Cresis UAV Critical Design Review: the Meridian
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CReSIS UAV Critical Design Review: The Meridian William Donovan University of Kansas 2335 Irving Hill Road Lawrence, KS 66045-7612 http://cresis.ku.edu Technical Report CReSIS TR 123 June 25, 2007 This work was supported by a grant from the National Science Foundation (#ANT-0424589). Executive Summary This report briefly describes the development of the three preliminary configuration designs proposed for the Meridian UAV. This report details the selection of the primary configuration and further, more detailed, analysis including Class II weight and Balance, Class II Stability and Control, Performance Analyses, Systems Design, Class II landing gear, structural arrangement, a manufacturing breakdown and a cost analysis. The design mission for this aircraft is to takeoff from a snow or ice runway, fly to a designated area, then use low frequency radar to perform measurements of ice sheets in Greenland and Antarctica. Three designs were developed: • A Monoplane with Structurally Integrated Antennas • A Monoplane with Antennas Hanging from the Wing • A Biplane with Antennas Structurally Integrated Into the Lower Wing The monoplane with antennas hanging from the wing was selected as the primary configuration for further development. This report describes the Class II design and analysis of that vehicle. i Acknowledgments This material is based upon work supported by the National Science Foundation under Grant No. AST-0424589. Any opinions, findings, and conclusions or recommendations expressed in this material are those of the author(s) and do not necessarily reflect the views of the National Science Foundation. ii Table of Contents Executive Summary..................................................................................................... i Acknowledgments ....................................................................................................... ii Table of Contents .......................................................................................................iii List of Figures.............................................................................................................. v List of Tables .............................................................................................................. vi Nomenclature ............................................................................................................ vii Abbreviations ...........................................................................................................viii 1 Summary of Preliminary Designs...................................................................... 9 2 Configuration Selection and Requirement Changes ..................................... 11 2.1.1 Engine Selection – Turboprop Variant ............................................... 12 3 Class II Design................................................................................................... 15 3.1 Class II Weight and Balance....................................................................... 15 3.1.1 The Aircraft V-n Diagram .................................................................. 15 3.2 Component Weight Estimations ................................................................. 18 3.3 Class II Stability and Control...................................................................... 22 3.3.1 Trim Diagrams.................................................................................... 22 3.3.2 Open Loop Dynamics ......................................................................... 31 3.3.3 Actuator Size and Rate Requirements ................................................ 37 3.4 Class II Aerodynamics................................................................................ 38 3.5 Propulsion ................................................................................................... 46 3.6 Performance Analysis................................................................................. 47 3.6.1 Stall Speed.......................................................................................... 47 3.6.2 Takeoff Distance................................................................................. 47 3.6.3 Climb................................................................................................... 48 3.6.4 Cruise Performance............................................................................. 48 3.6.5 Landing Distance................................................................................ 50 3.7 Systems ....................................................................................................... 51 3.7.1 Flight Control System......................................................................... 52 3.7.2 Electrical System ................................................................................ 54 3.7.3 Communications/Telemetry System................................................... 58 3.7.4 Fuel System......................................................................................... 59 3.7.5 Anti-Icing System ............................................................................... 60 3.8 Class II Landing Gear ................................................................................. 61 3.8.1 Tire Selection...................................................................................... 62 3.8.2 Strut Sizing..........................................................................................63 3.8.3 Landing Gear Integration.................................................................... 64 3.9 Structural Arrangement............................................................................... 66 3.9.1 Wing Structure.................................................................................... 67 3.9.2 Fuselage Structural Layout ................................................................. 70 3.10 Manufacturing Breakdown......................................................................... 74 3.11 Cost Analysis.............................................................................................. 75 iii 3.11.1 Research, Development, Test, and Evaluation Costs ......................... 77 3.11.2 Acquisition Cost..................................................................................77 3.11.3 Cost Estimate Summary...................................................................... 78 3.11.4 Cost Estimate Justification.................................................................. 81 4 Conclusions........................................................................................................ 84 5 References.......................................................................................................... 85 iv List of Figures Figure 1.1: Comparison of Fuel Usage for 3 Fine Scale Missions ............................. 10 Figure 1.2: Combined Takeoff Weight Regression Chart .......................................... 10 Figure 2.1 - Vivaldi Antenna ...................................................................................... 11 Figure 2.2: CAD Model of Innodyn 165TE................................................................ 13 Figure 3.1 - The Meridian UAV ................................................................................. 14 Figure 3.2 - V-n Diagram for the Meridian ................................................................ 17 Figure 3.3 - Center of Gravity Excursion for the Meridian ........................................ 20 Figure 3.4 – Component C.G. Locations .................................................................... 21 Figure 3.5 - Trim Diagram - Cruise............................................................................ 23 Figure 3.6 - Trim Diagram - Takeoff, Gear Down ..................................................... 24 Figure 3.7 - Trim Diagram - Takeoff, Gear Up .......................................................... 25 Figure 3.8 - Trim Diagram – Landing Heavy, Gear Down ........................................ 26 Figure 3.9 - Trim Diagram - Landing Heavy, Gear Up.............................................. 27 Figure 3.10 - Trim Diagram - Landing Light, Gear Down......................................... 28 Figure 3.11 - Trim Diagram - Landing Light, Gear Up.............................................. 29 Figure 3.12 - Trim Diagram - OEI.............................................................................. 30 Figure 3.13 - Drag Polars for the Meridian without Antennas ................................... 41 Figure 3.14 - Lift-to-Drag for the Meridian without Antennas .................................. 42 Figure 3.15 - Drag Polars for the Meridian with Antennas ........................................ 43 Figure 3.16 - Lift-to-Drag for the Meridian with Antennas........................................ 44 Figure 3.17 - Relationship of Parasite Area and Wetted Area for Various Single Engine Aircraft [6]...................................................................................................... 46 Figure 3.18 - Cloud Cap Tech. Piccolo II Autopilot [36]........................................... 52 Figure 3.19 - Piccolo II Architecture [36] .................................................................. 53 Figure 3.20 - Piccolo Ground Station and Pilot Controller (Operator Interface Not Shown) [36] ................................................................................................................ 53 Figure 3.21 - Electrical Load Profile for the Meridian