DOCSLIB.ORG

NASA Agency-Wide Approach for the Management of Resources Less Than 50 Years of Age Resource Significance Framework Area 1: Aero

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
NASA Agency-Wide Approach for the Management of Resources Less Than 50 Years of Age Resource Significance Framework Area 1: Aero NASA Agency-Wide Approach for the Management of Resources Less than 50 Years of Age Resource Significance Framework Area 1: Aeronautics Research December 24, 2020 DRAFT Prepared for: Rebecca Klein, Ph.D., RPA Federal Preservation Officer Office of Strategic Infrastructure NASA Headquarters 300 E Street, S.W. Washington, D.C. 20546 Prepared by: Carrie Albee, Architectural Historian Gray & Pape, Inc. 2005 East Franklin Street, Suite 2 Richmond, Virginia 23223 (804) 644-0656 NASA AGENCY-WIDE APPROACH FOR THE MANAGEMENT OF RESOURCES LESS THAN 50 YEARS OF AGE RSF: Aeronautics Research Chapter – December 24, 2020 Draft Table of Contents Table of Contents .............................................................................................................. i Acronyms ....................................................................................................................... iii 1.0 Introduction ............................................................................................................... 1 2.0 Methodology ............................................................................................................. 3 2.1 Scope of Study ....................................................................................................... 3 2.2 Project Development ............................................................................................... 3 2.3 Areas of Significance .............................................................................................. 5 2.4 Apex Events ........................................................................................................... 5 2.5 Citations ................................................................................................................. 5 2.6 Property Types ........................................................................................................ 6 2.7 Current Draft ........................................................................................................ 11 3.0 Agency Overview .................................................................................................... 12 3.1 Mission Directorates .............................................................................................. 13 3.2 NASA Locations .................................................................................................... 14 3.3 Real Property Assets .............................................................................................. 16 4.0 Area 1: Aeronautics Research ................................................................................... 18 4.1 Historical Overview ............................................................................................... 18 4.2 Aeronautics Research Centers ................................................................................ 20 4.3 Themes of Exceptional Importance ......................................................................... 26 4.4 Apex Events ......................................................................................................... 28 4.5 Property Types ...................................................................................................... 49 5.0 References ............................................................................................................... 66 Appendix 1: NASA Facility Classification Coding System .................................................. 72 List of Tables Table 3-1. NASA Centers and Component Facilities .......................................................... 15 Table 3-2. Evaluation Status of Real Property Assets by Center .......................................... 17 Table 4-1. Total Potential Tier 1 Assets by FCCS Basic Category ........................................ 52 Table 4-2. Facility Class 1 (Operational, Including Tracking & Data Acquisition & Training) 55 Table 4-3. Facility Class 2 (Maintenance & Production) ..................................................... 57 i NASA AGENCY-WIDE APPROACH FOR THE MANAGEMENT OF RESOURCES LESS THAN 50 YEARS OF AGE RSF: Aeronautics Research Chapter – December 24, 2020 Draft Table 4-4. Facility Class 3 (Research, Development & Testing) ........................................... 57 Table 4-5. Facility Class 4 (Supply) .................................................................................. 59 Table 4-6. Facility Class 5 (Hospital & Medical) ............................................................... 60 Table 4-7. Facility Class 6 (Administrative Buildings) ......................................................... 60 Table 4-8. Facility Class 7 (Housing & Community) ........................................................... 60 Table 4-9. Facility Class 8 (Utility & Ground Improvements) .............................................. 62 Table 4-10. Facility Class 9 (Land) ................................................................................... 65 Table 4-11. Facility Class (Unassigned) ............................................................................ 65 List of Figures Figure 2-1. FCCS Code for Research, Development, & Test Laboratories ............................ 10 Figure 3-1. NASA U.S. Locations ..................................................................................... 16 ii NASA AGENCY-WIDE APPROACH FOR THE MANAGEMENT OF RESOURCES LESS THAN 50 YEARS OF AGE RSF: Aeronautics Research Chapter – December 24, 2020 Draft Acronyms ACEE Aircraft Energy Efficiency ACHP Advisory Council on Historic Preservation ADECS Adaptive Digital Engine Control System AERL Aircraft Engine Research Laboratory AFB Air Force Base AFRC Armstrong Flight Research Center ARC Ames Research Center ARMD Aeronautics Research Mission Directorate BWB Blended Wing Body CAPA Central Airborne Performance Analyzer CAPCS Cooperative Airframe/Propulsion Control System CAS Control Augmentation System CCG National Register of Historic Places Criteria Consideration G CFD Computational Fluid Dynamics CRM Cultural Resource Managers DEEC Digital Electronic Engine Control DEFCS Digital Electronic Flight Control System DFBW Digital Fly-by-Wire DoD Department of Defense ELF Ellington Field FCCS Facility Classification Coding System FRED Facilities and Real Estate Division FY Fiscal Year GDSCC Goldstone Deep Space Communication Complex GP Gray & Pape, Inc. GRC Glenn Research Center GSFC Goddard Space Flight Center HARV High Alpha Research Vehicle HATP High Angle-of-Attack Technology Program HEO Human Exploration and Operations Mission Directorate iii NASA AGENCY-WIDE APPROACH FOR THE MANAGEMENT OF RESOURCES LESS THAN 50 YEARS OF AGE RSF: Aeronautics Research Chapter – December 24, 2020 Draft HIDEC Highly Integrated Digital Electronic Control HSG Herndon Solutions Group HTSF Highly Technical or Scientific Facilities ICRMP Integrated Cultural Resource Management Plan IPCS Integrated Propulsion Control System ISS International Space Station JPL Jet Propulsion Laboratory JSC Johnson Space Center KSC Kennedy Space Center LAFB Langley Air Force Base LaRC Langley Research Center LLRV Lunar Landing Research Vehicle LTV Ling-Temco-Vought MAF Michoud Assembly Facility MPD Multiple Property Documentation form MSFC Marshall Space Flight Center NACA National Advisory Committee on Aeronautics NAS Naval Air Station NASA National Aeronautics and Space Administration NATO North Atlantic Treaty Organization NETS NASA Environmental Tracking System NHL National Historic Landmark NHPA National Historic Preservation Act NPS National Park Service NRHP National Register of Historic Places NRP NASA Research Park OAPEC Organization of Arab Petroleum Exporting Countries PBOW Plum Brook Ordnance Works PBS Plum Brook Station PCA Propulsion Controlled Aircraft PSC Performance Seeking Control RD&T Research, development, and testing iv NASA AGENCY-WIDE APPROACH FOR THE MANAGEMENT OF RESOURCES LESS THAN 50 YEARS OF AGE RSF: Aeronautics Research Chapter – December 24, 2020 Draft RPMS Real Property Management System RSF Resource Significance Framework SCTF Sonny Carter Training Facility SCW Supercritical Wing SMD Science Mission Directorate SOFIA Stratospheric Observatory for Infrared Astronomy SOI Secretary of the Interior SRFCS Self-Repairing Flight Control System SSC Stennis Space Center SSFL Santa Susana Field Laboratory SSP Space Shuttle Program STMD Space Technology Mission Directorate STOL Short Takeoff and Landing TACT Transonic Aircraft Technology TRRA Tilt Rotor Research Aircraft UAV Unmanned Aerial Vehicle V/STOL Vertical/Short Takeoff and Landing WFF Wallops Flight Facility WSTF White Sands Test Facility v NASA AGENCY-WIDE APPROACH FOR THE MANAGEMENT OF RESOURCES LESS THAN 50 YEARS OF AGE RSF: Aeronautics Research Chapter – December 24, 2020 Draft 1.0 Introduction As defined by the National Register of Historic Places (NRHP), resources less than 50 years of age (<50) are generally not eligible for listing (i.e., they are not historic properties) unless they possess exceptional importance under the Criteria. However, NASA is a young agency with a scientific mission that makes it atypical among Federal agencies in both the character of its historic properties and the nature of the National Historic Preservation Act (NHPA) Section 106 undertakings. While most Federal agencies’ historic preservation programs prioritize resources that have reached 50 years of age (50+) and only evaluate resources under NRHP Criteria Consideration G (CCG) in limited cases of readily apparent significance (e.g., Cold War, Civil
Load more

Recommended publications
  • Method to Assess Lateral Handling Qualities of Aircraft with Wingtip Morphing
    Method to assess lateral handling qualities of aircraft with wingtip morphing Ga´etanDussart∗, Sezsy Yusufy, Vilius Portapas z, Guillermo Lopezxand Mudassir Lone{ Cranfield University, Dynamic Simulation and Control Group Cranfield, Bedfordshire, United Kingdom, MK43 0AL The impact of in-flight folding wingtip on roll characteristics of aircraft has been studied in the past. In this study, a handling qualities assessment carried out to de-risk further de- velopment of such a device. A specialised flight simulation campaign is prepared to evaluate the roll dynamics in different morphing configurations. Various manoeuvres, including the Offset Landing Manoeuvre and herein presented Slalom and Alignment Tracking task are used. Cooper Harper Rating scales and flight data analysis are used to collect pilot opinion and validate pilot-in-the-loop simulation results. This example is used to demonstrate the use of the slalom and Alignment Tracking manoeuvre for lateral dynamic assessment. I. Introduction A means to improve aircraft performance is to increase aircraft wingspan and raise aerodynamic effi- ciency.1,2 Then to comply with airport infrastructure limits, ground folding wingtips can be implemented as a solution, as seen on the NASA SUGAR concept (Fig.1a) or the Boeing 777X aircraft (Fig.1b). Moreover, in-flight folding can be considered to further justify the mechanism weight penalty and consolidate concept's viability. Two key applications were initially identified: gust loads alleviation capability demonstrated in past work,1 and flight dynamic and performance modifications, carried out through the preliminary identifi- cation of effect on key aerodynamic derivatives.3 This particular research demonstrated shifts of noticeable amplitude and trends in key lateral aerodynamic derivatives of a large generic aircraft.
    [Show full text]
  • University of Oklahoma Graduate College Design and Performance Evaluation of a Retractable Wingtip Vortex Reduction Device a Th
    UNIVERSITY OF OKLAHOMA GRADUATE COLLEGE DESIGN AND PERFORMANCE EVALUATION OF A RETRACTABLE WINGTIP VORTEX REDUCTION DEVICE A THESIS SUBMITTED TO THE GRADUATE FACULTY In partial fulfillment of the requirements for the Degree of Master of Science Mechanical Engineering By Tausif Jamal Norman, OK 2019 DESIGN AND PERFORMANCE EVALUATION OF A RETRACTABLE WINGTIP VORTEX REDUCTION DEVICE A THESIS APPROVED FOR THE SCHOOL OF AEROSPACE AND MECHANICAL ENGINEERING BY THE COMMITTEE CONSISTING OF Dr. D. Keith Walters, Chair Dr. Hamidreza Shabgard Dr. Prakash Vedula ©Copyright by Tausif Jamal 2019 All Rights Reserved. ABSTRACT As an airfoil achieves lift, the pressure differential at the wingtips trigger the roll up of fluid which results in swirling wakes. This wake is characterized by the presence of strong rotating cylindrical vortices that can persist for miles. Since large aircrafts can generate strong vortices, airports require a minimum separation between two aircrafts to ensure safe take-off and landing. Recently, there have been considerable efforts to address the effects of wingtip vortices such as the categorization of expected wake turbulence for commercial aircrafts to optimize the wait times during take-off and landing. However, apart from the implementation of winglets, there has been little effort to address the issue of wingtip vortices via minimal changes to airfoil design. The primary objective of this study is to evaluate the performance of a newly proposed retractable wingtip vortex reduction device for commercial aircrafts. The proposed design consists of longitudinal slits placed in the streamwise direction near the wingtip to reduce the pressure differential between the pressure and the suction sides.
    [Show full text]
  • Aircraft Winglet Design
    DEGREE PROJECT IN VEHICLE ENGINEERING, SECOND CYCLE, 15 CREDITS STOCKHOLM, SWEDEN 2020 Aircraft Winglet Design Increasing the aerodynamic efficiency of a wing HANLIN GONGZHANG ERIC AXTELIUS KTH ROYAL INSTITUTE OF TECHNOLOGY SCHOOL OF ENGINEERING SCIENCES 1 Abstract Aerodynamic drag can be decreased with respect to a wing’s geometry, and wingtip devices, so called winglets, play a vital role in wing design. The focus has been laid on studying the lift and drag forces generated by merging various winglet designs with a constrained aircraft wing. By using computational fluid dynamic (CFD) simulations alongside wind tunnel testing of scaled down 3D-printed models, one can evaluate such forces and determine each respective winglet’s contribution to the total lift and drag forces of the wing. At last, the efficiency of the wing was furtherly determined by evaluating its lift-to-drag ratios with the obtained lift and drag forces. The result from this study showed that the overall efficiency of the wing varied depending on the winglet design, with some designs noticeable more efficient than others according to the CFD-simulations. The shark fin-alike winglet was overall the most efficient design, followed shortly by the famous blended design found in many mid-sized airliners. The worst performing designs were surprisingly the fenced and spiroid designs, which had efficiencies on par with the wing without winglet. 2 Content Abstract 2 Introduction 4 Background 4 1.2 Purpose and structure of the thesis 4 1.3 Literature review 4 Method 9 2.1 Modelling
    [Show full text]
  • Commercial Aircraft Performance Improvement Using Winglets
    Nikola N. Gavrilović Commercial Aircraft Performance Graduate Research Assistant Improvement Using Winglets University of Belgrade Faculty of Mechanical Engineering Aerodynamic drag force breakdown of a typical transport aircraft shows Boško P. Rašuo that lift-induced drag can amount to as much as 40% of total drag at Full Professor cruise conditions and 80-90% of the total drag in take-off configuration. University of Belgrade Faculty of Mechanical Engineering One way of reducing lift-induced drag is by using wing-tip devices. By applying several types of winglets, which are already used on commercial George S. Dulikravich airplanes, we study their influence on aircraft performance. Numerical Full Professor investigation of five configurations of winglets is described and Florida International University preliminary indications of their aerodynamic performance are provided. Department of Mechanical and Materials Engineering, Miami, Florida, USA Moreover, using advanced multi-objective design optimization software an optimal one-parameter winglet configuration was detrmined that Vladimir Parezanović simultaneously minimizes drag and maximizes lift. Researcher Institute PPRIME, CNRS UPR3346 Poitiers, France Keywords: Winglet, Bionics, Computational fluid dynamics, Drag reduction, Lift-induced drag, Optimization 1. INTRODUCTION of soaring birds and their use of tip feathers to control flight, continued on the quest to reduce induced drag The main motivation for using wingtip devices is and improve aircraft performance and further develop reduction of lift-induced drag force. Environmental the concept of winglets in the late 1970s [4]. This issues and rising operational costs have forced industry research provided a fundamental knowledge and design to improve efficiency of commercial air transport and approach required for extremely attractive option to this has led to some innovative developments for improve aerodynamic efficiency of civilian aircraft, reducing lift-induced drag.
    [Show full text]
  • LYNCH-THESIS-2017.Pdf
    c Copyright by Michael K. Lynch 2017 All Rights Reserved BIO-INSPIRED ADAPTIVE WINGTIP DEVICES FOR LOW REYNOLDS NUMBER OPERATION BY MICHAEL K. LYNCH THESIS Submitted in partial fulfillment of the requirements for the degree of Master of Science in Mechanical Engineering in the Graduate College of the University of Illinois at Urbana-Champaign, 2017 Urbana, Illinois Adviser: Assistant Professor Aimy Wissa Abstract Birds are highly capable and maneuverable fliers, traits not currently shared with current unmanned aerial vehicles. They are able to achieve these flight capabilities by adapting the shape of their wings during flight in a variety of complex manners. One feature of bird wings, the primary feathers, separate to form wingtip gaps at the distal end of the wing. This research presents bio-inspired wingtip devices with varying wingtip gap sizes, defined as the chordwise distance between wingtip devices, for operation in low Reynolds number conditions of Re = 100,000, similar to conditions experienced by many species of birds. Lift and drag data was measured for planar and nonplanar wingtip devices with the total wingtip gap size ranging from 0% to 40%. For a planar wing with a gap size of 20%, the mean coefficient of lift in the pre-stall region is increased by 7.25%, and the maximum coefficient of lift is increased by 5.6% compared to a configuration with no gaps. The nonplanar wingtip device was shown to reduce the induced drag. The effect of wingtip gap sizes is shown to be independent of the planarity/nonplanarity of the wingtip device, thereby allowing designers to decouple the wingtip parameters to tune the desired lift and drag produced.
    [Show full text]
  • Aero Dynamic Analysis of Multi Winglets in Light Weight Aircraft
    SSRG International Journal of Mechanical Engineering (SSRG-IJME) – Special Issue ICRTETM March 2019 Aero Dynamic Analysis of Multi Winglets in Light Weight Aircraft J. Mathan#1,L.Ashwin#2, P.Bharath#3,P.Dharani Shankar#4,P.V.Jackson#5 #1Assistant Professor & Mechanical Engineering & KSRIET #2,3,4,5Final Year Student & Mechanical Engineering & KSRIET Tiruchengode,Namakkal(DT),Tamilnadu Abstract An analysis of multi-winglets as a device for of these devices such as winglets [2], tip-sails [3, 4, 5] reducing induced drag in low speed aircraft is and multi-winglets [6] take energy from the spiraling carried out, based on experimental investigations of a air flow in this region to create additional traction. wing-body half model at Re = 4•105. Winglet is a lift This makes possible to achieve expressive gains on augmenting device which is attached at the wing tip efficiency. Whitcomb [2], for example, shows that of an aircraft. A Winglets are used to improve the winglets could increase wing efficiency in 9% and aerodynamic efficiency of an aircraft by lowering the decrease the induced dragin20%. Some devices also formation of an Induced Drag which is caused by the break up the vortices into several parts, each one with wingtip vortices. Numerical studies have been carried less intensity. This facilitates their dispersion, an out to investigate the best aerodynamic performance important factor to decrease the time interval between of a subsonic aircraft wing at various cant angles of takeoff and landings at large airports [7]. A winglets. A baseline and six other different multi comparison of the wingtip devices [1] shows that winglets configurations were tested.
    [Show full text]
  • The EREA Vision on High Priority Research Axes Towards ATS 2050
    28TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES THE EREA VISION ON HIGH PRIORITY RESEARCH AXES TOWARDS AIR TRANSPORT SYSTEM 2050 Muriel Brunet1, Alte de Boer2, Volker Gollnick3, Steffen Loth4, Graciano Martinez5, Dennis Nieuwenhuisen6 ONERA1, NLR2, DLR3, DLR4, INTA5, NLR6 [email protected];[email protected];[email protected];[email protected]; [email protected];[email protected] Keywords: configuration, propulsion, subsystems, automation, airport Abstract Strategic Research and Innovation Agenda to be prepared by the Advisory Council for Aviation Europe is writing the future of its air transport research and innovation in Europe (ACARE). In in the new Strategic Research and Innovation this open context of building the future of Agenda. In this open context of building the aviation, the research centres have a key role in future of aviation, the research centres have a providing their vision independently of any key role in providing their vision independently economic interest. Therefore, the association of of any economic interest. Therefore, the the European Research Establishments in association of the European Research Aeronautics (EREA) has decided to provide to Establishments in Aeronautics (EREA) is the European commission and to the committed to provide to the European aeronautical community in general its vision on commission and to the aeronautical community the 2050 Air Transport System (ATS) and in general its vision on the 2050 air transport consequently its recommendations on high system and its recommendations on high priority research axes to be funded in order to priority research axes to be funded in order to pave the way towards 2050.
    [Show full text]
  • N 8900.525 NOTICE FEDERAL AVIATION ADMINISTRATION Effective Date: National Policy 10/7/19 Cancellation Date: 10/7/20
    U.S. DEPARTMENT OF TRANSPORTATION N 8900.525 NOTICE FEDERAL AVIATION ADMINISTRATION Effective Date: National Policy 10/7/19 Cancellation Date: 10/7/20 SUBJ: Revised FAA-Approved Deicing Program Updates, Winter 2019-2020 1. Purpose of This Notice. This notice provides inspectors with information on holdover times (HOT) and recommendations on various other ground deicing/anti-icing issues. This notice clarifies guidance regarding reported Aviation Routine Weather Report (METAR) obscurations to remove potential misinterpretations. Note: This notice is designed to be used in conjunction with the Federal Aviation Administration (FAA) Holdover Time Guidelines for Winter 2019-2020. The two documents complement each other and should be used together for a thorough understanding of the subject matter. 2. Audience. The primary audience for this notice is the Flight Standards (FS) Safety Assurance offices’ Principal Operations Inspectors (POI) responsible for approving an air carrier’s deicing program. The secondary audience includes air carriers and operators as well as the Safety Standards and Foundational Business offices. 3. Where You Can Find This Notice. You can find this notice on the MyFAA employee website at https://employees.faa.gov/tools_resources/orders_notices. Inspectors can access this notice through the Flight Standards Information Management System (FSIMS) at http://fsims.avs.faa.gov. Operators can find this notice on the FAA’s website at http://fsims.faa.gov. This notice is available to the public at http://www.faa.gov/regulations_policies/orders_notices. Note: The FAA Holdover Time Guidelines for Winter 2019-2020 and related tables referenced in this document can be found on the Air Transportation Division’s (AFS-200) Aircraft Ground Deicing website at http://www.faa.gov/other_visit/aviation_industry/airline_operators/airline_safety/ deicing.
    [Show full text]
  • In-Flight Wingtip Folding: Inspiration from the XB-70 Valkyrie Gaétan X
    International Journal of Aviation, Aeronautics, and Masthead Logo Aerospace Volume 6 | Issue 3 Article 7 2019 In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie Gaétan X. Dussart Cranfield University, [email protected] Mudassir Lone Cranfield University, [email protected] Ciaran O'Rourke Airbus Ltd, [email protected] Thomas Wilson Airbus Ltd, [email protected] Follow this and additional works at: https://commons.erau.edu/ijaaa Part of the Aeronautical Vehicles Commons, Applied Mechanics Commons, and the Aviation and Space Education Commons Scholarly Commons Citation Dussart, G. X., Lone, M., O'Rourke, C., & Wilson, T. (2019). In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie. International Journal of Aviation, Aeronautics, and Aerospace, 6(3). Retrieved from https://commons.erau.edu/ijaaa/vol6/iss3/7 This Article is brought to you for free and open access by the Journals at Scholarly Commons. It has been accepted for inclusion in International Journal of Aviation, Aeronautics, and Aerospace by an authorized administrator of Scholarly Commons. For more information, please contact [email protected], [email protected]. Dussart et al.: In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie Introduction To help develop future aircraft technologies, the authors investigated past developments and applications in the field of folding wingtips for inspiration, focusing on the XB-70 Valkyrie. Arguably the most iconic example of folding wingtip capable vehicle, it included the largest moving lifting surfaces ever flown and provides a good insight on the actuator and systems requirement for wingtip folding. Following a justification for incremental aircraft design changes, the authors introduce past and on-going developments in folding wingtip systems for large civil aircraft.
    [Show full text]
  • Identification of In-Flight Wingtip Folding Effects on the Roll
    aerospace Article Identification of In-Flight Wingtip Folding Effects on the Roll Characteristics of a Flexible Aircraft Gaétan Dussart *, Sezsy Yusuf and Mudassir Lone Dynamic Simulation and Control Group, School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire MK43 0AL, UK; sezsy.yusuf@cranfield.ac.uk (S.Y.); m.m.lone@cranfield.ac.uk (M.L.) * Correspondence: g.x.dussart@cranfield.ac.uk Received: 15 April 2019; Accepted: 24 May 2019; Published: 30 May 2019 Abstract: Wingtip folding is a means by which an aircraft’s wingspan can be extended, allowing designers to take advantage of the associated reduction in induced drag. This type of device can provide other benefits if used in flight, such as flight control and load alleviation. In this paper, the authors present a method to develop reduced order flight dynamic models for in-flight wingtip folding, which are suitable for implementation in real-time pilot-in-the-loop simulations. Aspects such as the impact of wingtip size and folding angle on aircraft roll dynamics are investigated along with failure scenarios using a time domain aeroservoelastic framework and an established system identification method. The process discussed in this paper helps remove the need for direct connection of complex physics based models to engineering flight simulators and the need for tedious programming of large look-up-tables in simulators. Instead, it has been shown that a generic polynomial model for roll aeroderivatives can be used in small roll perturbation conditions to simulate the roll characteristics of an aerodynamic derivative based large transport aircraft equipped with varying fold hinge lines and tip deflections.
    [Show full text]
  • In-Flight Wingtip Folding: Inspiration from the XB-70 Valkyrie
    International Journal of Aviation, Aeronautics, and Aerospace Volume 6 Issue 3 Article 7 2019 In-flight Wingtip olding:F Inspiration from the XB-70 Valkyrie Gaétan X. Dussart Cranfield University, [email protected] Mudassir Lone Cranfield University, [email protected] Ciaran O'Rourke Airbus Ltd, [email protected] Thomas Wilson Airbus Ltd, [email protected] Follow this and additional works at: https://commons.erau.edu/ijaaa Part of the Aeronautical Vehicles Commons, Applied Mechanics Commons, and the Aviation and Space Education Commons Scholarly Commons Citation Dussart, G. X., Lone, M., O'Rourke, C., & Wilson, T. (2019). In-flight Wingtip olding:F Inspiration from the XB-70 Valkyrie. International Journal of Aviation, Aeronautics, and Aerospace, 6(3). https://doi.org/ 10.15394/ijaaa.2019.1343 This Article is brought to you for free and open access by the Journals at Scholarly Commons. It has been accepted for inclusion in International Journal of Aviation, Aeronautics, and Aerospace by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. Dussart et al.: In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie Introduction To help develop future aircraft technologies, the authors investigated past developments and applications in the field of folding wingtips for inspiration, focusing on the XB-70 Valkyrie. Arguably the most iconic example of folding wingtip capable vehicle, it included the largest moving lifting surfaces ever flown and provides a good insight on the actuator and systems requirement for wingtip folding. Following a justification for incremental aircraft design changes, the authors introduce past and on-going developments in folding wingtip systems for large civil aircraft.
    [Show full text]
  • Preparation of Papers for AIAA Technical Conferences
    Adaptive C-Wing Flight Controls for a Universally-Electric Aircraft Ulrich Kling1 and Askin T. Isikveren2 Bauhaus Luftfahrt e.V., Munich, Germany, 80807 Rafic M. Ajaj3 University of Southampton, Southampton, United Kingdom, SO17 1BJ M.I. Friswell4 College of Engineering, Swansea University, Swansea, SA2 8PP, UK Optimisation of overall aircraft efficiency is mandatory for aircraft designers faced with the challenge of serving a growing demand for air transport with diminishing fossil resources. Going beyond the parameter space of conventional aircraft layouts, aerodynamic efficiency may be improved by radical new wing designs such as a non-planar C-wing. In this paper, the idea is to additionally equip the top part of a C-wing with an active poly-morphing capability, enabling the wing system to adapt to different flight phases. With this adaptive Top-Wing (TW), the non-planar wing itself can then provide sufficient handling and control authority for the aircraft. Hence, one may dispense with a dedicated horizontal stabiliser, leading to a tailless aircraft layout and further enhancing vehicular efficiency. An initial design of an electrically actuated, variable direct-camber and possibly in-direct-twist TW together with preliminary weight and actuation power estimate is presented. Nomenclature Angle of attack [°] Cm,CG Total pitching moments about the aircraft centre-of-gravity [-] Cmo,WFNP Pitching moment coefficient of the wing-fuselage-nacelles-pylons [-] Cm,MW Pitching moment coefficient due to Main-Wing [-] Cm,adp,TW Pitching moment
    [Show full text]