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A Preliminary Study of Solar-PO- Aircraft and Associated Power-T% NASA Contractor Report 3699 --I A Preliminary Study of Solar-PO- Aircraft and Associated Power-T% David W. Hall, Charles D. Fortenbach, Emanual V. Dimiceli, and Robert W. Parks CONTRACT NAS l- 1697 5 DECEMBER 1983 LQAN cow: IWIJRN -m AFWL TECJ-tNICAL iI3RA.%Y WRTLAND AFB, NM 8Tiit 2s 25th Anniversary 1958-1983 i, TECH LIBFWY KAFB, NM IIllill lllll111111111 III1IllIll11 III Ill1 0062313 NASA Contractor Report 3699 A Preliminary Study of Solar Powered Aircraft and Associated Power Trains David W. Hall, Charles D. Fortenbach, Emanual V. Dimiceli, and Robert W. Parks Lockheed Misdes and Space Company, Inc. SmnyuaZe, CaZifomia Prepared for Langley Research Center under Contract NASl-16975 National Aeronautics and Space Administration Scientific and Technical Information Branch 1983 -. - --we- -.-- ..--- -A ---.- -_---. - LI._--A--_-----_-___ ._ TABLE OF CONTENTS I Page SUMMARY................................ xi INTRODUCTION ............................. 1 Background ............................ 1 The Concept of Solar Powered Flight ............... 5 The Purpose of This Investigation ................ 6 Scope .............................. 11 SYMBOLS ................................ 12 POWERSUBSYSTEM SIZING METHODOLOGY . 20 Overview ............................. 20 Atmospheric Environment ..................... 28 Solar Radiation Environment ................... 31 Candidate Power Train Configurations ............... 47 Component Characterization .................... 55 VEHICLE DESIGN METHODOLOGY ...................... 88 Overview ............................. 88 Parametric Analysis Methods ................... 89 Aerodynamic Characterization ................... 96 Structure Mass Estimation .................... 105 Effect of Flight Profile on Vehicle Size ............. 114 Candidate Configurations ..................... 118 DISCUSSION OF RESULTS ......................... 125 Comparison of Candidate Power Trains ............... 125 iii TABLE OF CONTENTS (Continued) Page Capabilities of SOTA Components and Recommended Goals ...... 125 Vehicle Sizing Results ...................... 130 CONCLUDING REMARKS ........................... 151 Missions ............................. 151 Solar Radiation and Atmospheric Properties ............ 151 Energy Collection and Storage Components ............. 152 Thrust Generation Components .................... 152 Airframe Related Issues ..................... 153 APPENDICES A. Meteorological Data Applicable to Primary Mission ...... 154 B. Fuel Cell and Electrolyzer Performance Characteristics ... 159 C. Reactant Tank Sizing .................... 171 D. Heat Transfer for Energy Collector Surfaces ......... 176 E. A Theoretical Definition of Equilibrium Altitude ...... 183 REFERENCES .............................. 191 iv LIST OF FIGURES Page Figure 1. Existing Civilian and Military Missions Which Could Be Fulfilled by Solar HAPPs ............... 3 Figure 2. Benefits of High Altitude Flight ............ 3 Figure 3. Measured Gust Velocity Environment .......... ; 4 Figure 4. HAPP Balance Problem .................. 7 Figure 5. Generalized Power Train Schematic ............ 22 Figure 6. Solar Radiation Environment ............... 32 Figure 7. Variation in Solar Radiation Due to Earth's Elliptical Orbit.......................... 33 Figure 8. Seasonal Variation of Sun's Path Across the Sky . 34 Figure 9. Atmospheric Attenuation Coefficient . 36 Figure 10. Predicted Variation of Direct Intensity of Solar Flux with Altitudes . 36 Figure 11. The Solar Spectrum . 38 Figure 12. Spectral Shifts Due to Atmospheric Attenuation . 39 Figure 13. Earth-Sun Platform Geometry . 42 Figure 14. Albedo View Factor . 42 Figure 15. Earth Radiation as Seen From HAPP Reference Plane . 43 Figure 16. Illumination Integral Versus View Angle . 45 Figure 17. Comparison of Radiation Intensities . 46 Figure 18. Remote Source Power Train Alternatives for HAPPs . 49 Figure 19. Direct Drive Solar Thermal Power Train Configuration . 51 Figure 20. Indirect Drive Solar Thermal Power Train Configuration. 52 Figure 21. Solar Photovoltaic Power Train Configuration . 54 V LIST OF FIGURES (Continued) Page Figure 22. Cell Temperature and Efficiency as Functions of Time OfDay........................... 59 Figure 23. Solar Cell - Electrolyzer Matching for Horizontal Cells . 61 Figure 24. Determination of Generalized Mass Properties Constants for Fuel Cell and Electrolyzer Accessories . 66 Figure 25. Fuel Cell and Electrdlyzer Power Section Mass Data . 70 Figure 26. Baseline Heat Transfer Conditions . 72 Figure 27. Electrolyzer Efficiency and Mass Flow Rate as a Function OfTimeofDay....................... 74 Figure 28. Collector Area and Power Train Mass Versus Fuel Cell Efficiency . 80 Figure 29. Collector Area and Power Train Mass Versus Electrolyzer Efficiency . 80 Figure 30. Mass & Efficiency Summary for Motor and Controller . 82 Figure 31. Propeller Design for 1OKw Thrust Power . 85 Figure 32. Propeller Mass Optimization . 86 Figure 33. Baseline Propeller Design . 87 Figure 34. Historical Ranges of Power Loading and Wing Loading . 90 Figure 35. Parametric Sizing Methodology Results Showing Data Presentation Method Used . 91 Figure 36. Determination of Maximum Payload Weight Per Unit Installed Power . 94 Figure 37. Determination of Maximum Payload Design Point . 95 Figure 38. Typical Drag Polar . 96 Figure 39. Wing Panel Minimum Drag Coefficient . 99 vi LIST OF FIGURES (Continued) Page Figure 40. Experimentally Determined Lift Versus Drag Polars for Several High-Lift Airfoils . 103 Figure 41. Airfoil Characteristics for Four Low Speed Airfoils . 104 Figure 42. Preliminary Structural Design Utilizing Advanced Composities . 108 Figure 43. Relationship of Constant Dynamic Pressure to Performance Parameters with Increasing Altitude . 115 Figure 44. Four Possible Flight Profiles . 115 Figure 45. Effect of Flight Profile on Vehicle Size . 118 Figure 46. Configuration Evolution 1977 - 1979 . 120 Figure 47. Configuration Evolution 1980 - 1981 . 121 Figure 48. A Typical Variable Geometry Solar HAPP Configuration . 123 Figure 49. Baseline Solar Photovoltaic High Altitude Powered Platform........................ 124 Figure 50. Sensitivity of Solar Array Area to Component Efficiency Variations . 127 Figure 51. Sensitivity of Overall Power Train Mass to Component Efficiency Variations . 127 Figure 52. Sensitivity of Overall Power Train Mass to Solar Cell Efficiency Variations . 128 Figure 53. Variations of Solar Array Area to Solar Cell Efficiency . .' . y :. ? _ . 128 Figure 54. Effect of Changes in Altitude on Aircraft Size for the Baseline Configuration . 133 Figure 55. Effect of Changes in Latitude on Aircraft Size for the Baseline Configuration . 134 Figure 56. Effect of Changes in Day of Year on Aircraft Size for the Baseline Configuration . 135 vii LIST OF FIGURES (Continued) Page Figure 57. Parametric Determination of Solar HAPP RPV's for Primary Mission with Reduced Paylaod Mass . 136 Figure 58. Sensitivity of Collector Area to Payload Power and Duty Cycle . 138 Figure 59. Sensitivity of Power Train Mass to Payload Power and Duty Cycle . i 138 Figure 60. Sensitivity of Collector Area to Orientation at 38ON Latitude . 140 Figure 61. Sensitivity of Collector Area to Orientation at 20°N Latitude . 140 Figure 62. Sensitivity of Collector Area to Orientation at Oo Latitude . 141 Figure 63. Sensitivity of Power Train Mass to Collector Orientation at 380N Latitude . 141 Figure 64. Sensitivity of Power Train Mass to Collector Orientation at 20°N Latitude . 142 Figure 65. Sensitivity of Power Train Mass to Coleictor Orientation at O" Latitude . 142 Figure 66. Altitude-Velocity Profile for Baseline Solar HAPP RPV.......................... 143 Figure 67. Load Diagram for the Baseline Solar HAPP . 144 Figure 68. The Equilibrium Flight Energy Envelope for a Solar HAPP RPV Designed for the Primary Mission . 146 Figure 69. Planar Cross-Sections of Equilibrium Flight Energy Envelope . 146 Figure A-l Nearest Gridpoint Average to Primary Mission Area . 155 Figure A-2 Wind Histograms for the Southern (Left) and Northern (right) Extremities of the San Joaquin Valley . 156 viii LIST OF FIGURES (Continued) Page Figure A-3 Wind Flow Charts for the Continental United States at 22.6 Km (74 Kft) . 157 Figure A-4 Wind Profile for Cape Canaveral, Florida . 158 Figure B-l Fuel Cell Voltage as a Function of Current Density . 168 Figure B-2 Fuel Cell Voltage Efficiency as a Function of Current Density . 168 LIST OF TABLES Page Table 1. Missions Considered in This Study .............. xi Table 2. Why a High Altitude Long Endurance Platform? ........ 5 Table 3. Variables Affecting HAPP Parametrics ............ 8 Table 4. Major HAPP Design Drivers .................. 9 Table 5. HAPP Variables and Their Effects .............. 10 Table 6. Wind Speeds Greater than Design Condition . 30 Table 7. Summary of Reflectance Data for Earth Surface Features and Clouds . 41 Table 8. Alternative Technologies Available for High Altitude Long Endurance RPVs . 48 Table 9. Summary of Aggregate Efficiencies . 53 Table 10. Characteristics of Thermal Solar Energy Collectors . 57 Table 11. Characteristics of Photovoltaic Solar Energy Collectors . 60 Table 12. Theoretical Performance of Candidate Fuel Cell Reactants . 63 Table 13. Data on Mass Properties of Fuel Cell and Electrolyzer Accessories . 66 Table 14. Fuel Cell and Electrolyzer Power Section Mass Data . 69 Table 15. Vehicles Required for Each Flight Profile with Perfect Component Efficiencies . 116 Table 16. Comparison of Thermal and Photovoltaic
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