engine Placement . 30 3.7.3 Wing Placement . 30 3.7.4 Tail Configuration . 30 3.8 Final Configuration . 31 3.8.1 3-D View of the Final Design . 31 3.8.2 Summary of the Aircraft Parameters . 34 4 Propulsion Systems 35 4.1 Propulsion Requirements & Engine Selection . 35 4.2 Alternative Fuel Source Candidate - Hydrogen . 36 4 5 Weight and Balance & Component Weights 37 6 Aerodynamics 40 6.1 Aerodynamics Overview . 40 6.2 Airfoil Selection and Characteristics . 43 6.3 High-Lift Systems . 45 6.4 Airplane Drag Breakdown . 49 6.5 CFD Analysis . 50 6.5.1 Wingtip Cant Angle Trade Studies . 51 6.5.2 Airplane (3D) Lift Curves (cruise, takeoff, landing) . 52 6.5.3 Airplane Drag Polars (Cruise, Takeoff, Landing) . 53 7 Stability and Control 54 7.1 Horizontal Tail Sizing . 54 7.2 Vertical Tail Sizing . 55 7.3 Aircraft Trim Diagram . 56 7.4 Control Surface Sizing . 58 7.5 Pitch, Roll, and Yaw Characteristics . 59 8 Performance 60 8.1 Takeoff and Landing . 60 8.1.1 Takeoff . 60 8.1.2 Landing . 60 8.2 Climb Requirements . 61 8.3 Cruise Performance & Payload-Range . 62 8.4 Comparison with Baseline/Competing Aircraft . 63 8.5 Comparison with Baseline/Competing Aircraft . 63 9 Structural Layout, Materials, Manufacturing 64 9.1 Aircraft Structure, Material, and Manufacturing Choices . 64 9.2 V-n Diagram . 66 10 Systems 67 10.1 Cabin Layout . 67 10.2 Cockpit . 70 5 10.3 Emergency Egress, Fire Protection Safety Systems . 71 10.4 Landing Gear . 73 11 Detailed Design and Analysis: Hydrogen Storage 75 11.1 Sizing and Structures . 76 11.1.1 Shell . 76 11.1.2 Frame . 76 11.2 Storage . 79 11.3 Materials and Insulation . 81 11.3.1 Materials . 81 11.3.2 Insulation . 81 11.4 Structural Analysis . 83 11.5 Conclusions and Future Work . 84 12 Cost and Utilization 85 12.1 Capital Costs . 85 12.2 Utility Cost . 87 12.3 Comparisons to Competing Aircraft . 90 12.4 Lifecycle CO2 Analysis . 90 13 Conclusions and Recommendations 91 14 References 92 15 Appendix 97 15.1 Fuselage Calculations . 97 15.2 Weight Excursion Diagram Calculations . 99 15.3 Payload-Range Diagram Calculations . 100 15.4 Drag Breakdown: Parasitic Drag . 102 15.5 Aircraft Part Sizing Based on Max Takeoff Weight . 103 15.6 Calculating Various Landing Gear Parameters . 104 List of Tables 1 AVIAVIS Design Specifications . 12 6 2 Comparable Aircraft Specifications [3][6][8][9][19] . 17 3 Preliminary Sizing Results . ..
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