DOCSLIB.ORG

Advancementof- Proprotorechnology

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Advancementof- Proprotorechnology ..... _:'_;''' ' 00000001 ADVANCEMENTOF- PROPROTORTECHNOLOGY ,. TASK[ - DESIGNSTUDYSUMMARY , (NASACONTRACTNAS2-5386) (N.kSA-CR-1111682) ADVkliCBBENT OF PE_ROTOE NTq-11833 TECUNOLOG¥. TASK I- DESIGN STUDY SUNM_R¥ (Bell--HelicopteE Co,) 209 p HC $12,50 CSCL 01C Unclas G3/02 23270 REPORT 300,099"003 ; _'.' ',' ._ :_-)1 _I"1 i|,_ COMPANY POST OFFICE _OX 482 f-ORT WORTH TEXAS 76101 _ _ COMPANY 00000001-TSA03 13FL.L HELICOPTEI_ (:OMI-'ANY-- CoNT._NtS ," I • SUMMARY I-l II. INTRODUCTION II-I A. The Need for VTOL B. The Failure to Meet the VTOL Need II-2 C. The NASA Proof-Of-Concept Program II-2 D. The Tilt-E_oprotor Aircraft - A Promising VTOL Concept II-4 E. The Tilt-Proprotor Proof-Of-Concept Aircraft Evaluation Program II-6 ..;; III. DESIGN DESCRIPTION IIl-1 7_i A. General iII-i .....I B. Design Criteria III-9 _'_t. C. Proprotor 111-10 _" i. Blades 111-10 2. Hub III-i0 D. Drive System 111-11 E. Powerplant 111-12 I. Engine 111-12 2. Induction System 111-12 3. Oil System 111-13 4. Fuel System III-13 F. Airframe III-14 i. Wing III-14 2. Fuselage 111-15 3. Empennage 111-15 4. Landing Gear 111-16 G. Aircraft Systems 111-16 i. Conversion System 111-16 2. Hydraulic System 111-17 3. Electrical System 111-17 H. Aircraft Controls 111-18 I. Proprotor Controls 111-18 2. Flight Control Tli-19 3. Stability and Control Augmentation System 111-19 4. Proprotor Governor System III-20 5. Power Management 111-20 300-C99-O03 i O00000Ol-T.qAn4 J (_ BELL HELICOPTER C_O_IPAN_' CONTENTS - Continued IV. WEI_{T ANALYSIS IV-I A. Rotor Group IV-3 B. Wing Group IV-3 C.- Tail Group IV-4 D. Body Group IV-4 E. Alighting Gear Group IV-7 F. Controls Group IV-8 G.___Eng[ne Section and Nacelle Group IV-8 H. Propulsion Group IV-9 i. General Description IV-9 2. Engine Installation IV-9 _<_, 3. Conversion System IV-9 4. A_r Induction System IV-9 _'- 5. Exhaust System IV-9 _, 76.. LFubricatiel Systemon System Engine IV-IOIV-9 8. Engine Controls IV-IO 9, Startin$ System IV-lO IO. Rotor Pltch Governor Control IV-10 ii. Drive System IV-10 I. Instrument Group IV-12 J_Hydrauiics Group IV-14 K. Electrical Group IV-14 L. Electronics Group IV-14 M. Furnishings and Equipment Group IV-15 N. Air-Conditioning Equipment Group IV-15 V. APERFORMANCE. Summary V-iV-I B. Airframe Aerodynamics V-i I. Lift Analysis V-3 2. Drag Analysis V-3 I C. Proprotor Performance V-4 i. Description V-4 2. Method and Correlation V-6 I 3. Isolated Proprotor Performance V-7 D. Powerplant Performance V-7 ! I 300-099-003 it 00000001-TSA05 I i_ B FILH__.E _LI COPT£R C:O_rAN v ! CONTENTS ,ontlnued V-8 E. IIelicopter PerformaDce i, Hovering PerformaDce V-8 i 2. HelicopterRequired Level Flight Power V-8 3. Rate of Cli_b V-9 F. Airplane Performance V-9 i. Thrust Horsepower Required V-9 2. Flisht Envelope and Maximum Speed V-9 3. Maxlmum Rate of Climb V-10 4. Specific Range V-IO 5. Single Englne Performance V-10 i 6. Mission Profiles V-lO ,_ 7. STOL Performance V_ll VI. DYNAMIC STUDIES VI-I ':''Lk=-_._" A. Proprotor Dynamics VI-I ,_r'_; I. Natural Frequencies Vl-i _"_-- 2.- Loads VI-2 _':" 3. Blade Flapping VI-4 B. Airframe Dynamics Vl-4 i. Natural Frequencies VI-4 2. Vibration Levels VI-5 C. Stability Vl-6 1. Proprotor VI-6 2. Flight Mode Stability Vl-7 VII. NOISE Vll-i VIII. RECOMMENDED PROOF-OF-CONCEPT PROGRAM VIII-I A. Objective and Purpose VIII-I B. Program Plan VIII-I i. Phase I - Design and Fabrication VIII-2 2. Phase II - Flightworthiness Tests VIII-2 3. Phase III- Proof-of-Concept Flight Research VIII-5 C. Program Schedule VIII-6 IX. REFERENCES IX-I X. DESIGN LAYO_ffS x-l 300-099-003 iii 00000001-TSA06 BIEI .I 14El .ICOPTER Cn_I',_,N'," LIST OF FIGURES N__oo. T_tl______e Page I-1 Bell Model 300 Proof-Of-Concept Tilt- Proprotor Aircraft 1-3 II-i XV=/._Convertiplane 11-8 Version 266 I 11-2 Operational of Model Composite Aircraft 11-9 ] II-3 NASA-Ames_40-by--_0-Fo25-Foot Proprotor Performanceo_t Full-ScaleTest Tinunnelthe If-10 II-_ 25-Foot Proprotor Dynamic Test on Simulated Wing in the NASA 40-by-S0-Foot Full-Scale Tunnel ll-ll !_._ ,_ 11-5 Folding Proprotor VTOL Aircraft 11-12 4 ]_"" II-6 Mockup of Representative Civil Tilt- Proprotor Aircraft 11-13 11-7 Civil VTOL Aircraft Mission 11-14 11-8 Military VTOL Aircraft Mission II-15 IIl-i 25-Foot Proprotor Parameters III-22 111-2 Proprotor Stiffness and Mass Distribution 111-23 111-3 Wing Stiffness arid Panel Point Weight III-24 111-4 Fuselage Stiffness and Panel Point Weight 111-25 III-5 Vertical Tail Stiffness and Weight Distribution III-26 III-6 Horizontal Tail StlffnesE and Weight Distribution III-27 III-7 Collective Pitch Versus Conversion Angle 111-28 III-8 Differential Collect_ve Pitch Versus Conversion Angle 111-29 I 111-9 Fore and Aft Cyclic Pitch Versus Conversion Angle 111-30 I III-i0 Differential Cyclic Pitch Versus Conversion Angle 111-31 I !II-ii Differential Cyclic P_tch Versus Airspeed 111-32 I 300-099-003 {v 00000001.T_An7 BEL_! HELICOPTER _;r_._t'AN_" LIST OF FIGURES - Continued IV-I Wing Weight IV-16 IV-2 Fuselage Weight gstimation Parameters IV-I7 IV-3 Fuel System Weight IV-18 IV-4 Gear Stage Weight IV-19 IV-5 Main Transmission Schematic and Weight Data IV-20 V-I Mode[ S00 Aerodynamic Model in 7-by-lO-Foot Tunnel V-12 V-2 Airframe Lift Coefficient Versus Fuselage ,: Angle of Attac_ V-13 V-3 Airframe Drag Coefficient Versus Fuselage _?_[ Angle of Attack V-14 _ _i. ' V-4 Airframe Drag Coefficient Versus Lift _i. :. Coefficient V-15 _ V-5 Comparison of Full-Scale Aircraft Drag, Based on Tunnel Results and Calculated Data V-16 : V-6 Proprotor Blade Station Data, Radial Station 0.075 to 0.45 V-17 V=7 Proprotor Blade Section Data Blade • Station 0.45 to 0.70 V-18 V-8 Proprotor Blade Station Data, Radial I Station 0.70 to 0.90 - V-19 V-9 Proprotor Blade Section Data, Radial Station 0.90 to 1.00 q-20 I V-10 Proprotor Performance Correlation V-21 I V-If Boeing-VertBlade Parameolters[3-F(Bladeoot Diameter"E") Proprotor V-22 Versun Thrust V-23 i V-12 Proprotor Hovering Power Required V-13 Proprotor Efficie_icy Versus Shaft I Horsepower Sea Level V-24 V-if+ Proprotor Efficiency Versus Shaft I Horsepower i0,000 Feet V-25 I 300-099-003 v 00000001-TSA08 O 131::I I HEI-ICOPTElY (:C'IMI_ANY LIST OF FIGURES - Continued ¢. V-15 Proprotor Efficiency Versus Snaft V-26 Horsepower 20,000 Feet V-16 Twin Engine Proprotor Shaft Horsepower Available, Helicepter Mode V-27 V-17 Fuel Flow, Helicopter Mode V-28 V-18 Proprotor Shaft Horsepower Available Takeoff and 30-Minute Power V-29 V-19 Proprotor Shaft Horsepower Available, Normal Rated Power V-30 V-20 Fuel Flow, Airplane Mode V-31 : ,- V-21 Hover Ceilings_ V-32 j# _/ V-22 Hovering Figure of Merit V-33 :_ V-23 Proprotor Shaft Horsepower Required Versus .... ' True Airspeed, Helicopter Mode V-34 V-2q Lift Distribution Between Proprotor and Airframe in Helicopter Level Flight V-35 V-25 Rate of Climb, Helicopter Mode V-36 V-26 Thrust Horsepower Required Versus True Airspeed, Sea Level V-37 V-27 Thrust Horsepower Required Versus True Airspeed, i0,000 Feet V-38 V-28 Thrust Horsepower Required Versus True Airspeed, 20,000 Feet V-39 V-29 Proprotor Shaft Horsepower Required Versus True Airspeed, Airplane Mode, Sea Level V-40 V-30 Propro£or Shaft Horsepower Required Versus True A_rspeed, Airplane Mode, i0,000 Feet V-41 V-31 Proprotor Shaft Horsepower Required Versus True Airspeed, Airplane Mode, 20,000 Feet V-42 i V-32 AirplaneFlight EnvelopeMode and Maximum Speed, V-43 V-33 Maximum Rate of Climb, Airplane Mode V-44 I 300-099-003 vi m, E 00000001-TSA09 II_ I]I-:I .I H-FI .ICOPTER _:c,.,_,^'_v LIST OF FIGURES - Continued r, V-34 Nautical Miles Per Pound of Fuel Versus True Airspeed, Airplane Mode, Sea Level V-45 V-35 Nautlcal' Miles Per Pound of Fuel Versus True Airspeed, Airplane Mode, 10,000 Feet V-46 V-36 Nautical Miles Per Pound of Fuel Versus - True Airspeed, Airplane Mode, 20,000 Feet V-47 V-37 Single Engine Performance V-48 _: V-38 - Research Mission V-49 V-39 Civil Mission_ V-50 % V-40 Military Mission V-50 _'_!: ._I V-41 Ferry Mission V-51 ,_ " " V-42 STOL Takeoff Performance V-52 VI-l Proprotor Collective Mode Natural Frequencies VI-10 VI-2 Proprotor Cyclic Mode Natural Frequencies VI-ll Vl-3 Blade Oscillatory Stress at VH, Helicopter Mode VI-12 VI-4 Blade Limit Stress at VH, Airplane Mode VI-13 VI-5 Flapping Envelope in Airplane Mode VI-14 Vl-6 Airframe Symmetric Mode Natural Frequencies_ VI-15 VI-7 Airframe Asymmetric Mode Natural ) Frequeneies VI-16 VI-8 Pylon and Crew Station Vibration VI-17 VI-9 HelicopterPylon and CreModew Station Frequency Response, VI-18 I VI-lO PylonAirplaneand ModeCrew Station Frequency Response, Vl-19 i VI-II Mode].
Load more

Recommended publications
  • Seventeenth European Rotorcraft Forum
    ERF91-25 SEVENTEENTH EUROPEAN ROTORCRAFT FORUM Paper No. 91-25 V-22 PROPULSION SYSTEM DESIGN W. G. Sonneborn, E. 0. Kaiser, C. E. Covington, and K. Wilson Bell Helicopter Textron, Inc. Fort Worth, Texas U .S.A. SEPTEMBER 24-27, 1991 Berlin, Germany Deutsche ·oesellschaft fiir Luft- und Raumfahrt e. V. (DGLR) Godesberger Allee 70, 5300 Bonn 2, Germany OPGENOMENIN GEAUTOMATISEERDE ERF91-25 V-22 PROPULSION SYSTEM DESIGN W. G. Sonneborn E. 0. Kaiser C. E. Covington K. Wilson Bell Helicopter Textron, Inc. Fort Worth, Texas U.S.A. Abstract The next generation tiltrotor, the XV-15, truly dem­ onstrated the feasibility of the technology, especial­ The propulsion system of the V-22 Osprey, compris­ ly the tilting-engine concept. The free power tur­ ing the drive system, the power plant installation, bine allowed the rotor system to operate over a wide and the proprotor, is a unique design driven by the range of speeds without drive train shift mecha­ operational requirements of this tiltrotor aircraft. nisms. Pylon stability was satisfactory with a three­ bladed gimballed rotor attached to a stiff pylon. The drive system, which includes five gearboxes, shafting, and special nonlubricated flexible cou­ The V-22 propulsion design is the first design to plings, is described. The rationale for arrangement meet operational requirements as outlined in rigid and lessons learned is followed by a discussion of the NAVAIR specifications. Fly-by-wire control tech­ effect of special requirements such as shipboard nology simplifies the mechanical design, and use of compatibility and cooling. Lubrication system op­ composite materials achieves significant weight eration from horizontal to vertical modes, operation savings and other operational advantages.
    [Show full text]
  • Capabilities and Prospects for Improvement in Aircraft Icing Office of Aviation Research Washington, D.C
    DOT/FAA/AR-01/28 Capabilities and Prospects for Improvement in Aircraft Icing Office of Aviation Research Washington, D.C. 20591 Simulation Methods: Contributions to the 11C Working Group May 2001 Final Report This document is available to the U.S. public through the National Technical Information Service (NTIS), Springfield, Virginia 22161. U.S. Department of Transportation Federal Aviation Administration NOTICE This document is disseminated under the sponsorship of the U.S. Department of Transportation in the interest of information exchange. The United States Government assumes no liability for the contents or use thereof. The United States Government does not endorse products or manufacturers. Trade or manufacturer's names appear herein solely because they are considered essential to the objective of this report. This document does not constitute FAA certification policy. Consult your local FAA aircraft certification office as to its use. This report is available at the Federal Aviation Administration William J. Hughes Technical Center's Full-Text Technical Reports page: actlibrary.tc.faa.gov in Adobe Acrobat portable document format (PDF). Technical Report Documentation Page 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. DOT/FAA/AR-01/28 4. Title and Subtitle 5. Report Date CAPABILITIES AND PROSPECTS FOR IMPROVEMENT IN AIRCRAFT ICING May 2001 SIMULATION METHODS: CONTRIBUTIONS TO THE 11C WORKING 6. Performing Organization Code GROUP 7. Author(s) 8. Performing Organization Report No. 9. Performing Organization Name and Address 10. Work Unit No. (TRAIS) Federal Aviation Administration William J. Hughes Technical Center Aircraft Safety Research and Development Branch 11. Contract or Grant No.
    [Show full text]
  • Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment
    University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Masters Theses Graduate School 5-2006 Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment Scott Bennett Trail University of Tennessee - Knoxville Follow this and additional works at: https://trace.tennessee.edu/utk_gradthes Part of the Aerospace Engineering Commons Recommended Citation Trail, Scott Bennett, "Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment. " Master's Thesis, University of Tennessee, 2006. https://trace.tennessee.edu/utk_gradthes/1816 This Thesis is brought to you for free and open access by the Graduate School at TRACE: Tennessee Research and Creative Exchange. It has been accepted for inclusion in Masters Theses by an authorized administrator of TRACE: Tennessee Research and Creative Exchange. For more information, please contact [email protected]. To the Graduate Council: I am submitting herewith a thesis written by Scott Bennett Trail entitled "Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment." I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the equirr ements for the degree of Master of Science, with a major in Aviation Systems. Robert B. Richards, Major Professor We have read this thesis and recommend its acceptance: Rodney Allison, Frank Collins Accepted for the Council: Carolyn R. Hodges Vice Provost and Dean of the Graduate School (Original signatures are on file with official studentecor r ds.) To the Graduate Council: I am submitting herewith a thesis written by Scott Bennett Trail entitled “Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment”.
    [Show full text]
  • Aircraft of Today. Aerospace Education I
    DOCUMENT RESUME ED 068 287 SE 014 551 AUTHOR Sayler, D. S. TITLE Aircraft of Today. Aerospace EducationI. INSTITUTION Air Univ.,, Maxwell AFB, Ala. JuniorReserve Office Training Corps. SPONS AGENCY Department of Defense, Washington, D.C. PUB DATE 71 NOTE 179p. EDRS PRICE MF-$0.65 HC-$6.58 DESCRIPTORS *Aerospace Education; *Aerospace Technology; Instruction; National Defense; *PhysicalSciences; *Resource Materials; Supplementary Textbooks; *Textbooks ABSTRACT This textbook gives a brief idea aboutthe modern aircraft used in defense and forcommercial purposes. Aerospace technology in its present form has developedalong certain basic principles of aerodynamic forces. Differentparts in an airplane have different functions to balance theaircraft in air, provide a thrust, and control the general mechanisms.Profusely illustrated descriptions provide a picture of whatkinds of aircraft are used for cargo, passenger travel, bombing, and supersonicflights. Propulsion principles and descriptions of differentkinds of engines are quite helpful. At the end of each chapter,new terminology is listed. The book is not available on the market andis to be used only in the Air Force ROTC program. (PS) SC AEROSPACE EDUCATION I U S DEPARTMENT OF HEALTH. EDUCATION & WELFARE OFFICE OF EDUCATION THIS DOCUMENT HAS BEEN REPRO OUCH) EXACTLY AS RECEIVED FROM THE PERSON OR ORGANIZATION ORIG INATING IT POINTS OF VIEW OR OPIN 'IONS STATED 00 NOT NECESSARILY REPRESENT OFFICIAL OFFICE OF EOU CATION POSITION OR POLICY AIR FORCE JUNIOR ROTC MR,UNIVERS17/14AXWELL MR FORCEBASE, ALABAMA Aerospace Education I Aircraft of Today D. S. Sayler Academic Publications Division 3825th Support Group (Academic) AIR FORCE JUNIOR ROTC AIR UNIVERSITY MAXWELL AIR FORCE BASE, ALABAMA 2 1971 Thispublication has been reviewed and approvedby competent personnel of the preparing command in accordance with current directiveson doctrine, policy, essentiality, propriety, and quality.
    [Show full text]
  • Clean Sky 2 JU Work Plan 2014/2015
    Clean Sky 2 Joint Undertaking Amendment nr. 2 to Work Plan 2014-2015 Version 7 – March 2015 – Important Notice on the Clean Sky 2 Joint Undertaking (JU) Work Plan 2014-2015 This Work Plan covers the years 2014 and 2015. Due to the starting phase of the Clean Sky 2 Joint Undertaking under Regulation (EU) No 558/204 of 6 May 2014 the information contained in this Work Plan (topics list, description, budget, planning of calls) may be subject to updates. Any amended Work Plan will be announced and published on the JU’s website. © CSJU 2015 Please note that the copyright of this document and its content is the strict property of the JU. Any information related to this document disclosed by any other party shall not be construed as having been endorsed by to the JU. The JU expressly disclaims liability for any future changes of the content of this document. ~ Page intentionally left blank ~ Page 2 of 256 Clean Sky 2 Joint Undertaking Amendment nr. 2 to Work Plan 2014-2015 Document Version: V7 Date: 25/03/2015 Revision History Table Version n° Issue Date Reason for change V1 0First9/07/2014 Release V2 30/07/2014 The ANNEX I: 1st Call for Core-Partners: List and Full Description of Topics has been updated and regards the AIR-01-01 topic description: Part 2.1.2 - Open Rotor (CROR) and Ultra High by-pass ratio turbofan engine configurations (link to WP A-1.2), having a specific scope, was removed for consistency reasons. The intent is to publish this subject in the first Call for Partners.
    [Show full text]
  • A Reconfigurable VTOL Aircraft
    35th Annual AHS Student Design Competition A Reconfigurable VTOL Aircraft Sponsored by United States Army Research Laboratory Alfred Gessow Rotorcraft Center Department of Aerospace Engineering University of Maryland College Park, MD 20742 Nanjing University of Aeronautics and Astronautics Nanjing, China Executive Summary Metaltail: Reconfigured for the Future Swing Wing Mechanism Novel execution of sweeping wings reconfigures past problems into present-day solutions. Tailored Proprotor Design Common point design between rotors and propellers provides efficient performance for both hover and forward flight. Tailsitter Configuration An X-tail titanium frame ensures structural integrity for bearing landing loads. Modular Payload Bay State-of-the-Art Engines Innovative Hingeless Hub Large compartment and modular Two advanced turboshaft diesel Unique swashplate mounting rack offers flexibility for engines deliver unprecedented method results in compact hub assortment of payload packages. power for exceptional with shorter control rods. performance. Metaltail: Pushing the Envelope High in the montane forests of Ecuador, a steady hum of activity can be heard as Tyrian Metaltail hummingbirds skirt around the flora, pollinating the habitat. Using their high visual acuity, these small creatures can recognize a wide variety of colors and detect the slightest of motions. Coupled with their agile wing movements, they are able to precisely hover in place while in complex and dynamic environments. Inspired by these small but impressive flyers, Metaltail is a fully autonomous, high-speed, reconfigurable aircraft designed by the University of Maryland in response to the 35th Annual AHS Student Design Competition Request for Proposal (RFP) sponsored by the United States Army Research Laboratory (ARL). Developed as a Group 3 Unmanned Aerial Vehicle (UAV), Metaltail is an autonomous coaxial-proprotor swing-wing tailsitter that, like the high-altitude hummingbirds of Ecuador, leverages visual sensory information and adjustable wing geometry to maneuver in megacity environments.
    [Show full text]
  • NASA's First A
    NASA’s First A Aeronautics from 1958 to 2008 National Aeronautics and Space Administration Office of Communications Public Outreach Division History Program Office Washington, DC 2013 The NASA History Series NASA SP-2012-4412 NASA’s First A Aeronautics from 1958 to 2008 Robert G. Ferguson Library of Congress Cataloging-in-Publication Data Ferguson, Robert G. NASA’s first A : aeronautics from 1958 to 2008 / Robert G. Ferguson. p. cm. -- (The NASA history series) (NASA SP ; 2012-4412) 1. United States. National Aeronautics and Space Administration--History. 2. United States. National Advisory Committee for Aeronautics--History. I. Title. TL521.312.F47 2012 629.130973--dc23 2011029949 This publication is available as a free download at http://www.nasa.gov/ebooks. TABLE OF CONTENTS Acknowledgments vii Chapter 1: The First A: The Other NASA ..................................1 Chapter 2: NACA Research, 1945–58 .................................... 25 Chapter 3: Creating NASA and the Space Race ........................57 Chapter 4: Renovation and Revolution ................................... 93 Chapter 5: Cold War Revival and Ideological Muddle ............141 Chapter 6: The Icarus Decade ............................................... 175 Chapter 7: Caught in Irons ................................................... 203 Chapter 8: Conclusion .......................................................... 229 Appendix: Aeronautics Budget 235 The NASA History Series 241 Index 259 v ACKNOWLEDGMENTS Before naming individuals, I must express my gratitude to those who have labored, and continue to do so, to preserve and share NASA’s history. I came to this project after years of studying private industry, where sources are rare and often inaccessible. By contrast, NASA’s History Program Office and its peers at the laboratories have been toiling for five decades, archiving, cataloging, interviewing, supporting research, and underwriting authors.
    [Show full text]
  • A New VTOL Propelled Wing for Flying Cars
    A new VTOL propelled wing for flying cars: critical bibliographic analysis TRANCOSSI, Michele <http://orcid.org/0000-0002-7916-6278>, HUSSAIN, Mohammad, SHIVESH, Sharma and PASCOA, J Available from Sheffield Hallam University Research Archive (SHURA) at: http://shura.shu.ac.uk/16848/ This document is the author deposited version. You are advised to consult the publisher's version if you wish to cite from it. Published version TRANCOSSI, Michele, HUSSAIN, Mohammad, SHIVESH, Sharma and PASCOA, J (2017). A new VTOL propelled wing for flying cars: critical bibliographic analysis. SAE Technical Papers, 01 (2144), 1-14. Copyright and re-use policy See http://shura.shu.ac.uk/information.html Sheffield Hallam University Research Archive http://shura.shu.ac.uk 20XX-01-XXXX A new VTOL propelled wing for flying cars: critical bibliographic analysis Author, co-author (Do NOT enter this information. It will be pulled from participant tab in MyTechZone) Affiliation (Do NOT enter this information. It will be pulled from participant tab in MyTechZone) Abstract 2. acceleration of the fluid stream on the upper surface of the wing by mean of EDF propellers [13] that produces a much higher lift coefficient, with respect to any other aircrafts (up to 9-10); This paper is a preliminary step in the direction of the definition of a 3. very low stall speed (lower than 10m/s) and consequent increase radically new wing concept that has been conceived to maximize the of the flight envelope in the low speed domain up to 10÷12 m/s; lift even at low speeds. It is expected to equip new aerial vehicle 4.
    [Show full text]
  • Wide Speed Range Turboshaft Study
    NASA Contractor Report 198380 B, 11'3 Wide Speed Range Turboshaft Study Martin D'Angelo General Electric Company Lynn, Massachusetts August 1995 . Prepared for Lewis Research Center I Under Contract NAS3-2595 1 I (NASA-CR-198380) WIDE SPEED RANGE N96- 166Q6 TURBOSHAFT 5TUOY (GE) 43 p P Unclas National Aeronautics and Space Administration 63/07 0065449 TABLE OF CONTENTS SECTION Page No. Summary 1 Introduction 1 Background 1 Tilt Rotor Propulsion Issues 1 Wide Speed Range Turboshaft Study: Objectives & Methodology 2 Establishment Of Propulsion Requirements 3 Wide Speed Range Turboshaft Design Challenges 5 WSR Turboshaft Concept Screening Study 7 II Fixed Geometry Power Turbine With Incidence Tolerant Airfoils 7 Variable Power Turbine Stator And OGV Geometry 7 4 Stage Power Turbine With Tandem Airfoil Blade Rows 10 Variable Stator And Rotor Geometw Power Turbine 11 Dual Turbine Flowpaths With Flow Diverter 11 Multi-Stage Power Turbine With Clutchable Stage(s) 15 Single-To-Counter-Rotating Convertible Power Turbine 15 Fixed Geometry Power Turbine With System Optimized Cruise N~T15 Preliminary Design Of Selected WSR Turboshaft Concepts 20 Results Of Selected Concept Evaluation 32 MDHS Military Transport Propulsion System Comparison 32 Civil Transport Mission Analysis Of Selected Engine Concepts 34 Engine Shop Cost Comparison 36 Key WSR Turboshaft Technologies And Development Needs 36 Other WSR Turbine Technology Applications 37 I Bl LIST OF FIGURES 1 FIGURE Page No. m 1 Need For WSR Turboshaft 2 2 MDHC Military Transport Tiltwing 4 3 Military
    [Show full text]
  • IIIIII 11111Ll111111111llll111 Lllll111111ll1111111111 Ll1111111
    IIIIII 11111ll111111111llll111111lllll11111111ll1111111111 ll1111111 Ill11 1111 USOO538 1985A United States Patent C191 [ii] Patent Number: 5,381,985 Wechsler et al. [45] Date of Patent: Jan. 17, 1995 WINGTIP MOUNTED, COUNTER-ROTATING PROPROTOR FOR FOREIGN PATENT DOCUMENTS TILTWING AIR- 1005201 11/1957 France ................................. 24/7.3 Inventors: James K. Wechsler, Irvine, Calif.; OTHER PUBLICATIONS John W. Rutherford, Scottsdale, Aviation Week, “Hiller Awarded VTOL Contract” A*. Feb. 18, 1957 p. 37. Assignee: McDonnell Douglas Helicopter Co., Primary Examiner-Michael S. Huppert Mesa, Ariz. Assistant Examiner-Virna Lissi Ansley Appl. No.: 872,336 Attorney, Agent, or Firm-Donald E. Stout; John P. Scholl Filed Apr. 23,1992 [571 ABSTRACT Int. 11/48; B64C 27/08; c1.6 ...................... B64C A tiltwing aircraft, capable of in-fighe conversion be- B64C 27/22; B64C 27/52 tween a hover and forward cruise mode, employs a 244/7 244A2.4; U.S. c1. ................................... C; counter-rotating proprotor arrangement which permits 24/56 24/66 24/69 a significantly increased cruise efficiency without sacri- Field of Search 244/6, 7 C, 7 R, 12.4, .................. ficing either the size of the conversion envelope or the 244A7.23, 56, 66, 69 wing efficiency. A benefit in hover is also provided References Cited because of the lower effective disk loading for the coun- ter-rotating proprotor, as opposed to a single rotation U.S. PATENT DOCUMENTS proprotor of the same diameter. At least one proprotor 1,806,648 5/1931 Salisbury et al. ................... 24/7 R is provided on each wing section, preferablimounted 2,434,216 1/1948 Laskowitz ............................. 244/66 on the wingtip, with each proprotor having two cow- 2,494,368 1/1950 Steele et al.
    [Show full text]
  • Helicopter Noise Reduction Technology, Status Report
    Helicopter Noise Reduction Technology Status Report 21 April 2015 Contributors: ICCAIA: Snecma, Airbus Helicopters, Sikorsky Aircraft, Bell Helicopter, AgustaWestland, Turbomeca, Marenco Swisshelicopter Research Centers: NASA, DLR, ONERA, JAXA 1 Contents 1 Introduction .................................................................................................................................................. 3 2 Helicopter noise sources and related noise generation mechanisms ............................................................ 4 2.1 Rotor noise ........................................................................................................................................... 4 2.2 Anti-torque noise .................................................................................................................................. 4 2.3 Engine noise ......................................................................................................................................... 5 2.3.1 Turboshaft Engines.......................................................................................................................... 5 2.3.2 Piston Engines ................................................................................................................................. 5 2.4 Contribution of noise sources depending on flight condition .............................................................. 5 3 State-of-the-Art Helicopters ........................................................................................................................
    [Show full text]
  • Design Optimization of High-Speed Proprotor Aircraft
    f /,W-.-o5 NASA Technical Memorandum 103988 Design Optimization of High-Speed Proprotor Aircraft David R. Schleicher, James D. Phillips, and Kevin B. Carbajal (NASA-TM-I03988) DESIGN N94-26151 OPTIMIZATION OF HIGH-SPEEO PROPROTOR AIRCRAFT (NASA) 4O p Unclas G3/05 0208973 April 1993 National Aeronautics and Space Adminisb'ation "TL_',.h.._ NASA Technical Memorandum 103988 Design Optimization of High-Speed Proprotor Aircraft David R. Schleicher, James D. Phillips, and Kevin B. Carbajal Ames Research Center, Moffett Field, California April 1993 I_d/LqA National Aeronautics and Space Administration Ames Research Center Moffett Field, California 94035-1000 Contents Page Summary ................................................................................................................................................................................ 1 Nomenclature ......................................................................................................................................................................... I 1. Introduction ................................................................................................................................................................. I 2. Configurations and Mission ....................................................................................................................................... 2 3. Aircraft Synthesls .......................................................................................................................................................
    [Show full text]