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Airplane H-868 TECH LIBRARY KAFB. NM ___~~~.~ ~~ " . ~- ~ , I 2. Government Accession No. 3. Recipient's Catalog No. NASA CR-2561 "~- I ~ "" "~"" I"I b' I 4. Title and Subtitle Date I 5. Report I June 1975 APPLICATION OF ACTIVE CONTROLS TECHNOLOGY TO THE 6. Performing Organization Cod8 NASA JETSTAR AIRPLANE H-868 -. .. .. .- - - 7. Author(s1 8. Performing Organization Report No. R. H. Lange, J. F. Cahill, M. C. Campion, E. S. Bradley, D. G. MacWilkinson and J. W. Phillips " ~ 10. Work Unit ." ~~ ~~~ .. No. 9. Performing Organization Name and Address Lockheed-Georgia Company [11. Contractor Grant No. Marietta, Georgia NAS4-2121 '13.Type Report and Period ~ .- -. "". - --. ~~ ~ of Covered 12. SponsoringAgency Name andAddress Contractor Report - Final National Aeronautics and Space Administration 14. SponsoringAgency Code Washington, D. C. 20546 ".. ""I 15. Supplementary Notes NASA Technical Monitor: Dwain A. Deets, NASA Flight Research Center 16. Abstract A study has been made of the feasibility of modifying a JetStar air- plane into a demonstrator of benefits to be achieved from incorporating active control concepts in the preliminary design of transport type air- craft. Substantial benefits are shown in terms of fuel economy and community noise by virtue of reduction in induced drag through use of a high aspect ratio wing which is made possible by a gust alleviation system. An intermediate configuration was defined which helps to isolate the benefits produced by active controls technology from those due to other configuration variables. Also, an alternate configura- tion which incorporated composite structures, but not active controls technology, was defined in order to compare the benefits of composite structures with those of active controls technology. 117. Key117. (SuggestedWords Author(s)) by I 18. Distribution Statement Active controls technology Control-configured vehicle Unclassified - Unlimited Supercritical wing STAR Category 05 Design techniques 19. Security Classif. (of this report) 20. Security Classif. (of this page) NO. of Pages 22. Rice'21. Unclassified Unclassified 206 $7.25 *For sale by the National Technical Information Service, Springfield, Virginia 22151 TABLE OF CONTENTS -Page LIST OF FIGURES V LIST OF TABLES xi SUMMARY 1 INTRODUCTION 2 SYMBOLS 3 ABBREVIATIONS 9 STUDY OBJECTIVES, TECHNICAL APPROACH, AND 10 DESIGN REQUIREMENTS Study Objectives ' 10 Technical Approach 10 Design Requirements 11 METHODOLOGY AND BASIC DATA 15 Aerodynamic Data 15 Struc tura I Loads Data 16 Design Integration 16 Active Control System Development 17 ACT CONFIGURATION DEFINITION 18 Parametric Analysis 18 Wing Definition 18 Empennage Sizing and Definition 19 Control Surface Definition 20 Loads 20 FI utter 20 Configuration Description 21 Weight Summary 21 Airplane Performance 21 Active Controls System Implementation 24 Active Controls System Redundancy 27 INTERMEDIATE CONFIGURATION DEFINITION 31 Parametric Analysis 31 Selection Procedure 31 ...Ill P TABLE OF CONTENTS (Cont'd) -Page High Lift Data 32 Design Integration 33 Weight Summary 33 ALTERNATE CONFIGURATION DEFINITION 35 Parametric Analysis 36 Design Integration 36 Weight Summary 37 Performance 38 ACTIVE CONTROL TECHNOLOGY BENEFIT ANALYSIS 39 Ride Qualities 39 Community Noise Reduction 39 performance Improvement 40 Weight Comparison 40 BENEFIT PROJECTIONS FOR NEW DESIGNS 42 STUDY CONCLUSIONS 42 REFERENCES 43 APPENDIX A - AERODYNAMIC DATA AND DESIGN RATIONALE 45 APPENDIX B - STRUCTURAL LOADS ANALYSIS FOR THE ACT 53 CONFIGURATION APPENDIX C - DESIGN INTEGRATION 67 APPENDIX REFERENCES 77 FIGURES 78 IV FIGURES -Page 1. Study Plan 78 2. Center of Gravity Envelope 79 3. Structural Design Airspeeds 80 4. Wing Thickness Ratio 81 5. ACT Configuration Operating Weight and 82 Mission Fuel Requirement Matrix 6. Selection of ACT Configuration 83 7. Wing Twist and Camber 84 8. Effect of Trim and Stability on Horizontal Tai I Volume 85 9. Effect of Horizontal Tail Volume on 86 Short Period Damping 10. Vertical Tail Sizing 87 11. Dutch-rol I Requirements 88 12. ACT Configuration Empennage Geometry 89 13. ACT Airplane Configuration 90 14. ACT Airplane Wing Layout 91 15. ACT Configuration Low SpeedDrag Polars 92 16. ACT Clean Configuration Drag Polars 93 17. ACT Configuration Specific Range Data, 94 1 0668 M (35 000 Ft ) 18. ACT Configuration Specific Range Data, 95 11277.6 M (37000 Ft) 19. ACT Configuration Specific Range Data, 96 11887.2 M (39000 Ft) 20. ACT Configuration Specific Range Data, 97 12801.6 M (41 000 Ft) 21. ACT Configuration Specific Range Data, 98 131 06.4 M (43000 Ft) 22. ACT Configuration Specific RangeData, 99 13716 M (45000 Ft) V FIGURES (CONT'D) -Page 23. Command Control Added to Stability Augmentation 100 24. Flight Controls Pitch Axis 101 25. Lateral-Directional Augmentation 1 02 26. Lateral-Directional Stability Derivatives 103 27. Power Servo Mechanization 104 28. Mission Fuel Requirement and Operating Weight, 1a5 Intermediate Configuration 29. Intermediate Configuration Effect of Sweep on Ride 106 Discomfort index 30. Intermediate Configuration Selection 107 31. Intermediate Configuration LOW Speed Drag Polars 108 32. Intermediate Configuration 109 33. Intermediate Airplane Wing Layout 110 34. Alternate Configuration Mission Fuel and 111 Operating Weight 35. Alternate Configuration Selection 112 36. Alternate Configuration 113 37. Alternate Airplane Wing Layout 114 38. High-Lift Performance Comparison 115 39. Noise Profile Comparison FAR 36 Rules EPNdB 116 A1 . Experimental Lift and Moment Data 117 A2 Supercritical Wing Transonic Characteristics 118 A3. JetStar Model 1329-6A 119 Clean Configuration Drag Polars A4. JetStar Model 1329-6A Wing Fxternal Tank Drag 120 A5. JetstarModel 1329-6A Drag-Rise Characteristics 121 A6. Tail-Off Pitching Moment Characteristics 122 A7. Airfoil Lift Pitch Characteristics 123 A8. Full Scale Corrections to Maximum Lift Coefficient 124 vi FIGURES KONT'D) -page A9. Tail-Off Lift and Pitch Characteristics 125 A1 0. Wing Lift Characteristics 126 All. Wing Pitching Moment Characteristics 127 A12. Wing Basic Lift Distribution 128 A13. Wing Additional Lift Distribution 129 A14. Wing Aerodynamic Center Distribution 130 A15. Wing Basic Pitching Moment Distribution 131 A16. Wing Geometry for Loads Estimation 132 A17. Flap Effectiveness 133 A18. Flap Load Distributions 134 A19. Flap Hinge Moment Coefficients 135 A20. Wing Lift Distribution - AR = 9 MACH No. = 0.80 136 A21. Wing Pitching Moment Distribution - 137 AR = 9 MACH No.= 0.80 A22. Incremental Wing Lift Distribution Due to 138 Flap Deflection A23. Incremental Moment Distribution Due to 139 Flap Deflection A24. Incremental Lift Distribution Due to 140 Flap Deflection A25. Incremental Moment Distribution Due to 141 Flap Deflection A26. Incremental Lift Distribution Due to 142 Flap Deflection A27. Incremental Moment Distribution heto 143 Flap Deflection A28. Incremental Lift Distribution Due to 144 Flap Deflection vi i .. FIGURES (CONT'D) \ -Puge A29. IncrementalMoment Distribution Due to 1 45 Flap Deflection A30. Flap Effectiveness 146 A31 . Airplane Lift and Pitch Characteristics 147 A32. ComparisonAirplaneCharacteristics Lift of 148 A33. Comparison of AirplanePitching MomentCharacteristics 149 B1. SelectionStudy of Gust Condition 150 B2. Rigid Gust Response, No Active Controls 151 Up and Down Gusts B3. Assumed Flap Rate VariationWith HingeMoment 152 B4. Rigid Gust Response, Datum Control System 153 Up and Down Gusts B5. Rigid Gust Response,Datum Control System 154 Reduced C , Up and Down Gust h 0 B6. Effect of Elevator Gain, GE 155 B7. Effect of Flap and Elevator Gains 156 B8. Effect of Flap Time Constant, r (Washout ) 157 B9. Effect of Elevator Sensor Location 158 B10. Effect of Control Surface Rate - 6 159 611. Effect of Flap Hinge Moment at a= 0 160 B12. Effect of Elevator Gain, G 161 E B13. Effect of FlapConstant, t (Washout) 162 B14. Effect of Control Surface Rate, 6 163 815 Effect of Flap Hinge Moment at a= 0 164 B16. Effect of Gust Velocity, w 1 65 G viii FIGURES (CONT'D) Page 817. Rigid Response to Step Elevator, 166 Effect of Elevator Gain B18. Maneuver Load Variation with Elevator Gain, G 167 E B19. Flexible Upgust Response, No Active Controls 168 820. Flexible Downgust Response, No Active Controls 169 821. Wiq Root Bending Moment 170 B22. C. G. LoadFactor 171 B23. F!exible UpGust Response, 172 Effect of Lag Plus Washout Filter B24. Flexible Downgust Response, 173 Effect of Lag Plus Washout Fi I ter B25. Flexible Wing Root Bending Moment 174 B26. Effect of Flap Washout Filter Gain 175 B27. Effect of Flap Lag Filter Gain 176 828. Effect of Flap Washout and Lag Filter Gains 177 829. Effect of Flap No-Load Rate - io 178 830. Effect of Flap No-Load Rate - do 179 B31. Effect of Elevator Gain 180 832. Structural Design Airspeeds and Flutter Design Point 181 833. Typical Flutter Analysis Results Symmetric Case - 182 Empty Fuel B34. Effect of Fuel on Wing Flutter Speed 183 B35. Wing Stiffness 184 Cl. Jetstar Model 1329-6A General Arrangement 185 C3. JetStar Existing Center Section Structure 186 c3. Geometric Effects of Wing Sweep 187 c4. GeometryBaseline Wing 0 188 IX FIGURES KONT'D) -Page c5. ACT AirplaneWing Attachment 189 Frame Modification C6. IntermediateandAlternate Configurations 190 Effect of Sweep on Thickness c7. Wing Thickness at MLG Constraint 191 (For .524 Rad (30 Deg) Sweep) C8. Inboard FlapClearance Constraint 192 (For .524 Rad (30 Deg) Sweep) c9. RearSpar Location Constraint 193 (For .524 Rad (30 Deg) Sweep) c10. Effect Geometricalof Constraintson 194 Aspect Ratio and Fuel Weight
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