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NASA Contractor Report 177585 Technology Needs for High-Speed Rotorcraft (I) J. B. Wilkerson, J. J. Schneider, and K. M. Bartie _'A'_, _ I I7_ : _)) T_-CH"_-)L?GY _":_"__ r _ "_ c_.C CONTRACT NAS2-13041 May 1991 National Aeronautics and Space Administration NASA Contractor Report 177585 Technology Needs for High-Speed Rotorcraft (I) J. B. Wilkerson, J. J. Schneider, and K. M. Bartie Boeing Helicopters P.O. Box 16858 Philadelphia, PA 19142 Prepared for Ames Research Center CONTRACT NAS2-13041 May 1991 National Aeronautics and Space Administration Ames Research Center Moffett Field, California94035-1000 TABLE OF CONTENTS VOLUME I PAGE PREFACE .................................................................................................. iv _MMAR___'__°___'____°*-_____*______.__________°_____*____°_'____t__'__*_____________*____-*°____ .... °° 1 LIST OF FIGURES ................................................................................... 7 LIST OF TABLES ..................................................................................... 9 INTRODUCTION ..................................................................................... 10 SECTION 1. INITIAL CANDIDATE CONCEF_ CANDIDATE HIGH-SPEED ROTORCRAFT CONCEPTS .................... 12 Sizing and Constraints ................................................................. 12 Concept Definition ....................................................................... 16 CANDIDATE HIGH-SPEED ROTORCRAFT SELECTION ................. 37 Down-Select to 5 Candidates ...................................................... 38 DESIGN REQUIREMENTS ................................................................... 41 Mission Profiles ........................................................................... 41 Military Transport Rotorcraft .................................................... 41 Civil Passenger Rotorcmit ......................................................... 41 MISSION ANALYSIS ............................................................................. 42 TECHNOLOGY DEFINITION ............................................................... 43 Weights ....................................................................................... 43 Aerodynamics ............................................................................. 44 Propulsion ................................................................................... 45 TASK I CONCEPT TRADEOFFS .......................................................... 47 Concept Description and Sizing ................................................ 47 Conventional Tiltrotor ................................................... 47 Canard Tiltrotor ............................................................. 48 Variable Diameter Tiltrotor ........................................... 49 FoldingTiltrotor ............................................................. 50 Tiltwing ........................................ ................................... 50 CONCEPT COMPARISON ..................................................................... 52 Sensitivity Study ......................................................................... 53 Relative Cost ............................................................................... 54 DOWN-SELECT TO 2 CONCEF_ ....................................................... 54 SECTION 2. TECHNOLOGY EVALUATION CONCEPT DEFINITIONS ...................................................................... 58 High Speed Civil Tiltrotor .......................................................... 58 Military Folding Tiltrotor ........................................................... 62 HIGH SPEED CIVIL TILTROTOK ....................................................... 65 Rotor Performance ...................................................................... 65 Vehicle Performance .................................................................. 67 Acoustics ...................................................................................... 71 iii PRECEDING PAGE BLANK NOT FILMED TABLE OF CONTENTS - Continued PAGE MILITARY FOLDING TILTROTOR ..................................................... 72 Rotor Performance ..................................................................... 72 Vehicle Performance ................................................................... 76 Acoustics ..................................................................................... 78 VEHICLE SENSITIVITY ....................................................................... 80 Design Parameter Sensitivity .................................................... 80 Technology Sensitivity ............................................................... 84 AEROELASTICITY .................................................................................. 89 RELATIVE COST ASSESSMENT ......................................................... 90 STRUCTURES AND MATERIALS ......................................................... 93 SECTION 3. ENABLING TECHNOLOGY PLAN GENERAL DISCUSSION ....................................................................... 95 CRITICAL DESIGN ISSUES ................................................................. 97 High Speed Civil Ti]trotor .......................................................... 97 Military Folding Tiltrotor ........................................................... 98 COMMON CRITICAL TECHNOLOGIES .............................................. 100 Aerodynamics: High-Speed Wing/Canard Design ..................... 100 Aeroelasticity: Forward-Swept-Wing Design ............................ 102 Structures, Materials, and Weights ........................................... 103 Flight Control Laws .................................................................... 105 HIGH SPEED CIVIL TILTROTOR - SPECIFIC DESIGN ISSUES ...... 107 Rotor Aerodynamic Design ......................................................... 107 Aeroelastic Stability .................................................................... 108 Acoustics ...................................................................................... 110 External Noise ................................................................. 112 Internal Noise .................................................................. 112 Vibration ...................................................................................... 113 Flight Control Laws And Development_ ..................................... 115 MILITARY FOLDING TILTROTOR - SPECIFIC DESIGN ISSUES .. 116 Convertible Engine Propulsion ................................................... 117 Hub Design .................................................................................. 118 Automated Stop/Fold Procedure ................................................ 119 Aeroelasticity ............................................................................... 120 Flight Control Laws ..................................................................... 122 CONCLUSIONS ....................................................................................... 124 REFERENCES ......................................................................................... 125 VOLUME II (APPENDICES) A. SUBSTANTIATING DATA FOR TASK I................................... A- 1 B. SUPPLEMENTAL DATA FOR TASK II .................................... B-1 iv PREFACE This report was prepared for the National Aeronautics and Space Admnistration, NASA, Ames Research Center, Moffett Field, CA., in fulfillment of NASA Contract NAS2-13041. The study was performed for NASA Ames Research Center by Boeing Helicopters during the period June 1989 through November 1990. Mr. Peter Talbot and Mr. Marty Maisel of NASA Ames Research Center were the technical monitors. The Boeing Helicopters Program Manager was Mr. J. B. Wilkerson and the Configuration Man- ager was Mr. J. J. Schneider. Volume I of this report was prepared by Mr. J. Schneider and Mr. J. Wilkerson. Volume II was prepared by Mr. J. Wilkerson. Mr. K. Bartie prepared all the graphics, assisted in final report preparaton, and did the final report layup. Ms. M. McGuire typed the report. In addition, the following Boeing Helicopters engineering and management personnel made significant contributions to this study effort in either configuration analysis or in preparing the enabling technology plans: Acoustics: H. Sternfeld P. Ziegenbein Aerodynamics: L. Dadone J. Liu D. Paisley Cost Analysis: B. Celani Z. Jasnoff M. Smith Dynamics: R. Gabel P. Lang F. Tarzanin B. Vlaminck Flight Controls: F. Dones Handling Qualities: P_ Lacy Structures and Materials: G. Rossi Propulsion: R. Semple D. Woodley Weights: S. Dyess J. Wisniewski Joseph B. Wi]kerson SUMMARY The objective of this study was to identify high-speed rotorcraR concepts and the corresponding technology needed to greatly extend the cruise capabilities of rotorcraR beyond current capabili- ties, up to 450 knots, while retaining the helicopter attributes of low downwash velocities and temperatures: the so-called =sot_ footprint" characteristic. Task I conducted a broad survey which identified 20 candidate rotorcraft concepts with high- speed potential. These concepts were qualitatively evaluated and graded against 17 key discrimi- nators. The five concepts with the most potential were: 1. Conventional tiltrotor (a baseline rotorcraR) 2. Forward-swept-wing/canard tiltroter with advanced- geometry rotor 3. Forward-swept-wing/canard tiltrotor with variable diameter rotor 4. Forward-swept-wing/canard
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